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Garmin SA01535Wi_D Instruction Manual

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1. LRUS Stores all configuration fles in GDU 1800 MFD LRUs Stores all configuration fles in intemal memory Uses master Contains ACTIVE intemal memory Uses master configuration module for backup MFD settings The configuration module for backup MFD uses PFD internal configuration files for backup COUN EY mm No 1GIA63W No 2GIAG3W bec Contains ACTIVE Contains ACTIVE RED meal Saat Poin configuration files for R5485 configuration files for ee files for backup files for backup sans d 3 2 No 1GEA71 No 1 No 2 No 2GEA71 Contains GTX 33 3000 ater Contains settings Uses nein PFO internal tgs es ACTIVE setings Uses PFD RED intemal configuration files configuration fles settings Uses configuration files Tor backup pres PFD intemal CN Tor backup configuration files n for backup GDL 69A GWX 68 70 Contains Contains ACTIVE ACTIVE settings Uses 4 gt settings Uses PFD internal PED internal configuration fles configuration files for backup for backup Figure 3 14 G1000 LRU Configuration File Storage G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 17 190 00915 01 Revision 9 The GRS 77 7800 AHRS and GMU 44 Magnetometer do not have a configuration file However the GRS does store calibration data acquired during the post installation checkout
2. Continue to Section 6 16 3 6 16 3 Configuration Module Checkout GRS 77 or GRS 7800 AHRS Configuration Module is replaced All three GRS 77 or GRS 7800 and GMU 44 calibration procedures must be performed Proceed to Section 7 7 3 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 11 190 00915 01 Revision 9 Ifa GDC 74B Configuration Module is replaced Configuration settings must be reloaded to the GDC 74B per Section 3 9 then proceed to Section 7 6 1 Ifa GEA 71 Configuration Module is replaced Proceed to Section 7 4 1 If only the Master Configuration Module is replaced NOTE New Terrain Obstacle cards Jeppesen Aviation Database and other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number l Start the G1000 system in configuration mode 2 Goto the Configuration Upload Page on PFD 1 3 Press UPDT CFG softkey and press ENT If both PFD 1 and Master Configuration Module are replaced NOTE New Terrain Obstacle cards Jeppesen Aviation Database and other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number wil
3. and PFD2 Apply right left and up down localizer glideslope signals using the test equipment Verify that the Flight Director and flight controls respond appropriately Couple FD to PFDI by pressing the XFR button on the AFCS mode controller Verify FD is coupled to PFDI as indicated by a left pointing arrow on the AFCS mode controller next to the XFR button 11 Repeat step 9 while coupled to PFD1 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 8 13 19 0 00915 01 Revision 9 8 3 Maintenance Records This Post Installation Configuration Log should be completed during the initial installation and maintained with the aircraft permanent records Record the following information e number of the G1000 software loader card used to perform software loading or software updates Record part and serial numbers of any LRU which was replaced Record any database updates which were performed during maintenance e other applicable information related to the maintenance work performed on the aircraft Post Installation Configuration Log Date Aircraft Model Aircraft Make Aircraft Registration Aircraft Serial Engine G1000 Loader Card Prop Version Installed Enabled Installed Enabled Unit Option check if installed or Unit Option check if installed or configured configured 7 GDC 74B ADF Op
4. Execution Fault Internal Fault Return to Garmin for service Electrical Fault Internal Fault Return to Garmin for service Whisper Shout Fault Internal Fault Return to Garmin for service Transmit Power Fault Internal voltages are out of tolerance Check power connections to the GPA 65 to verify that they are not connected to ground or each other Ensure that power and ground connections to the GPA 65 connected in their proper place Verify input voltage and if it continues return to Garmin for service G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 93 Revision 9 Problem Cause Solution 1030 MHz Fault Internal Fault Return to Garmin for service 1090 MHz Fault Internal Fault Return to Garmin for service Fault Antenna connections or internal fault Ensure all antenna connections are correct otherwise return to Garmin for service Receiver Fault Antenna connections or internal fault Ensure all antenna connections are correct otherwise return to Garmin for service Transmitter Fault Antenna connections or internal fault Ensure all antenna connections are correct otherwise return to Garmin for service Baro Altitude Fault Baro Altimeter is not powered on or Verify that the baro altimeter has improper wiring power and is properly wired Improper configuration settings Verify the configuration
5. GARMIN G1000 GFC 700 System Maintenance Manual Hawker Beechcraft Model 200 B200 Series King Air Contains Instructions For Continued Airworthiness For STC SA01535WI D 190 00915 01 February 2014 Revision 9 This page intentionally left blank Copyright 2009 2014 Garmin Ltd or its subsidiaries All Rights Reserved Except as expressly provided herein no part of this manual may be reproduced copied transmitted disseminated downloaded or stored in any storage medium for any purpose without the express prior written consent of Garmin Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto provided that such electronic or printed copy this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited Garmin International Inc 1200 E 1514 Street Olathe KS 66062 USA Telephone 913 397 8200 www garmin com Garmin Europe Ltd Liberty House Bulls Copse Road Hounsdown Business Park Southampton 5040 9RB UK Phone 44 0 23 8052 4000 Fax 44 0 23 8052 4004 RECORD OF REVISIONS Revision Revision Date Description 5 5 11
6. GIA1 GEA2 data path is not functioning correctly e Verify GEA2 is powered on using the GEA Status page e Load GIAI and GEA2 configuration files e Swap GIAI and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIAI Red o Replace original GIAI if box turns green after swapping CHNL 2 GEA2 units e Swap GEA2 and reconfigure both GEA s to their new locations to confirm if the problem is in the original GEA2 o Replace original GEA2 if box turns green after swapping units Check the GIA1 GEA2 interconnect wiring for faults GIAT GEAQ2 data path functionality is unknown Reload GIAI Amber configuration files Green GIA1 GFC 700 data path is functioning correctly GIAI GFC 700 data path is not functioning correctly Red e Load GIAI configuration files GIA Gains file and GSA software CHNL 4 GFC 700 and gains file if LRU and Card versions are different Reference GFC section for further troubleshooting 700 data path functionality is unknown Reload GIAI Amber diua configuration files G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 19 190 00915 01 Revision 9 GIA2 RS 485 Channel LRU Indicator Status Green GIA2 GEAI data path is functioning correctly 2 data path is not functioning correctly e Verify GEA1 is powered on u
7. 3 53 4 18 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS TROUBLESHOOTING GSM 85A SERVO MOUNT CONFIGURATION GSM 86 SERVO MOUNT CONFIGURATION VERIFICATION OF SERVO MOUNT CONFIGURATION FLITECHARTS CONFIGURATION OPTIONAL CHARTVIEW ENABLE STANDARD TAWS B ENABLI OPTIONAL TAWS A ENABLE SUPPLEMENTAL DATABASE LOADING OPTIONAL SVS PATHWAYS ENABLE OPTIONAL ESP ENABLE SEARCH AND RESCUE ENABLE OPTIONAL GARMIN TCAS I ENABLE FROM GTS 825 TO GTS 855 OPTIONAL GARMIN TCAS II ENABLE FROM GTS 825 TO GTS 8000 AIRCRAFT REGISTRATION NUMBER ENTRY V1 V2 AIRSPEED OPTIONS SPLASH SCREEN LOADING NAVIGATION DATABASE LOADING CONFIGURATION OF NAVIGATION MAP FOR TRAFFIC SYSTEM CLEARING DEFAULT USER SETTINGS AIRWORTHINESS LIMITATIONS SERVICING INFORMATION MAINTENANCE INTERVALS VISUAL INSPECTION ELECTRICAL BONDING TEST GRS 77 oR GRS 7800 EARTH MAGNETIC FIELD UPDATES GSA 80 GREASING PROCEDURE FLAPS IN MOTION DISCRETE INPUT CHECK GSM 85A GSM 86 SLIP CLUTCH TORQUE CHECK PROCEDURE G1000 REDUNDANT CONNECTION CHECK ENGINE DATA CHECK TRIM ANNUNCIATOR CHECK G1000 MISCOMPARE CHECKS NOSE AVIONICS COMPARTMENT FANS OPERATIONAL CHECK INSTRUMENT PANEL FANS OPERATIONAL CHECK STANDBY BATTERY PERIODIC CHECKS POWER BUS CHECK EXTERIOR SKIN INSPECTION AROUND ANTENNAS G1000 ALERTING SYSTEM SYSTEM ANNUNCIATIONS 200 B200 SPECIFIC ALERTS TAWS TROUBLESHOOTING SYNT
8. Check the GIA2 GRS 77 or GRS 7800 2 interconnect wiring for faults Amber Green GIA2 GRS 77 or GRS 7800 2 data path functionality is unknown Reload GIA2 configuration files GIA2 GMA 1347D 2 data path is functioning correctly Red GIA2 GMA 1347D 2 data path is not functioning correctly e Load GIA2 and GMA 13470 2 configuration files e Swap 1347D 2 and 1347 1 reconfigure both GMA s to their new locations to confirm if the problem is in the original GMA 1347D 2 o Replace original GMA 1347D 2 if box turns green after swapping units e Swap GIA2 and GIAI reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA2 o Replace original GIA2 if box turns green after swapping units Check the 1 1347 2 interconnect wiring for faults Amber GIA1 GMA 1347 2 data path functionality is unknown Reload GIA2 configuration files Page 5 16 Revision 9 G1000 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 GIA2 ARINC 429 Channel IN2 145 GRS 77 or GRS 7800 1 GDC 74 2 Or GDC7400 2 Indicator Green Status GIA2 GRS 77 GRS 7800 1 data path is functioning correctly Red GIA2 GRS 77 or GRS 7800 1 data path is not functioning correctly e Reload GIA2 configuration file e Swap GIA2 and GIAI reconfigure both GIA s to their new location
9. Using the small FMS knob select the AUX TELEPHONE page 6 Ensure the system is showing Iridium signal strength best if aircraft is outside 7 Press TEL button on the pilot s GMA 8 Press the DIAL softkey on MFD 9 Enter the test phone number in the ENTER PHONE NUMBER field using the GCU keypad 10 Press the ENT key on the GCU keypad to accept the phone number 11 Press the ENT key on the GCU keypad to initiate the dialing sequence 12 When call is complete press the HANGUP softkey on the AUX TELEPHONE page on the MED to end the call Figure 7 19 AUX TELEPHONE page Tf no other service is to be performed continue to the return to service checks in Section 8 Page 7 66 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 31 Search and Rescue Functional Check On the MFD press the FPL key to display the Active Flight Plan Menu Press the MENU key to display the PAGE MENU Options Scroll through the choices with the FMS knob and select Search and Rescue Press ENT key to complete the selection and view the SAR flight plan menus MP icd OMNI From the Search and Rescue Menu turn the large and small FMS knobs to enter the starting waypoint B Press ENT key to complete the selection and move to the next option PATTERN type 7 Usethe FMS knob to move to the PATTERN type and select PARALLEL 8 With the FMS knob scroll through
10. Existing VHF COM 1 amp 2 Antennas GA 36 and 37 GPS WAAS Antennas GMA 1347D 1 amp 2 GEA 71 1 amp 2 e GDU 1040A 1 amp 2 GSA 80 e GRS 77 or GRS 7800 1 amp 2 Traffic System if installed The GIA 63W 1 interfaces to the following additional equipment GDC 74B 1 GTX 33 or GTX 3000 1 DME 42 if installed GSR 56 if installed per stand alone configuration The GIA 63W 2 interfaces to the following additional equipment GDC 74B 2 e GTX 33 or GTX 3000 2 ADF if installed e if installed e Radar Altimeter if installed Figure 2 6 GIA unit G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 5 190 00915 01 Revision 9 2 1 8 GEA 71 Engine Airframe Unit 2 The Garmin GEA 71 Engine Airframe Units provide engine airframe data to the G1000 system Data received from transducers sensors is processed and sent to GIA 63Ws via RS 485 digital interface and subsequently to the GDU 1500 MFD Engine parameters are normally displayed on the MFD In the event of MFD failure the engine parameters can be displayed on PFD 1 and or PFD 2 using display reversion The GEAs are located behind the instrument panel and is mounted in a vertical orientation Electrical power to GEA 1 is provided from Dual Fed Bus No 1 and to GEA 2 from Dual Fed Bus No 2 Both GEA units will power up immediately with external or aircraft power or battery
11. For other aircraft the FLIGHT ID TYPE field should be set to CONFIG ENTRY or PFD ENTRY NOTE The CONFIG ENTRY setting requires the Aircraft Registration ID number to be entered once in the FLIGHT ID field The PFD ENTRY setting allows the pilot to enter the Aircraft Registration ID number from the PFD via the TMR REF softkey 6 After each configuration setting change press the ENT key to configure the transponders 7 Press the ENT key on PFD1 to acknowledge prompt 8 After completing transponder configuration deactivate the cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 65 190 00915 01 Revision 9 3 48 2 System Software Version 0985 07 and Subsequent 1 v i geo P 3 49 With PFDI in configuration mode select the AIRCRAFT CONFIGURATION page on PFDI Select the AIRCRAFT REGISTRATION field and enter the aircraft s tail number Select the ICAO ADDRESS and enter the aircraft s 24 bit ICAO address If applicable select IATA AIRLINE DESIGNATOR field and enter the airline s 2 digit airline designator code Select the VFR CODE field and enter the desired code that will become active when the VFR key on the GDU is pressed Press the SET GTXT softkey and acknowledge the PFD1 prompt by pressing the ENT key Press the SET GTX softkey and acknowledge the PFD1 prompt by pressing the ENT key Press the
12. If no other service is to be performed continue to the return to service checks in Section 8 7 9 GSA 80 Servos Original Servo s Reinstalled No software loading is required if the removed servo s is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the return to service checks in Section 8 New Repaired or Exchange Servo s Installed If a new repaired or exchange servo is installed the correct software files and certification gains must be loaded to the unit See Section 3 9 and then continue to the return to service checks in Section 8 NOTE Refer to the appropriate servo installation drawing listed in Table 1 2 If no other service is to be performed continue to the return to service checks in Section 8 Page 7 26 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 10 GCU 477 FMS Controller Original GCU 477 Reinstalled No software or configuration loading is required if the removed GCU 477 is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the GCU 477 Test Section 7 10 1 New Repaired or Exchange GCU 477 Installed If a new repaired or exchange GCU 477 is installed the correct software and configuration files must be load
13. SET GTS softkey and acknowledge the PFD1 prompt by pressing the key After completing transponder configuration deactivate the cursor V1 V2 Airspeed Options This option increases the selectable range of the V1 airspeed bug and adds the V2 airspeed bug for aircraft having these parameters defined 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the System Upload page using the PFD1 small FMS knob 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Airframe Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight V1 Airspeed Options Press ENT key on PFDI 4 Verify V1 Airspeed Options is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor Page 3 66 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 50 Splash Screen Loading When all software and configuration has been loaded the splash screens must be loaded to all display units PFDI PFD2 and If not applied apply power to the G1000 syst
14. b Verify security of aft bulkhead connectors GFC 700 Equipment a Using flashlight inspect the servos servo gearboxes connectors support structure and control cables to ensure that no corrosion chaffing cracks or other defects exist b IfGSM 86 servo gearboxes are installed check that the retaining bolt for the slip clutch cartridge is not damaged or loose an assistant manually move the control surfaces and elevator trim wheel from stop to stop and visually observe the corresponding servo and control cabling Ensure there is no binding the control cabling and that the capstan rotates freely d Check the servo control cables in accordance with AC 43 13 1B Chapter 7 Section 8 Paragraph 7 149 to ensure no fraying corrosion or other damage exists If the condition of the cable is questionable replace it with a new one Check the tension on the control cables Refer to the respective servo installation drawing listed in Table 1 2 for cable tension specifications f Ensure that each cable is correctly attached to the clamps g Follow recommended checks for checking main control cables following the instructions in Chapter 27 Flight Controls of the King Air 200 Series Maintenance Manual listed in Table 1 2 h Reinstall the access panels if no other maintenance is to be performed The GMU 44 units mounted in the tailcone or the horizontal stabilizer Refer to Section 6 9 for
15. 2 Click the I Agree button on the confidentiality agreement page 3 Select Technical Tools then select Software Downloads 4 In the Keyword s filter enter 0985 and click on the Go button 5 screen similar to the one shown below will appear The numbers shown are for example only Download symbol Name Type Doc Publish D Date Cw 91000 King Air 200 300 Version Software Jun 17 2011 0905 04 Summary Support Content Name 61000 King Air 200 300 Version 0985 04 008 B0985 04 pat o Size kb 123 6 Click on the download symbol for the appropriate software version part number based upon the information provided in Garmin GA Drawing 005 00421 03 and save the file to the local hard drive G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 3 13 Revision 9 7 Double click the exe file that was downloaded The following window will pop up on the screen Ensure that there is an empty SD card in the card reader and then click Setup WinZip Self Extractor 006 B0985 04 0A exe e 51000 Software Update To install software press Setup WinZip Self Extractor 006 B0985 04 OA exe e 81000 Software Update install software press Setup NOTE When the extraction begins the program automatically deletes all current files on the SD card and copies the selected files to it regardless of the file fo
16. 2 Ensure the STBY ATT and STBY ALTM circuit breakers are closed 3 Ensure the MASTER PANEL LIGHTS rocker switch in the overhead panel is in the ON position 4 Ensure the STBY INSTR knob is turned to full bright Page 8 4 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 Step Desired Result 5 Select depress the STANDBY Verify the following BATTERY switch e STBY Attitude indicator motor is energized as indicated by the indicator motor and the absence of OFF flag STBY altimeter vibrator is active as indicated by vibrator noise and absence of flag e STBY attitude STBY Altimeter STBY Airspeed indicators are illuminated full bright Amber ON is annunciated full bright on the STANDBY BATTERY switch White STANDBY BATTERY legend on the standby battery switch is illuminated full bright 6 Activate aircraft power by selecting the on position of the BATTERY switch Verify the following 4 ON annunciation should extinguish on the STANDBY BATTERY switch e ARM should be fully illuminated green on the STANDBY BATTERY switch The STBY attitude STBY altimeter and STBY airspeed instrument lighting reverts to the aircraft settings The STBY attitude OFF flag not present and STBY altimeter vibrator remains active White STANDBY BATTERY legend on the standby battery switch remains illuminated 7 Deselect the STANDBY BAT
17. GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 24 3 RVSM Static Port Height Inspection The Gauging Assembly p n SPF 4 AIM BCH GE is available from Hawker Beechcraft Any alternate tool authorized in the King Air 200 Series Maintenance Manual for RVSM static port measurements may be substituted for this tool Initialize the tool as follows 1 Make sure the dial indicator reads negative when the plunger is pressed and positive when plunger is free 2 Place the gauging assembly on a flat surface gauge block or equivalent 3 Ensure the smaller needle is at approximately 1 4 Rotate the dial indicator to set the large needle at 0 as shown in Figure 7 10 DIAL INDICATOR Figure 7 10 Dial Indicator The static port measurements are obtained at four locations on each static port as shown in Figure 7 12 These measurements are used to find an AVERAGE and ANGLE for each of the four static ports The AVERAGE is calculated by adding the four measurements and dividing the total by 4 The ANGLE is calculated by subtracting the minimum measurement from the maximum measurement The calculated AVERAGE and ANGLE for each static port must fall within the ranges shown in Figure 7 13 Perform the static port measurement as follows 1 Wipe the surface of static ports clean with isopropyl alcohol 2 Place the gauging assembly onto the static port surface as shown in Figure 7 11 DIAL INDIC
18. GWX 68 Press ENT key PFDI 4 Verify King Air GWX 68 is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column and Software columns for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 35 190 00915 01 Revision 9 3 22 GWX 70 Software Configuration Follow this procedure to configure the GWX 70 Radar if installed Refer to section 3 21 if the GWX 68 Radar is installed Coordinate the GWX 68 configuration with Section 7 12 or GWX 70 Weather Radar 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key PFDI 3 Rotate the small FMS knob to highlight King Air GWX 70 Press ENT key on PFDI 4 Verify King Air GWX 70 is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in th
19. 1 or GRS7800 1 and ARINC 429 IN2 GDC74 1 or GDC7400 1 indicators are green Ref Section 5 2 1 1 With PFD2 selected in the SELECT UNIT window verify the ARINC 429 IN1 GRS77 2 or GRS7800 2 and ARINC 429 IN2 GDC74 2 or GDC7400 2 indicators are green Ref Section 5 2 1 1 Restart the G1000 in normal mode C PFD and MED Ethernet connection check includes ARINC connection check between ADCI and MED and between GRS1 and and the DISPLAY BACKUP button check 1 PW A 13 14 On the right hand circuit breaker panel open the MFD circuit breaker Verify NAV 1 COM 1 NAV 2 and COM 2 remain valid on both PFD 1 and PFD 2 Close the MFD circuit breaker and wait for MFD to initialize Open the PFD 2 circuit breaker Press the DISPLAY BACK UP button on the Pilot s GMA 1347D audio panel Verify NAV 2 and COM 2 are each replaced by a red X and NAV 1 and COM 1 remain valid on both the MFD and PFD 1 Press the DISPLAY BACK UP button on the Pilot s GMA 1347D audio panel to return to normal mode Close the PFD 2 circuit breaker and wait for PFD 2 to initialize Open the PFD 1 PRI and PFD 1 SEC circuit breakers Press the DISPLAY BACK UP button on the Co pilot s GMA 1347D audio panel Verify NAV 1 and COM 1 are each replaced by a red X and NAV 2 and COM 2 remain valid on both the MFD and PFD 2 Verify ADCI data and GRSI data can be displayed on Pr
20. 10 Approach Flaps calibration a Run the flaps to the APPROACH position b Using the force applicator deflect the transducer vane forward UP to the Pot 1 TG force measured in step 11 in Section 7 25 1 If the stall warning horn is already ON turn the Pot 1 CCW until the horn is OFF and then slowly turn the Pot 1 CW until the horn is ON again Press down on the vane until the horn is OFF and slowly release the vane If the horn is not ON when the vane is released turn the Pot 1 until the horn is ON Reduce the force on the vane to 0 TG and reposition the force applicator to apply a downward force on the vane d Calculate the Pot 4 TG force by adding 14 TG to the Pot 1 TG force Example If the Pot 1 force is 9 TG add 14 TG and the Pot 4 force is 5 TG e Install voltmeter leads between TP18 Lo and TP19 Hi of the SK100360 Breakout Box f Apply the calculated Pot 4 TG force to the vane with the force gram applicator g Adjust the Pot 4 on the lift computer until the voltage output from TP18 Lo and TP19 Hi reads 2 2 0 2 VDC on the voltmeter h Return the force on the force applicator to 0 TG 11 Flaps Extended calibration a Run the flaps to the FULL DOWN position b Using the force applicator deflect the transducer vane forward UP to the Pot 2 TG force measured in step 12 in Section 7 25 1 If the stall warning horn is already ON turn the Pot 2 CCW until the horn is OFF and the
21. 4 Largest Smallest UPPER LEFT LOWER LEFT UPPER RIGHT LOWER RIGHT Aircraft s n Date Figure 7 13 Static Port Measurement Log Page 7 46 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 24 4 RVSM Air Data System Check Perform the Air Data Test per Section 7 6 1 If either the pilot or copilot air data system does not meet the tolerances specified have maintenance checks performed on the air data system or the pitot static system IMPORTANT RVSM operations are prohibited until the air data system meets all test conditions G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 47 190 00915 01 Revision 9 7 24 5 RVSM In Flight Altitude Hold Check RVSM operation requires that the autopilot system accurately maintain the acquired altitude during non turbulent non gust cruise conditions The autopilot must be maintained in accordance with the G1000 System Maintenance Manual listed in Table 1 3 The autopilot must be shown to meet the performance specification of the following in flight altitude hold test 1 Verify the following conditions normal RVSM cruise flight Altitude FL290 to FL350 Altimeter setting 29 92 in Hg 1013 HPA Autopilot altitude hold engaged Non turbulent non gust conditions 2 Record the data from the primary cockpit displays as specified by Table 7 9 every 5 minutes fo
22. Check unit power and AP Disconnect power MON MOT PWR ON FAIL Check unit power and AP Disconnect power HALL 1 FAIL Check unit power and AP Disconnect power HALL 2 FAIL Check unit power and AP Disconnect power HALL 3 FAIL Check unit power and AP Disconnect power HALL 4 FAIL Check unit power and AP Disconnect power HALL 5 FAIL Check unit power and AP Disconnect power HALL 6 FAIL Check unit power and AP Disconnect power CURR OFFST FAIL Check unit power and AP Disconnect power SVO TYPE FAIL Check unit power and AP Disconnect power CERT DATA UNINSTALLED Upload the certification gain file to the Control board STRAP CODE MISMATCH Check the connector strap inputs to the unit Page 5 42 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 Normal Mode Faults GIA DIS FAULT Check the AP Disconnect power into the unit HOST DATA DIF Check the AHRS wiring to the system HOST DATA INV Check the AHRS wiring to the system SVO PWR INV Check unit power and AP Disconnect power STRP CODE CHNG Check the connector strap inputs to the unit MET STUCK SWTCH Check the MET switch inputs into the system MET STATUS Check the MET switch inputs into the system G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 43 190 00915 01 Revision 9 5 6 3 2 Downloading GIA and GSA Maintenance Logs If additional assistance
23. FLAP EXTEND changes to a valid condition 3 When the flap motion is completed verify the DATA indicators of the discrete inputs labeled FLAP EXTEND and FLAP RETRACT show an invalid condition 4 Retract the flaps up While the flaps are traveling up check that the DATA indicator of the discrete input labeled FLAP RETRACT changes to a valid condition 5 When the flap motion is completed verify the DATA indicators of the discrete inputs labeled FLAP EXTEND and FLAP RETRACT show an invalid condition 6 Repeat steps 1 through 5 for GIA2 7 The flap discrete input check is complete G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 21 190 00915 01 Revision 9 49 GSM 85A GSM 86 Slip Clutch Torque Check Procedure Perform the test per section 4 9 1 4 9 2 or 4 9 3 The following test procedures are the same for both the GSM 85 and the GSM 86 servo gearboxes 4 91 Automated Slip Clutch Test Procedure SW version 0985 04 and later 1 Before starting test select the AVIONICS MASTER PWR and BATT switches to OFF 2 Press and hold the ENT key on PFDI while applying aircraft EXT power and selecting the AVIONICS MASTER PWR and BATT switches to ON 3 Release the ENT key after INITIALIZING SYSTEM appears in the upper left corner of PFDI Steps 1 through 3 put PFDI in Configuration Mode and PFD2 MED in normal mode 4 Verify the correct type of servo gearbox is configured for ea
24. NOTE New Terrain Obstacle cards Jeppesen Aviation Database and other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The PFD 2 CONFIG PFD 2 G1000 System ID number will change configuration error Config service to new number when installing new reqd master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number Page 5 50 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 9 2 Database Alerts Failure Message MFD1 DB ERR MFD1 aviation database error exists PFD 1 DB ERR PFD 1 aviation database error exists PFD 2 DB ERR PFD 2 aviation database error exists Cause The MED or specified PFD has encountered an error in the Jeppesen aviation database Solution e Reload aviation database into the display e Contact Garmin Technical Support for assistance MFD1 DB ERR MFD1 terrain database error exists The MFD has encountered an error in the terrain database PFD 1 DB ERR PFD 1 terrain database error exists PFD 2 DB ERR PFD 2 terrain database error exists The specified PFD has encountered an error in the terrain database Confirm supplemental data card is inserted fully Reload the database or replace the supplemental datacard Contact Garmin product Support for further assis
25. OFF OFF OFF OFF GDC74 31 GRSTT 41 OFF OFF OFF FF OFF 15 Activate the cursor and select GIA2 in the SELECT UNIT field and then press the ENT key 16 Repeat Steps 13 and 14 G1000 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 8 7 Revision 9 17 On PFDI go to the CAN RS 485 CONFIGURATION page in the GIA Page Group 18 Verify that GIA1 is selected in the SELECT UNIT field 19 Observe the data indicators for all configured RS 485 channels 20 Verify all DATA indicators are GREEN indicating the channels are receiving data as shown CAN RS 485 CONFIGURATION GLa UNLT GIA1 CHANNEL INPUT DATA DATA SET CHNL 1 GOFF CHNL 2 10 485 CHANNEL INPUT DATA Data SET CHNL 7 mGEA 1 CHNL 2 GOFF I0FF CHNL 4 mGFC720 CHNL 5 OFF CHANNEL INPUT OUTPUT DATA SET OFF ACTV gt SET OUTPUT DATA acre GEA 1 OFF OFF 2903 OFF active OFF OFF active GEA 1 OFF OFF GFC720 OFF Figure 8 3 GIA Data Verification RS 485 21 Activate the cursor and select GIA2 in the SELECT UNIT field and then press the ENT key 22 Repeat Steps 18 and 19 Page 8 8 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 8 2 GFC 700 Ground Checkout The following procedures verify the proper operation of the GFC 700 AFCS after maintenance has been performed The technician perfo
26. On the GMC 710 couple the Flight Director to the right side by pressing the XFR button The arrow that is illuminated indicates which side is coupled No flight director modes should be active at this time NOTE On power up the coupled side will default to the left side Each time power is reapplied couple back to the right side and continue test steps 29 Repeat step thru 27 while coupled to right side 30 Remove power to the aircraft and avionics systems by placing the aircraft AVIONICS MASTER PWR and BATT switches to OFF 31 Wait 1 minute before re applying power for further testing as required Page 7 60 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 27 GTS Traffic System Functional Check This section is applicable to the GTS 820 825 TAS GTS 850 855 TCAS 1 and GTS 8000 TCAS traffic systems Perform the following tests to verify GTS 820 850 or GTS Processor operational and surveillance functions Use a ramp tester such as a TIC TR220 or equivalent to perform the tests To perform these tests for the GTS 820 825 850 855 GTS 8 traffic systems the aircraft must be the ground the Radar Altimeter circuit breaker if installed must be opened prior to GTS 8XX unit power on remain open throughout testing and the GTS 8XX must be in Ground Test mode For those tests with the GTS 8000 TCAS II configuration the Radar Altimeter circuit breaker if insta
27. Page 4 26 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 B AHRS and ADC data path check 1 Verify there are AHRS loss of data messages such as AHRS not receiving any GPS information not receiving backup GPS information using backup GPS source Place the G1000 in configuration mode In the GIA page group go to the GIA RS 232 ARINC 429 CONFIG page With GIAI selected in the SELECT UNIT window verify the RS232 Channel 1 GDC74 1 or GDC7400 1 and RS232 Channel 6 GRS77 1 or GRS7800 1 indicators are green Ref Section 5 2 1 2 With GIAI selected the SELECT UNIT window verify the ARINC 429 IN2 GRS77 2 or GRS7800 2 and ARINC 429 INS GDC74 1 or GDC7400 1 and ARINC 429 IN6 GRS77 1 or GRS7800 1 indicators are green Ref Section 5 2 1 2 With GIA2 selected the SELECT UNIT window verify the RS232 Channel 1 GDC74 2 or GDC7400 2 and RS232 Channel 6 GRS77 2 or GRS7800 2 indicators are green Ref Section 5 2 1 2 With GIA2 selected the SELECT UNIT window verify the ARINC 429 IN2 GRS77 1 or GRS7800 1 and ARINC 429 INS GDC74 2 or GDC7400 2 and ARINC 429 IN6 GRS77 2 or GRS7800 2 indicators are green Ref Section 5 2 1 2 In the GDU page group go to the GIA RS 232 ARINC 429 CONFIG page With PFDI selected the SELECT UNIT window verify the ARINC 429 IN1 GRS77
28. SOFTHARE VERSION CONFIGURATION ID CRG PART NUMBER SYSTEM ID Number Location Use the large FMS knob to scroll the cursor to GSR1 if GSR 56 is installed Record the GSR 56 serial number shown in the LRU INFO field For previously activated systems if the GSR 56 satellite receiver unit is replaced the new unit serial number must be registered with Garmin Connext Contact Garmin Product Support and follow the activation procedure as described previously in this section For previously activated systems if the GDL 59 wi fi datalink unit is replaced the system must be registered again This can be accomplished by entering the same passcode received during the intial activation process as described in the following steps Connect to an available network reference Section 7 29 for details 2 Using the large FMS knob select the AUX page group on the MFD Using the small FMS knob select the AUX REPORT STATUS page 3 Press the MENU key on the GCU to display the PAGE MENU window 4 With the Register With GFDS option highlighted press the ENT key on the GCU to display the GARMIN FLIGHT DATA SERVICE REGISTRATION window 5 Using the keypad on the GCU enter the access code provided by Garmin Product Support during the initial activation of the system in the NEW REGISTRATION ACCESS CODE field and press the ENT key on the GCU NOTE The replacement GDL 59 unit must be registered again even if the MFD already shows REGISTER
29. Support Configuration This section applies only to installations with the TAWS A option The procedures outlined in this section must be followed to load the necessary configuration files required to enable TAWS A gear and flap messages A TAWS A enable card is also required for this option see Section 3 41 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Airframe Options and press ENT key on PFD1 3 Rotate the small FMS knob to select King Air TAWS A Support Press ENT key PFDI 4 Verify the King Air TAWS A Support is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor Page 3 38 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 25 5 Voice No Callout Option Configuration This section applies only to installations with the TAWS A option If TAWS A voice callouts 400 300 200 100 are not desired f
30. TAWS Configuration 3 Key Test 7 Alert Configuration 4 Diagnostics 8 DAT Configuration GIA Page Group 1 Serial Configuration 3 GIA Configuration 5 GIA Status Page 2 GIA RS 485 Configuration 4 GIA COM Setup 6 GIA CAN Configuration GEA Page Group 1 Engine Configuration 2 GEA Status Page 3 GEA Configuration GTX Page Group 1 Serial Configuration 2 Transponder Configuration GTX Page Group Aircraft equipped with GTX 3000 1 Transponder Airframe Config 2 Transponder Wiring Config GRS Page Group 1 Inputs Configuration 2 GRS GMU Calibration ADC Page Group 1 ADC Configuration 2 GDC Configuration GFC Page Group 1 GFC Configuration 2 GFC Status GMA Page Group 1 GMA Configuration GDL Page Group 1 GDL 69 Configuration 3 GDL 59 Configuration 5 GSR 56 Configuration 2 GDL 59 Status 4 GDL 59 Report Configuration SW version 0985 06 and prior Page 3 10 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 1T Page Group 1 Remote Controller Status GWX Page Group 1 GWX Configuration GTS Page Group 1 GTS Configuration OTHER Page Group 1 Stormscope CAL Page Group 1 Fuel Tank Calibration 3 HSCM Calibration 2 Flaps amp Trim Calibration 4 DAT Calibration Appears only if option is installed G1000 GFC 700 System Maintenance
31. TERRAIN PROXIMITY or MAP TERRAIN Refer to section 3 40 for TAWS Configuration for configuring TAWS 3 Press the GCU MENU button and select Test TAWS System from the pop up menu Verify TAWS test annunciation is displayed on the MFD and both PFDs 4 After the TAWS test has completed verify that TAWS System Test Okay is heard over the cockpit speaker if selected and the headsets 5 Press the GCU MENU button again and select Inhibit TAWS from the pop up menu and press ENT on the GCU Verify TAWS INH is displayed on PFD 1 and PFD 2 6 Press the GCU MENU button again and select Enable TAWS from the pop up menu and press ENT on the GCU Verify the TAWS INH annunciation on the PFDs has extinguished 7 With a GPS position acquired shield or disconnect the GPS antennas to remove the GPS signal Verify LOI shows on the MFD and the TAWS N A and LOI annunciations show on the PFDs 8 Reconnect or remove the shield from the GPS antennas and verify the MFD LOI indication and PFD TAWS N A and LOI annunciations are removed once the GPS satellites are acquired 9 Pull PFD1 PRI and PFDI SEC circuit breakers Re power PFDI in configuration mode and use the PFD1 FMS knob to select the Audio Alert Configuration page 10 Ensure cockpit speaker is selected ON Use the PFD1 FMS knob to highlight each of the following messages then select PLAY Verify each of the following audio mes
32. and consequently from PFD memory to the LRU memory and vice versa by using the following two softkeys when available 5 gt read Set to Active softkey Allows the installer to send the information in the SET column data stored in the master config module to the ACTV column data used by LRU e gt 5 read Active to Set softkey Causes the LRUs current settings to be copied to master configuration module as SET items CAUTION The ACTV gt SET softkey must be used with caution If an improperly configured unit is installed this softkey causes the wrong configuration to replace the correct aircraft configuration In the first example shown in Figure 3 10 the SET columns do not match the ACTIVE columns The inequality between SET and ACTIVE indicates a configuration mismatch By pressing the SET gt ACTV softkey this copies the SET column to the LRU unit s configuration memory The settings then become the ACTIVE settings for the LRU being configured Configuration Mismatch Maser Configenion Module LRUManory Maser Configuration Mode LRUMmory 5 pm Configuration Correct Master Configuration Module LRUMemory Master Configuration Module LRUMemory om ome cm 7 Figure 3 10 SET gt ACTV Diagram When troubleshooting the system technicians can look for inequalities between SET and ACTIVE columns Certain problems can be re
33. enter the pass code in the ENTER PASSPHRASE field in the WPA SECURITY SETTINGS pop up window Press the ENT key on the GCU to accept the pass code then press the ENT key on the GCU again When the SAVE SETTINGS pop up window is displayed press the ENT key on the GCU keypad to select SAVE CONNECTION Enter the appropriate airport identifier in the SELECT AN AIRPORT TO ASSOCIATE WITH THE CONNECTION field then press the ENT key on the GCU to accept the identifier With the CONNECT button highlighted press the ENT key on the GCU to connect to the network Press the ENT key on the GCU if the verification window Are you sure you want to connect is displayed Verify that the CONNECTION STATUS field on the AUX WI FI SETUP page on the MFD indicates CONNECTED Tf no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 65 190 00915 01 Revision 9 7 30 GSR 56 Satellite Receiver Functional Check 1 Power up in configuration mode 2 On the PFDI select GDL page group using the large FMS knob 3 Using the small FMS knob select the GSR56 Configuration page Ver displayed and information is available the page can be WIN Wo Figure 7 18 GSR56 Configuration Page Restart the G1000 System in Normal Mode 5 Using the large FMS knob select the AUX page group on
34. l Press PFD softkey PFD1 and PFD2 Toggle the and BRG2 softkey until the ADF bearing is shown on PFD1 and PFD2 2 Verify that the ADF window is not invalid no red 3 Using the ADF control head select a known valid local ADF Verify that the ADF bearing pointer moves towards a bearing and stabilizes 4 Select ADF and SPKR GMAI and GMA2 Using the ADF control head select ANT mode Verify that the audio from the station tuned can be heard on the pilots and copilots headset and cockpit speaker 5 Increment the ADF volume control from full low to full high Verify the volume increases and decreases appropriately over pilots and copilots headset and cockpit speaker If no other service is to be performed continue to the return to service checks in Section 8 7 21 5500 Radar Altimeter Functional Check This check verifies that the G1000 radar altimeter interface is operates correctly 1 Navigate to the AUX SYSTEM STATUS page on the MFD 2 Press the RA TEST softkey and verify that the RA TEST annunciation is displayed on both PFDs 3 Verify 40 feet is displayed in the RA display window on both PFDs 4 Press the RA TEST softkey again Verify the RA readout window decreases to 0 feet on PFD1 and PFD2 5 Pull the RADIO ALTM circuit breaker Verify on PFD 1 and PFD 2 that an RA FAIL message is displayed 6 Reset the RADIO ALTM circuit breaker If no other service is to be performed
35. shelf brackets and connectors for corrosion other defects Check the integrity of the shield block ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment GSR 56 iridium option only Tail Location Inspectthe GSR 56 unit if installed shelf brackets and connectors for corrosion or other defects Check the integrity of the shield block ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment Page 4 16 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Lightning Strike Inspection Procedure Item Description Procedure Initials a A post lightning strike inspection must be done for a suspected or actual lightning strike to antennas or the OAT probes Inspect antenna probe and surrounding GTP 59 OAT Probe installation to ensure that there is no structural damage around the areas where orAntenna lightning may have attached If there is visible sign of damage to the probe or antenna then it should be replaced per section 6 Refer to the Hawker Beechcraft Structural Inspection and Repair Manual listed in Table 1 2 for any aircraft structural repairs A Magnetometer Interference Test per Section 5 15 4 and GRS 77 or GRS 7800 and GMU 44 Magnetic Calibration per Section 7 7 4 must be performed after a GMU 44
36. unit has been turned off This unit is very delicate handle like eggs Refer to the 4200 Series Attitude Indicator Installation Manual listed in Table 1 2 for more handling instructions Removal 1 Remove per Section 6 1 2 Disconnect the electrical connector of the standby attitude indicator 3 Use a 0 060 6 Spline wrench to remove the knob from the front of the standby attitude indicator 4 Use a Phillips screwdriver to remove the three attachment screws from the front of the standby attitude indicator Remove the standby attitude indicator Reinstallation 1 Ensure the lighting control voltage switches on rear of unit are set for 28V 1 BH 2 Reinstallation of the standby attitude indicator is the reverse of the removal Reference the Main Instrument Panel Installation drawing listed in Table 1 2 for more details 3 If further maintenance is not required proceed to Section 8 6 28 GIA Cooling Fans Removal 1 Gain access into the nose avionics equipment bay 2 Disconnect the cooling fan hoses from the cooling fan Take necessary precautions to prevent any foreign debris from entering the fan hoses during maintenance 3 Disconnect the electrical connector of the cooling fan 4 Use Phillips screwdriver to remove the attachment screws and fan inlet duct if installed from the cooling fan 5 Remove the cooling fan Page 6 18 G1000 700 System Maintenance Ma
37. 2 19 GRA 5500 Radar Altimeter Figure 2 20 200 B200 Electrical Distribution Post G1000 STC Figure 2 21 G1000 Component Power Sources Figure 2 22 Pitot Static System Post G1000 STC Figure 2 23 G1000 GFC 700 Block Diagram Figure 3 1 GDU 1040A Control Interface Figure 3 2 GDU 1500 Control Interface Figure 3 3 G1000 Sofikeys Figure 3 4 MFD Controls GCU 477 shown Figure 3 5 AFCS Controls GMC 710 shown Figure 3 6 GMA 1347D Controls Figure 3 7 Normal Mode Figure 3 8 Automatic Reversion with failure Figure 3 9 Manual Reversion with pilot PFD failure Figure 3 10 SET ACTV Diagram Figure 3 11 Loss of Communication Figure 3 12 Configuration Stati Figure 3 13 Data Transmission Indicators Figure 3 14 G1000 LRU Configuration File Storage Figure 3 15 GRS GDC Configuration Settings Storage Figure 3 16 Software Configuration Overview Figure 3 17 Airframe Options Figure 3 18 Propeller Options Figure 3 19 Configuration Software Load Page Figure 3 21 Stormscope Configuration Figure 3 22 Servo Mount Configuration Verification Figure 3 23 Supplemental Database Synchronization Figure 3 24 Aircraft Registratioi Figure 3 25 Navigation Database Synchronization Figure 4 1 GIA T O Page Figure 4 2 Discrete Valid Invalid Indication Figure 4 3 GFC Status Page Figure 4 4 GFC Status Pag G1000 GFC 700 System Maintenance Manual 200 B200 Serie
38. 22 Replace GEA 71 Check oil pressure sensor GEA wiring Oil Pressure e Replace oil pressure sensor Replace GEA 71 Check oil temperature sensor GEA wiring Replace oil temperature sensor Replace GEA 71 Oil Temperature Page 5 26 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 2 4 ADF DME Failure A DME or ADF failure is represented by the following red X s Refer to GI000 GFC 700 Wiring Diagram and King Air 200 Series Maintenance Manual listed in Table 1 2 as needed Invalid Field Sensor Solutions ADF Ensure that GIA 63 2 is properly functioning Reload the ADF option configurations Check for proper operation of the ADF receiver Ensure that the receiver is receiving power Check ADF GIA2 interconnect For other failures of the ADF system refer to King Air 200 Series Maintenance Manual listed in Table 1 2 DME Ensure that GIA 63 1 is properly functioning Reload the DME option configurations Check for proper operation of the DME receiver Ensure that the receiver is receiving power Check DME GIA1 interconnect For other failures of the DME system refer to the King Air 200 Series Maintenance Manual listed in Table 1 2 G1000 700 System Maintenance Manual 200 B200 Series King Air Page 5 27 190 00915 01 Revision 9 5 3 200 B200 Spec
39. 28 f this section If no other service is to be performed continue to the return to service checks in ctivation of Garmin Connext In order to activate the optional GDL 59 wi fi datalink and optional GSR 56 satellite receiver for Garmin Connext contact Garmin Product Support at one of the following numbers M F 7 00 a m to 7 00 p m Central Standard Time Central USA e 1 866 739 5687 toll free in USA 1 913 440 1135 worldwide Have the fol lowing information ready prior to calling factivating services for a GDL 59 only installation Aircraft tail number serial number manufacturer and model G1000 system ID number e Ifactivating services for a GDL 59 and GSR 56 installation o Aircraft tail number serial number manufacturer and model o GSR 56 unit serial number o 1000 system ID number Name of aircraft owner and contact information o Credit card information G1000 700 System Maintenance Manual 200 B200 Series King Air Page 7 63 190 00915 01 Revision 9 Garmin Connext will provide additional information for activation of data services To obtain the G1000 system ID number and GSR 56 unit serial number accomplish the following Turn the large FMS knob on the MED to select the AUX page group Turn the small FMS knob to select the SYSTEM STATUS page Record the SYSTEM ID number shown in the AIRFRAME field This number is unique for each G1000 system AIRFRAME
40. 40 Rudder full left 2 50 Rudder full right 3 00 Rudder Trim full left 3 10 Rudder Trim full right 3 20 Elevator full nose UP 330 Elevator full nose DN 355 Elevator trim full nose UP manual electric m Elevator trim full nose DN manual electric 4 00 End of test Table 5 5 Magnetometer Interference Test Sequence Page 5 74 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 6 When the CALIBRATE field is blinking press the ENT key to begin the procedure and have a stopwatch ready to begin recording the elapsed time NOTE It is important that the time equals zero moment corresponds with the moment the PFD first displays the blinking TEST COMPLETE Message Select TEST wen finished Tis site vil den la daa 7 The operator should carry out the actions called for in the prepared test sequence NOTE It is important that all actions are carried out in the order and at the precise elapsed time as specified in the prepared test sequence 8 When the operator has completed the actions specified in the test sequence press the ENTER button to indicate that the process is complete When this is done the TEST COMPLETE field stops blinking 9 PFDI informs the operator if the installation has passed or failed the magnetometer interference test If the test passes no further action is required for this test If the test fails the installati
41. 60 NM Observe the MFD to ensure the proper positioning of the test strikes Verify the strikes are within 10 degrees of the 30 degree azimuth increment and within 12 NM of 60 NM When complete set WX PA for 55 NM set the MFD for 50 NM or the next highest available range and repeat test On the MFD verify the sensor plots points just outside of 25 NM and the strikes are within 10 degrees of the 30 degree azimuth and within 5 NM of 27 5 NM Repeat above setting the MFD for 25 NM or the next highest available range and the WX PA for 15 NM On the MFD verify the positioning of test strikes are within 10 degrees of azimuth and within 2 NM of 7 5 NM Restart the G1000 in configuration mode by opening the PFD and MFD circuit breakers While holding the ENT keys on the PFDs and MFD restore power by closing the PFDs and MFD circuit breakers Select the OTHER page group on the MFD The STORMSCOPE page is shown by default If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 33 190 00915 01 Revision 9 7 15 7 15 1 TAWS Functional Check 1 Functional Check for TAWS B With the G1000 in Normal Mode use the GCU FMS knob to select the MAP group and TAWS page on the MED 2 Verify that the title at the top of the page reads MAP TAWS B NOTE If TAWS has not been enabled the title will read MAP
42. 60234 08 Removal 1 Remove GEA 71 per Section 6 4 Remove GEA connector backplate Remove connector assembly J711 from the backplate Remove screws item 7 and cover item 6 from the backshell item 5 Unscrew thermocouple from boss backshell Extract the thermocouple pins from the connector G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 13 190 00915 01 Revision 9 Replacement 1 Crimp pins item 2 onto each of the thermocouple wires item 1 Ensure that pre stripped wire length is 1 8 prior to crimping 2 Insert newly crimped pins and wires into the appropriate connector housing location item 4 as specified by King Air 200 B200 Wiring Diagram listed in Table 1 2 3 Place thermocouple body item 1 onto the backshell boss item 5 Place the thermocouple as shown in Figure 6 4 so that the wires exit towards the bottom of the backshell 4 Fasten thermocouple tightly to backshell using the provided screw item 3 5 Fasten cover item 6 to backshell using screws item 7 6 Continue to Section 7 4 1 and verify that the ITT indications are valid on the MFD 6 18 GPS WAAS Antennas Removal 1 Gain access to the antenna coaxial cable connector by removing the cabin interior ceiling panel Refer to the Antenna Install drawing listed in Table 1 2 2 Disconnect the antenna coaxial cable 3 Remove the antenna mounting screws 4 Remove antenna Reinstal
43. 7 20 ADF Functional Check 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Airframe Options and press ENT key on PFDI 3 Rotate the small FMS knob to select King Air ADF Option Press ENT key on PFDI 4 Verify the King Air ADF Option is displayed in the Item window Press LOAD 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 41 190 00915 01 Revision 9 3 28 DME Option Configuration This section loads the necessary configuration files for those aircraft equipped with a DME Coordinate the DME configuration with Section 7 19 DME Functional Check 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Airframe Options and press ENT k
44. 96 100 AMBIENT TEMPERATURE F Figure 4 5 Ambient Temperature Conversion Chart Page 4 30 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 4 11 3 Torque Mri ANE qu Remove power from aircraft Disconnect the left engine firewall connector J102 Connect the Signal Generator to pins HI and R LO of J102 Apply external power to aircraft and start the G1000 in normal mode Using the Signal Generator inject DC signals specified in Table 4 15 and verify the indications are within the specified tolerances Test Point VDC Torque Indication FT LB 0 00 02 0 0 2 2 12 02 1100 2 2 88 02 1500 2 4 30 02 2240 4 2 Table 4 15 Torque Indication Test Points On the right hand circuit breaker panel open GIA1 PRI and GIAI SEC circuit breakers and verify the last observed torque indication remains unchanged Reset the the GIAI PRI and GIA SEC circuit breakers Repeat steps 1 through 5 using right engine firewall connector J103 pins C HI and R LO Pull the GIA 2 circuit breaker and verify the last observed torque indication remains unchanged Reset the GIA 2 circuit breaker Remove power from aircraft and reconnect left and right engine firewall connectors G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 31 190 00915 01 Revision 9 4 12 Trim Annunciator Check This procedure
45. Alone Option Configuration Follow this procedure to enable the optional GSR 56 satellite receiver function when installed as a stand alone option Stand alone GSR 56 configurations do not require the GDL 59 Wi Fi data link software configuration installation Coordinate the GSR 56 configuration with Section 7 30 GSR 56 Satellite Receiver Functional Check 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFDI 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight King Air GSR 56 Stand Alone Press ENT key on PFDI 4 Verify King Air GSR 56 Stand Alone is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor Page 3 32 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 19 GRS 77 AHRS Software Configuration Follow this procedure to configure the GRS 77 AHRS if installed Refer to section 3 20 if the G
46. Cause Solution e If message occurred on the first power up after unlocking TAWS cycle power to initialize TAWS e Ensure each GDU contains the correct database data card e Ensure the G1000 is configured for TAWS A TAWS system failure has Y Ifthe system is not configured occurred for TAWS reconfigure per Section 3 9 6 e Verify GIAs are online e Ensure a database GDU SW mismatch has not occurred Ifa mismatch has occurred load correct database software files or replace the terrain card TEST TAWS system is currently N A Test will be conducted up to two being tested minutes ani Enable TAWS system alerting by ITAWS INHB alerting is pressing the INHIBIT softkey on the MAP TAWS e Ensure valid GPS position is received from the AUX GPS GPS system integrity not high STATUS page enough to enable TAWS Check GPS antenna amp associated coaxial cabling e Troubleshoot GIAs TAMS N A e Verify GIAs are online GPRS FAIL A GPWS system failure has e Verify radar altimeter input is valid occurred e Verify baro altitude and vertical speed input are valid G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 29 190 00915 01 Revision 9 5 5 Synthetic Vision and Pathways Troubleshooting The SVS Pathways software feature requires the following G1000 sensors data to be valid e AHRS He
47. Cause Solutions e Load GMC configuration files e Replace GMC e If problem persists replace master configuration module check config module wiring for faults and replace if necessary NOTE New Terrain Obstacle cards The G1000 has detected a Jeppesen Aviation Database and CUR kam d Config error GMC 710 configuration other optional features i e mismatch TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number Check wiring for faults ref Failed Path troubleshooting section 5 7 e Replace the GMC 710 The G1000 has detected a GMC FAIL GMC is inoperative failure in the GMC 710 The system has detected an Load the correct software version MANIFEST GMC software ed incorrect software version See Section 3 9 for the Software loaded in the GMC 710 Load Procedure Page 5 78 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 19 GCU 477 Troubleshooting 5 19 1 Failure Message GCU CNFG GCU Config error Config service req d GCU 477 Alerts and Problems Cause The G1000 has detected a GCU 477 configuration mismatch Solutions e Load GCU configuration files e Replac
48. Data Fault e Attempt configuration per the configuration Download the assert log and send to Garmin for diagnosis FPGA Fault e If upload of FPGA image was recently attempted retry the upload Other wise return unit to Garmin for service ROM Fault lt If upload of audio image or IGRF magnetic field image was recently attempted retry the upload Other wise return unit to Garmin for service Execution Fault Cycle power and retry self test lt Download the assert log and send to Garmin for diagnosis Return unit to Garmin for service if fault persists Electrical Fault Check aircraft power supply lt Download the assert log and send to Garmin for diagnosis Return unit to Garmin for service if fault persists Page 5 94 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Whisper Shout Fault Check cable loss configuration antenna installation and all cable connections and retry self test Return unit to Garmin for service if fault persists Transmit Power Fault 1030 MHz Fault 1090 MHz Fault Check aircraft power supply Return unit to Garmin for service if fault persists Cycle power and retry self test Return unit to Garmin for service if fault persists Cycle power and retry self test Return unit to Garmin for service if fault persists Receiver Cal Fault Transmitter Cal Fault Check antenna installation and all cable connections and retr
49. Diagnostics Terminal page in the System group This page allows the technician to view maintenance logs associated with the GFC 700 3 Choose GIA I or GIA 2 in the LRU window m 4 Inthe SERVO window choose NONE to view the GIA Maintenance Log or choose a servo to view their logs 5 Using the FMS knob choose VIEW MAINTENANCE LOG in the COMMAND window 6 Press ENT key 7 When the Maintenance Log data starts to display in the OUTPUT window you may see More press any key to continue at the bottom of the OUTPUT window This informs you there is more data to display and the system has paused allowing you to view the data before continuing To see more of the data reselect the VIEW MAINTENANCE LOG in the COMMAND window and press the ENT key The press any key to continue function is not active at this time 8 Scroll through the OUTPUT list by pressing the OUTPUT sofikey G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 35 190 00915 01 Revision 9 9 GIA Maintenance Log can record any of the following faults FCS Task not started Bad gains The FCS task has not started because the gains are not present or have been corrupted Reload the gain files to correct FCS Task not started Gain structure out of range The FCS task has not started because the gains are not compatible with the GIA software Reload the gain files to correct PFT FAIL Tim
50. FUNCTIONAL CHECK 7417 CHARTVIEW FUNCTIONAL CHECK 7 18 SAFETAXI FUNCTIONAL CHECK 7419 DME FUNCTIONAL CHECK 7 20 ADF FUNCTIONAL CHECK 7 21 5500 RADAR ALTIMETER FUNCTIONAL CHECK 7 22 NON GARMIN RADAR ALTIMETER CHECK OPTIONAL 7 23 WEIGHT ON WHEELS AND LOW SPEED AWARENESS BAND CHECK 724 RVSM CHECKS 7 25 SAFE FLIGHT LIFT COMPUTER GROUND CALIBRATION 7 26 ESP FUNCTIONAL CHECK 727 GTS TRAFFIC SYSTEM FUNCTIONAL CHECK 7 28 ACTIVATION OF GARMIN CONNEXT 7 29 59 WI FI DATA LINK FUNCTIONAL CHECK 7 30 GSR 56 SATELLITE RECEIVER FUNCTIONAL CHECK 7 31 SEARCH AND RESCUE FUNCTIONAL CHECK SYSTEM RETURN TO SERVICE PROCEDURE 8 1 BACKUP PATH SYSTEM TESTING 82 700 GROUND CHECKOUT 83 MAINTENANCE RECORDS Page iv G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 LIST OF ILLUSTRATIONS FIGURE Figure 2 1 Display Unit Figure 2 2 Audio Panel Figure 2 3 AFCS Controller Figure 2 4 FMS Controller Figure 2 5 Transponder Figure 2 6 GIA unit Figure 2 7 GEA unit Figure 2 8 Air Data Computer Figure 2 9 OAT probe Figure 2 10 AHRS Figure 2 11 Magnetometer Figure 2 12 GDL 69A Datalink Figure 2 13 GDL 59 Wi Fi Datalink Figure 2 14 GSR 56 Satellite Receive Figure 2 15 GTS 820 850 Traffic System Figure 2 16 GTS Traffic Processoi Figure 2 17 Weather Radar Figure 2 18 Servo Figure
51. Figure 3 16 Software Configuration Overview G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 3 19 Revision 9 3 9 0 MFD amp PFD Software Load Follow this procedure to load software to either PFD or the MFD 1 Connect a ground power unit to the external power receptacle and turn on the ground power unit Set the BAT and AVIONICS MASTER PWR switches to ON 3 With the G1000 and GFC 700 powered on pull the MFD PFD 1 PRI PFD 1 SEC and PFD 2 circuit breakers 4 Insert the software loader card into top card slot in the desired PFD or MFD See Section 3 8 for information on creating or obtaining a software loader card NOTE If loading software to all displays it is preferred to load PFD 2 first followed by the MED and then PFD 1 5 While holding the ENT key on the display restore power by closing the appropriate circuit breaker s 6 When the words appear in the upper left corner of the display release the ENT key 7 Press the ENT key or the sofkey labeled YES to acknowledge the following prompt see also note below for MED DO YOU WANT TO UPDATE SYSTEM FILES NO WILL BE ASSUMED IN 30 SECONDS NOTE For the MFD use the far right soft key on the MFD in lieu of the ENT key where called out in Steps 3 through 7 The ENT key for the MFD is located on the GCU 477 FMS controller and may not function prior to software load 8 New software is
52. Fillet seal around antenna Refer to the Antenna Install drawing listed in Table 1 2 4 Reinstall the aft cabin ceiling panel 5 Proceed to Section 7 30 for testing of GSR 56 6 21 Wi Fi Antenna Removal l Gain access to the antenna coaxial cable connector by opening the tail access door behind the aft pressure bulkhead Refer to the Antenna Install drawing listed in Table 1 2 2 Disconnect the antenna coaxial cable 3 Remove the antenna mounting screws 4 Remove antenna Reinstallation i Install antenna using retained mounting screws 2 Connect the antenna coaxial cable 3 Fillet seal around antenna Refer to the Antenna Install drawing listed in Table 1 2 4 Secure the tail access door 5 Proceed to Section 7 29 for testing of the GDL 59 6 22 Signal Conditioners Removal 1 For Signal Conditioner No 1 remove PFD1 from the instrument panel as per Section 6 1 For Signal Conditioner No 2 remove PFD2 from the instrument panel as per Section 6 1 2 Remove 3 top screws from Signal Conditioner rack 3 Slide mounting tray out from rack and disconnect the unit connector If needed remove MFD as per Section 6 1 to access the Signal Conditioner connector 4 Remove the four mounting bolts and remove the Signal Conditioner unit 5 If planning to reinstall the same unit it is not necessary to disconnect the ground strap from the unit ground stud If replacing with a new unit disconnect the ground strap from the removed uni
53. Flight Test and Calibration procedure in accordance with the King Air 200 Series Maintenance Manual listed in Table 1 2 Section 27 31 00 3 Ifthe stall warning points for the new lift computer were set to match the lift computer that was removed adjustments to the new lift computer may not be necessary in flight If the stall warning points are adjusted in flight verify the LAA output per Section 7 25 2 4 Enable the STABILITY amp PROTECTION item via MFD AUX SYSTEM SETUP 2 page Verify that the message ESP OFF is not present 7 26 ESP Functional Check NOTE This procedure is required only for aircraft with the optional Electronic Stability and Protection ESP feature 1 Apply power to the aircraft and avionics systems by placing the aircraft AVIONICS MASTER PWR and BATT switches to ON Ensure G1000 system and components are powered and operating normally Verify the DISPLAY BACKUP button on the audio panel is pushed in so that the GDUs will not operate in reversionary mode 3 Verify no AHRS ADC Autopilot PFD AFCS Mode Controller GCU alert messages or monitor flags HDG MISCOMP etc are present on PFDI or PFD2 4 On initial power up verify that the MFD splash screen includes a graphic similar to the following m GARMIN King Air with Electronic Stability and Protection ESP 5 On the GMC 710 couple the Flight Director to the left side by pressing the XFR button The arrow that is illuminated indic
54. Flight director command bars remain view with autopilot in HDG and ALT mode 17 Replace AHRSI to normal attitude and verify that attitude display on PFD1 displays current aircraft attitude 18 Repeat Steps 13 through 17 for AHRS2 19 The G1000 Miscompare checks are complete Page 4 34 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 414 Nose Avionics Compartment Fans Operational Check This procedure will verify that airflow is present from the ported avionics cooling fans to the 1 and 2 GIA units The fan speed monitoring circuits and annunciations are checked by the G1000 Cooling Fan Fail Annunciation Check in Section 8 1 4 and a Visual Inspection of the fan and its hoses is accomplished in Section 4 4 This check requires the G1000 to be powered 1 Gain access to the nose avionics compartment Disconnect cooling fan hose from the pilot side GIA and verify airflow is present Reconnect the cooling fan hose to the GIA and secure using MS3367 5 9 cable tie Repeat Steps 2 through 3 for the copilot side GIA Sr ro The Nose Avionics Compartment Fans Operational Check is complete 4 15 Instrument Panel Fans Operational Check This procedure will verify that airflow is present from PFD1 MFD and PFD2 cooling fans fan speed monitoring circuits and annunciations are checked by the G1000 Cooling Fan Fail Annunciation Check in Section 8 1 4 This check requires the
55. G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 44 Oil Pressure Indication Functional Check The test tools and equipment listed in Table 7 3 are provided for reference only and are not specifically required Any product conforming to the specification listed may be used It is the responsibility of the technician or mechanic to determine the applicable specification prior to testing Table 7 3 Oil Pressure Indication Test Equipment Name Requirement DC Power Supply 0 10Vdc The following steps are required to be completed on both engines as necessary 1 Remove the engine cowling Ref King Air 200 Series Maintenance Manual Chapter 71 10 00 to gain access to the engine Oil Pressure Transmitter connector P12 TU i og de Table 7 4 Apply external power to aircraft Set the BATT and AVIONICS MASTER PWR switches to ON Disconnect the P12 connector from the Oil Pressure Transmitter Connect the DC Power Supply to pins A and B of the P12 connector Set the DC Power Supply to the output voltages specified in the table below Table 7 4 Oil Pressure Test Points Test Point VDC Indication PSI 0 0 4 1 25 50 4 2 50 100 4 3 75 150 4 5 00 200 4 Observe MFD in normal mode and verify Oil Pressure indications match those values listed in G1000 GFC 700 System Maintenance
56. G1000 Accessories Configuration Module Replacement Qty 7 Removal amp Replacement 6 16 GEA 71 Backshell Thermocouple Qty 2 Removal amp Replacement 6 17 On Condit GTP 59 Probe Removal amp Replacement 67 beh Qty 2 Removal amp Replacement Cooling Fane a8 Refer to Master Drawing List listed in Table N A 1 2 for installation drawings G1000 Lightning Protection Perform the Phase 3 electrical bonding Electrical Bonding resistance check of 61000 equipment 453 Phot Test Perform the Phase 4 electrical bonding resistance check of G1000 equipment 454 Phase 4 Lightning Strike to GTP 59 OAT Probe Inspect the antenna probe and surrounding i or Antenna installation per Table 4 9 Ex On Condition Actual or Suspected i i 44 Lightning Strike to the Inspect the GIA Fan discrete output On Condition Aircraft Table 4 9 G1000 700 System Maintenance Manual 200 B200 Series King Air Page 4 9 190 00915 01 Revision 9 Item Description Procedure Section No Interval Engine Airframe Sensors ITT Thermocouple Cable Qty 2 Oil Pressure Sensor Qty 2 Oil Temperature Sensor Qty 2 Removal amp Replacement Torque Transmitter Refer to King Air 200 Series Maintenance Qty 2 Manual listed in Table 1 2 NA On Condition Fuel Flow Transmitter Qty 2 Prop Tachometer Qty 2 Engine Speed Tachometer Qty 2 signal conditioner Qty 2 R
57. GDU 1040A display unit Page 6 4 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 6 7 GTP 59 OAT Probe Removal 1 Using deep socket to hold the probe in place on the outside of the aircraft loosen the GTP 59 mounting nut and remove the GTP 59 Reinstallation 1 Installation is the reverse of removal 2 No configuration is required for the GTP 59 Test according to Section 7 6 3 6 8 GRS 77 or GRS 7800 AHRS GRS 77 Removal l Gain access to the forward avionics compartment in the nose of the aircraft 2 Disconnect the AHRS connector 3 Loosen the four Phillips thumbscrews with a screwdriver until they are free from the rack 4 Gently lift the GRS 77 from the mounting rack If the mounting rack is removed the GRS 77 must be re calibrated Do not loosen mounting bolts See Section 7 7 GRS 77 Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage Place the GRS 77 on the mounting plate ensuring the orientation is correct Fasten the unit to the plate using the Phillips thumbscrews Connect the connector to the GRS 77 Calibrate and test the GRS 77 according to Section 7 7 de GRS 7800 Remova 1 Gain access to the forward avionics compartment in the nose of the aircraft 2 Disconnect the AHRS connector 3 Pull back on the lockdown mechanisms and simultaneously turn counterclockwise until free 4 Dise
58. GFC Status page for additional GFC 700 system Review the fault and assert logs for the GIAs and servos e Isolate the fault to an LRU Replace this LRU and confirm Resolution Check specifically for proper operation of the GIA 63 Integrated Avionics Units GRS 77 GRS 7800 AHRS Units GDC 74B GDC 7400 Air Data Computers AI GSA 80 Servos displays PFD displays press the ALERTS softkey verify that all LRUs have a green check see Section 5 status software and certification gains GIAs and GSA 80 servos information see Section 5 6 2 the resolution of the annunciation Pitch Axis Failure e Check the AUX SYSTEM STATUS page to see if the Pitch Trim Axis Failure Check that the affected servo is receiving power Check the servo wiring and connector Yaw Axis Failure e For pitch trim check pitch trim switch operation to verify e If failure condition still exists remove and replace the Roll Axis Failure servo is online green check switch contacts are not stuck affected servo AHRS Monitor Failure e Ifthe AHRS inputs have been determined to be unreasonable while the AP is engaged in air this message will be displayed until AHRS inputs are determined reasonable for 5 seconds Elevator Mis Trim Down e If elevator mistrim annunciations persist check the pitch and Check the servo wiring and connectors Ensure th
59. GIA and see what step it is failing NOTE The PFT status is communicated between GIA1 and GIA2 using HSDB As a result both the PFD and must be powered for this state to pass PFT step 15 PFT completed The PFT has successfully completed PFT step 16 PFT failed The PFT has failed G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 39 190 00915 01 Revision 9 5 6 3 1 Servo Faults and Troubleshooting Whenever a servo fault occurs a status message is logged to the corresponding servo control or monitor maintenance log This information is also accompanied by a time and date stamp An RTC DATE entry is made every time a servo is powered on it is normally not useful for troubleshooting The following is a listing of possible faults that could be reported in a GSA fault log Faults can occur in either the monitor board processor or the control board processor both of which are contained in the GSA unit 5 6 3 1 1 Monitor Processor The monitor processor contains the logs that are found in these processors 2 Pitch Servo 4 Roll Servo 6 Yaw 8 Pitch Trim Servo There are two main groupings of faults that can occur in the monitor processor The first grouping of faults can occur during the GSA unit pre flight test PFT If there is a fault during PFT the unit will not be able to transition to normal mode and the only way to clear this state would be to cycle unit power
60. GSM 86 King Air 200 B200 005 00421 48 Pitch Trim Servo Install w GSM 86 King Air 200 B200 005 00421 51 Wire Harness Installation Nose King Air 200 B200 005 00421 52 Wire Harness Installation Cabin King Air 200 B200 005 00421 53 Wire Harness Installation Tail King Air 200 B200 005 00421 54 Control Wheel Modification King Air 200 B200 005 00421 55 Overhead Control Panel Modification King Air 200 B200 005 00421 31 Pedestal Re Configuration King Air 200 B200 005 00421 56 Circuit Breaker Panel Modification King Air 200 B200 005 00421 58 Glareshield Lighting Modification King Air 20 8200 005 00421 A9 Optional Equipment Install Tail Shelf King Air 200 8200 005 00421 00 Hawker Beechcraft Document 101 590010 39 Beech Super King Air 200 and 2007 Wiring Diagram Manual 101 590010 133 Super King Air Wiring Diagram Manual 101 590010 161 Super King Air Wiring Diagram Manual 101 590010 19 Super King Air 200 Series Maintenance Manual 101 590010 453 Super King Air 200 Series Airworthiness Limitations Manual 101 590097 13 King Air Series Component Maintenance Manual 98 39006 Structural Inspection and Repair Manual Other Documents 85 292 1 1033 Signal Conditioner Installation Manual Meggitt Vibro Meter Mid Continent Instruments Installation Manual and Operating Instructions 4200 Series Attitude Indicator 9016182 TP 3
61. Main Instrument Panel Installation drawing listed in Table 1 2 Reinstall the MFD and PFDs as described in Section 6 Page 4 14 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 Table 4 7 Cabin Area Visual Inspection Procedure Item Description Procedure Initials Inspect all external antennas for leading edge erosion and condition of base Antennas seals GPS WAAS top diversity transponder s Iridium top and bottom GA 58 traffic antennas if installed To gain access for the following Inspections remove floorboards in cabin at FS 185 00 and FS 246 750 Inspect all exposed wire harness for chafing damage proper routing of wire Cabin Wiring bundles and security of attachment in accordance with AC 43 13 1B Harness Chapter 11 Section 8 Paragraph 11 96 and the Cabin Wire Harness Routing drawing listed in Table 1 2 Inspect the GTX 33 or GTX 3000 units shelf brackets and connectors for GTX 33 Qty 2 corrosion or other defects Check the integrity of the shield block ground Cabin Location attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment GDL59 a Inspectthe GDL 59 urit if installed shelf brackets and connectors for wifi option only corrosion or other defects Check the integrity of the shield block ground attachments to the harness connector assembly as well a
62. Manual 200 B200 Series King Air 190 00915 01 Page 7 11 Revision 9 7 5 GTX 33 or GTX 3000 Transponder Original GTX 33 or GTX 3000 is Reinstalled No software or configuration loading is required if the removed GTX 33 or GTX 3000 is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to GTX 33 or GTX 3000 Test Section 7 5 2 Original GTX 33 or GTX 3000 Installed in Opposite Locations for Troubleshootin No software loading is required if the original GTX 1 and GTX 2 are installed in opposite locations Continue to Transponder Configuration Section 7 5 1 New Repaired or Exchange GTX 33 or GTX 3000 is Installed If a new repaired or exchange GTX 33 or GTX 3000 is installed the correct software and configuration files must be loaded to the unit per Section 3 9 Continue to Transponder Configuration Section 7 5 1 7 51 Transponder Configuration l Ifnot applied apply power to the G1000 system 2 With PFDI in configuration mode select the GTX page group then select the TRANSPONDER CONFIGURATION page on PFD1 3 The ADDRESS TYPE default is US TAIL To enter a non US Mode S registration number set the ADDRESS field to HEX ID 4 Activate the cursor and highlight the MODE S ADDRESS field Use the small large FMS knobs to enter the US aircraft registration n
63. Out mode displayed on WX PA menu and press MENU ENTER 12 Select the bottom mount antenna configuration on the WX PA keyboard A key 13 Selecta cardinal bearing and a range of 120 NM 14 Use the F1 and F2 keys to adjust range and and F4 keys to adjust heading NOTE The WX 500 will plot data at one half the range selected on the WX PA Page 7 32 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 15 16 17 18 20 21 22 23 24 25 26 27 28 Press MENU ENTER to start the test Observe the MFD to ensure the proper positioning of the strikes based on range and azimuth settings on the WX PA Change the cardinal bearings and verify correct test strikes Verify the strikes are within 10 degrees of the selected azimuth and plot at 60NM 1 2 120 NM Verify after 20 seconds of operation the strike counter reads 580 40 After testing for all ranges and bearings indicated press 2ND then MENU ENTER to return to the main menu Select Circular Pattern mode on the WX PA mode menu and press MENU ENTER Select bottom mount antenna configuration on the WX PA keyboard A key NOTE The MED should be set at 100 NM or next highest available range on the 360 degree weather screen and in strike mode Use the F1 and F2 keys to select 120 NM range and press MENU ENTER to start the test Verify the WX 500 plots discharge points at approximately
64. P12 connector Apply external power to aircraft and start the G1000 in normal mode wo p hoe Using a Signal Generator inject DC signals specified in Table 4 13 and verify the indications are within specified tolerances Test Point Vdc Indication PSI 0 0 10 05 4 125 10 50 4 2 50 10 100 4 4 3 75 10 150 4 4 5 00 10 200 4 Table 4 13 Oil Pressure Indication Test Points 6 On the right hand circuit breaker panel open the GIA1 PRI and GIA1 SEC circuit breakers and verify the last observed oil pressure indication remains unchanged Reset the GIAI PRI and GIA1 SEC circuit breakers 7 Repeat steps 1 through 5 using pins A and of right engine P12 connector 8 Pull the GIA 2 circuit breaker and verify the last observed oil pressure indication remains unchanged Reset the GIA 2 circuit breaker 9 Remove power from aircraft and reconnect left and right engine oil pressure transmitter connectors 4 11 2 ITT 1 Remove power from aircraft 2 Disconnect all thermocouple wires except for the Alumel Green 10 and Chromel White 8 leads from the left hand engine thermocouple junction block mounted to the gas generator case Ref King Air 200 Series Maintenance Manual Chapter 77 00 00 3 Connect the Thermocouple Calibrator or equivalent across the Alumel Green 10 and Chromel White 8 leads of the thermocouple junction block Make sure the polarity of the Alumel
65. PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 8 Press ENT key on PFDI to acknowledge upload complete 9 Deactivate cursor 10 Verify the servo mount configuration per section 3 37 Page 3 54 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 7 Verification of Servo Mount Configuration For software versions 0985 04 and later the section 4 9 1 slip clutch torque check procedure requires the correct type of GSM servo gearbox to be configured The following procedure verifies the type of servo gearbox that is configured for each servo 1 With PFDI in configuration mode use the large FMS knob PFDI to select the GDU page then select AIRFRAME CONFIGURATION using the small FMS knob Activate cursor and rotate the large FMS knob to scroll to the last entries in the AIRFRAME field Verify the correct type of GSM servo gearbox GSM 85 or GSM 86 is installed for each servo AIRFRAME CONFIGURATION IDENTIFICATION RCRAFT King Air 200 8 IRSPEEDS ATION CENTER OFFSET ENGINE TYPE TURBOPROP groon 4 VERTICAL 10 NUM ENGINES 2 groon ATRFRAHE NUH CYLINDERS 1 barber_pole R ENG S N OVERSPEED WARNING RPH 2700 Ur PITCH GSM 85A MIN TACH TIMER RPH 0 ML GSH 85 TACH TIMER 1 1 RPH a YAW GSM 854 PITCH TRIN GSM 85 m Torque G B00R0eH20 3 99500e 22 149208873 ALT TAPE RANGE 1
66. PFD displays are located on either side of the MFD with the stand by instruments located between the Pilot s PFD PFD 1 and the MFD GMA 1347D Audio Panels are located outboard of each PFD Additionally a 710 AFCS Controller is located the upper instrument panel above the and a GCU 477 is installed in the pedestal GCU 477 provides the control interface for the MFD The GDU 1500 communicates with the GDU 1040A units GDL 69A datalink GWX68 or GWX 70 weather radar optional GDLS9 wi fi datalink and optional GTS 820 850 or GTS Processor traffic through a high speed data bus HSDB Ethernet connection The GDU 1500 communicates with the GCU 477 via RS 232 digital interface The GDU 1040A units communicate with each other and the GIA 63W units through a high speed data bus HSDB Ethernet connection PED 1 receives primary electrical power from the new Essential Bus and secondary electrical power from Dual Fed Bus No 1 PFD 2 receives electrical power from Dual Fed Bus No 2 Electrical power to the MED is also provided by the Essential Bus The displays will power up immediately with external or aircraft power or battery operation displays are installed in the King Air panel using turn fasteners Three CDU cooling fans are also installed behind the panel for PFD and MFD cooling Figure 2 1 Display Units Page 2 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 009
67. PFDI pilot while applying power using the PFDI PRI and PFD SEC circuit breakers 8 Release the ENT key after INITIALIZING SYSTEM appears in the upper left corner of PFD1 CAUTION The Configuration Mode contains certain pages and settings that are critical to aircraft operation and safety These pages are protected and cannot be modified unless the technician is properly authorized and equipped However most protected pages are viewable to allow system awareness for troubleshooting NOTE If the specific procedure requires an SD card to be in the top slot of the PFD MFD this card must be inserted prior to applying power to the PFD MFD Any time a card is inserted the power to the PFD MFD must be cycled NOTE For a complete description and breakdown of each Configuration Mode page refer to the G1000 System Maintenance Manual listed in Table 1 3 3 7 1 SET gt ACTV Configuration Throughout the configuration mode pages there are SET and ACTIVE columns for input output settings and other parameters SET Refers to a setting or group of settings that reside in PFD Internal Memory and or the Master Configuration Module ACTIVE Refers to an active setting or parameter currently being used by the LRU LRUs store the active settings within internal memory G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 7 190 00915 01 Revision 9 Data can be manually copied from one column to the other
68. PFDI to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the TAWS B Enable Card from PFDI G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 57 190 00915 01 Revision 9 3 44 Optional TAWS A Enable Follow this procedure to enable the TAWS Class A function A TAWS A Enable Card as specified on General Arrangement Drawing 005 00421 03 will be required for this procedure NOTE The G1000 has various features that require the use of unlock enable cards to activate the feature Throughout this document these cards are generically referred to as enable cards In some cases the actual label on the physical card may say unlock If uncertain the technician should verify the card part number prior to use Ensure that the TAWS A Support Configuration has been loaded per Section 3 24 Ensure that the RAD ALT Option Configuration has been loaded per Section 3 29 Coordinate this configuration with Section 7 15 TAWS Functional Check 1 With the TAWS A Enable card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFDI 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight Configuration Files and press ENT key on PFD1 3 Rotate the small FMS knob to highlight Enable TAWS A Press ENT key on PFD1 4 Verify Enable TAW
69. Passenger Address Telephone Music MUSIC Speaker Marker Beacon Mute E Marker Beacon Signal Sensitivity Transceiver Audio Aircraft Navigation Radio Audio Manual Squelch Digital Recording Playback NTR Intercom System ICS 299 Cabin Intercom ICS VOL 50 Small Knob Master VOL Large Knob Reversionary Mode AY BACKUP Figure 3 6 GMA 1347D Controls Page 3 4 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 5 G1000 Normal Mode To start the G1000 system in Normal Mode 1 With a ground power unit connected to the external power receptacle set the BAT switch to ON The following G1000 equipment is powered displays amp display e GRS 77 or GRS 7800 AHRS Units e GDC 74B or GDC 7400 Air Data Computers e GIA 1 and GIA 2 COM listed separately e GEA 71 Engine Airframe Units e 477 FMS Control Unit e GMC 710 Autopilot Control Unit e GMA 1347D Digital Audio Panel 1 e 1 e GTX 33 or GTX 3000 Mode S Transponder 1 Set the AVIONICS MASTER switch to ON The following G1000 equipment is powered e GTX 33 or GTX 3000 Mode S Transponder 2 e GMA 1347 Digital Audio Panel 2 COM 2 e GDL 69A Datalink Unit e GSA Servos e GWX 68 or GWX 70 Weather Radar Unit e Traffic System e GDL 59 GSR 56 Wi Fi Satellite Optional e Iridium Heater optional Radar Altimeter Optional T
70. RS 232 Channel LRU Indicator Status Green PFD1 GMC 710 data path is functioning correctly PFD1 GMC 710 data path is not functioning correctly Verify GMC710 is powered on If GMC 710 will not power on remove unit and verify power and ground are present at the GMC connector If power or ground is not present troubleshoot aircraft wiring for faults E If power and ground are present replace CHNL2 GMC710 9 GMC 710 e Load PFD1 and GMC 710 configuration files e Swap PFDland PFD to confirm if the problem is in the original PFD1 o Replace original PFDI if box turns green after swapping displays e Check the PFDI GMC 710 interconnect wiring for faults Replace GMC 710 if problem remains PFD1 GMC 710 data path functionality is unknown Reload Amber M PFDI configuration file Page 5 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 PFD 1 ARINC 429 Channel LI Indicator Status G PFDI GRS 77 or GRS 7800 1 data path is functioning correctly PFDI GRS 77 or GRS 7800 1 data path is not functioning correctly e Verify GRS77 or GRS 7800 1 status is using the System Status page on the MFD If it is not correct condition before proceeding reference GRS troubleshooting sections o Swap GRSI and GRS2 no reconfiguration required to confirm if the problem is in the original GRSI o Replace original GRS1 if box
71. Reciever with GDL 59 Wi Fi Data Link Option Configuration Follow this procedure to enable the optional GSR 56 satellite receiver function If the GSR 56 option is reloaded for any reason and the airplane is configured with a GDL 59 the GDL 59 option must also be reloaded per Section 3 16 prior to loading the GSR 56 option Coordinate the GSR 56 configuration with GDL 59 Wi Fi Data Link Option with Section 7 30 GSR 56 Satellite Receiver Functional Check 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob PFDI 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight King Air GSR 56 with GDL 59 Press ENT key on PFDI 4 Verify King Air GSR 56 with GDL 59 is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 31 190 00915 01 Revision 9 3 18 GSR 56 Satellite Reciever Stand
72. Reference the Antenna Install drawing listed in Table 1 2 for more details 2 Disconnect the eight coax quick lock connectors 3 Disconnect the electrical connector 4 Remove the four mounting screws that hold the unit to the installation brackets Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Reattach the unit to the mounting brackets reusing existing hardware Page 6 20 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 Connect the eight coax connectors Note the color coded bands which match the mating connectors on the unit 4 Reconnect the electrical connector pigtail 5 Ensure that all connectors coax and electrical are locked in place 6 Reinstall cabin interior 7 No configuration is required for the GPA 65 Test the GTS 820 850 per Section 7 27 6 32 58 Traffic Antennas Removal l Gain access to the antenna coaxial cable connectors by removing the cabin interior ceiling panel Refer to the Antenna Install drawing listed in Table 1 2 2 Disconnect the four coaxial cable connectors 3 Remove the antenna mounting screws 4 Remove antenna Reinstallation 1 Install antenna using retained mounting screws 2 Connect the four coaxial cable connectors Note the color coded bands which match the mating connectors 3 Fillet seal around antenna Refer to the Antenna Install drawing listed
73. Series King Air Page 4 5 190 00915 01 Revision 9 Description Procedure Item Section No Interval Verify proper operation of the GFC700 by performing the following 821 Pre Flight Test 559 700 Periodic FCS Switch Checks aoe Phase 2 and 4 Autopilot Operation Checks i For installations with the GSM 86 servo 8 23 gearbox Autopilot Clutch Overpower Check TAWS Functional n Periodic TAWS function check 745 Phase 4 GDU 1040A PED Removal amp Replacement 64 On Condition Qty 2 GDU 1500 MFD Removal amp Replacement 64 On Condition Removal amp Replacement 62 On Condition GMA 1347D Test YAT Phase 2 and 4 GMA 1347D Qty 2 Landing Gear Aural Alert Check 722 Phase 2 and 4 XM Audio Suppression Check 723 Phase 2 and 4 GIA 63W IAU Qty 2 63 Removal amp Replacement On Condition GEA 71 EAU Qty 2 64 GTX 33 or GTX Removal amp Replacement 65 Condition 3000 Transponder Qty 2 Special Inspection Perform GTX 33 752 24 Calendar Months GDC 74B or Removal amp Replacement 66 Condition GDC 7400 Air Data Computer Qty 2 Special Inspection Perform Air Data Test 761 24 Calendar Months Special inspection for RVSM compliant aircraft only NOTE These checks required for initial RVSM 24 Calendar Months RVSM checks compliance 7 24 On Condition These checks also required when see note e a static port is removed
74. Servicing Information G1000 LRU maintenance is on condition only No component level overhaul is required for this type design change 4 21 On Condition Servicing Condition replacement and or servicing should occur when an item exhibits conditions symptoms and or abnormalities defined in Section 5 of this manual Replacement and or servicing should be made only after the technician troubleshoots the system to the extent determined necessary by using the guidance in this manual along with common avionics maintenance practices IMPORTANT It is impossible to provide guidance for every conceivable failure scenario within the scope of this manual Every effort has been made to provide comprehensive guidance for possible failures The information in this document should always be combined with sound aviation maintenance practices and a thorough knowledge of the system Use sound avionics maintenance practices when working around or on G1000 equipment The remainder of this document is organized in the following fashion e Section 4 3 lists maintenance requirements related to the G1000 system e Section 6 gives instructions regarding the removal and replacement of physical G1000 equipment and parts e Section 7 gives configuration and testing instructions to be accomplished if G1000 equipment parts are removed or replaced e Section 8 specifies system return to service procedures The beginning of Section 6 provid
75. System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 40 Standard TAWS B Enable Follow this procedure to enable the TAWS Class B function A TAWS B Enable Card as specified on General Arrangement Drawing 005 00421 03 will be required for this procedure NOTE The G1000 has various features that require the use of unlock enable cards to activate the feature Throughout this document these cards are generically referred to as enable cards In some cases the actual label on the physical card may say unlock If uncertain the technician should verify the card part number prior to use Coordinate this configuration with Section 7 15 TAWS Functional Check 1 With the TAWS B Enable card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob PFDI 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight Configuration Files and press ENT key on PFD1 3 Rotate the small FMS knob to highlight Enable TAWS Press ENT key on PFDI 4 Verify Enable TAWS is displayed in the Item window Press LOAD softkey 5 Monitor load progr following Verify software load completes without errors as indicated by the Green PASS in the Configuration column for each item loaded Upload Complete COMPLETE in the summary box 6 Press ENT key on
76. Torque 7 43 Fuel Flow Indication Functional Check The test tools and equipment listed in Table 7 1 are provided for reference only and are not specifically required Any product conforming to the specification listed may be used It is the responsibility of the technician or mechanic to determine the applicable specification prior to testing Table 7 1 Fuel Flow Indication Test Equipment Name Requirement Decade Box 0 1k ohms Signal Generator 0 10Vde 0 1k Hz The following steps are required to be completed on both engines as necessary 1 Remove the engine cowling Ref King Air 200 Series Maintenance Manual Chapter 71 10 00 to gain access to the engine MTS fuel flow transmitter connector P6 Disconnect the P6 connector from the fuel flow transmitter Connect the Decade Box set to a resistance of 1000 10 Q to pins C and D of the P6 connector Connect the Signal Generator to pins A and B of the P6 connector Apply external power to aircraft Set the BATT and AVIONICS MASTER PWR switches to ON Pi MW GA BR ee Inject a 25 mV P P signal with the signal generator and simulate the frequencies specified in the table below 8 Observe MFD in normal mode and verify fuel flow indications match those values listed in Table 7 2 Table 7 2 Fuel Flow Test Points Test Point Hz Indication PPH 0 0 2 140 100 10 561 400 10 841 600 10 Page 7 10
77. View Maintenance Log for GIA data to allow it to continue scrolling down the screen pressing any key will not continue disregard the text instruction you to do so Continue to scroll through all the OUTPUT data until you see the text End of Fault Log Move the curser back to the LRU box select GIA2 in the LRU drop down menu and then press the ENT key to select it Skip the SERVO box and move the cursor to the COMMAND box and select View Maintenance Log in the drop down menu then press the ENT key The error log data will be displayed in the OUTPUT box If you see the more press any key to continue text at the bottom of the screen you may need to reselect View Maintenance Log for GIA data to allow it to continue scrolling down the screen pressing any key will not continue disregard the text instruction you to do so Continue to scroll through all the OUTPUT data until you see the text End of Fault Log If you need to download Servo fault logs usually done at the request of Garmin Product Support perform the following steps Otherwise skip to step 10 a Inthe LRU box you may select either GIA1 or GIA2 b In the SERVO box choose a servo using the FMS knobs Each servo contains two logs one the Monitor MON processor and one in the Control CTL processor You must download both for each servo separately Inthe COMMAND box select View Maintenance Log and press
78. WITH SHO COVER OFF FOR CLARITY Sosese 6 210 LOOKING DOWN SAFE FLIGHT LIFT COMPUTER P N C 05606 1 NOT TO SCALE Figure 7 14 C 05606 1 Lift Computer Page 7 54 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 Figure 7 15 Breakout Box G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 55 190 00915 01 Revision 9 positioner ab 3 into vane opening 8 Tum screws 2 and 6 as required to bring gage pressure arm 7 to bear on surface of vane 8 within 2 Hook anchor tab 3 onto the mounting plate 1 22 of tip a anchor tab engaged shit positioner until cone 6 Apply pressure to aft surface of vane 8 for negative pony d aix femen h Fa eum hon tip grams and forward surface for positive tip grams T 1 counterclockwise until knob clutch slips mm 7 Tum soe 6 to ad lora oram as read Figure 7 16 Force Applicator Usage Instructions Page 7 56 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 25 3 Safe Flight Lift Computer Flight Calibration NOTE This procedure is required only for aircraft with the optional Electronic Stability and Protection ESP feature 1 Disable the STABILITY amp PROTECTION item via AUX SYSTEM SETUP 2 page Verify that the message ESP OFF is present m Perform the
79. Wo CoP Figure 5 4 System Annunciations 5 2 1 Failed Path Messages The following message indicates there is a data path connected to the GDU PFD1 PFD1 or MFD or the GIA 63W 1 or 2 that has failed FAILED PATH A data path has failed The FAILED PATH message is triggered by a timeout of any one digital channel The channels that are checked are listed on these pages in config mode 1 GDU RS 232 ARINC 429 CONFIG PFD1 2 and MFD 2 GIA RS 232 ARINC 429 CONFIG GIA and GIA2 3 GIA CAN RS 485 CONFIGURATION GIA and GIA2 IMPORTANT Once the FAILED PATH message has been triggered it will remain on the list of messages until the next power cycle This latching was implemented so that for intermittent failures the message would remain at the end of the flight to alert maintenance crew Also this keeps the crew from having to acknowledge message repeatedly in the case of intermittent failures The box next to each channel indicates the current status of the channel per the below e Red X data path is known to be failed e Amber question mark data path status is unknown e Green checkmark data path is known to be good G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 5 190 00915 01 Revision 9 The applicable data paths can be verified by viewing the following configuration mode pages 5 2 1 1 GDU RS 232 ARINC 429 CONFIG Page PFD 1
80. above If the plot reveals a discharge curve that meets or exceeds the MINIMUM ACCEPTABLE DISCHARGE CURVE the unit is considered satisfactory 10 If unit discharge plot is satisfactory and no other failures were revealed perform the Charging Procedure within 2 hours of completion of the discharge test Return the unit into service 4 16 3 Cell Isolation Test NOTE No power should be applied to PS 835 Emergency Power Supply during test This test is performed with the battery removed from the aircraft A Press and hold TEST SWITCH Figure 4 6 Item 4 If no OUTPUT VOLTAGE MONITOR LED s come on 1 Position all INDIVIDUAL CELL DIP SWITCHES Figure 4 6 Item 5 to the ON position 2 Press and hold TEST SWITCH Figure 4 6 Item 4 and observe the INDIVIDUAL CELL MONITOR LED s Figure 4 6 Item 1 a If all INDIVIDUAL CELL MONITOR LED s come on except 0512 the unit is damaged and requires repair at an authorized repair station b If all INDIVIDUAL CELL MONITOR LED s are a low battery voltage condition exists B Perform the Charging Procedure 4 16 4 Charging Procedure Constant Voltage Charging Method Locally manufacture a power cable using 16A WG wire and the appropriate mating connector Include Diode 15 Adc min 50 0 PIV or greater to prevent battery discharge in case of loss of power from the power source Using the external power supply apply 30 0 Vdc 10A maximum current limited to J1 connector pins 11 a
81. and Chromel leads are strictly observed when making connections 4 Apply external power to aircraft and start the G1000 in normal mode 5 Using the Thermocouple Calibrator or equivalent inject the DC signals specified in Table 4 14 and verify the indications are within specified tolerances If the Thermocouple Calibrator is not temperature compensated use the chart shown in Figure 4 5 to convert the ambient temperature to millivolts and subtract from Table 4 14 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 29 190 00915 01 Revision 9 Test Point degC DC signal mV Indication degC 200 8 137 200 4 17 400 16 395 400 17 600 24 902 600 12 800 33 277 800 4 7 1000 41 269 1000 12 1200 48 828 1200 17 Table 4 14 ITT Indication Test Points 6 the right hand circuit breaker panel open the GIA1 PRI and SEC circuit breakers and verify the last observed ITT indication remains unchanged Reset the the GIAI PRI and GIAI SEC circuit breakers 7 Repeat steps through 5 using the right hand engine thermocouple junction block 8 Pull the GIA 2 circuit breaker and verify the last observed ITT indication remains unchanged Reset the GIA 2 circuit breaker 9 Remove power from aircraft and reconnect all thermocouple wires to the junction blocks y 0 004x 0 7181 os o2 a2 2 16 EJ w 1 70
82. and all servos PFT step 10 Updating servo RTC This step is setting the system time in the servos to by the same time as the GIA system time This step should never fail PFT step 11 Verify servo PFT status This step is checking to make sure the servos have all passed their own PFT If this step fails please proceed to servo PFT explanation below Page 5 38 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 PFT step 12 Verify AP disconnect enabled This step is checking to make sure GIA1 GIA2 and all servos have are connected to 28 volt AP disconnect If this step fails make sure the AP disconnect input to GIA1 GIA2 and all servos is connected and registering 28 volts Make sure the AP disconnect switch has been installed in the aircraft Make sure no one is holding the AP disconnect switch down on the yoke PFT step 13 Verify servo validity This step is checking to make sure all the Servos are up and communicating with valid data to the GIA in TDM mode If this step fails then make sure all Servos are turned on and communicating by checking for green boxes on the GFC configuration page PFT step 14 Verify cross GIA PFT is completed This step is checking to make sure the other GIA is also on step 14 of its PFT If this step fails try cycling power on GIA2 and all servos If PFT still fails at step 14 then you will need to go check the PFT status of the other
83. appropriate HSI source by using the CDI softkey NOTE The PFD HSI does not show a course deviation bar unless a valid VHF NAV frequency is tuned GFC 700 VOR LOC GS Test 1 Ensure FD is coupled to PFD1 as indicated by left pointing arrow next to AFCS mode controller XFR button Simulate a VOR signal on a radial equivalent to the aircraft heading Tune the NAV 1 and 2 receivers to the simulation frequency Set the HSI PFDI to VORI by pressing the CDI soft key until VORI is selected Set the HSI on PFD2 to VOR2 by pressing the CDI soft key until VOR2 is selected Rotate CRS1 and CRS2 knobs to set VORI and VOR2 course pointers to aircraft heading CDI Synchronization must be set to OFF on the AUX SYSTEM SETUP 1 page on Verify full scale deflection of VOR1 and VOR2 CDI by varying CRS1 and CRS2 selected course at least 10 left and right Reset course pointers to aircraft heading Engage the autopilot and press the NAV key on the AFCS mode controller Using the CRS1 knob alter course by 10 to the right Verify the flight director and aircraft controls respond by flying to the VOR course Repeat to the left Couple FD to PFD2 by pressing the XFR button on the AFCS mode controller Verify FD is coupled right as indicated by a right pointing arrow on the AFCS mode controller next to button Repeat step 5 using CRS2 knob while coupled to PFD2 Set CRS1 and CRS2 course pointers to aircraft
84. assembly to unit 5 Configure and test the GWX 68 or GWX 70 according to Section 7 12 1 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 9 190 00915 01 Revision 9 6 16 Configuration Modules 6 16 1 Configuration Module Removal amp Replacement Configuration modules Reference Figure 6 2 and Table 6 1 Item 1 shown below are located in the following LRU harness connector backshells Item 6 GDU 1040A PFD GRS 77 AHRS GDC 74B Air Data Computer and the GEA 71 Engine Airframe Unit Additionally the GRS 7800 has a different configuration module that is located in the GRS 7800 connector backshell Refer to Section 6 16 2 for the GRS 7800 configuration module removal and replacement instructions Refer to the Master Drawing List listed in Table 1 2 for specific installation drawings Figure 6 2 Configuration Module Installation Table 6 1 Configuration Module Kit 011 00979 00 Item Description Qty Needed Garmin Part Number 1 Configuration Module PCB Board Assembly w EEPROM amp Temp 1 012 00605 00 or 02 2 Spacer Config Module 1 213 00043 00 3 Cable 4 Conductor Harness 1 325 00122 00 4 Pins 22 AWG HD 5 336 00021 00 Removal 1 Disconnect connector from LRU 2 Remove 2 screws 8 from cover 7 and remove cover 3 Unplug connector from configuration module 1 4 Remove configuration module Installation 1 Inspect connector for damaged pins 4 2 Place conf
85. attaching the magnetometer pigtail harness to the shelf Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Fasten the GMU to the aircraft mounting bracket 3 Attach the magnetometer pigtail harness to the shelf with a cable tie 4 Reinstall tailcone and connect the electrical wiring harnes 5 Calibrate and test the GMU 44 according to Section 7 7 For Horizontal Stabilizer Location left or right side Removal 1 Remove inspection access panel second from inboard from lower side of the horizontal stabilizer to gain access to the GMU electrical wiring harness 2 Disconnect GMU pigtail harness from the electrical wiring harness 3 Remove the screws and flux valve access cover from the upper side of horizontal stabilizer 4 Mark the orientation of the GMU adapter plate assembly to the flux valve mounting dish 5 Remove three screws washers connecting the GMU adapter plate assembly to the flux valve mounting dish 6 Remove three screws connecting the GMU to the GMU adapter plate assembly 7 If the unit is to be replaced remove cable ties attaching the phenolic wire guard to the unit and retain the wire guard and grommet from the pigtail harness Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Reinstall the three screws attaching the GMU to the GMU adapter plate assembly 3 Ifa new GMU is
86. be repeated 7 Close No 1 dual bus feeder circuit breaker RH No 1 Verify PFD1 FAN FAIL and GIAI FAN FAIL alert messages are not shown on the PFD If messages illuminates check dual bus feeder circuit breaker RH No 1 associated limiter and diode 8 Open No 1 dual bus feeder circuit breaker RH No 1 9 Close No 1 dual bus feeder circuit breaker LH No 1 Verify PFDI FAN FAIL and GIA FAN FAIL alert messages are not shown on the PFD If messages illuminates check dual bus feeder circuit breaker LH No 1 associated limiter and diode 10 Close No 1 dual bus feeder circuit breaker RH No 1 11 Open No 2 dual bus feeder circuit breaker LH No 2 Verify PFD 2 remains powered If power to PFD 2 is removed check dual bus feeder circuit breaker RH No 2 associated limiter and diode 12 Open No 2 dual bus feeder circuit breaker RH No 2 Verify PFD 2 is not powered 13 Close No 2 dual bus feeder circuit breaker LH No 2 Verify PFD 2 powers up If PFD 2 remains without power check dual bus feeder circuit breaker LH No 2 associated limiter and diode 14 Close No 2 dual bus feeder circuit breaker RH No 2 15 If no other service is to performed remove aircraft power uc pa BY 4 17 2 Dual Bus Feeder Diodes Check Supersedes King Air 200 Series Maintenance Manual 24 50 00 periodic inspection of dual bus feeder diodes 1 Remove aircraft power by turning BATT and AVIONICS MASTER switches to OFF position 2 Remove all electrical power from t
87. cell phone or a device using cell phone GMU 44 technology is not turned on even in a monitoring state in the cabin e Cycle power after moving aircraft away from metal objects to determine if metal objects were the source of the interference Allow up to five minutes for the heading to reinitialize e Perform a Magnetometer Interference Test to check for interference from onboard electrical system components e g NAV lights Pay particular attention to any new electrical devices that have been installed since the aircraft was new Correct any discrepancies that do not allow this test to pass before continuing e Ensure GRS 77 or GRS 7800 GMU 44 connectors are secure e Check the wiring and any inline connectors between the GRS and GMU for faults e MRecalibrate the GMU 44 e Load configuration files to the PFD1 PFD2 GIA1 and GIA2 Y f problem persists replace the GMU 44 Y If problem persists replace the GRS 77 or GRS 7800 Page 5 24 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 Invalid Data Field Associated LRU s GRS 77 or GRS 7800 amp GMU 44 Solution If this message persists longer than five minutes perform AHRS calibration procedures as described in Section 7 7 3 Engine Airframe Sensors All Invalid GEA 71 amp GIA 63W If software was loaded to a new GDU display be sure that the user settings for
88. channels are receiving data as shown below 600477 50477 T Figure 8 1 GDU Data Verification ARINC 429 7 OnPFDI activate the cursor and select PFD2 in the SELECT UNIT field and press the ENT key 8 Repeat Steps 5 and 6 9 OnPFDI activate the cursor and select MFD1 in the SELECT UNIT field and press the ENT key 10 Repeat Steps 5 and 6 11 On PFDI go to the GIA Page Group Go to the RS 232 ARINC 429 CONFIG page 12 Verify that GIAI is selected in the SELECT UNIT field 13 Observe the data indicators for all configured RS 232 and ARINC 429 channels except GIA DEBUG including the GRS 77 or GRS 7800 and GDC 74 ARINC 429 channels 14 Verify all DATA indicators are GREEN indicating the channels are receiving data as shown in the following image Page 8 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 RS 232 ARINC 423 CONFIG N CHANNEL INPUT bara ser anve GDC74 81 6074 21 GIA DEBUG GTA DEBUG OFF OFF OFF OFF GTX 33 1 w TIS GTX 33 1 w TIS 68677 1 GRS77 81 GHA1347 1 GHAT347 1 or OFF active Low Low Low Low Low High Low Low Low Low Low DUNNDLLU OUTPUT 60274 1 GIA DEBUG OFF OFF GTX 33 1 TIS GRST7 1 CHA1347 91 GDC74 1 08577 91 OFF OFF Figure 8 2 GIA Data Verification ARINC429 RS 232 GDC74 1 GIA DEBUG OFF OFF GTX 33 1 v TIS GRS77 1 GMA1347 1 OFF acne
89. checks the pitch trim PTRM annunciation from both GIA 1 and GIA 2 and the mis trim AFCS status alerts 1 Ensure the G1000 is in normal mode autopilot is not engaged and the mode controller XFR key is selected to the pilot side 2 Press the left part of the pilot s pitch trim switch upwards for approximately 10 seconds and verify that the red PTRM annunciation is displayed on both PFD 1 and PFD 2 3 Release the switch and wait for the PTRM annunciation to clear Press the left part of the pilot s pitch trim switch downwards for approximately 10 seconds and verify that the red PTRM annunciation is displayed on both PFD 1 and PFD 2 Release the switch and wait for the PTRM annunciation to clear Repeat Steps 2 through 5 for the right part of the pilot s pitch trim switch Repeat Steps 2 through 6 for the copilot s pitch trim switch po uh e une Select copilot side by pressing the XFR key on the mode controller changes active GIA to GIA 2 Repeat Steps 2 through 7 and verify annunciations are displayed on both PFD 1 and PFD 2 10 Re select pilot side by pressing XFR key on the mode controller changes active GIA back to GIA 1 11 Hold the control yoke in the center position and center the pitch trim wheel 12 Press the Go Around button on the throttle and engage the autopilot Apply a forward load on the control yoke Verify that the pitch trim wheel rotates in the UP direction 13 Disconnect the autopilot by
90. cursor NOTE The DATA window is only updated once every five seconds G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 49 190 00915 01 Revision 9 3 32 ESP Support with AOA Option Configuration This section applies only to installations with the ESP option with AOA modes A new Safe Flight lift computer is used for this configuration The procedures outlined in this section must be followed to load the necessary configuration files required to enable ESP messages and functions An Enhanced AFCS unlock card is also required for this option see Section 3 44 Coordinate this configuration with Section 7 26 ESP Functional Check 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFDI 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Airframe Options and press ENT key on PFDI 3 Rotate the small FMS knob to highlight King Air 200 B200 ESP Support with AoA For software version 0985 03 the option is labeled King Air 200 B200 Series ESP Support Press ENT key on PFDI 4 Verify King Air 200 B200 ESP Support with AoA or King Air 200 B200 Series ESP Support is displayed in the Item window Press LOAD sofikey 5 Monitor load progress Verify software load completes without errors as indicated by t
91. detail gaining access to the GMU ls on GMU 44 Qty 2 For each GMU 44 do the following b Remove the three Phillips screws holding the GMU to the mounting bracket Be sure to use a non magnetic screwdriver to avoid harming the c Carefully remove the assembly taking care not to damage unit or wiring and inspect the GMU 44 and mounting plate d Inspect the mounting hardware and GMU 44 for corrosion or other damage e Inspect all exposed GMU wiring and ensure no chaffing wear or other damage exists in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Wire Harness Installation Tail drawing listed in Table 1 2 Pay particular attention to possible areas of chafing f Reinstall the GMU 44 GRA 5500 Radar Altimeter Inspect the GRA 5500 unit if installed and connectors for corrosion or other defects Check the integrity of the shield block ground attachments to the harness connector assembly as well as the integrity of the individual shield and their attachment GTX 33 or GTX 3000 Qty 2 Tail Location Inspect the GTX 33 or GTX 3000 units shelf brackets and connectors for corrosion or other defects Check the integrity of the shield block ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment GDL 59 wi fi option only Tail Location Inspectthe GDL 59 unit if installed
92. heading Tune the NAV 1 and NAV 2 receivers to the simulation frequency Set the HSI on PFDI to VORI by pressing the CDI soft key until VORI is selected Set the HSI on PFD2 to VOR2 by pressing the CDI soft key until VOR2 is selected Rotate CRS1 and CRS2 knobs to set VORI and VOR2 course pointers to aircraft heading CDI Synchronization must be set to OFF on the AUX SYSTEM SETUP 1 page on the MFD Verify full scale deflection of VOR1 and VOR2 CDI by varying the selected course at least 10 left and right Reset course pointers to aircraft heading Engage the autopilot and press the NAV key on the AFCS mode controller Using the CRS1 knob alter course by 10 to the right Verify the flight director and aircraft controls respond by flying to the VOR course Repeat to the left Couple FD to PFD2 by pressing the XFR button on the AFCS mode controller Verify FD is coupled right as indicated by a right pointing arrow on the AFCS mode controller next to the XFR button Repeat step 5 using CRS2 knob while coupled to PFD2 Set CRS1 and CRS2 course pointers to aircraft heading Simulate a Localizer Glideslope signal Tune this signal on NAV 1 and NAV 2 receiver Set the PFD1 HSI to LOCI and PFD2 HSI to LOC2 by pressing CDI soft key until LOCI and LOC2 is selected Use the test equipment to center the deviation bars localizer and glideslope on PFD1 and PFD2 Press the APR key on the AFCS mode controller Verify that the LOC and GS annunciations are green
93. installed e the RVSM critical region is repaired or painted GRS 77 or GRS 7800 Removal 8 Replacement 68 AHRS Qty 2 Magnetic variation database update 46 GMU 44 Magnetometer Qty 2 GDL 69A 6 10 GWX 68 or GWX 70 6 15 On Condition 710 Removal amp Replacement 6 14 GCU 477 6 13 GTS 820 850 Traffic Unit 530 GTS Traffic Processor 8 45 4 6 61000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 Item Description Procedure Section No Interval GRA 5500 6 36 GPA 65 Unit 6 31 GDL On Condition 59 Wi Fi Removal amp Replacement 6 33 Datalink GSR 56 Satellite 6 30 Receiver For aircraft equipped per MDL 005 00421 00 Rev 15 or previous revisions and not modified per Garmin Service Bulletin G1000 Cooling Fan 1375 Verify the operation of the fan Fail Annunciation power and fan speed monitoring circuits 8 1 4 220 hours max Check for GIA1 fan and GIA2 fan NOTE See Section 6 28 Figure 6 5 for identification of cooling fan installation applicable for this maintenance interval For aircraft equipped per MDL 005 00421 00 Rev 16 or later FAA approved revisions or modified per Garmin Service Bulletin G1000 Cooling Fan 1375 Verify the operation of the fan power Fail Annunciation and fan speed monitoring circuits for GIA1 8 14 820 hours max Check fan and GIA fan NOTE See Section 6 28 Figure 6 6 for identification of coo
94. is installed the correct software and configuration files must be loaded to the unit See Section 3 9 If ChartView or TAWS were previously installed these must be reactivated See Sections 3 39 and 3 40 respectively If any other options were previously installed these must also be reactivated per Section 3 9 Then continue to the PFD MFD Test procedure G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 1 190 00915 01 Revision 9 7 1 1 PFD MFD Test 1 Allow displays to initialize for 1 minute 2 Check that all COM NAV display fields are valid in the top corners of both PFDs 3 Check that attitude heading altitude airspeed vertical speed and OAT fields are valid within 2 minutes of power up on both PFDs 4 Press the SENSOR softkey on each PFD and switch between ADCI and ADC2 Verify that data from both GDC air data computers is valid on both displays 5 Press the SENSOR softkey on each PFD and switch between AHRSI and AHRS2 Verify that data from both GRS 77s 7800s is valid on both displays 6 Check that the engine instrument fields are valid on the MFD 00 Normal Mode Check 7 Push the red DISPLAY BACKUP button on the pilot side 13470 Verify that the pilot side PFD and MED displays enter reversion mode MED should have valid altitude airspeed vertical speed COMMI 2 NAVI NAV2 and engine instruments 8 De activate pilot side reversion mode by pushing the DISPLAY BACKU
95. is used to measure stall warning points of the lift computer 1 Gain access to the stall warning computer 2 Connect the breakout box P N SK100360 or equivalent between the lift computer and the airplane wiring harness see Figure 7 15 3 Make sure that the stall warning heat system is turned OFF 4 Remove the potentiometer access cover plate from the lift computer 5 Simulate an in flight condition as follows Bypass the landing gear safety switch by connecting an electrical ground to TP 7 of the breakout box This is best accomplished by placing a jumper between TP 2 and TP 7 of the breakout box G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 49 190 00915 01 Revision 9 CAUTION The anchor tab of the force applicator can be bent if the knob that applies tension to the transducer mounting plate is over tightened Use care when installing the force applicator to prevent damage to the anchor tab Refer to the data supplied with the force applicator 6 Install the 1952 3 gauge 2 to 15 gram scale in the force applicator see Figure 7 16 onto the left wing in accordance with the manufacturer s instructions Refer to the data supplied with the force applicator The force arm must be positioned so that the applied force is within 1 32 inch of the transducer vane tip Forces applied forward or up will be classified as minus values Forces applied aft or down will be classified as plus values Make su
96. left blank Page 5 96 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 6 Equipment Removal amp Installation This section describes how to remove and replace equipment in the King Air 200 B200 associated with this STC After removal and replacement LRUs must be configured and tested as described in Section 7 CAUTION When removing and or replacing any G1000 component always ensure that aircraft power is off Unplug any auxiliary power supplies Before performing maintenance it is required that the technician verify the LRU software part number and version number matches the software configuration listed in the General Arrangement drawing listed in Table 1 2 NOTE After installation or maintenance of electrical components near the GMU 44 magnetometers either tail or horizontal stabilizer locations perform the Calibration Procedure E Magnetometer Interference Test reference Section 5 and Procedure B GRS 77 or GRS 7800 and GMU 44 magnetic Calibration reference Section 7 To check an LRU software part number and or version follow the procedure defined in Section 3 9 3 If a faulty LRU is not reporting its software version and part number check aircraft maintenance logs for last software version loaded and verify against the General Arrangement drawing The Software Manifest page may also be used to check part numbers and versions The General Arrangement drawing allows alternate
97. locking stud alignment marks are in the vertical position 4 Use a 3 32 hex drive tool to turn each of the four locking sockets 1 4 turn clockwise This may require applying a small amount of forward pressure to engage the turn sockets 5 Configure and test the GCU 477 according to Section 7 10 6 14 GMC 710 Removal 1 Use a 3 32 hex drive tool to turn each of the four locking sockets 1 4 turn counterclockwise until they reach their stops 2 Disconnect backshell assembly from unit Reinstallation 1 Inspect connector s for damaged pins 2 Connect backshell assembly to unit Page 6 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 Hold unit flush with the mounting bracket ensuring locking stud alignment marks are in the vertical position 4 Use a 3 32 hex drive tool to turn each of the four locking sockets turn clockwise This may require applying a small amount of forward pressure to engage the turn sockets 5 Configure and test the GMC 710 according to Section 7 11 6 15 GWX 68 or GWX 70 Removal 1 Gain access by removing nose radome 2 Disconnect backshell assembly from unit 3 Use a 3 16 hex drive tool to remove each of the four mounting screws Reinstallation l Inspect connector for damaged pins 2 Hold unit flush with the radar mount 3 Usea 3 16 hex drive tool to tighten each of the four mounting screws 4 Connect backshell
98. must be inserted top slot of PFD 1 G1000 system must be powered on PFD and MFD must have correct software PFD 1 and MFD must be successfully configured with AIRFRAME SYSTEM MANIFEST MFD1 PFD 1 and PFD 2 configuration files Load Software Configuration files to GMA 1347D GDC 74B or GDC 7400 GEA 71 GRS 77 or GRS 7800 software only GMU 44 software only GTX 33 or GTX 3000 SW Loader Card must be inserted into PFD 1 top slot G1000 must be powered on PFD 1 and MFD must have correct software and configuration settings GIA 63Ws must have correct software GIA 63Ws must be successfully configured with GIA1 and GIA2 configuration files Data path from GIA1 to each LRU must be operational G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 81 Revision 9 5 21 Backshell Backplate Connectors The following figures depict the backplate connectors as viewed with the LRU removed COM ANTENNA CONNECTOR COM BOARD CONNECTOR P601 COOLING PORT T MAIN DISCRETE CONNECTOR P604 MAIN SERIAL CONNECTOR P603 GPS ANTENNA CONNECTO 1 0 CONNECTOR 2 P606 1 0 CONNECTOR 1 P605 G S ANTENNA CONNECT R NAV ANTENNA CONNECTOR VOR ILS CONNECTOR P60 Figure 5 8 GIA 63W Backplate Connectors Page 5 82 G1000 700 System Maintenance Manual 200 B200 Series King
99. neutral position depends on the flap position See table below Flaps Output Full Up 0 3 to 1 3 VDC Approach 0 75 to 1 75 VDC Full Down 1 1 to 2 1 VDC If the output on TP 18 Lo and TP 19 Hi is not within the ranges specified replace the Lift Computer If the output on TP 18 Lo and TP 19 Hi is within the ranges specified check the aircraft wiring in accordance with the appropriate Garmin wiring schematic 5 25 1 Lift Computer Functional Pinout Pin Function Information 1 1 28 VDC Input 2 28 VDC ground 4 O Flap Transmitter Excitation 28 VDC 5 Flap Transmitter Input Half Flap 28 VDC input from the flap transmitter 6 Flap Transmitter Input Full Flap 28 VDC input from the flap transmitter 7 1 Squat Switch Input Logic Open Ground Ground In Air 8 Self Test Input Ground Test 9 O Valid 28 VDC Valid Open Fail 10 28 VDC Essential Bus Input Jumpered from pin 1 of the mating connector 12 O Pre Stall Warning 1 28 VDC Stall Warning 15 O Pre Stall Warning 2 Ground Stall Warning 16 O Transducer Self Test Output 15 VDC for On Ground self test to Lift Transducer Pin 8 of the transducer 17 O System Fail 28 VDC output Fail 18 O Low Airspeed Awareness LAA Lo This output is 0 VDC at stall warning Potentiometers 3 4 and 5 on top of the computer are used to adjust th
100. operation NOTE On serial numbers BB 1484 1486 and subsequent the electrical system includes 1 ENG INSTR and R ENG INSTR buses which after this STC are powered from Dual Fed Bus No 1 and No 2 respectively On these aircraft GEA 1 receives power from Dual Fed Bus No 1 via the L ENG INSTR bus and GEA 2 receives power from Dual Fed Bus No 2 via the R ENG INSTR bus Each GEA interfaces to the following sensors for its onside engine Pressure Sensor Temperature Sensor Fuel Flow Sensor via onside Signal Conditioner Turbine Speed Sensor via onside Signal Conditioner Propeller Speed Sensor via onside Signal Conditioner Torque Sensor Interstage Turbine Temperature ITT Sensor Figure 2 7 GEA unit Page 2 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 2 1 9 Digital Air Data Computer 2 The Garmin GDC 74B or GDC 7400 air data computers compile information from the pitot static system and various outside air temperature OAT and awareness sensors and provide digital air data computations to the G1000 system The GDC communicates with the GIA 63W GDU 1040A and GRS 77 7800 using ARINC 429 digital interface The unit is mounted behind the instrument panel GDC 1 receives primary electrical power from the Essential Bus and a secondary power supply from Dual Fed Bus No 1 GDC 2 receives power from Dual Fed Bus No 2 GDC 1 and GDC 2 connect to
101. opposite unit racks no software loading is required If the GRS rack s was not removed or loosened continue to the GRS GMU Test Section 7 7 6 If the GRS rack s was removed or loosened continue to the GRS GMU Calibration Procedures Section 74 New Repaired or Exchange GRS is Installed Ifa new repaired or exchange GRS is installed then software must be loaded Continue to Section 3 9 for software loading then proceed as follows If the GRS rack s was not removed or loosened continue to the GRS GMU Test Section 7 7 6 If the GRS rack s was removed or loosened continue to the GRS GMU Calibration Procedures Section 74 New GRS Configuration Module is Installed If the GRS configuration module is replaced no software loading is required Continue to the GRS GMU Calibration Procedures Section 7 7 1 Original GMU 44 is Reinstalled If the original GMU 44 is reinstalled then no software loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the GRS GMU Test Section 7 7 6 Original GMU 44 is Installed in Opposite Location for Troubleshooting If the original GMU 1 and GMU 2 are installed in opposite locations GMU 1 and GMU 2 in opposite unit racks no software loading is required However performing the Magnetometer Calibration Procedure is required Continue to the GRS GMU Magnetic Cal
102. or TAWS System Failure voice If test failed TAWS status alert Terrain self test AWS Available voice TAWS status alert Terrain available Vertical Track voice Vertical navigation alerting function Climb Climb voice TCAS II Resolution Advisory Climb at the rate depicted by the solid green bar on the vertical speed tape on the PFD Descend Descend voice TCAS II Resolution Advisory Descend at the rate depicted by the solid green bar on the vertical speed tape on the PFD Monitor Vertical Speed vo S II Resolution Advisory Verify vertical speed is out of the solid G1000 700 System Maintenance Manual 200 190 00915 01 B200 Series King Air Page 5 3 Revision 9 Ted bar on the vertical speed tape on the PFD Level Off Level Off voice TCAS II Resolution Advisory Reduce vertical speed to zero feet per minute Clear of Conflict voice TCAS II Resolution Advisory Range is increasing and separation is adequate to reurn to the applicable clearance unless otherwise directed by ATC Climb Crossing Climb Climb Cros limb voice TCAS II Resolution Advisory Climb at the rated depicted by the solid green bar on the vertical speed tape on the PFD Safe separation is achieved by climbing through the threat s flight path Descend Crossing Descend Descend C
103. other approved sources G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 41 190 00915 01 Revision 9 This page intentionally left blank Page 4 42 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 TROUBLESHOOTING This section provides instructions and guidance for G1000 system troubleshooting as installed in the King Air 200 B200 IMPORTANT Sections 6 7 and 8 provide detailed instructions on equipment removal replacement configuration and return to service testing Anytime a G1000 component or LRU is removed swapped or replaced the technician must follow the procedures given in Sections 6 7 and 8 to ensure proper operation of the system Troubleshoot the G1000 system by first identifying then isolating the specific failure to the responsible LRU There are several indications that the G1000 presents to the pilot or technician showing overall system condition A course of action should be determined based on the information presented on the display This section shows possible scenarios likely to be encountered during normal operation and gives troubleshooting guidance to the technician to resolve problems Figure 5 1 AUX System Status Page sth The AUX System Status page is the 5 page in the AUX Page Group and displays the following information for each LRU and sub function e Status A green check is display
104. other input is received If the DISPLAY BACKUP button is pushed again during this 5 second interval the timer will repeat the count Figure 3 9 Manual Reversion with pilot PFD failure Page 3 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 7 Configuration Mode Overview Throughout this document references are made to the PFD1 PFD2 and or MFD being in configuration mode The configuration mode exists to provide the avionics technician with a means of configuring checking and calibrating various G1000 sub systems Troubleshooting and diagnostics information can also be viewed in this mode To start the G1000 system in configuration mode follow these steps 1 Apply power to the G1000 system by applying aircraft EXT power selecting the AVIONICS MASTER PWR and BATT switches to ON 2 Pull the PFD PRI SEC and PFD2 circuit breakers 3 Press and hold the ENT key on PFD2 co pilot while applying power using the PFD2 circuit breaker 4 Release the ENT key after INITIALIZING SYSTEM appears in the upper left corner of PFD2 5 Press and hold the far right softkey on the MFD while applying power using the circuit breaker Note that the ENT key on the GCU 477 MFD controller may be used after initial software loads 6 Release the softkey after INITIALIZING SYSTEM appears in the upper left corner of the MED 7 Press and hold the ENT key on
105. proper operation Removal amp Replacement GSA 80 Servos Refer to Master Drawing List listed in Table 6 11 On Condition 1 2 for installation drawings Removal amp Replacement Refer to the servo install drawings listed in 6 12 On Condition Master Drawing List listed in Table 1 2 GSM 85A 86 Servo Gear Box all For installations with the GSM 86 servo gearbox verify that the pitch roll yaw 49 Special and pitch trim GSM 86 slip clutch torque 3 000 hours max values are within acceptable limits GSM 86 Servo Gear Box Slip Clutch Torque Check GSM 85A Servo For installations with the GSM 85A servo Gear Box Slip gearbox verify that the pitch roll yaw Clutch Torque and pitch trim GSM 85A slip clutch 49 420 hours max Check torque values are within acceptable limits Denotes Airworthiness Limitation Maintenance Requirement See Section 4 1 Page 4 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 Manual Item Description Procedure Section No Interval wow anon Yont te pai o 1e winno race Speed Awareness assembly and the No 1 and No 2 GIA 123 220 hours max inputs and the air ground status logic Special Exterior skin Inspect the exterior skin around 10 000 cycles inspection around antennas for cracks and loose and 418 initial antennas missing fasteners 1 000 cycles repeat
106. rack ensuring the GRA 5500 rear feet are aligned in the mounting rack slots 3 Slide the GRA 5500 back until the feet are fully engaged with the mounting rack 4 Lift the lockdown mechanism collar in place on the GRA 5500 hook and hand turn the lockdown mechanism knob clockwise until the GRA 5500 is secure and cannot reasonably be ratcheted any tighter by hand 5 Connect the electrical connector 6 Connect the two coaxial cable connectors 7 Configure the GRA 5500 according to Section 3 29 and test per Section 7 22 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 23 190 00915 01 Revision 9 This page intentionally left blank Page 6 24 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 G1000 Equipment Configuration amp Testing This section provides procedures to be followed after a piece of G1000 equipment is replaced At the beginning of each LRU section instructions are given to guide the technician for various removal replacement scenarios These instructions define necessary procedures to be followed for situations where original equipment was reinstalled as well as for situations where new equipment new serial number is installed CAUTION Remove Supplemental Database Cards from the lower slot of all displays before loading software into any unit Not removing the cards may corrupt them Replacing corrupted database cards a
107. small FMS knob to highlight Enhanced AFCS and press ENT key on PFDI 3 Rotate the small FMS knob to select Enable Enhanced AFCS Press ENT key on PFDI 4 Verify Enable Enhanced AFCS is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the Enhanced AFCS Unlock Card from PFDI G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 61 190 00915 01 Revision 9 3 45 Search and Rescue Enable Follow this procedure to enable the Search and Rescue SAR function A SAR Enable Card as specified on the General Arrangement Drawing 005 00421 03 will be required for this procedure NOTE The G1000 has various features that require the use of unlock enable cards to activate the feature Throughout this document these cards are generically referred to as enable cards In some cases the actual label on the physical card may say unlock If uncertain the technician should verify the card part number prior to use Coordinate this configuration with Section 7 31 Search and Rescue Functional Check 1 With the SAR Enable card in the top s
108. small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key PFDI 3 Rotate the small FMS knob to highlight King Air GRS 7800 Press ENT key on PFDI 4 Verify King Air GRS 7800 is displayed the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column and Software column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor Page 3 34 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 21 GWX 68 Software Configuration Follow this procedure to configure the GWX 68 Radar if installed Refer to section 3 22 if the GWX 70 Radar is installed Coordinate the GWX 68 configuration with Section 7 12 or GWX 70 Weather Radar 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key PFDI 3 Rotate the small FMS knob to highlight King Air
109. software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 47 190 00915 01 Revision 9 3 31 1 Lightning System Configuration Load Confirmation Coordinate the StormScope configuration with Section 7 14 Stormscope Functional Check 1 With PFDI in configuration mode use PFD1 large FMS knob to select OTHER and the Stormscope configuration page STATUS FLAG a ran HEADING VALID HEADING sic FLAG SE sic REF RIGGER OO STE FOE San psi E Figure 3 20 Stormscope Configuration Page 2 Activate the cursor to highlight the DATA field Use the small FMS knob to open the drop down menu then select Config and press ENT key on PFDI EE DATA Figure 3 21 Stormscope Configuration Page 3 48 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 Verify that the DATA window shows the following Hdg None 13 1 Jumper 32 Jumper Hdg Valid Flag No Fla Flag Sense Hdg Value aircraft heading Inhibit Line Off Antenna Mount Bottom 13 3 4 Deactivate the
110. the BACK softkey 8 Select the VERTICAL softkey 9 Select the TILT softkey to activate the cursor the TILT field 10 On GCU turn the small FMS knob to select the desired antenna tilt angle Press ENT key Press the GCU FMS knob to remove the cursor 11 Select the GAIN softkey to activate the cursor in the GAIN field 12 On turn the small FMS knob to adjust the gain for the desirable level Verify the gain setting is visible in the gain field as a movable horizontal bar in a flashing box and the line pointer is a reference depicting the calibrated position Press the FMS knob to remove the cursor 13 On select the GAIN softkey again to recalibrate the gain Verify CALIBRATED is displayed in the GAIN field 14 Select the MODE softkey 15 Select the OFF softkey Page 7 30 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 13 Non Garmin Traffic System Functional Check 1 Select the TRAFFIC MAP page on the 2 Verify that the STANDBY OPERATE TEST and ALT MODE soft keys are available on the bottom of the Verify that an operating mode STANDBY OPERATE or TEST not TAS FAIL is displayed in the upper left corner of the traffic map Verify that NO DATA is not displayed in yellow in the center of the display over the aircraft symbol NOTE If the ALT MODE softkey is not displayed the G1000 has not been properly con
111. the WX 500 and verify that no failed test messages appear If fault messages do appear refer to the WX 500 Installation Manual for troubleshooting 2 Following successful power up verify the following mod Access to both 3600 and 1200 weather view modes All available ranges can be displayed Access to the cell mode and strike mode Strike counter is displayed in all weather modes and ranges 3 Key COMI and COM several times on different frequencies representing the lower mid and upper portion of the VHF COM frequency band Verify keying of COMI or COM2 does not cause strike data to appear on the MFD 4 Operate DME XPDR 1 XPDR 2 and weather radar Verify these systems do not cause strike data to appear on the MFD 5 Connect the WX PA cable to the WX PA antenna 6 Position the WX PA antenna on the WX 500 antenna Ensure the connection is tight If necessary use tape to secure the WX PA antenna Ensure the FORWARD arrows are aligned and the WX PA antenna suction cups are positioned forward of center along the longitudinal axis 7 Secure the WX PA cable to the aircraft with the attached suction cup and route the cable to the cockpit 8 Connect the remaining cable end to the WX PA 9 Power up the WX PA and verify the WX 500 is in the weather mapping mode i e 3600 weather view at the 200 NM range 10 Setthe WX 500 to STRIKE mode 100 NM range or next highest available range 11 Select the Continuous
112. the individual shields and their GIA 63W Qty 2 Inspectthe GIA 63W units racks and connectors for corrosion or other defects Check the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment Standby Battery Inspect the standby battery rack and connectors for corrosion or other defaults b Inspectthe standby battery fuses and associated bracket for corrosion or other defects GIA Avionics Fan Qty 2 Inspect remote avionics fans and hoses for dirt accumulation and other damage Remove excess dirt as required GTS 820 850 Traffic or GTS Traffic Processor option Inspect the GTS 820 850 or GTS Traffic Processor unit if installed rack and connectors for corrosion or other defects Check the integrity of the shield block individual shields and their attachment ground attachments to the harness connector assembly as well as the integrity of the LMD Rack and Modules Inspect the LMD rack modules and terminations for corrosion or other defects Nose Wiring harness Inspect bulkhead connectors for security of attachment corrosion or other defects b Inspect wire and coax for chafing damage proper routing of wire bundles and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Nose Wire Harness Routing drawing listed
113. the interface to the GWX 68 or GWX 70 weather radar and optional GDL59 wi fi datalink by acting as a communications hub between the MFD and GWX 68 GWX 70 and GDL 59 via HSDB The GDL 69 also provides XM Radio weather and music entertainment through means of a dedicated satellite data link The GDL 69A is mounted behind the instrument panel Power to the GDL 69A is received from the Avionics No 2 bus The GDL 69A sends weather data through the HSDB bus to the MFD where the data link interface is controlled Digital audio is sent directly to the GMA 1347D Audio Panel Optional remote control GRC 10 and remote control transceiver GRT 10 may be interfaced with the GDL 69A Installation of the GRC 10 and 10 is in accordance with Garmin STC SA01487SE or other approved data Refer to the approved Instructions for Continued Airworthiness information for these units It is recommended that GRT 10 be powered from the Entertainment Bus Figure 2 12 GDL 69A Datalink 2 1 14 GDL 59 Wi Fi Datalink optional The GDL 59 provides a POTS plain old telephone service phone interface and a high speed data link between the aircraft systems and ground computers while the aircraft is on the ground using the IEEE 802 1 1g Wi Fi protocol GDL 59 also provides the interface to an optional GSR 56 satellite datalink which adds airborne low speed data link and voice communication capability The GDL 59 unit interfaces to the Garmin Integrated Flig
114. the options and change the fields as desired or leave the default entries 9 Press ENT key with the ACTIVATE SAR field highlighted to complete and activate the flight plan 10 Verify the parallel track search pattern is on the Navigation Map page If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 67 190 00915 01 Revision 9 This page intentionally left blank Page 7 68 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 8 System Return to Service Procedure After reinstalling any G1000 LRU verify the correct LRU software part numbers and versions against the numbers listed on the General Arrangement drawing listed in Table 1 2 To check an LRU software part number and or version follow the procedure defined in Section 3 9 3 8 1 Backup Path System Testing This final checkout tests various secondary communications paths to ensure that the paths function correctly Perform the following steps and verify the results of each test Before starting create a simple Direct To flight plan to an airport or other waypoint that is greater than 31 NM from the present aircraft position Verify that the phase of flight displayed on the GPS CDI is ENR 8 1 1 Step GPS Failure Test Desired Result Single GPS Failure Condition 1 Ensure GPS satellites
115. this STC are powered from Dual Fed Bus No 1 and No 2 respectively On these aircraft the No 1 Engine Signal Conditioner receives power from Dual Fed Bus No 1 via the L ENG INSTR bus and the No 2 Engine Signal Conditioner receives power from Dual Fed Bus No 2 via the R ENG INSTR bus 2 1 23 Standby Airspeed Indicator A Standby Airspeed indicator Aerosonic part number 25030 0184 is installed between PFD 1 and the Due to varying airspeed marking requirements four marking options are used To determine the appropriate option for a specific aircraft configuration refer to the General Arrangement drawing Garmin Document 005 00421 03 The standby airspeed indicator does not require electrical power for normal operation except for internal instrument lighting which is powered from Dual Fed No 1 Bus and the emergency standby battery This unit is connected to the right hand pitot static system 2 1 24 Standby Altimeter A standby altimeter Aerosonic part number 16650 1172 or Thommen part number 3A43 22 35F 28 I FU is installed between PFD 1 and This unit incorporates a vibrator to ensure accurate display altitude information The vibrator is powered by the new Standby Instrument Bus and the emergency standby battery Internal lighting of this unit is powered from Dual Fed No 1 Bus and the emergency standby battery This unit is connected to the right hand static system 2 1 25 Standby Attitude Indicator The Mid Con
116. turns green after swapping units INI GRS 77 or Red GRS 7800 1 e Load PFD configuration file e Swap PFDI and to confirm if the problem is in the original PFD1 o Replace original PFD1 if box turns green after swapping displays e Swap GRSI and GRS2 no reconfiguration required to confirm if the problem is in the original GRS1 o Replace original GRS1 if box turns green after swapping units Check the PFD1 GRS 77 or GRS 7800 1 interconnect wiring for faults Amber PFDI GRS 77 or GRS 7800 1 data path functionally is unknown Reload PFDI configuration file Green PFDI GDC 1 data path is functioning correctly PFDI GDC 1 data path is not functioning correctly e Verify GDC 1 status is OK using the System Status page on MFD If it is not correct condition before proceeding reference GDC troubleshooting sections GDC 74B 1 e Load PFD1 and GDC 1 configuration files IN2 Or Red e Swap PFDI and to confirm if the problem is in the CSI original PFDI Y o Replace original PFD1 if box turns green after swapping displays e Check the PFD1 GDC 1 interconnect wiring for faults Replace GDC 1 if problem remains Amber PFDI GDC 1 data path functionality is unknown Reload PFD configuration file G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 7 190 00915 01 Revision 9 PFD 2 RS 232 Channel LRU Indicator Status Green PFD2 GMC 710 data
117. twice in the failed axis If the test does not pass the servo gearbox must be removed from the aircraft and tested adjusted per the Servo Gearbox Adjustment Fixture Procedure in Section 4 9 3 4 9 2 Manual Slip Clutch Test Procedure SW version 0985 03 and earlier 1 With in Configuration Mode go to the Page Group and select STATUS Configuration Page using the FMS knob GFC STATUS GIA stay EONLIOK BOARD STATUS por se piscowect SERVO 2 PA proca RES LOD CALL CAL m G LOAD CELL CAL m ENEN sew 2 me D GLIP TEST RESILI unm 717 mam trib TEST SY TEST ALT Figure 4 4 GFC Status Page IMPORTANT It is highly recommended that the following test be performed at temperatures between 50 and 120 Use FMS knob to select the desired servo Verify that the PFT status field shows PASSED Verify that the aircraft control surface to be checked is free to travel throughout its range of motion Press the ENG CLCH softkey on the PFD With the clutch engaged take hold of the aircraft controls and manually overcome the clutch Move the control surface to be tested from stop to stop a minimum of two times each direction 7 Position the control surface the neutral position full forward position if the PITCH SERVO is selected Press the DIS CLCH softkey IMPORTANT If the test must be stopped firmly grasp the aircraft con
118. unlock card will need to be replaced if the master configuration module is changed The 91000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number Page 5 56 Revision 9 G1000 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 5 10 GIA 63 Troubleshooting 5 10 1 COM Symptom Recommended Action e Switch GIA1 and GIA2 to verify location of problem Y f problem follows unit replace GIA Y If problem does not follow unit check COM antenna and cabling for faults e Switch GIA1 and GIA2 to verify location of problem Y f problem follows unit replace GIA Y If problem does not follow unit check COM antenna and cabling for faults e Switch GIA1 and GIA2 to verify location of problem Y f problem follows unit replace GIA Y f problem persists replace GMA1 with a known good unit v If problem persists reinstall original GMA1 and replace GMA2 Weak COM transmit power Weak COM receiver No COM sidetone 5 10 2 NAV Symptom Recommended Action e Set up a NAV COM Ramp Test Set to radiate a test signal e Switch GIA1 and GIA2 to verify location of problem Weak NAV receiver Y If problem follows unit replace GIA Y If problem does not follow unit check NAV antenna coupler and cabling for faults 510 3 G S Symptom Rec
119. use the GTX 33 33D or GTX 3000 transponder configuration loaded per Sections 3 14 or 3 15 respectively There are two different procedures in this section one for G1000 System Software Version 0985 06 and previous and one for G1000 System Software Version 0985 07 and subsequent 3 48 1 System Software Version 0985 06 and Previous l If not applied apply power to the G1000 system 2 With PFDI in configuration mode select the GTX page group then select the TRANSPONDER CONFIGURATION page 3 The ADDRESS TYPE default is US TAIL To enter a non US Mode S registration number set the ADDRESS field to HEX ID 4 Activate the cursor and highlight the MODE S ADDRESS field Use the small large FMS knobs to enter the US aircraft registration number or other Mode S registration number TRANSPONDER CONFIGURATION CONFIGURATION E POR 2 VFR CODE 1200 1200 AIRCRAFT WEIGHT 15500 LBS lt 15 508 LBS X AIRSPEED 300 KTS 300 KTS ADDRESS TYPE US TAIL US TAIL MODE 5 ADDRESS N N FLIGHT 10 TYPE SAHE AS TAIL SAME AS TAIL FLIGHT ID N N ENHANCED SURVETL ENABLED ENABLED ADS B TRANSMIT PFD CONFIG PFD CONFIG AIRCRAFT WIDTH 23 MT lt 23 MT AIRCRAFT LENGTH lt 15 MT lt 15 MT SURVEIL INTEGRITY lt 4x1 5 ERR HR FLT lt 4x1 5 ERR HR FLT Figure 3 24 Aircraft Registration 5 For US registered aircraft the FLIGHT ID TYPE field should be set to SAME AS TAIL
120. verification 2 Ensure that the transmitter or receiver TX RX that you are testing is significantly closer to the ramp tester than another operating RX TX or erroneous and inaccurate results may occur All four quadrants 0 90 180 and 270 degrees will be similarly tested to verify bearing of simulated intruder supplied via the ramp tester are correctly displayed on the MAP TRAFFIC MAP page of the MFD 3 Set up a stationary intruder by selecting the following on the ramp tester Intruder type ATCRBS Intruder Start Distance 2 nm Intruder Start Altitude GTS 8XX 50 000 ft Intruder Start Altitude GTS 8000 Local field elevation Vertical Speed 0 fpm Velocity 0 kts on some ramp testers a velocity greater than 0 kts is required and a stationary intruder is created by not starting the scenario 4 Position ramp tester at 0 degrees 5 Initiate the intruder scenario and verify a target is annunciated on the MAP TRAFFIC MAP page of the MFD at the correct bearing of approximately 0 degree azimuth at 2 NM and co altitude read as 00 above a filled diamond indicating proximate traffic 6 On the ramp tester toggle intruder traffic to standby or off 7 Reposition ramp tester and reengage the same intruder scenario for 90 180 and 270 degrees 8 Verify a target is annunciated on the MAP TRAFFIC MAP page of the MFD at the same bearing as the ramp tester 9 If the bearing is not as anticipated or multiple targets are displaye
121. views for enhanced position awareness Any map page that displays the navigation view can also show the SafeTaxi airport layout within the maximum configured range The following is a list of pages where the SafeTaxi feature can be seen e Navigation Map Page Inset map e Weather Datalink Page e Airport Information Page e Intersection Information Page Information Page e VOR Information Page e User Waypoint Information Page e Trip Planning Page e Nearest Pages 1 Use the FMS knob on GCU to select the AUX System Status page and select DBASE softkey Use the small FMS knob to scroll to CHART category and verify FliteCharts is displayed in blue text adjacent to CHART 2 Verify the FliteCharts database REGION CYCLE number EFFECTIVE EXPIRES and DISABLES dates of the subscription appear in blue text 3 Use the FMS knob on the GCU to select MAP Navigation Map page 4 On GCU press MENU With Map Setup highlighted press ENT on GCU Rotate the small GCU FMS knob to select the Aviation group and press the ENT key on GCU 5 Turn the GCU large FMS Knob to scroll through the Aviation Group options to 6 Turnthe GCU small FMS Knob to display the range of distances 7 Turnthe GCU FMS Knob to select 5000ft as the distance for maximum SafeTaxi display range and then press the GCU ENT key to complete the selection 8 Using the GCU range k
122. well as the integrity of the individual shields and their attachment Inspect the GMA 13470 unit including face of unit rack and connectors for corrosion or other defects Check the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment GMA 13470 Qty 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 13 190 00915 01 Revision 9 Description Procedure Initials PFD and MFD Fans a Inspect fans for accumulation of dirt and other damage Remove excess dirt as Qty 3 required a Inspect the GDL 69A unit rack and connectors for corrosion or other defects Check GDL 69A the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment Inspect the GMC 710 unit including face of the unit mount and connectors for corrosion or other defects Check the integrity of the SHIELD BLOCK ground 710 attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment Signal Conditioner a Inspectthe signal conditioner unit mount and connectors for corrosion or other Qty 2 defects Inspect the standby attitude indicator unit including face of unit and connector for Standby Attitude corrosion or other de
123. 00 B200 Series King Air Revision 9 190 00915 01 1 4 Publications The following documents are required by this maintenance manual to perform maintenance It is the responsibility of the owner operator to ensure latest versions of these documents are used during operation servicing or maintenance of the airplane Table 1 2 Required Documents Part Number Garmin Document Master Drawing List Garmin G1000 GFC 700 in Hawker Beechcraft Model 200 8200 Series King Air 005 W0025 00 Wiring Diagram G1000 GFC 700 King Air 200 B200 005 00421 03 General Arrangement G1000 GFC700 AFCS King Air 200 B200 Series 005 00421 32 GWX Radar Install King Air 200 B200 005 00421 33 Antenna Install King Air 200 B200 005 00421 30 Main Instrument Panel Installation King Air 200 B200 005 00421 34 Electrical Equipment Install Nose Bay King Air 200 B200 005 00421 35 Roll Servo Install w GSM 85A King Air 200 B200 005 00421 36 Yaw Servo Install wGSM 85A King Air 200 B200 005 00421 37 Pitch Servo Install w GSM 85A King Air 200 B200 005 00421 38 Pitch Trim Servo Install w GSM 85A King Air 200 8200 005 00421 39 Magnetometer Install King Air 200 B200 005 00421 40 OAT Sensor Install King Air 200 B200 005 00421 41 Transponder Install King Air 200 B200 005 00421 42 Datalink Install King Air 200 B200 005 00421 45 Roll Servo Install w GSM 86 King Air 200 B200 005 00421 46 Yaw Servo Install w GSM 86 King Air 200 B200 005 00421 47 Pitch Servo Install w
124. 00 B200 Series King Air Revision 9 190 00915 01 3 35 GSM 85A Servo Mount Configuration For software versions 0985 04 and later the section 4 9 1 slip clutch torque check procedure requires the correct type of GSM servo gearbox to be configured It is not required to load this configuration if GSM 86 servo gearboxes are installed for all servos default configuration 1 8 9 With the loader card the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob PFDI Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key on PFD1 Rotate the small FMS knob to highlight King Air 200 B200 GSM 85A Servo Mounts Press ENT key on PFDI Verify King Air 200 B200 GSM 85A Servo Mounts is displayed in the Item window Deselect any servos that have GSM 86 servo gearboxes installed by scrolling to the servo and pressing ENT key on PFDI When all of the servos that have GSM 85A servo gearboxes are selected press LOAD softkey Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box Press ENT key on to acknowledge upload complete Deactivate cursor 10 Verify the servo
125. 00 Cockpit Reference Guide listed in Table 1 2 for basic operation The integrated transponder altitude reporting system must be verified in accordance with Title 14 of the Code of Federal Regulations 14 CFR 91 411 and 91 413 every 24 calendar months or any time the transponder is removed This test requires the use of a Mode 5 ramp generator Specific instructions for operating the ramp tester are contained in the applicable operator s manual Refer to 14 CFR Part 43 Appendices E and F for testing criteria Note that for GTX 33D or GTX 3000 units the aircraft must be put on jacks to simulate an in air condition in order to test the Mode S diversity transmission channel isolation If no other service is to be performed continue to the return to service checks in Section 8 7 6 GDC 74B or GDC 7400 Air Data Computer Original GDC wi Reinstalled No software or configuration loading is required if the removed GDC 74B or GDC 7400 is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to GDC 74B or GDC 7400 Test Section 7 6 1 Original GDC unit Installed in Opposite Locations for Troubleshooting No software loading is required if the original GDC 1 and GDC 2 are installed in opposite locations Continue to GDC 74B or GDC 7400 Test Section 7 6 1 New Repaired or Exchange GDC unit is Installed If a new re
126. 1 Lift Computer Reinstalled No ground or flight calibration is required if the removed C 05606 1 Lift Computer is re installed and the potentiometers are not adjusted This does not include units that were returned for repair as their calibration will need to be completed at installation New Repaired or Exchange C 05606 1 Lift Computer Installed If a new repaired or exchange 05606 1 Lift Computer is installed the ground and flight calibration will need to be accomplished See Section 7 25 2 for the ground calibration and Section 7 25 3 for the flight calibration of the C 05606 1 Lift Computer NOTE Safe Flight P N C 05606 1 lift computers are equipped with six adjustable potentiometers in the top of the computer The potentiometers are marked 0 1 2 3 4 and 5 Ref Figure 7 14 The potentiometers marked 0 1 and 2 are used to calibrate the stall warning points for the three flap positions full up approach and full down The potentiometers marked 3 4 and 5 are used to calibrate the Low Airspeed Awareness LAA output for the three flap positions full up approach and full down which determines Electronic Stability and Protection ESP and Autopilot Underspeed Protection USP alpha floor symbol position 7 25 1 Measuring Lift Computer Stall Warning Points Prior to removal of the lift computer it is recommended that the stall warning points from the lift computer installed in the aircraft be measured This section
127. 1 and 2 on MFD AUX GPS STATUS page If one or both GPS receivers cannot acquire a position lock see GPS troubleshooting section Troubleshoot GIA1 2 GRS1 wiring for faults ref Failed Path troubleshooting section Replace the GRS 77 or GRS 7800 AHRS2 GPS 52 not receiving backup GPS information The GRS 77 or GRS 7800 2 is not receiving backup GPS information from either GIA 63 AHRS2 GPS AHRS2 operating exclusively in no GPS mode The GRS 77 or GRS 7800 2 is operating in the absence of GPS AHRS2 GPS AHRS2 not receiving any GPS information The GRS 77 or GRS 7800 2 is not receiving GPS data from the GPS receivers AHRS2 GPS AHRS2 using backup GPS source The GRS 77 or GRS 7800 2 is using the backup GPS data path Ensure that a cell phone or a device using cell phone technology is not turned on even monitoring state in the cabin Check GPS status for GIA 1 and 2 on MFD AUX GPS STATUS page If one or both GPS receivers cannot acquire a position lock see GPS troubleshooting section Troubleshoot GIA1 2 GRS2 wiring for faults ref Failed Path troubleshooting section Replace the GRS 77 or GRS 7800 2 AHRS MAG DB AHRS magnetic model database version mismatch The G1000 has detected a magnetic model database version mismatch Load AHRS magnetic model field in both GRS units G1000 GFC 700 System Maintenanc
128. 12 15 e 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 e e e o o o e 6 31 32 33 34 3 36 37 3 39 40 41 42 43 44 Figure 5 21 GWX 68 Backshell Connector 681 Bi 65 66 42 43 44 45 46 47 48 40 50 e 10 11 12 13 14 15 16 Figure 5 23 GTS 820 850 Mating Connectors P8001 and P8002 Rear View Figure 5 24 GTS 820 850 Mating Connector P8003 Rear View 0000000060 43 44 45 46 47 48 49 50 51 e eee 22 23 24 25 28 29 30 31 33 34 3 4 5 6 7 8 9 10 1 12 Figure 5 25 GTS Processor Connector P8001 1000 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 86 Revision 9 Figure 5 26 GPA 65 Mating Connector P651 Rear View Figure 5 27 Signal Conditioner 1PVIB1 and 2PVIB1 Rear View Figure 5 28 GDL 59 Mating Connector 1P591 Rear View Figure 5 29 GSR 56 Mating Connector 1P561 Rear View G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 87 190 00915 01 Revision 9 Figure 5 30 GRA 5500 Connector P55001 Page 5 88 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 22 Symptom Warning flag pops into view indicating that the gyro motor is not receiving sufficient power to operate Standby Attitude Indicator Tro
129. 12 Updated procedures for software version 0985 04 90414 6 7 19 12 es GA drawing reference error in Section 93256 Add SW v0985 06 added GDC 7400 option 10 24 12 updated section 4 airworthiness limitations 35300 8 6 5 13 Update for GMU 44 in horizontal stabilizer 103013 9 2 21 14 Update for GRS 7800 GTX 3000 GTS Processor 111858 DOCUMENT PAGINATION Section Pagination Table of Contents i viii Section 1 131 16 Section 2 2 1 2 20 Section 3 3 1 3 70 Section 4 4 1 4 42 Section 5 5 1 5 96 Section 6 6 1 6 24 Section 7 7 1 7 68 Section 8 8 1 8 15 PageA G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 INFORMATION SUBJECT TO EXPORT CONTROL LAWS This document may contain information which is subject to the Export Administration Regulations EAR issued by the United States Department of Commerce 15 CFR Chapter VII Subchapter C and which may not be exported released or disclosed to foreign nationals inside or outside the United States without first obtaining an export license The preceding statement is required to be included on any and all reproductions in whole or in part of this manual WARNING This product its packaging and its components contain chemicals known to the State of California to cause cancer birth defects or reproductive harm This Notice is being provided in accordance with Californi
130. 1234 in the window Press the XPDR key until the light to the right of the button is lit Verify a flashing box appears in the XPDR 2 code window Using GCU477 keypad enter in a code of 1234 Verify XPDR2 shows a code of 1234 in the window If no other service is to be performed continue to the return to service checks in Section 8 Page 7 28 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 31 GMC 710 AFCS Controller Original GMC 710 Reinstalled No software or configuration loading is required if the removed GMC 710 is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the GMC 710 Test Section 7 11 1 New Repaired or Exchange GMC 710 Installed If a new repaired or exchange GMC 710 is installed the correct software and configuration files must be loaded to the unit See Section 3 9 and then continue to the GMC 710 Test Section 7 11 1 7 11 1 GMC 710 Test Perform a basic operational check on the GMC 710 The following knob wheel and key presses and rotations are to be performed on the GMC 710 1 Ensure the G1000 is operating in normal mode and the autopilot is operational 2 Press the FD key a few times verify the Flight Director display on PFD1 toggles on and off Leave the flight director displayed 3 Press the XFR key and verify the whi
131. 15 01 21 3 13470 Audio Panel 2 The Garmin GMA 1347D Audio Panel integrates NAV COM digital audio intercom system and marker beacon controls The 200 B200 installation includes two GMA 1347D panels The GMA 1347D panels provide control of all cockpit intercom mic systems as well as NAV COM ILS audio The units also provide display reversion mode control through a large red button Warning and alert audio received by the GMA 1347Ds is processed by and received from the GIA 63W Integrated Avionics Units AUs Electrical power to GMA 1 is provided from the Essential bus Electrical power to GMA 2 is provided from Avionics Bus No 1 GMA 1 will be powered immediately with external or aircraft power or battery operation GMA 2 will operate after selecting Avionics Master on The GMA 1347D units interface with the existing marker beacon antenna as well as existing mic and phone jacks and oxygen mask mic Figure 2 2 Audio Panel 21 4 GMC 710 AFCS Control Unit The dedicated AFCS controls on the GMC 710 allow crew control interface with the various GFC 700 autopilot flight director functions GMC 710 controls are discussed in detail in the G1000 King Air 200 B200 Series Cockpit Reference Guide The GMC 710 is powered by Dual Fed Bus No 1 Figure 2 3 AFCS Controller G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 3 190 00915 01 Revision 9 2 1 5 GCU 477 FMS Control Unit The GCU 477 functions as
132. 1PVIB1 and 2PVIBI Figure 5 28 GDL 59 Mating Connector 1P591 Figure 5 29 GSR 56 Mating Connector 1P561 Figure 5 30 GRA 5500 Connector P55001 Figure 6 1 Servo Gear Figure 6 2 Configuration Module Installation Figure 6 3 GRS 7800 Configuration Module Installation Figure 6 4 GEA Backshell Thermocouple Figure 6 5 GIA Cooling Fan Installation Figure 6 6 GIA Cooling Fan Inlet Duct Installation Figure 7 1 G1000 Normal Mode Check Figure 7 2 Marker Beacon Symbology Figure 7 3 AUX GPS STATUS Page Figure 7 4 Normal Engine Instrument Markings MFD Figure 7 5 Aircraft Registration Figure 7 6 Engine Run Up Test Page Figure 7 7 Normal Mode AHRS Check Figure 7 8 Low Speed Awareness Band Symbolizatio Figure 7 9 RVSM Critical Region Figure 7 10 Dial Indicator Figure 7 11 Static Port Measurement Figure 7 12 Static Port Measurement locations Figure 7 13 Static Port Measurement Log Page vi G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 Figure 7 14 C 05606 1 Lift Computer Figure 7 15 Breakout Box Figure 7 16 Force Applicator Usage Instructions Figure 7 17 GTS 820 850 or GTS Processor GND TEST softkey 7 61 Figure 7 18 GSR56 Configuration Page Figure 7 19 AUX TELEPHONE page Figure 8 1 GDU Data Verification ARINC 429 Figure 8 2 GIA Data Verification ARINC429 RS 232 Figur
133. 2 receiver Replace GIA GPS1 FAIL GPS1 is inoperative The system has detected a failure in GPS1 receiver GPS2 FAIL GPS2 is inoperative The system has detected a failure in GPS2 receiver Switch GIA1 and GIA2 to verify location of problem v If problem follows the unit replace GIA Y If problem does not follow the unit check GPS antenna and cabling Page 5 62 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Failure Message Cause Solution LOI GPS integrity lost Crosscheck with other NAVS If the primary receiver is a WAAS sensor the alert indicates that GPS position data has timed out GPS NAV LOST Loss of GPS navigation Insufficient satellites There is no GPS position fix available or the system is in dead reckoning mode GPS NAV LOST Loss of GPS navigation Position error The G1000 has detected an internal position warning has occurred GPS NAV LOST Loss of GPS navigation GPS fail The G1000 has detected a GPS engine failure e Verity the area the aircraft was traveling through did not have loss of GPS coverage FAA NOTAMs may be issued for periods of outages or the US Coast Guard website http www navcen usc ic S notices default htm will have notices posted Using the MFD AUX GPS Status page verify the signal strength bars are not erratic If s
134. 27 249 3 02415 03 TAS TAPE RANGE 3 72918 03 VS RANGE 4000 4 06745e 03 352512e 03 LEFT TANK USEABLE 1825 218 RIGHT TANK USEABLE 1825 218 CNTR TANK USEABLE ri TYPE Jet A Figure 3 22 Servo Mount Configuration Verification 4 Deactivate cursor If any of the servo gearboxes shown do not match the actual installation on the aircraft reload the correct servo gearbox configuration per section 3 35 or 3 36 as applicable G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 55 190 00915 01 Revision 9 3 38 FliteCharts Configuration If ChartView has previously been enabled and is no longer desired follow the procedures outlined in this section to return the G1000 system to the basic FliteChart functions If ChartView has not been enabled the following procedure is not required Loading of the baseline configuration for the specific airframe is required for enabling FliteChart functions Reload the baseline configuration and all applicable options as described in Section 3 9 Reloading the baseline configuration disables all previously enabled options NOTE The G1000 can only be configured for FliteCharts or ChartView but not both Performing this procedure will automatically disable the ChartView function Coordinate this configuration with Section 7 16 FliteCharts Functional Check 3 39 Optional ChartView Enable Follow this procedure to activate th
135. 3 GMC 710 AFCS CONTROLS 34 1347D AUDIO PANEL 3 5 1000 NORMAL MODE 3 6 REVERSIONARY MODE 3 7 CONFIGURATION MODE OVERVIEW 3 8 G1000 GFC 700 SOFTWARE INFORMATION 3 9 G1000 SOFTWARE CONFIGURATION PROCEDURE 3 10 GDC 74B AIR DATA COMPUTER SOFTWARE CONFIGURATION 3 1 GDC 7400 AIR DATA COMPUTER SOFTWARE CONFIGURATION 3 12 GTS 820 850 TRAFFIC SYSTEM CONFIGURATION 313 GTS TRAFFIC PROCESSOR 3 14 GTX 33 33D CONFIGURATION 3 15 GTX 3000 CONFIGURATION 316 GDL 59 WI FI DATA LINK OPTION CONFIGURATION 317 GSR 56 SATELLITE RECIEVER WITH GDL 59 WI FI DATA LINK OPTION CONFIGURATION 3 31 318 GSR 56 SATELLITE RECIEVER STAND ALONE OPTION CONFIGURATION 319 GRS 77 AHRS SOFTWARE CONFIGURATION 3 20 GRS 7800 AHRS SOFTWARE CONFIGURATION 321 GWX 68 SOFTWARE CONFIGURATION 322 GWX 70 SOFTWARE CONFIGURATION 323 GMU 44 SOFTWARE CONFIGURATION 324 TAWS A SUPPORT CONFIGURATION 3 25 TAWS A VOICE NO CALLOUT OPTION CONFIGURATION 326 TAWS A VOICE CALLOUT OPTION CONFIGURATION 327 ADF OPTION CONFIGURATION 3 28 DME OPTION CONFIGURATION 329 RAD ALT OPTION CONFIGURATIO 3 30 NON GARMIN TRAFFIC SYSTEM OPTION CONFIGURATION 3 31 LIGHTNING SYSTEM OPTION CONFIGURATION 3 32 ESP SUPPORT WITH AOA OPTION CONFIGURATIO 3 33 ESP SUPPORT NO AOA OPTION CONFIGURATION 3 34 POTS HANDSET CONFIGURATION G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Pagei 190 00915 01 Revision 9
136. 36 L 3 Avionics Systems Emergency Power Supply Installation Manual PS 835 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 1 5 190 00915 01 Revision 9 The following publications are recommended to be on hand during the performance of maintenance activities Table 1 3 Reference Publications Part Number Garmin Document EET Alfano Fight Manu Supplement G1000 Hawker Beechcraft 200 200C 190 00929 01 G1000 Cockpit Reference Guide for the Beechcraft 200 B200 190 00355 04 GDL 69 Series XM Satellite Radio Activation Instructions G1000 G1000H System Maintenance Manual Standard 190 00907 00 Piston Turboprop Helicopter 190 00303 72 GSA8X GSM85 A Installation Manual 190 00303 83 GSM 86 Servo Gear Box Installation Manual 190 00313 63 GMU 44 Installation Location Magnetic Interference Survey Procedure 190 00313 12 Circular Connector and Configuration Module Installation Instructions Generic installation manuals for individual Garmin LRUs are also available through the Dealer Resource Center section of the Garmin web site refer to Section 1 5 for details 1 5 Revision and Distribution This document is required for maintaining the continued airworthiness of the aircraft When this document is revised every page will be revised to indicate current revision level Garmin Dealers may obtain the latest revision of this document on the Garmin Dealer Resource Center we
137. 4 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 5 9 6 Common Problems Symptom Failure Recommended Action Message Noise in Audio Most often the cause of the noise is external to the GMA Try the following to locate the source of the noise before replacing the GMA Try a different pair of headsets Noise cancelling headsets may pick up and or generate more noise than standard headsets from their own circuitry Check for noise with the engine turned off Ifthe noise is present only when the engine is running check the generator and or ignition system as possible sources of noise see applicable airframe specific maintenance manual Check for noise as all electrical equipment is turned on and off strobes other radios etc Ifthe noise is identified from one electrical system or component refer to the applicable airframe specific maintenance manual Ensure the NAV COM squelch is not open Ensure the ADF and DME audio is not active e Ensure the marker beacon audio is not active Ensure the ICS squelch is not open v Master squelch level can be adjusted on the GMA CONFIGURATION page for higher noise environments e Replace unit only after all possible external sources of noise are eliminated Buttons Do Not Work Some buttons are disabled in the CONFIGURATION page by default This is to remove potential sources of audio noise for inputs that ar
138. 4B GDC 7400 with a known good unit Y df problem persists replace the GTP 59 Page 5 22 Revision 9 G1000 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Invalid Data Field ATTITUDE FAIL Associated LRU s GRS 77 or GRS 7800 Solution Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin Cycle GRS 77 or GRS 7800 power to restart initialization Ensure GRS 77 or GRS 7800 connecter is secure and proper wire harness strain relief is provided Ensure the GRS 77 or GRS 7800 is fastened down tightly in it s mounting rack and that the mounting rack is not loose CAUTION do not loosen the mounting rack hardware to the airframe shelf or the aircraft will need to be re leveled and the PITCH ROLL OFFSET procedure performed Ensure GPS has acquired at least four satellites has 3D navigation solution and DOP of less than 5 0 This is particularly important for an ATTITUDE FAIL that appears during ground operation only Perform an Engine Run Up Test to check if engine vibration is causing the GRS 77 or GRS 7800 to go offline Load configuration files to the PFD MFD GIA1 and GIA2 Calibrate the GRS 77 or GRS 7800 Pitch Roll Offset and Magnetometer Calibration Replace GRS 77 or GRS 7800 Y If problem persists replace GRS 77 or GRS 7800 configuration module Y Contact Gar
139. 5 Pull PFD1 PRI and PFDI SEC circuit breakers Re power PFD1 in configuration mode and use the PFD1 FMS knob to select the Audio Alert Configuration page G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 35 190 00915 01 Revision 9 16 Ensure cockpit speaker is selected ON Use the PFD1 FMS knob to highlight each of the following messages then select PLAY Verify each of the following audio messages are played Terrain Ahead 2X Terrain Ahead Pull Up 2X Too Low Terrain Too Low Flaps Too Low Gear Obstacle Ahead 2X Sink Rate Obstacle Ahead Pull Up 2X Pull Up Five Hundred Don t Sink Four Hundred Caution Terrain 2X Three Hundred Terrain 2X Pull Up 2X Two Hundred Terrain 2X One Hundred Caution Obstacle 2X Glide Slope Obstacle 2X Pull Up 2X Glide Path 17 Pull the PFDI PRI and PFDI SEC circuit breakers and re power PFD1 in normal operating mode NOTE The following steps require the movement of the flaps and landing gear This portion of the check can be accomplished in conjunction with the Landing Gear Aural Alert and XM Audio Suppression Test in Section 7 2 2 18 Place the airplane on jacks Ref King Air 200 Series Maintenance Manual Chapter 7 00 00 with the wheels clear of the ground 19 Ensure all equipment and personnel are clear of the flaps and landing gear Place the flaps and landing gear in the full down positio
140. 7 Ifthe minimum and maximum torque values are within the specified range in Table 4 11 the GSM slip clutch is acceptable Reinstall the GSM 85A or GSM 86 servo gearbox per Section 6 12 8 Ifthe minimum and maximum torque values are not within the specified range in Table 4 11 the GSM 86 slip clutch cartridge must be replaced or the GSM 85A must be adjusted 9 For GSM 85A only If adjustment is required remove cotter pin and adjust the nut on the capstan as needed to obtain the torque value listed in Table 4 11 as shown on the torque wrench Position the nut to align with holes in the capstan shaft and install a new cotter pin 10 When finished remove the fixture cable and then remove the servo gearbox from the fixture 11 Install the GSM 85A or GSM 86 servo gearbox per Section 6 12 Table 4 11 GSM 85A GSM 86 Slip Clutch Torque Settings Servo Pitch Trim Pitch Yaw Roll GSM 85A 65 8 in Ibs 32 5 in Ibs 90 10 in Ibs 135 13 in Ibs GSM 86 66 19 in Ibs 32 9 in lbs 90 27 in Ibs 135 40 in Ibs Valid with continuous travel servo gearbox only G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 25 190 00915 01 Revision 9 4 10 01000 Redundant Connection Check NOTE Throughout this check prior to the 0985 07 software version indicators showing GDC 74 are applicable to the GDC 74B and the optional GDC 7400 air data computers For software version 0985 07 and subsequent indic
141. A voice callouts are the default configuration Follow the procedures outlined in this section to load the necessary configuration files to enable TAWS A voice callouts Coordinate the TAWS A Voice No Callout Option configuration with Section 7 15 TAWS Functional Check 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Airframe Options and press ENT key on PFD1 3 Rotate the small FMS knob to select King Air TAWS A Voice Callout Installation Option Press ENT key on PFD1 4 Verify the King Air TAWS A Voice Callout Installation Option is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded COMPLETE in the summary box 6 Select ENT key on PFDI to acknowledge upload complete Upload Complete 7 Deactivate cursor Page 3 40 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 27 ADF Option Configuration This section loads the necessary configuration files for those aircraft equipped with an ADF Coordinate the ADF configuration with Section
142. A white N A box is normal GIA2 GTX 33 or GTX 3000 2 data path is functioning correctly Red GIA2 GTX 33 or GTX 3000 2 data path is not functioning correctly Load GIA2 and GTX 33 or GTX 3000 2 configuration files e Swap GIA2 and GIAI reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA o Replace original GIA2 if box turns green after swapping units e Check the GIA2 GTX 33 or GTX 3000 2 interconnect wiring for faults Replace GTX 33 or GTX 3000 2 if problem remains Amber GIA2 GTX 33 or GTX 3000 2 data path functionality is unknown Reload GIA2 configuration files G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 15 190 00915 01 Revision 9 GIA2 RS 232 continued Channel LRU Indicator Status CHNL 6 CHNL 7 GRS 77 or GRS 7800 2 GMA 1347D 2 Green GIA2 GRS 77 or GRS 7800 2 data path is functioning correctly Red GIA2 GRS 77 or GRS 7800 2 data path is not functioning correctly e Load GIA2 configuration files Swap GIA2 and GIAI reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA1 o Replace original GIA2 if box turns green after swapping units e Swap GRS2 and GRS no reconfiguration required to confirm if the problem is in the original GRS2 o Replace original GRS2 if box turns green after swapping units
143. ATOR 53 a GAGING ASSEMBLY 3 STATIC PORT FUSELAGE SKIN l jy Figure 7 11 Static Port Measurement G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 45 190 00915 01 Revision 9 NOTE The dial indicator shows 0 100 inch when completely flush Therefore subtract the readings from 0 100 inch to determine the actual static port height This should be completed before making any calculations 3 For each static port measure the static port height at the A B C and D locations as shown in Figure 7 12 Record the measurements in the measurement log Figure 7 13 4 Calculate the AVERAGE for each static port using the measurements by adding the four measurements and dividing the total by 4 Record the AVERAGE in the measurement log Figure 7 13 5 Ensure the AVERAGE for each static port is within tolerance 0 045 to 0 085 inch If it is not remove and reinstall the static ports as necessary to meet the tolerance 6 Calculate the ANGLE for each static port by subtracting the smallest of the A B or D measurements from the largest of the A B C or D measurements Record the ANGLE in the measurement log Figure 7 13 7 Ensure the ANGLE for each static port is within tolerance 0 000 to 0 026 inch If it is not remove and reinstall the static ports as necessary to meet the tolerance Figure 7 12 Static Port Measurement locations AVERAGE ANGLE 5 p A B C D
144. Air Revision 9 190 00915 01 P712 P711 Figure 5 9 GEA 71 Backplate Connectors P13471 P13472 Figure 5 10 GMA 13470 Backplate Connectors COOLING PORT P331 TOP ANTENNA CONNECTOR BOTTOM ANTENNA CONNECTOR Figure 5 11 GTX 33 33D Backplate Connectors G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 83 190 00915 01 Revision 9 45 44 43 2 51 50 49 48 47 P3301 3 54 55 58 57 62 61 60 59 2 Figure 5 12 GTX 3000 Connectors P3301 and P3302 Figure 5 13 GDU 1040A 1500 Backshell Connector P10401 or P15001 Figure 5 14 GRS 77 Backshell Connector P771 Figure 5 15 GRS 7800 Backshell Connector P78001 200 B200 Series King Air aintenance Manual 1000 700 System G Page 5 84 190 00915 01 Revision 9 Figure 5 16 GDC 74B Backshell Connector P74B1 Figure 5 17 GDC 7400 Mating Connector P74001 Figure 5 18 GDL 69A Backplate Connector P69A1 Figure 5 19 GCU 477 Backshell Connector P4751 Figure 5 20 GMC 710 Backshell Connector P7101 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 85 Revision 9 13 14 1 4 5 7 8 9 10 1
145. DC 74B or GDC 7400 1 body milli volts GDC 74B or GDC 7400 2 body milli volts e OAT 1 Probe base nut inside fuselage milli volts e OAT 2 Probe base nut inside fuselage milli volts GDL 69A body milli volts e Engine Signal Conditioner 1 near mounting holes of case milli volts e Engine Signal Conditioner 2 near mounting holes of case milli volts PFDI Cooling fan metal base milli volts PFD2 Cooling fan metal base milli volts Cooling fan metal base milli volts Cabin Compartment GTX 33 if installed in Cabin not Tail 1 toj GTX 33 if installed in Cabin not Tail 2 top milli volts GSA 80 Roll Servo body milli volts milli volts Ensure that at each PFD or MFD test point no more than 20 milli volts 20 mQ are present Ensure that at each other test point no more than 2 5 milli volts 2 5 mQ are present In this case voltage is equivalent to resistance Q given that precisely amp reference current is present TIP If 1 amp reference current cannot be maintained note the difference between the attainable current and amp reference current Do not allow the reference current to exceed 1 5 amps Calculate the percentage difference and apply this to the voltage reading to obtain the equivalent resistance Example If the measured current is 1 2 amps 20 high from the target 1 amp current then the allowable voltage measurement would be 20 high 2 5 milli volts would now be 3 0 mil
146. DME NAVI mode Verify that the DME window display is set to the NAVI frequency of 108 00 On PFDI and PFD2 select the DME NAV2 mode by pressing the ENT softkey Verify that the DME window display is set to the NAV2 frequency of 117 00 On PFDI and PFD2 select the DME HOLD mode by using the FMS knob Verify that the last selected NAV frequency of 117 00 remains the same when the NAV2 frequency is changed Deselect DME HOLD On the NAV Test Set set up a DME test and note the nav frequency Tune NAV to the test set frequency and set PFD1 and PFD2 DME MODE to NAVI Set NAV 2 to a frequency other than the test set frequency Verify that the DME distance on PFD1 and PFD2 match the test set Select or verify selected DME and SPKR buttons and GMA2 audio panels to select the DME audio and select speaker to ON Verify that the DME audio can be heard over the cockpit speakers On PFDI and PFD2 set the DME mode to NAV2 and verify that the DME distance is dashed out Tune NAV 2 to the test set frequency Set NAV 1 to a frequency other than the test set frequency Verify that the DME distance on PFD1 and PFD2 match the test set If no other service is to be performed continue to the return to service checks in Section 8 Page 7 40 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 20 ADF Functional Check This check verifies that the ADF G1000 interface operates correctly
147. Distribution Post 61000 STC Page 2 16 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 FAN 4 Comme Mere 2 Figure 2 21 61000 Component Power Sources A G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 2 17 Revision 9 Pitot Static System The following schematic shows the pitot static system as modified by this installation 2 4 glad See 2 aod to md dida H Eo Invasoras i dubie Eomeeeltrlr nonoa ou 10714 avast d i viva ers s a 1 T i vananoo mous pee Wis ism ini any isle A i go Genus porna A 3Hnss3Hd GHVMHOS 190 00915 01 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Figure 2 22 Pitot Static System Post G1000 STC Page 2 18 Revision 9 2 5 Shield Block Grounds The connectors on Garmin G1000 LRUs utilize the Shield Block grounding system to provide necessary ground reference to wire shielding and or transducers The shield block terminati
148. E and check for audio over the copilot s headset 4 Press the SPKR key on copilot s audio panel and verify that the selected audio is heard over the copilot s speaker Failsafe Operation Check 1347D 1 1 Turn the GMA 13470 1 off by pulling the AUDIO NO 1 circuit breaker This directs all COM 1 phone audio MIC audio and MIC key to the pilot s position m 2 Check the failsafe operation by exercising the COM 1 boom mic hand mic microphone key and audio over the headphones All volume control for the COM audio should be through the PFD volume control Verify proper operation of COM 1 using the failsafe operation 3 Close the AUDIO NO circuit breaker to continue testing Failsafe Operation Check 1347D 2 1 Turn the GMA 1347D 2 off by pulling the AUDIO NO 2 circuit breaker This directs all COM 2 phone audio MIC audio and MIC key to the co pilot s position 2 Check the failsafe operation by exercising the 2 boom mic hand mic microphone key and audio over the headphones All volume control for the COM audio should be through the PFD volume control Verify proper operation of COM 2 using the failsafe operation 3 Close the AUDIO NO 2 circuit breaker to continue testing Marker Beacon Test Figure 7 2 Marker Beacon Symbology 1 Using a ramp tester simulate the outer marker middle marker and inner marker signals by following the test equipment manufacturer s instructions Verify tha
149. ED in the STATUS window 6 With the REGISTER field highlighted press the ENT key on 7 Verify that the STATUS field indicates REGISTERED and that the data displayed in the CURRENT REGISTRATION field matches the aircraft information Page 7 64 G1000 700 System Maintenance Manual 200 8200 Series King Air Revision 9 190 00915 01 7 29 GDL 59 Wi Fi Data Link Functional Check This check verifies GDL 59 Wi Fi Data Link interface i configured and is functional This check requires an operating and available wireless network to be within range of the aircraft NOTE This check only verifies the data output from the G1000 equipment Any equipment wiring added that is not part of the installation data will need separate testing and verification not covered as part of this document Start the G1000 System in Normal Mode Using the large FMS knob select the AUX page group on the MFD Using the small FMS knob select the AUX REPORT STATUS page Press the WI FI softkey on the MFD to select the AUX WI FI SETUP page Press the AVAIL softkey on the MFD to display the available WI FI networks Press the FMS knob on the GCU to activate the cursor and rotate the small FMS knob to highlight the desired network in the AVAILABLE NETWORKS field Press the CONNECT softkey on the MFD to connect to the network Skip to step 12 if the selected network is a non secure network If the selected network is a secure network
150. ENGINE N A T680d 006 80544 2 f Figure 3 19 Configuration Software Load Page 6 Observe software loading progress and verify software load completes without errors as indicated by the following e Green PASS or White N A in SOFTWARE and CONFIGURATION columns e Upload Complete COMPLETE in the summary box 7 Press PFDI ENT key to acknowledge the Upload Complete box 8 For system software version 0985 06 and later load the GDC software and configuration per Section 3 10 for the GDC 74B LRU or per Section 3 11 for the GDC 7400 LRU as applicable Page 3 22 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 9 3 Software Load Confirmation Anytime software and configuration loading procedures are accomplished during maintenance conduct a final software review of the system l Start the PFD in Configuration Mode as described in Section 3 7 2 Go to the System Status page using the FMS knob Activate the cursor and toggle to the LRU window 3 Highlight each of the items in the LRU window by activating the cursor pushing the FMS knob as required to verify the software part number and version displayed matches with the information in the General Arrangement drawing 005 0042 1 03 G1000 GFC 700 AFCS King Air 200 B200 IMPORTANT It is essential that the software versions be checked and matched against the listed versions in the Gen
151. FECT Figure 3 25 Navigation Database Synchronization Page 3 68 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 8 If an error occurs during synchronization one of the following messages will be displayed followed by the affected GDU Err No Space SD card does not contain sufficient memory Timeout system timed out prior to the database transfer completing Err displayed for all other errors Note that a power cycle is required to restart synchronization when Err No Space or Err is shown 9 When the synchronization is complete the status is shown as Complete 10 Cycle power to PFD1 PFD2 and by resetting the PFD1 PFDI SEC PFD2 and MFD circuit breakers 11 The standby navigation databases PFD1 PFD2 and are now updated 12 On the AUX SYSTEM STATUS page press the MFD1 DB softkey Scroll through all of the databases contained in the MFD and confirm that the correct databases are loaded 13 Press DB softkey again to toggle to PFD1 DB Scroll through all of the databases contained in the PFD1 and confirm that the correct databases are loaded 14 Press the PFDI DB sofikey again to toggle to PFD2 DB Scroll through all of the databases contained in the PFD2 and confirm that the correct databases are loaded 3 52 Configuration of Navigation Map for Traffic System 1 With the in normal mode use
152. FET ORE RUIGATTOR THTERRAL E EXPIRES REGION erae EFFECTIVE Figure 3 23 Supplemental Database Synchronization 7 If an error occurs during synchronization one of the following messages will be displayed followed by the affected GDU Err No Space SD card does not contain sufficient memory Timeout system timed out prior to the database transfer completing Canceled an active synchronization has been cancelled due to the SYNC DBS softkey being unpressed Err displayed for all other errors Note that a power cycle is required to restart synchronization when Err No Space or Err is shown 8 When the synchronization is complete the status is shown as Complete 9 Cycle power to PFD1 PFD2 and 10 The supplemental databases in PFD1 PFD2 and MFD are now updated 11 On the AUX SYSTEM STATUS page press the MFD1 DB softkey Scroll through all of the databases contained in the MFD and confirm that the correct databases are loaded 12 Press the MFD1 DB softkey again to toggle to PFD1 DB Scroll through all of the databases contained in the PFDI and confirm that the correct databases are loaded 13 Press the PFD1 DB softkey again to toggle to PFD2 DB Scroll through all of the databases contained in the PFD2 and confirm that the correct databases are loaded G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 59 190 00915 01 Revision 9 3 43 Optional SVS Pathways E
153. FMS knob to scroll to CHART 3 Verify ChartView is displayed in blue text adjacent to CHART 4 Verify the ChartView database cycle number is displayed in blue text and the ChartView database is current 5 Deactivate the cursor and use the large GCU FMS knob to select the Navigation Map Page then press the SHW CHRT softkey 6 Verify the airport chart is displayed and the following softkeys are displayed some softkeys may be grayed out CHRT OPT APR CHRT WX INFO 1 NOTAM e DP GO BACK STAR 7 Press CHRT OPT softkey and verify the following softkeys are displayed some softkeys may be grayed out e ALL e HEADER PLAN e PROFILE e MINIMUMS FIT WDTH e FULL SCN BACK If no other service is to be performed continue to the return to service checks in Section 8 Page 7 38 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 18 SafeTaxi Functional Check The maximum map ranges for enhanced detail are configurable by the flight crew When zoomed in close enough to show the airport detail the map reveals runways with numbers taxiways with identifying letters numbers and airport landmarks including ramps buildings control towers and other prominent features Resolution is greater at lower map ranges When the aircraft location is within the screen boundary including within SafeTaxi ranges an airplane symbol is shown on any of the navigation map
154. FMS knob to select the Navigation Map page then press GCU MENU key to display the PAGE MENU Turn the small right knob to select or verify selected Map Setup and press the ENT key and verify TRAFFIC is selected ON Verify the flashing cursor highlights the GROUP field Turn the GCU small FMS knob to select Traffic and press ENT on GCU If not already selected use the GCU FMS knob to make the following selections e TRAFFIC MODE ALL TRAFFIC e TRAFFIC SMBL 300NM e TRAFFIC LBL 300NM Return to the Map Page by pressing the GCU FMS knob or momentarily pressing and holding the CLR key Deactivate cursor 3 53 Clearing Default User Settings l Remove power from PFD1 PFD2 and MFD by pulling the PFD1 PRI PFDI SEC PFD2 and MED circuit breakers 2 While holding the CLR button on PFDI reset PFD1 PRI and PFDI SEC circuit breakers 3 While holding the CLR button on PFD 2 reset the PFD2 circuit breaker 4 While holding the second key from the right side of the beginning on the right side of the count 2 keys to the left reset the circuit breaker 5 When prompted to clear user settings select the YES softkey on each unit G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 69 190 00915 01 Revision 9 This page intentionally left blank Page 3 70 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 4 Instructions for Cont
155. G1000 equipment Section 8 System Return to Service Procedure Specifies return to service procedures to be performed upon completion of maintenance of the G1000 system G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 1 3 190 00915 01 Revision 9 1 3 Definitions Abbreviations ADF Automatic Direction Finder ADTS Air Data Test Set AFCS Automatic Flight Control System AFM Airplane Flight Manual AFMS Airplane Flight Manual Supplement AHRS Attitude Heading Reference System CDU Control Display Unit CFR Code of Federal Regulations DME Distance Measuring Equipment EAU Engine Airframe Unit ESP Electronic Stability and Protection GPS Global Positioning System GPWS Ground Proximity Warning System HSDB High Speed Data Bus Ethernet IAU Integrated Avionics Unit ICS Inter Com System ITT Interstage Turbine Temperature LRU Line Replaceable Unit MED Multi Function Display OAT Outside Air Temperature PFD Primary Flight Display RVSM Reduced Vertical Separation Minimum STBY Standby STBY ATT Standby Attitude Indicator STBY ALT Standby Altimeter STBY A S Standby Airspeed Indicator STC Supplemental Type Certificate TAWS Terrain Awareness amp Warning System WAAS Wide Area Augmentation System VHF Very High Frequency 1 3 1 Units of Measure Unless otherwise stated all units of measure are English units Page 1 4 G1000 700 System Maintenance Manual 2
156. G1000 to be powered on 1 Remove PFD1 as described in Section 6 1 steps 1 and 2 Removal 2 Identify the PFDI cooling fan and verify airflow is present 3 Reinstall PFD1 as described in Section 6 1 steps 2 through 4 Reinstallation 4 Repeat Steps 1 through 3 for the MFD and PFD2 5 The Instrument Panel Fans Operational Check is complete G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 35 190 00915 01 Revision 9 4 16 Standby Battery Periodic Checks 4 16 1 Charge Check Refer to the PS 835 Emergency Power Supply Installation Manual listed in Table 1 2 With the PS 835 battery installed in the aircraft and aircraft power applied verify all four Battery Voltage LEDs are lit to indicate the battery is being charged see Figure 4 6 With the PS 835 battery installed in the aircraft and no aircraft power applied press TEST SWITCH Figure 4 6 Item 4 into TEST position for 5 seconds The PS 835 indicates that it is adequately charged when the VOLTAGE LEVEL 24Vde LED Figure 4 6 Item 2 illuminates momentarily AND the 20Vde LED Figure 4 6 Item 6 remains lit during the test If the VOLTAGE LEVEL 24Vdc LED does not at least momentarily illuminate while the 20Vdc LED is illuminated perform the Section 4 16 3 Cell Isolation Test because the battery is incapable of providing adequate power Table 4 16 Standby Battery Required Equipment DESCRIPTION VENDOR SPECIFICATION Power Sup
157. GMA needs service Return unit for repair GMA2 SERVICE GMA needs service Return unit for repair Cause The system has determined that the specified GMA 1347D needs service Solution e Replace GMA GMAT FAIL GMAT in inoperative GMA2 FAIL GMA2 in inoperative The system has detected a failure in the specified GMA 1347D e Ensure GMAT is receiving power e Ensure both GIAs are receiving power e Ensure all GDUs are receiving power e Ensure the GMA GIA RS 232 data lines are working properly e Ensure the GIA GDU Ethernet data lines are working properly Replace GMA1 MANIFEST GMA1 software mismatch Communication Halted mismatch Communication Halted MANIFEST GMA2 software The system has detected an incorrect software version loaded in the specified GMA 1347D Load the correct unit software See Section 3 9 for the Software Loading procedure 1 CONFIG configuration error Config service req d GMA2 CONFIG GMA2 configuration error Config service reqd The system has detected a GMA 1347D configuration mismatch for the specified unit Load GMA configuration files see Section 3 9 Replace GMA e If problem persists replace master configuration module check config module wiring for faults and replace if necessary NOTE New Terrain Obstacle cards Jeppesen Aviation Database and other optional features TAWS
158. HETIC VISION AND PATHWAYS TROUBLESHOOTING 700 AFCS TROUBLESHOOTING BACKUP COMMUNICATIONS PATH CHECKS GDU 104X TROUBLESHOOTING GDU 104X ALERTS GIA 63 TROUBLESHOOTING GIA ALERT MESSAGES GEA TROUBLESHOOTING GTX TROUBLESHOOTING Page ii G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 14 GDL 69A TROUBLESHOOTING 5 15 GRS 77 OR GRS 7800 AND GMU 44 TROUBLESHOOTING 5 16 GDC 74B GDC 7400 TROUBLESHOOTING 5 7 GWX 68 OR GWX 70 TROUBLESHOOTING 5 18 GMC 710 TROUBLESHOOTING 5 19 GCU 477 TROUBLESHOOTING 5 20 SOFTWARE CONFIGURATION TROUBLESHOOTING 521 BACKSHELL BACKPLATE CONNECTORS 5 22 STANDBY ATTITUDE INDICATOR TROUBLESHOOTING 5 23 STANDBY AIRSPEED INDICATOR TROUBLESHOOTING 5 24 STANDBY ALTIMETER TROUBLESHOOTING 525 SAFE FLIGHT LIFT COMPUTER TROUBLESHOOTING 526 GDL 59 TROUBLESHOOTING 527 GSR 56 TROUBLESHOOTING 5 28 GTS 820 850 TROUBLESHOOTING 5 29 GTS TRAFFIC PROCESSOR TROUBLESHOOTING 6 EQUIPMENT REMOVAL amp INSTALLATION 6 1 GDU 1040A 1500 6 2 GMA 1347D AUDIO PANEL 6 3 63W INTEGRATED AVIONICS UNITS 64 71 ENGINE AIRFRAME UNIT 6 5 GTX33 OR GTX 3000 TRANSPONDER 6 6 GDC 74B GDC 7400 AIR DATA COMPUTER 6 7 59 OAT PROBE 68 GRS 77 OR GRS 7800 AHRS 6 9 GMU 44 MAGNETOMETER 6 10 GDL 69A 6 11 GSA 80 SERVOS 6 12 GSM 85A 86 SER
159. I appears MFD Map e TAWS aural alert amp annunciation given When GPS satellites are re acquired verify that the INTEG OK annunciation is given on the HSI in white for a brief period of time then disappears After seconds of stable GPS position reacquisition verify the TAWS AVAILABLE aural alert is given Verify that the system returns to normal navigation mode GPS CDI restored LOI annunciation removed amp GPS data magenta G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 8 1 Revision 9 8 1 2 Step GIA Failure Test Desired Result GIA 1 Failure Condition 1 Ensure GPS satellites are acquired 2 Open GIA1 primary and secondary CBs 3 Verify desired results 4 Allow system to re acquire satellites and return to normal display modes Close GIA1 primary and secondary CBs For a GIA 1 failure condition the following shall occur NAV 1 and COMM tuning fields on PFD1 and PFD2 are invalid red X L R engine data remains valid XPDR1 is Inoperative GMAT Is Inoperative AHRS is using backup GPS source AHRS2 not receiving backup GPS Information An amber is displayed on PFD1 and PFD2 AHRS and ADC data remain valid on PFD1 and PFD2 GIA 2 Failure Condition 1 Open GIA 2 CB 2 Verify desired results 3 Close GIA 2 CB Allow system to re acquire satellites and return to normal display modes For a GIA 2 failu
160. MED 4th page in AUX group Two softkeys on the bottom of the display allow the user to toggle between GPS 1 and GPS 2 Verify that both receivers show 3D DIFF NAV on the MED Continue to the VHF COM Interference test NOTE It may be necessary to temporarily disable or move away from GPS repeaters while testing as repeaters may adversely affect GPS receiver performance Page 7 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 VHF COM Interference Test This test must be conducted outside Use of a GPS repeater inside a hangar may result in a failed test This procedure assumes that the system is currently set to 25 kHz COM channel spacing Once the signal acquisition test has been completed successfully perform the following steps 1 2 pouce ys 18 19 On the monitor GPS signal strength bars the AUX GPS STATUS page On the PFD ensure that the CDI is set to GPS If it is not press the CDI softkey until GPS ENR is displayed Verify that the GPS INTEG flag is out of view Select 121 150 MHz on the No 1 COM transceiver Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels During the transmit period verify that the GPS INTEG flag does not come into view on the PFD and verify that GPS 1 does not lose a 3 D navigation solution on the MFD Repeat steps 5 and 6 and re transmit while monitoring GPS 2 sign
161. MFD Apply power to the PFD1 PFD2 and A prompt similar to the following will be displayed on the MFD DO YOU WANT TO UPDATE THE STANDBY NAVIGATION DATABASE ON THE BOTTOM CARD THE STANDBY DA WILL BE ACTIVATED UPON THE FIRST ON GROUND POWER CYCLE ON OR AFTER 80 08 SYSTEM TIME ON THE EFFECTIVE DATE Select the YES softkey to confirm the standby navigation database update After the database is updated a prompt similar to the following will be displayed on the MFD 00 WANT TO UPDATE THE ACTIVE NAVIGATION DATABASE SELECTING YES WILL QUERWRITE THE ACTIVE NAVIGATION DATABASE FROM LOWIDE WORLDWIDE 84 890 Select the NO softkey to allow the system to use the database when it becomes effective NOTE If the new database is not yet effective but it is desired to use the new database immediately select the YES softkey To eliminate database mismatch errors when selecting the YES softkey the database must also be loaded on PFD1 and PFD2 individually following the same process The system will synchronize and automatically update as necessary Monitor the synchronization process on the AUX SYSTEM STATUS page in the SYNC STATUS sub section within the DATABASE window This sub section is only present when a sync is occurring or has occurred on the current power cycle HED DATABASE SYNC STATUS STANDBY NAVIGATION INTERHAL RESTON EFFECTIVE EXPIRES STANDE BOTTON CARD REGION cerae EF
162. Manual 200 B200 Series King Air 190 00915 01 Page 3 11 Revision 9 3 8 G1000 GFC 700 Software Information NOTE The following sections provide a detailed description of loading all G1000 software and configuration files which may be excessive for individual LRU removal and replacement If removing and replacing individual LRUs refer to Section 6 of this manual for the necessary steps 3 8 1 01000 Software Image All software and configuration files were certified by Garmin and are considered part of FAA approved Type Design data Approved software and hardware definitions for each STC Configuration are defined on the appropriate General Arrangement drawing listed in Table 1 2 G1000 software and configuration files are controlled via the approved software image part number listed on the General Arrangement drawing listed in Table 1 2 This software image is loaded into the G1000 using a software loader card The installer shall create this software loader card by downloading the approved software image in accordance with section 3 8 2 NOTE Only SanDisk and Toshiba brand SD cards are recommended for use with the G1000 system NOTE Installers may obtain this software image already on a loader card by ordering Garmin Part number 010 00798 XX directly from Garmin Reference the General Arrangement drawing listed in Table 1 2 for part number information IMPORTANT To satisfy the G1000 GFC700 STC requirements for the 200 B200
163. OLING has poor cooling Reducing power usage PFD 1 has exceeded its operating temperature range e cooling fan and wiring for proper operation if applicable Y Replace cooling fan if unable to determine if operating correctly Y f problem persists replace the PFD1 e If problem continues contact Garmin Aviation Product Support for assistance PFD 2 COOLING has poor cooling Reducing power usage PFD 2 has exceeded its operating temperature range e Check cooling fan and wiring for proper operation if applicable Y Replace cooling fan if unable to determine if operating correctly Y f problem persists replace the PFD2 e If problem continues contact Garmin Aviation Product Support for assistance Page 5 52 Revision 9 G1000 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 5 94 Key Alerts Failure Message MFD1 key KEYSTK key is stuck Cause The SYSTEM has determined a key is stuck on MED1 PFD 1 key KEYSTK key is stuck The system has determined a key is stuck on the PFD 1 PFD 2 key KEYSTK key is stuck 5 9 5 F lure Message XTALK ERROR A flight display cross talk error has occurred The system has determined a key is stuck on the PFD 2 Miscellaneous Alerts Cause A communication error has occurred between the MFD and or PFDs Solution e t
164. P button Verify PFD 1 and MFD return to normal display modes 9 Repeat Step 1 using GMA2 Ensure that PFD 2 and MED enter reversion mode and MED displays valid altitude airspeed vertical speed COMMI COMM2 NAVI NAV2 and engine instruments 10 De activate co pilot s side reversion mode by pushing the DISPLAY BACKUP button Verify PFD 2 and return to normal display modes 11 Select TAWS page on the MFD 12 Verify that the title at the top of the page reads TAWS B or MAP TAWS A If TAWS has not been enabled the title will read MAP TERRAIN PROXIMITY or MAP TERRAIN 13 Press the MENU button and select Test TAWS from the pop up menu 14 After TAWS test has completed verify that System Test Okay is heard over the cockpit speaker 15 If no other service is to be performed perform final return to service test as specified in Section 8 Page 7 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 2 GMA 1347D Audio Panel Original 1347 Reinstalled No software configuration loading or testing is required if the removed GMA 1347D is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the final return to service checks in Section 8 Original GMA 1347D Installed in Opposite Locati
165. Qty 2 suspected or actual lightning strike lightning strike can result in a change in the magnetic properties of steel components in the area of the magnetometers which can cause unacceptable magnetic interference levels a Verify the GIA fan DISC out is correctly annunciating when the FAN is not working by GIA Fans performing tests per section 8 1 4 45 Electrical Bonding Test The following bonding tests are provided for G1000 equipped 200 B200 King Air aircraft as a requirement beyond what is given in the aircraft maintenance manual The electrical bonding checks are split into two tests Phase 3 Electrical Bonding Test and Phase 4 Electrical bonding test This places the bonding test requirement for each G1000 LRU in the same phase as the visual inspection of that zone to minimize access requirements 4 5 1 Requirements All G1000 equipment must be installed Gain access for the procedure listed below in Section 4 5 3 as required and in accordance with the King Air 200 Series Maintenance Manual It is recommended that these tests are conducted after visual inspection of the zone to minimize access requirements 4 5 2 Test Equipment A milli ohm meter and Kelvin probes are recommended for this test However a standard voltmeter power supply with adjustable current limit and ammeter may be substituted The following procedure is written using the voltmeter power supply and ammeter All test equipment must have v
166. RS 7800 AHRS are installed Coordinate the GRS 77 configuration with Section 7 7 AHRS GMU 44 Magnetometer 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key PFDI 3 Rotate the small FMS knob to highlight King Air GRS 77 Press ENT key PFDI 4 Verify King Air GRS 77 is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column and Software column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 33 190 00915 01 Revision 9 3 20 GRS 7800 AHRS Software Configuration Follow this procedure to configure the GRS 7800 AHRS if installed Refer to section 3 19 if the GRS 77 AHRS are installed Coordinate the GRS 7800 configuration with Section 7 7 AHRS GMU 44 Magnetometer 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the
167. RS AHRS units can provide heading data to an approved third party TCAS device through an ARINC 429 digital interface Additionally the GRS 7800 AHRS provides heading with or without the aiding of the Garmin GMU 44 magnetometer When operating without the aid of the magnetometer the GRS 7800 is functionally similar to that of a Directional Gyro GRS 1 receives primary electrical power from the Essential Bus and a secondary power supply from the Dual Fed No 1 Bus GRS 2 receives electrical power from Dual Fed No 2 bus GRS 77 GRS 7800 Figure 2 10 AHRS 2 1 12 GMU 44 Magnetometer 2 The GMU 44 provides horizontal and vertical magnetic field information to the GRS AHRS This allows heading to be calculated and provides assistance during AHRS alignment The GMU 44 units are mounted in the tailcone or in the horizontal stabilizer The 011 00870 20 GMU 44 units may only be installed in the horizontal stabilizer The GMU 44 units were modified to account for low clearance installations and have a 90 degree pig tail harness versus the straight harness on the 011 08870 10 GMU 44 units The units receive power directly from the GRS units and communicate with the GRS units via RS 485 digital interface GMU 44 00 amp 10 Unit GMU 44 20 Unit CN Figure 2 11 Magnetometer Page 2 8 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 2 1 13 GDL 69A Datalink The GDL 69A provides
168. S A is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the TAWS A Enable Card from PFD1 Page 3 58 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 42 Supplemental Database Loading 1 Open PFDI PFD2 and MED circuit breakers 2 Remove the SD card containing the supplemental databases from the lower slot of the MFD Supplemental databases include basemap Safetaxi airport terrain obstacle airport directory and terrain databases 3 Download the current supplemental databases to the SD card 4 Reinsert the SD card containing the current supplemental databases into the lower slot of the MFD 5 Close PFD1 PFD2 and MFD circuit breakers 6 The system will synchronize the data to the PFDs as necessary FliteCharts and ChartView are located only on the MFD and do not require synchronization Monitor the synchronization process on the AUX SYSTEM STATUS page in the SYNC STATUS sub section within the DATABASE window This sub section is only present when a sync is occurring or has occurred on the current power cycle SO
169. SORY softkey annunciation acknowledges the presence of the alert and displays the advisory message in the Alert Window ADVISORY Figure 5 3 ADVISORY Softkey Annunciation Annunciation System Failure Annunciations Typically a large red X appears in windows when a failure is detected in the LRU providing the information to the window Page 5 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 Aural amp Audio Alerts The G1000 system is capable of issuing audio and aural voice alerts for various situations The following alerts are utilized by the G1000 Alert Name Traffic voice Purpose Traffic Advisory No Traffic voice Traffic Unavailable linimums Minimums voice Minimums Aural Alert Alt Alert aural Altitude Alerting Function aution Terrain Caution Terrain voice and Terrain Ahead Terrain Ahead voice TAWS Caution alert Reduced required terrain clearance Or Imminent impact with terrain Terrain Terrain Pull Up Pull Up voice and Terrain Ahead Pull Up Terrain Ahead Pull Up voice TAWS Warning alert Reduced required terrain clearance Or Imminent impact with terrain Terrain Terrain voice TAWS Caution alert GPWS mode 2 Excessive Closure Rate Too Low Terrain voice TAWS Caution alert GPWS mode 4A BIC Flight into terrain takeoff or hi
170. Service Bulletin 0533 addresses the most recent update to the 2005 database Service Bulletins may be obtained from www garmin com at the Dealer Resource Center portion of the web site 47 GSA 80 Greasing Procedure The GSA 80 servo greasing procedure is required only when the GSA 80 is removed and reinstalled Refer to Section 6 11 for details Page 4 20 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 48 Flaps in motion Discrete Input Check To perform this check all G1000 and 700 equipment must be installed and operational Start PFD1 in Configuration Mode and go to the GIA Page Group and select the GIA I O Configuration Page using the FMS knob Perform the following che GIA 1 0 CONFIGURATION OUTPUT 7 Dara TYPE E AUDIO INHIBIT 1 ta OFF F E F a iS LDG DN F CPLT PIT ARM E PLT PIT TRM ARM ta OFF OFF F E 2 F FLAP EXTEND E FLAP RETRACT B R Of F PLT PIT E PLT PIT F CPLT PIT 1 E CPLT PIT 1 m m m m m D m Figure 4 1 GIA I O Page Invalid lid Figure 4 2 Discrete Valid Invalid Indications Verify the DATA indicators of the discrete inputs labeled FLAP EXTEND and FLAP RETRACT show an invalid condition 2 Extend the flaps down While the flaps are traveling down check that the DATA indicator of the discrete input labeled
171. TERY switch Verify the following ARM annunciation extinguishes on the STANDBY BATTERY switch STBY attitude OFF flag not present and STBY altimeter vibrator remains active White STANDBY BATTERY legend on the standby battery switch remains illuminated 8 Remove aircraft power by selecting the battery switch to OFF position Verify the following e The STBY Attitude OFF flag is in view is deactivated the sound of the motor may be present as the gyro spools down The STBY altimeter vibrator is deactivated The STBY attitude STBY altimeter STBY airspeed and magnetic compass are no longer illuminated White STANDBY BATTERY legend on the standby battery switch extinguishes G1000 700 System Maintenance Manual 200 B200 Series King Air Page 8 5 190 00915 01 Revision 9 8 1 6 01000 Backup Path Test 1 Remove power from the displays by opening the following circuit breakers e PFDI PRI e PFDI SEC e PFD2 MFD 2 Close the PFD1 PRI PFD1 SEC PFD2 and MED circuit breakers while holding the ENT key on each display far right key on MED until the words INITIALIZING SYSTEM appear 3 In configuration mode go to the GDU Page Group PFDI 4 On PFDI activate the cursor and select PFDI in the SELECT UNIT field and press ENT 5 Observe the GRS 77 or GRS 7800 and GDC 74 DATA indicators in the ARINC 429 window 6 Verify both indicators are GREEN indicating the
172. TX2 GTX 330 OPTIONAL Table 7 8 RVSM Required Avionics G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 43 190 00915 01 Revision 9 7 24 2 RVSM Critical Region Visual Inspection The RVSM critical region is a 24 x 24 inch area around the static ports on both sides of the airplane The corners of the RVSM critical region are to be marked on the aircraft with placards or paint of a contrasting color see Figure 7 9 The RVSM critical region must meet the following visual inspection criteria 1 The fuselage skin must be free from damage All skin repairs within the RVSM critical region must be flush no external doublers If any damage is found the area must be repaired Locations of existing protruding head rivets in frames and skin laps are acceptable 2 The paint including stripes must be uniform and smooth Remove any paint blisters or flaking and sand smooth Any decals or placards must be flush with no peeling edges 3 The static ports must be free from any corrosion elongation of holes deformation or obstructions If any damage is found replace the static port 4 The oxygen servicing door on the right hand side must close approximately flush with the fuselage skin and be free from damage or deformation The ELT access hole cover on the right hand side must be in place o i stanc poms Er a false OMY S I i Figure 7 9 RVSM Critical Region Page 7 44 G1000
173. The second grouping of faults can occur during normal mode These faults generally cause a disconnect of power to the GSA and report that a fault has occurred to the GIA The Notes column indicates any actions that can be taken to troubleshoot the problem in the aircraft by the technician Any faults that not listed here indicate an internal problem requiring replacement of the servo If the items in the Notes column check out ok replace the servo Page 5 40 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 MONITOR PFT STEP PFT Faults NOTES INTERNAL COMM FAIL This can sometimes be a result of a failure on the other internal servo board check faults on the other processor UNSW POWER INV Check unit power MON SOL PWR ON FAIL Check unit power and AP Disconnect power CTL SOL PWR ON FAIL Check unit power and AP Disconnect power SOL PWR FAIL Check unit power and AP Disconnect power CERT DATA UNINSTALLED Upload the certification gain file to the Monitor board STRAP CODE MISMATCH Check the connector strap inputs to the unit Normal Mode Faults MONITOR FAULT NOTES GIA DIS FAULT Check the AP Disconnect power into the unit HOST DATA DIF Check the AHRS wiring to the system HOST DATA INV Check the AHRS wiring to the system SVO PWR INV Check unit power and AP Disconnect po
174. VO GEARBOX 6 13 GCU 477 6 14 GMC 710 6 15 GWX 68 OR GWX 70 6 16 CONFIGURATION MODULES 617 GEA 71 BACKSHELL THERMOCOUPLE REMOVAL amp REPLACEMENT 6 18 GPS WAAS ANTENNAS 6 19 DIVERSITY TRANSPONDER ANTENNA 6 20 IRIDIUM ANTENNA 621 WI FI ANTENNA 6 22 SIGNAL CONDITIONERS 6 23 INSTRUMENT PANEL ANNUNCIATORS PROP SYNCH AND STANDBY BATTERY 6 24 1 3 AVIONICS BF GOODRICH PS 835 C OR D MODEL EMERGENCY BATTERY 6 25 STANDBY AIRSPEED INDICATO 6 26 STANDBY ALTIMETE 627 STANDBY ATTITUDE INDICATOR 6 28 GIA COOLING FANS 6 29 GDU COOLING FANS 6 30 GTS 820 850 TRAFFIC UNIT 6 31 GPA 65 PA LNA UNIT 632 GA 58 TRAFFIC ANTENNAS 6 33 GDL 59 WI FI DATALINK 6 34 56 SATELLITE RECEIVE 6 35 GTS TRAFFIC PROCESSOR 6 36 GRA 5500 RADAR ALTIMETER G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page iii 190 00915 01 Revision 9 7 G1000 EQUIPMENT CONFIGURATION amp TESTI 7 GDU 1040 1500 MFD amp PFD 7 2 1347 AUDIO PANEL 7 3 GIA 63W INTEGRATED AVIONICS UNIT 74 71 ENGINE AIRFRAME UNIT 7 5 GTX 33 OR GTX 3000 TRANSPONDER 7 6 GDC 74B OR GDC 7400 AIR DATA COMPUTER 77 GRS AHRS GMU 44 MAGNETOMETER 7 8 GDL 69A XM DATA LINK 79 GSA 80 SERVOS 7 10 GCU 477 FMS CONTROLLER 741 GMC 710 AFCS CONTROLLER 742 68 OR GWX 70 WEATHER RADAR 7 13 NON GARMIN TRAFFIC SYSTEM FUNCTIONAL CHECK 7 14 STORMSCOPE FUNCTIONAL CHECK 7 15 TAWS FUNCTIONAL CHECK 7 16 FLITECHARTS
175. a o Replace origina GIA2 if box turns green after GRS 7800 2 swapping units e Swap GRS2 and GRS no reconfiguration required to confirm if the problem is in the original GRS2 o Replace original GRS2 if box turns green after swapping units e Check the GIA2 GRS 77 GRS 7800 2 interconnect wiring for faults Amber GIA2 GRS 77 or GRS 7800 2 data path functionality is unknown Reload GIA2 configuration files Page 5 18 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 2 1 3 GIA CAN RS 485 CONFIGURATION Page GIAI RS 485 Channel LRU Indicator Status Green GIAI GEAI data path is functioning correctly GIA1 GEAI data path is not functioning correctly e Verify GEA1 is powered on using GEA Status page e Load GIAI and configuration files e Swap GIAI and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIAI Red o Replace original GIA1 if box turns green after swapping CHNL 1 units e Swap and GEA2 reconfigure both GEA s to their new locations to confirm if the problem is in the original o Replace original if box turns green after swapping units Check the GIA1 GEA1 interconnect wiring for faults data path functionality is unknown Reload GIAI Amber configuration files Green GIA1 GEA2 data path is functioning correctly
176. a s Proposition 65 If you have any questions or would like additional information please refer to our web site at www garmin com prop65 CAUTION The GDU lens is coated with a special anti reflective coating that is very sensitive to skin oils waxes and abrasive cleaners CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI REFLECTIVE COATING It is very important to clean the lens using a clean lint free cloth and an eyeglass lens cleaner that is specified as safe for anti reflective coatings IMPORTANT All G1000 screen shots used in this document are current at the time of publication Screen shots are intended to provide visual reference only All information depicted in screen shots including software file names versions and part numbers is subject to change and may not be up to date Page B G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 TABLE OF CONTENTS PARAGRAPH 1 INTRODUCTION l l CONTENT SCOPE PURPOSE 1 2 ORGANIZATION 1 3 DEFINITIONS ABBREVIATIONS 1 4 PUBLICATIONS 1 5 REVISION AND DISTRIBUTION 2 SYSTEM DESCRIPTION 2 1 EQUIPMENT DESCRIPTIONS 22 91000 OPTIONAL INTERFACES 2 3 ELECTRICAL POWER DISTRIBUTION 24 SYSTEM 2 5 SHIELD BLOCK GROUNDS 2 6 1000 700 BLOCK DIAGRAM 3 1000 CONTROL amp OPERATION 3 1 1040A AND GDU 1500 DISPLAYS 32 GCU 477 MFD CONTROLLER 3
177. ading GPS Position 9 Arc Second Terrain Data In the event that one the above items fails or is unavailable the SVS Pathways feature is automatically removed from the PFD The following table describes possible symptoms associated with the SVS Pathways feature and provides corresponding actions for troubleshooting Table 5 1 SVS Troubleshooting SYN VIS softkey does not appear on PFD softkey tier Symptom Recommended Action Follow the steps in Section 3 43 to reactivate the SVS Pathways feature 3D terrain presentation does not appear on PFD Verify that P N 010 00330 43 terrain datacar of the PFD and MFD re installed in the lower slot Verify that the alert messages shown in Table 5 2 are not displayed on the PED Alerts Window If so follow the solutions described in Table 5 2 Verify that the G1000 AHRS and heading data are valid on the PFD Verify that a valid GPS 3D position solution is being received Troubleshoot these systems in accordance with sections 5 10 4 and 5 15 Ifa terrain database update has just been performed allow the system time to initialize and verify the data When the databases have been verified the current database cycle and version are reported on AUX System Status page Failure Message SVS SVS DISABLED Out of available terrain region The following table provides SVS Pathways specific alert messages which may appear in the Alerts Window on t
178. affic Processor Removal 1 Gain access to the left forward avionics compartment in the nose of the aircraft 2 Disconnect the eight coaxial cable connectors 3 Disconnect the three electrical connectors 4 Unlock the unit from the rack by loosening the ratcheting latch mechanism 5 Remove the unit from the rack Reinstallation ile Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Insert the unit into the installation rack 3 Lock the unit into the rack by using the ratcheting latch mechanism 4 Connect the eight coaxial cable connectors Note the color coded bands which match the mating connectors 5 Connect the three electrical connectors Page 6 22 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 6 36 GRA 5500 Radar Altimeter Removal 1 Gain access to the avionics shelf in the tail area 2 Disconnect the electrical connector 3 Disconnect the two coaxial cable connectors making note of which cable is Transmit Tx and which cable is Receive Rx 4 Pull back on the lockdown mechanism and simultaneously turn counterclockwise until free 5 Disengage the lockdown mechanism collar from the GRA 5500 hook and slide the GRA 5500 forward to remove the unit from the rack Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Place the unit on the mounting
179. ail Filtered vertical acceleration monitor failed h Roll Accel Fail Roll acceleration monitor has failed i Normal Accel Fail Normal acceleration has failed Troubleshoot the GRS 77 or GRS 7800 for the cause of the failure Stuck switch invalidated parameter lt AXIS gt MET switch in the specified axis is stuck Check the MET trim switches for proper operation PRMTR lt PARAMETER gt MODE lt MODE gt Parameter lost The mode specified by lt MODE gt has been disengaged because the parameter specified by PARAMETERC has become invalid The following is a list of some of the possible values for lt gt a AD TDM Comm Valid The specified mode has been disengaged because communication with the servos via the Time Division Multiplexer protocol has been lost b AP Pitch MET not stuck The specified mode has been disengaged due to a stuck pitch MET switch Check the MET trim switches for proper identification Page 5 36 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 63 GIA Pre Flight Test Steps PFT step 0 System initialization verify GFC powered This step is checking to make sure the GFC is powered up It checks to make sure the GIA AP disconnect input is connected to 28 volts and makes sure the Servos are up and communicating If this step fails make sure the GIA is connected to AP disconnect by using the GFC configuration page Also make su
180. al antennas probes fairings or radomes along the sides of the airplane that may impact the air data system or aircraft performance may also invalidate the RVSM certification for this aircraft RVSM Required Avionics Check With the PFD in configuration mode select the System Status page using the small FMS knob Press the small FMS knob to activate the cursor Highlight each of the following items in the LRU window and verify that the required software part number and version matches the information in the General Arrangement drawing listed in Table 1 2 Verify hardware part number by visual inspection of the units Record the results in Table 7 8 HARDWARE SOFTWARE STATUE rem DESCRIPTION PART NUMBER DESCRIPTION Part NuMBER ven REPORT MAIN SUB SYSTEM GAT AUDIO GIA AUDIO 1 ctscowsauer GPSWAAS ENGINE GPs CERTIFICATION GAINS GFC CERT GIA 1 MAIN SUB SYSTEM Gu AUDIO GIA AUDIO 2 ciasswiause GPSWAAS ENGINE GPs2 CERTIFICATION GAINS GFC CERT GIA 2 SYSTEM PFDT 3 Gbuo A pron FPGA PEDI FPGA SYSTEM PFD2 4 GDU1040APFDg2 FPGA PFD2 FPGA SYSTEM MEDI 5 epussoourD FPGA MED FPGA _ aoc748 ave n SYSTEM GDC 7400 OPTIONAL FPGA Get FPGA UG TEC E SYSTEM nce 7 aDC 7400 OPTIONAL FPGA GDC2 FPGA TX 33000 TRANSPONDER 1 GTX 33 3000 SYSTEM GTX 330 OPTIONAL GTX333000 9 THANSPONDER 2 GTX 33 3000 SYSTEM G
181. al levels on the MFD Repeat steps 4 through 7 for each of the following frequencies 121 175 MHz 121 200 MHz 131 250 MHz 131 275 MHz 131 300 MHz Repeat steps 4 through 8 for the No 2 COM transceiver GIA2 On the MFD select the AUX SYSTEM SETUP page Under the COM CONFIG field change the COM channel spacing from 25 kHz to 8 33 kHz Go back to the AUX GPS STATUS page Select 121 185 MHz on the No 1 COM transceiver Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels During the transmit period verify that the GPS INTEG flag does not come into view on the PED and verify that GPS 1 does not lose a 3 D navigation solution on the MFD Repeat steps 14 and 15 and re transmit while monitoring GPS 2 signal levels on the MFD Repeat steps 14 through 16 for each of the following frequencies 121 190 MHz e 130 285 MHz 131 290 Mhz Repeat steps 14 through 17 for the No 2 COM transceiver GIA2 On the MFD select the AUX SYSTEM SETUP page and change the COM channel spacing back to 25 kHz Continue to the VOR LOC GS Test G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 7 190 00915 01 Revision 9 VOR LOC GS Test Check the VOR ILS and Glideslope functions with ramp test equipment Operate the equipment according to the test equipment manufacturer s instructions Adjust the RF signal to a level adequate to perform the test Select the
182. alid calibration records 4 5 3 Phase Electrical Bonding Procedure 1 Connect the positive lead of the power supply to the engine compartment grounding bracket battery negative connection to the airframe Connect touch the positive lead of the voltmeter to the same point NOTE Ensure that the voltmeter and power supply probes do not touch so as not to induce contact resistance 2 Touch negative lead of power supply to each of the test points listed while performing Step 3 At each point configure the power supply to produce 1 amp before measuring voltage Use an ammeter to ensure current is within amp 100 milli amp at each point 3 Set the voltmeter to measure milli volts and null the reading Measure the voltage from the engine grounding bracket step 1 to each of the following points and record the voltage Perform Step 2 at each point to ensure that 1 amp 100 milli amp is present before measuring G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 17 190 00915 01 Revision 9 Pilot Compartment metal case of PFD 1 milli volts Top metal case of PFD 2 milli volts metal case of MFD milli volts metal case of GMA 1347D 1 milli volts Top metal case of GMA 1347D 2 milli volts metal case of GCU 477 milli volts metal case of GMC 710 milli volts e 71 1 body milli volts 71 2 body milli volts G
183. ance Manual 200 B200 Series King Air 190 00915 01 5 11 6 GIA Configuration Alerts Failure Message MANIFEST GIA1 software mismatch Communication Halted Cause The system has detected an incorrect software version loaded GIA1 MANIFEST GIA software mismatch Communication Halted The system has detected an incorrect software version loaded GIA2 Solution e Load the correct software See Section 3 9 for the Software Loading procedure GIA1 CONFIG GIA1 audio GIA2 CONFIG GIA2 audio config error Config service req d config error Config service req d The GIA s audio configuration files are incorrect or missing e Reload audio configuration files GIA1 CONFIG GIA1 configuration error Config service reqd GIA2 CONFIG GIA2 configuration error Config service req d The system has detected a GIA configuration mismatch If GIAs are not properly configured after being swapped replaced this message appears Load the configuration files for that GIA See Section 3 9 for GIA 63 Configuration Loading procedure e If problem persists replace master configuration module check config module harness for faults and replace if necessary NOTE e Terrain Obstacle cards Jeppesen Aviation Database and other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID numb
184. approach flaps Pot 1 TG value d Return the force on the vane to 0 TG 12 Flaps Extended Pot 2 measurement a b Run the flaps to the FULL DOWN position Install voltmeter leads between TP5 Hi and TP2 Lo TP6 Hi and TP2 Lo of the SK100360 Breakout Box Ensure that 28 VDC is ONLY present between TP6 and TP2 If the flap information is incorrect troubleshoot in accordance with King Air 200 Series Maintenance Manual procedure 27 31 00 Using the force applicator slowly apply a negative TG force forward UP on the vane until the stall warning horn sounds Record the flaps extended Pot 2 TG value Return the force on the vane to 0 TG and remove the force applicator from the aircraft Page 7 50 Revision 9 G1000 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 13 Place the BATT master switch to the OFF position 14 Remove external power to the aircraft 15 Remove the breakout box from the aircraft 16 Reinstall the potentiometer access cover plate on the lift computer 7 25 2 Calibration of the C 05606 1 Lift Computer NOTE For calibration of the stall warning points reference King Air 200 Series Maintenance Manual listed in Table 1 2 section 27 31 00 The procedures listed here are provided to augment the King Air 200 Series Maintenance Manual and allow the installer to adjust the stall warning points Pots 0 1 and 2 and LAA output Pots 3 4 and 5 simultaneously to save s
185. are acquired 2 Place a shroud over the GPS antenna for GIA 1 to prevent signal reception Verify loss of signal on MFD AUX page 4 3 Check for desired results 4 Remove shroud from the GIA 1 GPS antenna and allow system to re acquire satellites 5 Place a shroud over the GPS antenna for GIA 2 to prevent signal reception Verify loss of signal on MFD AUX page 4 6 Check for desired results 7 Remove shroud from the GIA 2 GPS antenna For each of the single GPS failure conditions the following shall remain valid on the PFD throughout the procedure Attitude and Heading from AHRS Airspeed Altitude Vertical Speed and from Air Data Computer GPS Course Deviation Indicator For a GIA1 GPS Failure an amber BOTH ON GPS2 is displayed on PFD 1 and PFD 2 For GIA2 GPS Failure an amber BOTH ON GPS1 is displayed on PFD 1 and PFD 2 Dual GPS Failure Condition 1 Ensure GPS satellites are acquired 2 Cover both GPS antennas Verify loss of signal on MFD AUX page 4 3 Check for desired results Remove shrouds from GPS antennas 5 Allow both receivers to re acquire satellite signals before continuing For a dual GPS failure condition the following shall occur e GPS CDI flags LOI on both PFDs Attitude and Heading remain valid from both AHRS on both PFDs Airspeed Altitude Vertical Speed and OAT remain valid from both Air Data Computers on both PFDs e LO
186. ates which side is coupled No flight director modes should be active at this time G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 57 190 00915 01 Revision 9 E 6 On the GCU rotate the inner FMS knob to activate the AUX SYSTEM SETUP page on the MFD 7 MFD AUX SYSTEM SETUP page press the SETUP 2 softkey 8 Verify that on the MFD SETUP 2 page there is a window for Stability amp Protection and the status is ENABLED 9 Verify on PFD 1 and PFD 2 that there are no ESP FAIL ESP OFF or ESP DEGRADE alert messages 10 Cover both GPSI and GPS2 antennas 11 Verify on PFD 1 and PFD 2 the ESP Roll Indices are displayed at 45 on the roll indicator on the Attitude Display 12 For installations with AOA mode verify on PFD 1 and PFD 2 that there is an ESP DEGRADE alert message ESP DEGRADE inoperctive 13 On the GCU press the inner FMS knob to activate the cursor then rotate the outer FMS knob to select the Stability amp Protection window on the MFD 14 Rotate the inner FMS knob to change the status to DISABLED 15 Verify that on the MFD SETUP 2 page Stability amp Protection window that the status is DISABLED P AQA mode is 16 Verify on PFD and PFD 2 the ESP Roll Indices are not displayed at 45 on the roll indicator on the Attitude Display Page 7 58 G1000 GFC 700 System Maintenance Manual 200 B200 Series King A
187. ators show GDC 74 for the GDC 74B and GDC 7400 for the GDC 7400 air data computer Perform the following steps to verify the following The primary PRI and secondary SEC power sources for GIA 1 GRS 1 PFD 1 and GDC 1 B The AHRS and ADC data path to PFD C PFD and MFD Ethernet connection includes ARINC connection between ADC and MFD and DISPLAY BACKUP button function D Engine data availability to the displays and GPS data availability to the AHRS with either GIA inoperative A PRI and SEC power sources for PFD 1 GIA 1 GRS 1 and GDC 1 check 1 Connect a ground power unit to the external power receptacle and turn on the ground power unit 2 Set the BAT and AVIONICS MASTER PWR switches to ON 3 With the G1000 system in normal mode pull the following circuit breakers on the right hand circuit breaker panel e PFD 1 PRI e AHRS 1 PRI ADC 1 e GIA 1 PRI 4 Wait at least 5 seconds then verify the data on PFD1 remains valid and the following alert messages are not present e GIA I FAIL or any related message such as COMI NAVI XPDRI GPS1 e AHRS FAIL e ADC 1 FAIL FAILED DATA PATH 5 Close the circuit breakers listed in step 3 6 Repeat step 4 7 Pull the following circuit breakers on the right hand circuit breaker panel e PFD 1 SEC e AHRS 1 SEC e ADC 1 SEC e GIA 1 SEC 8 Wait at least 5 seconds then repeat step 4 9 Close the circuit breakers listed in step 7
188. body milli volts GSA 80 Yaw Servo body milli volts 5500 Radar Altimeter mili volts GTX 33 if installed in Tail not Cabin or GTX 3000 1 top milli volts GTX 33 if installed in Tail not Cabin or GTX 3000 2 top milli volts TIP If 1 amp reference current cannot be maintained note the difference between the attainable current and amp reference current Do not allow the reference current to exceed 1 5 amps Calculate the percentage difference and apply this to the voltage reading to obtain the equivalent resistance Example If the measured current is 1 2 amps 20 high from the target 1 amp current then the allowable voltage measurement would be 20 high 2 5 milli volts would now be 3 0 milli volts G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 19 190 00915 01 Revision 9 46 GRS 77 or GRS 7800 Earth Magnetic Field Updates The GRS 77 or GRS 7800 utilizes an Earth magnetic field model which is updated once every five years The update is expected to be available from Garmin in each of the following years 2010 2015 and every five years thereafter as long as the GRS 77 or GRS 7800 remains a Garmin supported product The G1000 system alerts the operator that the magnetic field database is out of date by issuing the message AHRS SERVICE AHRS Magnetic field model needs update Garmin will distribute update instructions when updates are available As of this writing Garmin
189. bsite Owner operators may obtain the latest revision of this document from the https fly garmin com Support page or by contacting a Garmin dealer contacting Garmin Product Support at 913 397 8200 toll free 866 739 5687 or using around the world contact information on https fly garmin com A Garmin Service Bulletin describing the revision to this document will be sent to Garmin dealers if the revision is determined to be significant Page 1 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 2 SYSTEM DESCRIPTION 2 1 Equipment Descriptions 2 1 1 GFC 700 Operation The GFC 700 is a fail passive digital flight control system composed of multiple G1000 LRUs and servos The following functions are provided by the GFC 700 in this installation e Flight Director e Autopilot e Pitch Trim lt Yaw Damper e Electronic Stability and Protection optional Flight Direc The Flight Directors operate within the GIA 63Ws and use data from the G1000 system including air attitude and flight data to calculate commands for display to the pilot and for the Autopilot Flight director command bars and mode annunciations are sent to the PFDs through a high speed Ethernet connection for display to the pilot and copilot The flight directors operate independently of the autopilot and allow the pilot to hand fly the command bars if desired The GMC 710 allows the pilot to switch the active director betw
190. cess to the avionics shelf in the tail area 2 Pull back on the lockdown mechanism and simultaneously turn counterclockwise until free 3 Disengage the lockdown mechanism collar from the GTX 3000 hook and gently slide the GTX 3000 from the mounting rack GTX 3000 Reinstallation Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 1 2 Place the GTX 3000 on the mounting rack 3 Slide the GTX 3000 back until the foot is fully engaged with the mounting rack 4 Lift the lockdown mechanism collar in plance on the GTX 3000 hook and hand turn lockdown mechanism knobs clockwise until the GTX 3000 is secure 5 Configure and test the GTX 33 according to Section 7 5 6 6 GDC 74B GDC 7400 Air Data Computer Removal 1 Gain access by removing the appropriate GDU 1040A display unit see Section 6 1 2 Disconnect the pitot static plumbing from the rear of the unit Disconnect the single connector 3 Loosen each thumbscrew on the hold down clamp and remove the clamp 4 Carefully remove the unit from its mount Reinstallation l Inspect the connector and pins for damage Inspect the pitot static plumbing for damage Repair any damage 2 Place the unit in the mounting tray Position the locking clamp and fasten using the thumbscrews 3 Connect the backshell assembly and pitot static plumbing to the unit 4 Configure and test the GDC 74B GDC 7400 according to Section 7 6 5 Reinstall
191. ch servo per Section 3 37 5 the in Normal Mode press the red DISPLAY BACKUP button on the pilot s GMA audio panel to place the MFD in reversion mode 6 With in Configuration Mode go to the Page Group and select STATUS page using the FMS knobs AOL EDD STATS evo EST a DRY GU FST CAT Figure 4 3 GFC Status Page IMPORTANT It is highly recommended that the following test be performed at temperatures between 50 F and 120 F 7 Use the FMS knob to select the desired servo Pitch Roll Yaw or Pitch Trim 8 Verify that the PFT status field shows PASSED 9 Verify that the aircraft control surface to be checked is free to travel throughout its range of motion 10 Press the TEST SVO softkey the PFD Follow prompts to begin the test IMPORTANT If the test must be stopped firmly grasp the aircraft control being moved and press the red AP DISC switch on the aircraft control wheel If an abnormal disconnect of servo occurs reset the AFCS SERVO circuit breaker and repeat the test 11 When test is completed verify the CLUTCH TEST PASS message is displayed on 12 Repeat steps 4 through 8 for each servo axis Pitch Roll Yaw and Pitch Trim Page 4 22 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 13 Ifthe CLUTCH TEST FAIL message is displayed on for any axis repeat the test
192. configuration file 7 e Swap PFD2 and PFD to confirm if the problem is in the original PFD2 o Replace original PFD2 if box turns green after swapping displays e Swap GRSI and GRS2 no reconfiguration required to confirm if the problem is in the original GRS1 o Replace original GRS1 if box turns green after swapping units e Check the PFD2 GRS 77 or GRS 7800 2 interconnect wiring for faults Amber PFD2 GRS 77 or GRS 7800 2 data path functionality is unknown Reload PFD2 configuration file Green PFD2 GDC 2 data path is functioning correctly PFD2 GDC 2 data path is not functioning correctly Verify GDC 2 status is OK using the System Status page on the MFD If it is not correct condition before proceeding reference GDC troubleshooting sections e Load PFD2 and GDC 2 configuration files i or Red e Swap PFD2 and PFDI to confirm if the problem is in the aoc original PFD2 An o Replace original PFD2 if box turns green after swapping displays Check the PFD2 GDC 2 interconnect wiring for faults Replace GDC 2 if problem remains Amber PFD2 GDC 2 data path functionality is unknown Reload PFD2 configuration file G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 9 190 00915 01 Revision 9 MFDI RS 232 Channel CHNL 1 LRU GCU 477 Indicator Green Status MFD1 GCU 477 data path is functioning correctly Red MFDI GCU 477 data pa
193. continue to the return to service checks in Section 8 7 22 Non Garmin Radar Altimeter Check Optional This check verifies that the G1000 radar altimeter interface is operates correctly NOTE This check only verifies the data output from the G1000 equipment equipment wiring added that is not part of the installation data will need separate testing and verification not covered as part of this document Navigate to AUX SYSTEM STATUS page on Press the RA TEST softkey and verify that RA TEST annunciation is displayed on both PFDs Verify 50 feet is displayed in the RA display window on both PFDs Press the RA TEST softkey again Verify the RA readout window displays 2500 feet and decreases to 0 feet on PFDI and PFD 2 5 Pull the RADIO ALTM circuit breaker Verify on PFD 1 and PFD 2 that an RA FAIL message is displayed 6 Reset the RADIO ALTM circuit breaker If no other service is to be performed continue to the return to service checks in Section 8 Se ae G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 41 190 00915 01 Revision 9 7 22 Weight on Wheels and Low Speed Awareness Band Check This procedure will verify that the GDU air ground status uses valid Weight on Wheels WOW inputs 1 2 8 Ensure aircraft is positioned with weight on wheels Apply external power to the aircraft Set BATT and AVIONICS MASTER switches to ON and wait for al
194. control cables following the instructions in Chapter 27 Flight Controls of the King Air 200 Series Maintenance Manual h Reinstall the access panels if no other maintenance is to be performed To gain access for the following inspection remove the left cabin sidewall panel at FS 158 a Inspect the GPA 65 PA LNA unit if installed brackets and connectors for fers canes corrosion other defects Check the integrity of the shield block ground lor any attachments to the harness connector assembly as well as the integrity of the n i individual shields and their attachment G1000 700 System Maintenance Manual 200 B200 Series King Air Page 4 15 190 00915 01 Revision 9 Table 4 8 Rear Fuselage and Empennage Visual Inspection Procedure Wi fi Antenna Description Procedure Inspect the external wi fi antenna if installed for leading edge erosion and condition of base seals To gain access for the following Inspections refer to the servo installation drawings and the King Air 200 Series Maintenance Manual listed in Table 1 2 Initials Tail Wiring Harness _ Inspect all exposed wire harness for chafing damage proper routing of wire bundles and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Tail Wire Harness Routing drawing listed in Table 1 2 Pay particular attention to possible areas of chaffing
195. correct Temperature Fault Fan is not operating Poor ventilation at the Verify the fan is running and the unit mounting location is getting adequate ventilation TCAS Equipage Fault Broken wire improper configuration Verify configuration settings on the transponder and the GTS Ensure proper wiring between the transponder and the GTS Radio Altitude Fault Radar Altimeter is not powered on or Verify that the radar altimeter has improper wiring power and is properly wired Improper configuration settings Verify the configuration is correct Red on a data port on the Improper wiring wrong port or speed Ensure the port is properly wired to configuration page selected the GTS 820 850 and the correct settings are selected on the configuration page 5 29 GTS Traffic Processor Troubleshooting Symptom Recommended Action Unit does not power up Ensure power is properly wired to the GTS Traffic Processor and the Data failed message TRFC circuit breaker is closed Verify that the GTS Traffic Processor is configured correctly for the desired display Traffic Display erroneously Check the mutual suppression line to ensure it is connected to the correct indicates TA at own ship pins at the GTS Processor as well as the installed transponder Ensure position there are no fractures in the wire and that the suppression line is functioning properly Calibration Data Fault e Return unit to Garmin for service Configuration
196. ction press the ENT key To cancel a selection press the small FMS knob in again deactivating the cursor The CLR key may also be used to cancel a selection or deactivate the cursor Page 3 2 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 2 GCU 477 MFD Controller The MED controls are located on the GCU 477 as shown in Figure 3 4 Range pan Flight FMS ctrl knob planning keys knob MENU Alpha entry keys Numeric Entry keys Figure 3 4 MFD Controls GCU 477 shown 3 3 GMC 710 AFCS Controls Comm Nav Tranponder keys The dedicated AFCS controls located on the GMC 710 are discussed in detail in the G1000 CRG The following figure is provided for reference Flight director transfer key Heading mode key mode k Navigation mode key TN Approach Flight director mode key Vertical speed made key mode key MUST mode selector mace key 27 Yaw damper key Bak BK sere qu Fightlevel change mode key Speed key Nose Up Nose Dn Figure 3 5 AFCS Controls GMC 710 shown Course 2 selector G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 3 3 Revision 9 3 4 GMA 1347D Audio Panel Figure 3 6 provides the audio panel controls Transmitters Transceiver Audio
197. d If a new repaired or exchange GWX 68 or GWX 70 is installed the correct software and configuration files must be loaded to the unit See Section 3 9 and then continue to the GWX 68 or GWX 70 Test Section 7 12 1 7 12 1 GWX 68 or GWX 70 Test Operation of the GWX 68 or GWX 70 Weather Radar is accomplished using the MFD GCU 477 Refer to G1000 200 B200 King Air Cockpit Reference Guide listed in Table 1 2 for basic operation NOTE Before energizing the equipment be sure microwave radiation safety precautions including both fuel and personnel safety considerations have been observed These include clearing all personnel to an area beyond the maximum permissible exposure level MPEL boundary The MPEL for the GWX 68 is 11 feet and the GWX 70 is 10 feet 1 On the GCU turn the large FMS knob to select the Map Page Group then turn the small FMS knob to select the Weather Radar page 2 Select the MODE softkey 3 Select the STANDBY softkey to initiate the one minute warm up period Verify the radar enters the standby mode after the warm up is complete 4 Select the MODE softkey 5 Select the WEATHER softkey After reading the CAUTION statement turn the large FMS knob to select YES Press the GCU ENT key 6 Select the STAB ON softkey to activate antenna stabilization or select the STAB OFF softkey to deactivate Verify the current stabilization condition is shown in the upper right of the weather radar display 7 Select
198. d GIA Audio and Config files from a loader card see Section 4 3 and on for instructions Be sure to reload the config files for any optional equipment installed on the aircraft that require the GIA config to be updated e Cycle power on the system and allow it to restart in normal mode Place the aircraft outside and allow 15 30 minutes for the GPS to acquire a position and download a new almanac Y If clearing nonvolatile memory is unsuccessful and the GPS still can not acquire a position replace the GIA Y _ If problem does not follow unit check GPS antenna and cabling Page 5 58 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 5 11 GIA Alert Messages 5 11 1 COM Alerts Failure Message Cause Solutions COMI SERVICE COM needs service Return unit for repair The system has determined COMI needs service Replace GIA1 according to instructions in Section 6 COM SERVICE COM needs service Return unit for repair The system has determined CON needs service Replace GIA2 according to instructions in Section 6 COMI PTT COM push to talk key is stuck The COMI external push to talk PTT switch is stuck in the enabled or pressed state Press the push to talk switch s again to cycle its operation Check push to talk switch s and wiring Check GIA1 GMA 1347D 1 interconnect Switch GIA1 and GIA2 to identity whether the unit o
199. d during tests verify the following e Coax cable connectors are properly secured at the bulkhead adapter fittings GA58 antennas GTS unit and GPA 65 unit Connections are made to the proper channels and color coded heat shrink is the same color on both ends of coax cables e Connectors are correctly installed on coax cables If no other service is to be performed continue to the return to service checks in Section 8 7 27 2 Ramp Test The following test provides a scenario that will converge and intercept the GTS 820 850 or GTS Processor to assure proper operational and surveillance functions The GTS 820 850 or GTS Processor must be in Ground Test mode 1 On the MAP TRAFFIC MAP page of the MED press the OPERATE softkey for GTS 8XX or TAIRA softkey for GTS 8000 2 For GTS 8000 only change BARO setting to 29 92 in Hg on PFDI and PFD2 3 Position ramp tester at 90 degrees 4 Select the following on the ramp tester Intruder type ATCRBS Intruder Start Distance 15 nm Intruder Start Altitude GTS 8 50 300 ft Intruder Start Altitude GTS 8000 300 ft above PFD1 PFD2 displayed altitude Vertical Speed 0 fpm Page 7 62 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 e Velocity 600 kts 5 Initiate the intruder scenario and observe the following Traffic should be acquired at approximately 10 NM at 90 degree bearing and co altitude Observe intruder close
200. d on the PFDs For King Air installations the GRA 5500 is configured to output the value height Above Ground Level to the pilot through the GDU The GRA interfaces to the existing radar altimeter antennas and GIA 2 via the ARINC 429 digital bus The GRA 5500 is located below the lower avionics equipment shelf in the tail section The GRA 5500 is powered from the No 2 Avionics Bus Figure 2 19 GRA 5500 Radar Altimeter 2 1 21 Garmin G36 and 37 GPS WAAS Antennas This installation uses one G36 GPS WAAS antenna and a G37 GPS WAAS XM antenna The antennas are located in the upper forward cabin at F S 152 Page 2 12 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 2 1 22 Signal Conditioner 2 Each GEA 71 receives signals from its on side engine turbine speed sensor propeller speed sensor and fuel flow sensors via a Meggitt Vibro Meter Signal Conditioner This unit converts the signals from the engine sensors to a signal usable by the GEA 71 These units are installed behind the instrument panel Electrical power to the No 1 Engine Signal Conditioner is provided from Dual Fed Bus No 1 and to the No 2 Engine Signal Conditioner from Dual Fed Bus No 2 Both signal conditioners will power up immediately with external or aircraft power or battery operation NOTE On serial numbers BB 1484 1486 and subsequent the electrical system includes the L ENG INSTR and R ENG INSTR buses which after
201. de access for visual inspections below Inspect all fwd bulkhead connectors for security of attachment b _ Inspect all instrument panel wiring and coax for chafing damage proper routing of wire bundles and security of attachment in accordance with 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Cabin Wire Harness Routing drawing listed in Table 1 2 Pay particular attention to possible areas of chaffing Inspect all other exposed 01000 GFC wiring and coax for chafing damage proper routing of wire bundles and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Cabin Wire Harness Routing drawing listed in Table 1 2 Pay particular attention to possible areas of chaffing 91000 Wiring harness Visually inspect each GDC 74B or GDC7400 unit mount and connector for corrosion or other defects Check the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment b Visually inspect the pitot static plumbing and ensure it is secure and in good condition and routed to provide positive moisture drainage GDC 74B or GDC 7400 Air Data Computer Qty 2 GEA 71 Engine Inspect the GEA 71 unit rack and connectors for corrosion or other defects Check Airframe Unit Qty 2 the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as
202. ded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor G1000 700 System Maintenance Manual 200 B200 Series King Air Page 3 25 190 00915 01 Revision 9 3 12 GTS 820 850 Traffic System Configuration Follow this procedure to enable the GTS 820 850 traffic system function for the G1000 system if required NOTE 1000 can only be configured for TIS or TAS TCAS but not both Performing this procedure will automatically disable the TIS function Coordinate this configuration with Section 7 27 GTS Traffic System Functional Check NOTE Configuration of the GTS 820 850 TAS TCAS I will require the GTS system to be configured with the aircraft mode S address Coordinate this configuration with Section 3 48 Aircraft Registration Number Entry 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the System Upload page on using the small FMS knob 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key on PFDI 3 Rotate the small FMS knob to highlight King Air GTS 8XX TAS TCAS I Press ENT key on PFDI 4 Verify the King Air GTS 8XX TAS TCAST is displayed in the Item window Press LOAD 5 Monitor load progress Verify software load completes
203. dio ID The unit must be on for approximately one hour after the request for the refresh has been sent to receive the signal Y Alternatively you may also go to XM s website and enter the radio 10 to have a refresh signal sent Y If there is still problems receiving weather products after performing the above step call XM and have the account deactivated and a new account activated to clear out any corrupt account information Y Verify there is a good ground connection through the aircraft between the MFD and the GDL69 69A unit Reference the Aircraft Maintenance Manual for instructions on how to check bonding and ground points Y f problem persists replace the GDL 69 69A 5 Page 5 68 Revision 9 G1000 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 5 14 2 GDL 69A Alerts Failure Message Cause Solutions e Replace GDL 69 e Check GDL 69A antenna and cabling Checkthe GDL 69A and MFD interconnect e Reload configuration file See Section 3 9 for the Configuration Procedure e f problem persists replace master configuration module check config module harness for faults and replace if The G1000 has detected a failure GDL 69 FAIL GDL 69 has failed in the GDL 69A necessary GDL69CONFIG GDL69 The G1000 has detected a GDL NOTE configuration eror Config service goa configuration mismatch New Terrain Obstacle cards Jeppesen reqd Aviation Database and o
204. does not meet the tolerances specified have maintenance checks performed on the air data system or the pitot static system Page 7 14 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 Table 7 5 Air Data System Test Pid Altitude FT Airspeed KIAS AIRDATA L AIR DATA2 AIRDATA2 Nominal ALT lt J Altitude Tolerance Tolerance Tolerance Tolerance Actual Actual Actual Actual 0 2 20 3 20 a EE 400 0 3720 3720 3 2 E 9 0 lo 2720 2720 wa EZ 132 0 3720 2720 a 33 198 9 1000 3 20 2720 EE EZ Soj 1000 2000 2725 EE 5 2 5 2 So 200 4000 3 25 3 25 a 5 2 80 4000 5000 2730 2730 a HD ol 8000 5000 2730 2730 a 5 2 560 8000 10000 2730 2730 5 2 5 2 o0 10000 11000 2 25 3 25 a H2 o 11000 13000 2 40 2 40 xa 33 50 13000 14000 3 40 3 40 a EZ sof 14000 16000 2 45 3 45 5 2 5 2 160 18000 3 45 2 45 a 2 fio 18000 19000 3 47 3 47 5 2 EA os 18983 19000 3 47 3 47 a 5 2 fea 18971 19000 3 47 3 47 5 2 5 2 65 18958 19000 Ex 47 a 12 oo 18947 19000 HAT 3 47 wa 5 2 551 18947 19000 47 EE ua 32 53 18947 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 7 15 Revision 9 Air Data System Test Continued Test Point Alt
205. dure is applicable only to aircraft that have XM radio subscriptions WARNING The following steps require movement of the landing gear Ensure aircraft is safe for the operation of the landing gear before proceeding 1 Jack aircraft to allow operation of landing gear reference King Air 200 Series Maintenance Manual Chapter 7 00 00 2 Ensure both left and right throttles are at IDLE position 3 While monitoring pilot and copilot XM audio retract landing gear to the full up and locked position and verify the following e landing gear warning horn is active XM audio is muted in the pilot and co pilot stations 4 Increase both left and right throttles forward of IDLE position towards takeoff position and verify the following landing gear warning horn is not active XM audio can be heard For aircraft not equipped with a tone generator deselect mute softkey or adjust XM volume to restore XM audio Extend landing gear to the full down and locked position and return both throttles to idle position Remove aircraft from jacks Ensure STALL WARN circuit breaker is closed While monitoring pilot and copilot XM audio press the STALL WARN TEST switch and verify the following Se e sn Stall warning tone is active XM audio is muted in the pilot and co pilot stations 9 Release the STALL WARN TEST switch and verify the following Stall warning tone is not active XM audio can be heard For aircraft not equipped with a ton
206. e Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin Ensure the four GRS 77 or GRS 7800 mounting screws are tight Finger tight is not sufficient a screwdriver must be used to verify Ensure mounting rack and airframe shelf are secure and all hardware and brackets are present CAUTION do not loosen the mounting rack hardware to the airframe shelf or the aircraft will need to be re leveled and the PITCH ROLL OFFSET procedure performed Ensure GRS 77 or GRS 7800 connector is securely fastened and proper strain relief is provided Remove GRS 77 or GRS 7800 connector and verify there are no bent pins Replace the GRS 77 or GRS 7800 Contact Garmin for further troubleshooting if required Page 5 70 Revision 9 G1000 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 5 15 2 GRS Alerts Failure Message MANIFEST GRS1 software mismatch Communication halted mismatch Communication halted MANIFEST GRS2 software Cause The system has detected an incorrect software version loaded in the specified GRS 77 or GRS 7800 Solutions Load correct software version See Section 3 9 for the Software Load Procedure AHRS1 SERVICE AHRS1 magnetic field model needs update magnetic field model needs update AHRS2 SERVICE 52 The AHRS magnetic field model should be updated for th
207. e 19 O LAA Output Hi LAA outputs to 2 2 VDC Pot 3 0 flaps LAA adjustment Pot 4 flaps LAA adjustment Pot 5 full flaps LAA adjustment 22 O Lift Transducer Test Point Varying voltage from Lift Transducer 23 Signal Ground 24 O Lift Transducer Excitation Voltage Hi 10 VAC 700 Hz nominal 25 O Lift Transducer Excitation Voltage Lo 26 Lift Transducer Secondary Fast Input 27 Lift Transducer Center Tap Common Lift Transducer Secondary Input into the computer 28 Lift Transducer Secondary Slow Input G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 91 Revision 9 5 25 2 Lift Transducer Functional Pinout Pin Function Information 1 O Slow Secondary Pin Hi Vane resistance Pins 6 to 7 Lo 70 ohms 2 Center E Core Primary Pin Hi Fast Secondary Pins 3 to 4 Lo 320 ohms o Fast Secondary Pin Hi Sadr Cord ori 19 Lo S20 ohms 4 Secondary Pin Lo Pins 2 to 5 Lo 140 ohms 5 1 Center E Core Primary Pin Lo Self Test coil Pins 8 to 7 Lo 50 ohms 6 24 Vane Heater Pip HI All resistances are 20 7 Vane Heater Pin Lo 8 Self Test Coil Pin Hi Transducer Mounting Plate heater resistance is 2 1 20 ohms at ambient temperature 5 26 GDL 59 Troubleshooting Symptom Recommended Action e Check power wiring and pin out of GDL 59 unit Ensure GDL 59 con
208. e pitch reference Verify the command bars move down 1 degree and the control wheel begins moving forward Hold the controls and press CWS to re center the command bars and stop control wheel movement 7 With the Autopilot still engaged and the CWS button pressed move the control wheel to its aft limit Release the CWS button and apply continuous forward pressure slowly moving the control wheel After a brief delay verify the trim wheel begins moving in a trim up direction 8 Grip the control wheel and press the CWS button Verify trim motion stops Move the control wheel to the forward limit and release the CWS button Slowly move the control wheel aft After a brief delay verify the trim wheel begins to trim down Relieve pressure on the wheel and verify the trim motion stops Check that the trim wheel is free to turn Hold the control wheel and press the AP YD DISC TRIM INTRPT switch to disconnect the autopilot Page 8 12 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 8 26 VOR LOC GS Test Pe eq 10 form the following test using ramp test equipment Operate the equipment according to the test juipment manufacturer s instructions NOTE The PFD HSI does not show a course deviation bar unless a valid VHF NAV frequency is tuned Ensure FD is coupled to PFD1 as indicated by a left pointing arrow next to button Simulate a VOR signal on a radial equivalent to the aircraft
209. e specified unit Appears on ground only Load updated AHRS magnetic field file See Section 4 6 GEO LIMITS AHRS1 too far north south no magnetic compass north south no magnetic compass GEO LIMITS 52 too far No magnetic compass information available due to being too far north or south Operate the aircraft only within the limits as specified in the G1000 GFC 700 King Air 200 B200 AFMS listed in Table 1 3 AHRS1 TAS AHRS1 not receiving airspeed AHRS2 TAS AHRS2 not receiving airspeed The specified GRS 77 or GRS 7800 is not receiving airspeed from the GDC 74B GDC 7400 Check GRS GDC interconnect for faults Replace the GDC 74B GDC 7400 e If problem persists replace the GRS 77 or GRS 7800 AHRS1 GPS AHRS1 not receiving backup GPS information The GRS 77 or GRS 7800 1 is not receiving backup GPS information from either GIA 63 AHRS1 GPS AHRS1 operating exclusively in no GPS mode The GRS 77 or GRS 7800 1 is operating in the absence of GPS AHRS1 GPS AHRS1 not receiving any GPS information The GRS 77 or GRS 7800 1 is not receiving GPS data from the GPS receivers AHRS1 GPS AHRS1 using backup GPS source The GRS 77 or GRS 7800 1 is using the backup GPS data path Ensure that a cell phone or a device using cell phone technology is not turned on even a monitoring state in the cabin Check GPS status for GIA
210. e 8 3 GIA Data Verification RS 485 Figure 8 4 Pre Flight Test LIST OF TABLES TABLE Table 1 1 G1000 System Software Version Table 1 2 Required Documents Table 1 3 Reference Publications Table 4 1 Maintenance Intervals Table 4 2 Discontinued Maintenance Interval Table 4 3 Nose Section Visual Inspection Procedur Table 4 4 Nose Avionics Compartment Visual Inspection Procedure Table 4 5 Pilot s Compartment Visual Inspection Procedure Table 4 6 Instrument Panel G1000 Equipment Visual Inspection Procedure Table 4 7 Cabin Area Visual Inspection Procedure Table 4 8 Rear Fuselage and Empennage Visual Inspection Procedure Table 4 9 Lightning Strike Inspection Procedure Table 4 10 Measured Torque Table 4 11 GSM 85A GSM 86 Slip Clutch Torque Settings Table 4 12 Engine Data Check Test Equipment Table 4 13 Oil Pressure Indication Test Points Table 4 14 ITT Indication Test Points Table 4 15 Torque Indication Test Point Table 4 16 Standby Battery Required Equipment Table 5 1 SVS Troubleshooting Table 5 2 SVS Related Alert Messages Table 5 3 AFCS Annunciation Troubleshooting Table 5 4 AFCS General Troubleshooting Table 5 5 Magnetometer Interference Test Sequence Table 6 1 Configuration Module Kit 011 00979 00 Table 6 2 GRS 7800 Configuration Module Parts Table 6 3 Thermocouple Kit 011 00981 00 Table 7 1 Fuel Flow Indication Test Equipment Table 7 2 Fuel Flow Test Points Tab
211. e ChartView option A ChartView Enable Card as specified in 005 00421 03 General Arrangement Drawing King Air 200 B200 will be required for this procedure NOTE The required ChartView databases are subscription based and are to be procured by the installing agency directly from Jeppesen NOTE The G1000 can only be configured for FliteCharts or ChartView but not both Performing this procedure will automatically disable the FliteChart option Coordinate this configuration with Section 7 17 ChartView Functional Check 1 With the ChartView Enable card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFDI 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight Configuration Files and press ENT key PFDI 3 Rotate the small FMS knob to highlight Enable ChartView Press ENT key on PFD1 4 Verify Enable ChartView is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the ChartView Enable card from PFDI Page 3 56 G1000 700
212. e Configuration column and Software columns for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor Page 3 36 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 23 44 Software Configuration Follow this procedure to configure the GMU 44 magnetometers Coordinate the GMU 44 configuration with Section 7 7 AHRS GMU 44 Magnetometer 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key on PFDI 3 Rotate the small FMS knob to highlight King Air GMU 44 Press ENT key on PFDI 4 Verify King Air GMU 44 is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration and Software columns for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 37 190 00915 01 Revision 9 3 24 5
213. e GCU e If problem persists replace master configuration module check config module wiring for faults and replace if necessary NOTE New Terrain Obstacle cards Jeppesen Aviation Database and other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number GCU FAIL GCU is inoperative The G1000 has detected a failure in the GCU 477 Check wiring for faults ref Failed Path troubleshooting section e Replace the GCU 477 MANIFEST GCU software mismatch Communication halted The system has detected an incorrect software version loaded in GCU 477 Loadthe correct software version See Section 3 9 for the Software Load Procedure G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 79 Revision 9 5 20 Software Configuration Troubleshooting Problem Solutions MED or PED displays do not power up e Ensure that the criteria listed in Section 5 20 1 are fulfilled for the applicable situation e Ensure power is present at display backshell connector e Troubleshoot per the Blank Display GDU section Software file load fails e Ensure that criteria listed in Secti
214. e GDU STATUS page in configuration mode ensure CCFT CRNT 1 amp 2 levels are above 50 Y If the CCFT levels are not above 50 apply light to the photocell and observe if the CCFT level rises Y Ifthe CCFT level rises disregard the message v Ifthe CCFT level does not rise replace the MFD Replace the MFD PFD 1 SERVICE needs service Return unit for repair PFD 2 SERVICE needs service Return unit for repair The G1000 has determined the specified PFD needs service e Ensure the PFD connector is fully seated and locked e Ifthe unit was started in a very dark environment the photocells may not have enough light to initially raise the CCFT level Go to the GDU STATUS page in configuration mode ensure CCFT CRNT 1 amp 2 levels are above 50 v Ifthe CCFT levels are not above 50 apply light to the photocell and observe if the CCFT level rises Y If the CCFT level rises disregard the message v Ifthe CCFT level does not rise replace the PFD Replace the PFD PFD 1 VOLTAGE PFD 1 has low voltage Reducing power usage PFD 2 VOLTAGE PFD 2 has low voltage Reducing power usage The specified PFD supply voltage is low Check input voltage to PFD If input voltage is ok replace PFD MFD1 VOLTAGE MFD1 has low voltage Reducing power usage The MFD supply voltage is low Check input voltage to MFD If input voltage is ok replace MFD Page 5 5
215. e Manual 200 B200 Series King Air 190 00915 01 Page 5 71 Revision 9 Failure Message Cause Solutions MAG VAR WARN Large magnetic variance Verify all course angles Magnetic variance value from GMU 44 is not accurate If flying near large radio towers or other sources of possible electromagnetic interference the condition should correct itself as the aircraft leaves the area If problem persists run magnetic interference check in Section 5 15 4 to check for magnetic interference in the aircraft Difference in the pitch sensors is Perform Calibration Procedure 1 GRS PIT MISCOMP 77 or GRS 7800 Pitch Roll Offset greater than 5 degrees Calibration reference Section 7 Piece he rell Bod CE Perform Calibration Procedure A1 GRS ROL MISCOMP p Rd i 77 or GRS 7800 Pitch Roll Offset greater than 6 degrees Calibration reference Section 7 5 15 3 GMU Alerts Failure Message Cause Solutions MANIFEST software mismatch Communication halted MANIFEST GMU2 software Load the correct software version See Section 3 9 for the Software Load The system has detected an incorrect software version loaded in the specified GMU 44 Procedure mismatch Communication halted HDG FAULT AHRS1 e Check GMU 44 GRS 77 or GRS magnetometer fault has occurred A fault has occurred in the 7800 interconnect for faults specified magnetometer heading v Replace GMU 44 will be
216. e generator deselect mute softkey or adjust XM volume to restore XM audio G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 5 190 00915 01 Revision 9 7 3 GIA 63W Integrated Avionics Unit Original GIA 63W s Reinstalled No software or configuration loading is required if the removed GIA is re installed in its original position and GIA2 in their original racks This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the return to service checks in Section 8 Original GIA 63Ws Swapped for Troubleshooting No software loading is required if the originally installed GIA units are re installed in opposite positions and GIA2 in opposite unit racks However configuration loading is required See Section 3 9 and then continue to the GIA 63W Test Section 7 3 1 New Repaired or Exchange GIA 63W s Installed Ifa new repaired or exchange GIA 63 is installed the correct software and configuration files must be loaded to the unit See Section 3 9 and then continue to the GIA 63W Test Section 7 3 1 7 3 1 GIA 63W Test GPS Signal Acq n Figure 7 3 AUX GPS STATUS Page MFD The GIA 63W units should normally acquire a GPS navigation solution within 5 to 10 minutes of startup provided the aircraft is outside or indoors with a GPS repeater Select the GPS STATUS page on the
217. e load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the SVS Enable card from PFD1 Page 3 60 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 44 Optional ESP Enable Follow this procedure to enable the Electronic Stability and Protection ESP function An Enhanced AFCS Unlock Card as specified on General Arrangement Drawing 005 00421 03 will be required for this procedure NOTE The G1000 has various features that require the use of unlock enable cards to activate the feature Throughout this document these cards are generically referred to as enable cards In some cases the actual label on the physical card may say unlock If uncertain the technician should verify the card part number prior to use Ensure that the ESP Support Configuration has been loaded per Section 3 32 or 3 33 Coordinate this configuration with Section 7 26 ESP Functional Check 1 With the Enhanced AFCS Unlock card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the
218. e not used If in doubt as to which buttons should be disabled reload GMA config files and other config files for optional equipment installed in the aircraft i e ADF HF etc from the loader card COM Bleedover e Verify on the GMA CONFIGURATION page that Disable Split COM has a green box Due to the closeness of the COM antennas and high power of the COM transceivers Split COM operation is not approved If the box is black indicating COM button is active highlight Disable Split COM with the cursor and press the ENT key to tum the box green which will deactivate Split COM mode Speaker Cuts Out Reduce volume level of the item that caused the speaker to cut out when turned up A speaker protection circuit disables the speaker output if the volume is too high If the volume is not sufficient replace aircraft cabin speaker reference the Airframe Maintenance Manual Mic Audio Heard in Reduce ICS Volume Speaker e Ensure both GMA units are receiving power e Ensure both units are properly configured by verifying there are GMA alert messages Check interconnect wiring between the GMA s for faults GMA XTALK GMA crosstalk error has occurred Replace GMA1 e If problem persists reinstall GMA and replace GMA2 G1000 700 System Maintenance Manual 200 B200 Series King Air Page 5 55 190 00915 01 Revision 9 5 97 GMA Alerts Failure Message GMA1 SERVICE
219. e performed by making counter clockwise turns for the purpose of evaluating the site for magnetic disturbances If the PFD displays the CALIBRATION SUCCESSFUL SITE IS CLEAN message upon completion of the Magnetometer Calibration Procedure in each clockwise and counter clockwise direction then the candidate site is sufficiently free of magnetic disturbances and is acceptable for performing the Magnetometer Calibration Procedure It is important to obtain successful result in both the clockwise and counter clockwise directions to ensure that the magnetometer sweeps over a large enough area at the candidate site If the PFD displays either the MAG FIELD AT SITE NOT UNIFORM or MAG FIELD AT SITE DIFFERS FROM IGRF MODEL message upon completion of the Magnetometer Calibration Procedure in either of the two directions then the site contains magnetic disturbances that are too large G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 21 190 00915 01 Revision 9 7 7 4 Procedure B GRS 77 or GRS 7800 and GMU 44 Magnetic Calibration NOTE Procedure A 1 Section 7 7 2 must first be successfully accomplished before performing Procedure B only for situations where the GRS was replaced with a new unit Start the aircraft engine following the procedures referenced in the appropriate King Air AFM or AFMS as shown in the General Arrangement drawing listed in Table 1 2 After aircraft engine startup taxi t
220. e servo is Elevator Mis Trim Up Aileron Mistrim Right Check the aircraft control adjustments e If mistrim condition still exists remove and replace the pitch trim servos for proper operation Verify that the servo is online at the AUX SYSTEM STATUS page receiving power affected servo Check for possible fuel imbalance Check aileron control adjustments G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 31 190 00915 01 Revision 9 Annunciation Condition Resolution Aileron Mistrim e If mistrim condition still exists remove and replace the roll Left servo Rudder Mistrim Check rudder control adjustments Right e f mistrim condition still exists remove and replace the yaw servo Rudder Mistrim Left Allow the system to complete pre flight tests PFT Pre Flight Test preflight test should finish within 2 minutes If it does Fails not pass the red PFT annunciation is shown In case of PFT failure see Section 5 6 3 for additional PFT diagnostics Table 5 4 AFCS General Troubleshooting Condition Poor AP Performance Limited AP Authority Resolution Check each servo gearbox slip clutch per Section 4 9 Verify the clutches are not excessively loose and are within torque limits Check aircraft controls for proper balancing and adjustment per the King Air 200 Series Maintena
221. e vertical separation from the maneuvering threat aircraft Climb Climb Now Climb Climb Now voice TCAS II Resolution Advisory Climb at the rate depicted by the solid green bar on the vertical speed tape on the PFD Received after a DESCEND resolution advisory and indicates a reversal in direction is required to achieve safe vertical separation from the maneuvering threat aircraft Descend Descend Now Descend Descend Now voice TCAS Resolution Advisory Descend at the rate depicted by the solid green bar on the vertical speed tape on the PFD Received after a CLIMB resolution advisory and indicates a reversal in direction is required to achieve safe vertical separation from the maneuvering threat aircraft These aural alerts are specific to installations with the GTS Processor configured as a GTS 8000 TCAS II unit For installations of other approved TCAS II stems these alert and visual indications may be slightly different For instance MONITOR VERTICAL SPEED in the GTS processor installation is ADJUST VERTICAL SPEED for the third party TCAS II installation Page 5 4 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 5 2 System Annunciations If data fields become invalid due to an LRU failure the PFD MFD typically annunciates the failure with a large red X as shown in Figure 5 4 RO FIL
222. ed for properly operating LRUs red x appears when an internal LRU fault is detected and it has taken itself offline or if the MFD can not communicate with the LRU Serial Number Each LRU serial number is displayed functions such as GPS and GS are contained within an LRU therefore serial numbers are not shown for these Current SW Version Loaded When troubleshooting first check to ensure that each LRU status is green and that the correct software is loaded in each unit Additional airframe and database information is also displayed on this page G1000 700 System Maintenance Manual 200 B200 Series King Air Page 5 1 190 00915 01 Revision 9 5 1 G1000 Alerting System System Annunciators A dota poth T GHAZ FAIL is inoperative GHA FAIL GMAT is inoperative Alerts Softkey RVI Annunciation Figure 5 2 Alerts amp Annunciations The G1000 Alert System conveys alerts to the pilot using combinations of the following features Alert Window The Alert window displays alert text messages Pressing the ALERTS softkey displays the Alerts window Pressing the ALERTS softkey again removes the Alerts window from the display Sofi When the G1000 Alerting System issues an alert the ALERTS softkey is used as a flashing annunciation to accompany the alert During the alert the ALERTS softkey label changes to ADVISORY as shown in Figure 5 3 Pressing the ADVI
223. ed to the unit See Section 3 9 and then continue to the GCU 477 Test Section 7 10 1 7 10 1 GCU 477 Test Perform the following key and knob presses and knob rotations on the GCU 477 and verify the actions on the MFD 1 Rotate the large FMS knob and verify that the page groups change 2 Rotate the small FMS knob and verify that the pages change within the page groups 3 Use the large FMS knob to display the MAP page group and the small FMS knob to display the NAVIGATION MAP page Rotate the RANGE knob to the right and verify the map display zooms out Rotate the RANGE knob to the left and verify the map display zooms in Press the RANGE knob to get the pointer on the map display Move the RANGE knob to the left and verify the pointer moves to the left Move the pointer up right and down and verify that the pointer moves accordingly Press the RANGE knob to stop displaying the pointer 10 Press the left and right arrowheads of the SOFTKEY SELECT keys Verify softkeys highlighting on the changes 11 Press the SEL key to select one of the softkeys 12 Press the gt key to display the DIRECT TO page 13 Use the keypad to type KIXD and verify KIXD is displayed on the MFD 14 Press the SPC key to add a space and then the BACK key to delete the space 15 Press the CLR key to clear the field 16 Type K34 and then press the ENTER key twice Verify that the flight path to K34 is displayed on the map 17 Pres
224. ed white 8 Initiate passenger address using pilot s headset boom mic by keying the pilot s PTT Verify the following Clear PA audio can be heard over cabin speaker and CABIN ICS headsets selected annunciator GMAI flashes once per second during PA address 9 Repeat Step 8 using pilot hand mic 10 Initiate passenger address using copilot s headset boom mic by keying the copilot s PTT Verify the following Clear PA audio can be heard over cabin speaker and CABIN ICS headsets e PA selected annunciator on GMA1 flashes once per second during PA address 11 Repeat Step 10 using copilot hand mic G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 3 190 00915 01 Revision 9 Transceiver Operational Check Perform a ramp test radio check by exercising the installed transceivers microphone microphone key and audio over the headphones and speaker Verify that communications are clear and PTT operation is correct for each pilot position 1 On the pilot s audio panel select the audio source corresponding to each installed avionics unit i e NAVI NAV2 COMI 2 ADF and DME and check for audio over the pilot s headset Press the SPKR key on pilot s audio panel and verify that the selected audio is heard over the pilot s speaker 3 On the copilot s audio panel select the audio source corresponding to each installed avionics unit i e NAVI NAV2 COMI COMO ADF and DM
225. edure Verify PRI and SEC power sources for PFD 1 GIA 1 GRS 1 GDC 1 Verify secondary paths for AHRS ADC engine parameters and GPS data Verify the operation of PFD and MFD 4 10 220 hours max Ethernet connections Verity ARINC connection between ADC1 and MFD and between GRS1 and MFD Verity DISPLAY BACKUP button function G1000 Redundant Connection Check Verify engine data is available and Engine Data Check accurate with GIA 1 or GIA 2 inoperative 2n 820 hours max Trim Annunciator Verify trim annunciators function 412 220 hours max G1000 Miscompare Verify AHRS airspeed and altitude Check miscompare monitors function properly 413 820 hours max Verify availability of power bus feeders essential bus No 1 dual feed bus No 2 4474 620 hours max dual feed bus Power Bus Feeder Check Dual Bus Feeder Diodes Check Inspection of dual bus feeder diodes 4172 Phase 3 Check for and troubleshoot any alerts G1000 Alerts provided in the alert window per the 5 On Condition referenced manual section AS 6 18 On Condition Diversity Transponder 7 Antenna Removal amp Replacement 6 19 On Condition RATE Refer to Master Drawing List listed in Table 536 prem e 1 2 for installation drawings WiFi Antenna 621 On Condition GA Be afe 632 On Condition Flaps in motion Test the Flaps in motion discrete inputs to m Peseta she Discrete Input Check the G1000 to verify
226. een flight director 1 GIA1 and flight director 2 GIA2 Autopilot The autopilot operates within one high speed GSA 80 servo pitch trim and three GSA 80 servos pitch roll and yaw Flight director data is processed within the servos and turned into aircraft flight control surface commands The autopilot cannot operate unless the flight director is engaged Manual Electric Trim When the autopilot is not engaged the pitch trim servo may be used to provide a Manual Electric Pitch Trim MEPT function This allows the pilot or co pilot to adjust pitch trim from the PITCH TRIM switch on the control wheel in lieu of using the elevator trim wheel Trim speeds are scheduled to provide easier control over a wide speed or configuration range The PITCH TRIM switch is split into two halves The left half arms MEPT The right half controls direction Both halves must be actuated at the same time to command the pitch trim servo to operate If only one half of the PITCH TRIM switch is actuated for more than 3 seconds a red PTRM message will appear on the PFDs Yaw Damper The yaw damper reduces Dutch roll tendencies and coordinates turns It can operate independently of the autopilot and may be used during normal hand flight maneuvers Electronic Stability and Protection Electronic Stability and Protection ESP is an optional function that is intended to assist the pilot in maintaining the airplane in a safe flight condition within the aircra
227. em Remove power from PFD1 PFD2 and MFD by opening the PFD1 PRI SEC PFD2 and MFD circuit breakers Par Insert the software loader card in the upper slot of PFD2 Apply power to PFD2 When prompted to update system files press the NO softkey When prompted to update splash screen files press the YES softkey Remove the loader card from PFD2 and insert it into the upper slot of the MFD Apply power to the MFD and repeat steps 5 and 6 Remove the loader card from the MFD and insert it into the upper slot of PFD1 Apply power to PFDI and repeat steps 5 and 6 Cycle power to the and splash screen will be present NOTE seer away os Any time software and or configuration is loaded to the system the splash screens will need to be reloaded to all three display units G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 67 190 00915 01 Revision 9 3 51 Navigation Database Loading A new navigation database cycle may be loaded before it is effective The new database will be stored on the G1000 bottom SD card until it becomes effective The G1000 will automatically update to use the new database at the first on ground power on after its effectivity date Follow this procedure to load the navigation database 1 Remove power from the PFD1 PFD2 and Insert an SD card containing the latest cycle Jeppesen navigation database data supplied by Jeppesen into the top slot of the
228. em when loading software Remove power only when instructed by the following procedure As a general rule all displays should be in the same mode configuration or normal unless instructed otherwise 1 Ensure loader card is inserted into top card slot of PFD1 On PFDI select the System Upload page using PFDI small FMS knob Activate the cursor and use the PFD1 small FMS knob to highlight the GROUP field Scroll small FMS knob to select the appropriate airframe and engine combination Press the PFD1 ENT key to select the configuration m Figure 3 17 Airframe Options 3 Once an airframe type is selected the cursor moves to the ITEM window Rotate PFD1 small FMS knob to activate the drop down menu Move the cursor to highlight the appropriate propeller configuration for the aircraft and press ENT on PFDI NOTE Not all propellers are available for selection with each airframe and engine configuration Only those props that are approved for installation on a particular airframe engine are available in the drop down selection window Figure 3 18 Propeller Options 4 Once the propeller type is selected the cursor moves to the PRODUCT windo Select the software and or configuration which is to be loaded for each G1000 LRU G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 21 190 00915 01 Revision 9 NOTE The PRODUCT window displays information regarding each G1000 LRU The LRU column depicts
229. emoval amp Replacement On Condition Annunciator Switch dos Prop Sync Other Equipment Removal amp Replacement 6 25 On Condition Standby Airspeed T Indicator tatic pressure system test according to 14 CFR 91 411 and Part 43 Appendix E NIA 24 Calendar Months Removal amp Replacement 6 26 On Condition Standby Altimeter Test according to 14 CFR 91 411 and Part 43 Appendix E N A 24 Calendar Months Standby Attitude pu iod Removal amp Replacement 627 On Condition L 3 PS 835 C or D Removal amp Replacement 6 24 On Condition Standby Battery Capacity test of standby battery 4 16 2 12 Calendar Months o 220 hours max or Standby Battery Verity the standby battery is being Charge Check charged A161 6 Calendar Months Verity STBY ATT amp STBY ALT vibrator operate and STBY STBY ALT amp Instrument STBy A S illumination function on either Electtical Power aircraft power or standby battery power 815 220 hours max standby compass checked during existing maintenance Annunciator Switch Removal 8 Replacement 6 23 On Condition Standby Battery Denotes Airworthiness Limitation Maintenance Requirement See Section 4 1 Page 4 10 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 4 31 Discontinued Maintenance Table 4 2 shows a list of inspections and tests that are listed in the King Air 200 Series Maintenance Manual but may be no
230. ent regions Americas International Atlantic etc Load same type aviation database to all displays G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 51 Revision 9 Failure Message Cause Solution DB MISMATCH Airport Terrain database version mismatch Xtalk is off The PFDs and or MFD have different Airport Terrain database versions installed DB MISMATCH Terrain database version mismatch The PFDs and or MFD have different terrain database versions installed DB MISMATCH Obstacle database version mismatch The PFDs and or MFD have different obstacle database versions installed DB MISMATCH Terrain database type mismatch 5 9 3 Cooling Alerts Failure Message The PFDs and or MFD have different terrain database types installed i e different regions Americas International Atlantic etc Cause Confirm supplemental data card is inserted fully Reload the database or replace the supplemental datacard Solution MFD1 COOLING has poor cooling Reducing power usage MFD1 has exceeded its operating temperature range e Check cooling fan and wiring for proper operation if applicable Y Replace cooling fan if unable to determine if operating correctly Y f problem persists replace the MFD e If problem continues contact Garmin Aviation Product Support for assistance PFD 1 CO
231. eout lt 5 gt Pre flight test has failed because the specified step has not passed in the allotted time See the GIA pre flight steps for a description of the possible values for lt STEP gt on the failed GIA and corrective actions PFT FAIL Cross GIA Failed State lt STEP gt Pre flight test has failed on opposite GIA lt STEP gt specifies the pre flight test step on selected GIA that was in progress when the pre flight test failed on the opposite GIA See the GIA pre flight steps for a description of the possible values for lt STEP gt on the failed GIA and corrective actions PFT FAIL lt 5 gt Pre flight has failed because the step specified has failed See the GIA pre flight test steps for a description of the possible values for lt STEP gt on the failed GIA and corrective actions AHRS MON invalid lt 5 gt The AHRS monitor has detected that the AHRS data is invalid The possible values for STATE are a Mon Prmtr Invalid The ARINC 429 data used by one of the monitors has not been received b Attitude Prmtr Invalid The ARINC 429 pitch or roll angle has not been received Exceeded Attitude Limits The pitch or roll angle has exceeded the engagement limits 4 Cross Hdg Accel Fail Cross heading acceleration monitor failed Vert Accel Fail Vertical acceleration monitor failed f Fltrd Cross Hdg Accel Fail Filtered cross heading acceleration monitor failed g Fltrd Vert Accel F
232. er will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number HW MISMATCH GIA hardware mismatch GIA1 communication halted mismatch GIA2 communication halted HW MISMATCH GIA hardware The G1000 has detected a non WAAS GIA 63 Replace GIA with WAAS unit GIA1 SERVICE GIA1 needs service Return unit for repair service Return unit for repair GIA2 SERVICE GIA2 needs The G1000 has detected a failure in the specified GIA Replace suspect GIA G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 65 Revision 9 5 12 Troubleshooting 5 12 1 GEA Alerts Failure Message Cause Solution MANIFEST 1 software mismatch Communication halted MANIFEST GEA2 software mismatch Communication halted The system has detected an incorrect software version loaded in the specified GEA 71 Load the correct software verion See Section 3 9 for GEA 71 Software Load Procedure GEA1 CONFIG GEA1 configuration error Config service req d GEA1 CONFIG GEA2 configuration error Config service req d The system has detected a configuration mismatch in the specified GEA 71 Load GEA configuration files See Section 3 9 for GEA 71 Configuration Procedure e If problem
233. eral Arrangement drawing listed in Table 1 2 Software Configuration is a critical part of the G1000 operation and must be verified before returning an aircraft to service If any software version and or part number does not match those specified by the General Arrangement drawing or if the software is not successfully loaded DO NOT continue Troubleshoot and resolve the issue before continuing G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 23 190 00915 01 Revision 9 3 10 GDC 74B Air Data Computer Software Configuration For system software version 0985 06 and later follow this procedure to configure the GDC 74B air data computers if installed Refer to section 3 11 if the GDC 7400 air data computers are installed Coordinate the GDC 74B configuration with Section 7 6 GDC 74B or GDC 7400 Air Data Computer 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key on PFDI 3 Rotate the small FMS knob to highlight King Air GDC 74B models 200 B200 only Press ENT key PFDI 4 Verify King Air GDC 74B models 200 B200 only is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify sof
234. es instructions to check the software part number and version of each LRU before removing a unit Procedures in Section 7 require the same check after LRU replacement and software loading IMPORTANT All structural repairs associated with this installation are to be addressed in accordance with the Hawker Beechcraft Structural Inspection and Repair Manual listed in Table 1 2 NOTE After replacing or servicing electrical components near the GMU 44 magnetometers the Magnetometer Interference Test reference Section 5 and Magnetometer Calibration Procedure reference Section 7 must be performed Page 4 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 4 2 2 The following tools are needed to perform maintenance tasks on G1000 equipment Required Tools Calibrated Milli ohm meter OR Agilent 34410A Ammeter or equivalent Fluke 187 Voltmeter or equivalent Variable DC Power Supply capable of providing 1 amp current 2 Non Magnetic Phillips Screwdriver 3 32 Hex tool Calibrated digital level Required for AHRS Procedure A Calibration Calibrated VHF NAV COM ILS ramp tester or equivalent Calibrated transponder ramp tester or equivalent Calibrated pitot static ramp tester Outdoor line of site to GPS satellite signals or GPS indoor repeater Headset microphone Ground Power Unit Capable of supplying 28 Vdc Calibrated Flight Control Cable Tension Meter or equivalent 2 Am
235. ess LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration and Software columns for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 27 190 00915 01 Revision 9 3 14 GTX 33 33D Configuration Do not perform this step if the TCAS II System Option was loaded per section 3 47 Follow the procedures outlined in this section to load the necessary software and configuration files to enable the GTX33 33D transponders Coordinate the GTX 33 33D configuration with Section 7 5 GTX 33 or GTX 3000 Transponder 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the System Upload page using the PFD1 small FMS knob 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight King Air GTX 33ES Press ENT key PFDI 4 Verify King Air GTX 33ES is displayed in the Item window Press LOAD 5 Monitor load progress Verify software load completes without errors as indicated by the following Green PASS the Co
236. ess the DISPLAY BACK UP button on the Co pilot s GMA 1347D audio panel to return to normal mode Close the PFD 1 PRI and PFD 1 SEC circuit breakers and wait for PFD 1 to initialize G1000 700 System Maintenance Manual 200 B200 Series King Air Page 4 27 190 00915 01 Revision 9 D Engine data availability to the displays and GPS data availability to the AHRS with either GIA inoperative check 1 Open GIAI primary and secondary CBs 2 Verify the following 1 and COMMI tuning fields on PFD 1 and PFD 2 are invalid red X L R engine data remains valid XPDRI is Inoperative GMAL is Inoperative AHRSI is using backup GPS source AHRS2 not receiving backup GPS Information An amber BOTH ON GPSJjis displayed PFD 1 and PED 2 AHRS and ADC data remain valid PFD 1 and PFD 2 3 Close primary and secondary CBs Allow system to re acquire satellites and return to normal display modes 4 Open GIA2 CB 5 Verify the following and COMM tuning fields on PFD 1 and PFD 2 are invalid red X LIR engine data remains valid XPDR2 is Inoperative 2 Is Inoperative AHRS is using backup GPS source AHRSI not receiving backup GPS Information An amber BOTH ON GPS is displayed on PFD 1 and PFD 2 AHRS and ADC data remain valid PFD 1 and PFD 2 6 Close GIA2 CB Allow system to re acquire satellites and return to normal display modes 7 Open primar
237. etup time 1 Connect the SK100360 breakout box between the Safe Flight P N C 05606 1 lift computer and the mating aircraft harness see Figure 7 15 2 Make sure the stall warning heater system is turned OFF 3 Remove the potentiometer access cover plate from the lift computer 4 Simulate an in flight condition as follows Bypass the landing gear safety switch by connecting an electrical ground to TP7 of the breakout box This is best accomplished by placing a jumper between TP2 and TP7 of the breakout box CAUTION The anchor tab of the force applicator can be bent if the knob that applies tension to the transducer mounting plate is over tightened Use care when installing the force applicator to prevent damage to the anchor tab Refer to the data supplied with the force applicator 5 Install the appropriate gauge 1952 1 gauge 0 5 to 3 gram scale or the 1952 3 gauge 2 to 15 gram scale in the force applicator see Figure 7 16 onto the left wing in accordance with the manufacturer s instructions Refer to the data supplied with the force applicator The force arm must be positioned so that the applied force is within 1 32 inch of the transducer vane tip Forces applied forward or up will be classified as minus values Forces applied aft or down will be classified as plus values Make sure that the vane is free to move with the force applicator 6 Apply external power to the aircraft 7 Place the BATT master switch to the ON pos
238. ewdriver of any length into the card slot e NOT pry against the overlay e DO NOT force the SD Card out e Use a small screwdriver in the groove on the side of the exposed end of the card to help pull out the card e Push the card in further to release the card locking mechanism e Check SD Card for having more than one label Two or more labels on the card will cause sticking Y Remove all but one label e Ensure the SD card is from Toshiba or SanDisk Use of other SD Cards is not recommended If card was inserted with the label facing to the right do not attempt to remove Return the unit to Garmin for repair A button knob joystick does not appear to function e to the GDU TEST page in configuration mode and verify button knob or joystick operates correctly by observing a change in color from red to green in the button knob joystick icon when the button knob joystick is pressed If a button is stuck the button icon will be green without pressing the button as soon as you turn to the GDU TEST page If problem is verified replace GDU G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 47 190 00915 01 Revision 9 Symptom Terrain Obstacle Safetaxi does not display Recommended Action Ensure supplemental data cards are inserted correctly in the lower slots of all three GDU s Allow the system to verify the data on the cards for approximately five minutes after po
239. existing pitot static ports Refer to Figure 2 22 for a schematic of the aircraft s pitot static system and its connections to the G1000 STC installed equipment IMPORTANT Aircraft modified by this STC are eligible to be approved for RVSM operation RVSM critical maintenance instructions contained in this document must be followed in order to guarantee performance within RVSM specifications GDC 74B GDC 7400 optional Figure 2 8 Air Data Computer 2 1 10 OAT Probe 2 The Garmin GTP 59 OAT Probes provide the GDC 74B or optional GDC7400 with air temperature data The OAT probes are mounted to the bottom of the fuselage at F S 113 5 Figure 2 9 OAT probe G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 7 190 00915 01 Revision 9 2 1 11 Attitude amp Heading Reference System 2 The Garmin GRS 77 AHRS or GRS 7800 AHRS units provide attitude and heading information to the GI1000 system The units mounted in the nose equipment bay contain advanced tilt sensors accelerometers and rate sensors The unit interfaces with the Garmin Air Data Computers and GMU44 Magnetometer and utilizes GPS signals from the GIA 63Ws Actual attitude and heading information is sent using ARINC 429 digital interface to both GDU 1040As and GIA 63Ws The GRS interfaces with and provides power to the GMU 44 Magnetometer The GRS supplies attitude and heading information directly to the PFDs MFD and GIAs The 42 G
240. ey on PFD1 3 Rotate the small FMS knob to highlight King Air DME Option Press ENT key PFDI 4 Verify the King Air DME Option is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor Page 3 42 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 29 RAD ALT Option Configuration This section loads the necessary configuration files for those aircraft equipped with a radar altimeter When all sub sections are complete coordinate the RAD ALT configuration with Section 7 21 GRA 5500 Radar Altimeter Functional Check 1 With the loader card in the top slot of PFDI and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Airframe Options and press ENT key on PFDI 3 Rotate the small FMS knob to highlight King Air RAD ALT Option Press ENT key on PFDI 4 Verify the King Air RAD ALT Option is displayed in the Item window Press LOAD sofikey 5 Monitor load progress Ver
241. fects Check the integrity of the harness connector assembly in Indicator accordance with AC 43 13 1B Chapter 11 Section 8 Paragraphs 11 96 and 11 100 and the Cabin Wire Harness Routing drawing listed in Table 1 2 Inspect the standby airspeed indicator unit including face of unit and connector for Standby Airspeed corrosion or other defects Indicator b Visually inspect the plumbing and harness connector assembly and ensure it is secure and in good condition Inspect the standby altimeter indicator unit including face of the unit and connector for corrosion or other defects b Visually inspect the plumbing and harness connector assembly and ensure it is secure and in good condition Standby Altimeter Inspect circuit breaker panel wiring and circuit breakers for chafing damage other defects and proper routing of wire bundles and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 the appropriate Circuit Circuit Breaker Breaker Panel Modification drawing listed in Table 1 2 and the Cabin Wire Harness Panels Routing drawing listed in Table 1 2 Pay particular attention to possible areas of chaffing b Inspectedgelit overlay panels for damage or defect c Reinstall the circuit breaker edgelit overlays to the circuit breaker panels _ Inspect that all required placards are installed Placards must be legible secure and Placards in good condition Refer to the
242. field PFD1 and PFD2 are within the tolerances specified in Table 7 6 Table 7 6 Vertical Speed Table 7 6 3 OAT Probe Check l Ensure on side sensors for PFD1 and PFD2 2000 100 1000 50 500 45 200 45 0 N A No VS Display 200 45 500 45 1000 50 2000 100 2 Ensure the outside air temperature OAT probes and a calibrated thermometer stabilize at ambient temperature 3 Verify that the OAT measurement shown PFD1 and PFD2 in degrees Celsius indicate within 2 C of the ambient temperature as measured by the calibrated thermometer If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 7 17 Revision 9 7 7 GRS AHRS GMU 44 Magnetometer Original GRS is Reinstalled If the original GRS is reinstalled then no software loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process If the GRS rack was not removed or loosened continue to the GRS GMU Test Section 7 7 6 If the GRS rack was removed or loosened continue to the GRS GMU Calibration Procedures Section 7 7 1 Original GRS is Installed in Opposite Location for Troubleshooting If the original GRS 1 and GRS 2 are installed in opposite locations GRS 1 and GRS 2 in
243. figuration mode Use the FMS small knob to highlight GRS 1 for calibration and press the ENT key The SELECT PROCEDURE field is not blinking Initiate the AHRS engine run up vibration test procedure by performing the following steps a Select the ENGINE RUN UP TEST procedure and press the ENT key b Follow the checklist items displayed on the PFD and press the ENT key as each one is completed or confirmed When the CALIBRATE field is blinking press the ENT key to begin the procedure The PFD display instructs the operator to gradually increase power from idle to full throttle and back to idle over a period of 2 4 minutes When the operator has completed the engine run up and the engine is back to an idle setting press the ENT key to indicate that the process is complete When this is done the TEST COMPLETE field stops blinking The PFD informs the operator if the installation has passed or failed the vibration test If the test fails the specific measurements causing the failure are identified and associated numeric values are displayed on the PFD Page 7 24 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 NOTE Should a failure occur the technician may perform the Engine Run up test up to 3 times successively before corrective action must be taken If the test does not pass after three attempts then the installation should not be considered reliable until the source of the vib
244. figuration option has been loaded No communication with GDL 59 e Verify that a wi fi network is configured and available e Ensure the wi fi antenna is within range of a wi fi network 7 Remove any obstacles between the aircraft wi fi antenna and the wi fi No or low quality wi fi signal y M quati w tisigt network hub that may be blocking the signal Check the wi fi antenna cable and connectors e Verify antenna ground plane is adequate Connects to wi fi but cannotsend Activate Garmin Connext reference Section 7 28 Note that a replacement GDL 59 unit must be registered again even if the MFD already shows report data REGISTERED Page 5 92 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 27 Symptom GSR 56 Troubleshooting Recommended Action No communication with GSR 56 Check power wiring and pin out of GSR 56 unit Ensure GSR 56 configuration option has been loaded No or low quality Iridium signal e Ensure the Iridium antenna has an unobstructed view of satellite constellation Check the Iridium antenna cable and connectors e Verify antenna ground plane is adequate No audio output Check wiring from GSR 56 to GDL 59 or from GSR 56 to GIA 1 stand alone as applicable to the installation Verify subscription with Garmin Connext reference Section 7 28 Unable to make a phone call Verify signa
245. figured for the traffic system Reference Section 3 29 Non Garmin Traffic System Option Configuration to enable the traffic system 3 Press the OPERATE soft key and verify that OPERATING is displayed in the upper left corner of the traffic map 4 Press the STANDBY soft key and verify that STANDBY is displayed in the upper left corner of the traffic map 5 Press the TEST soft key and verify that TEST is displayed in the upper left corner of the traffic map and a traffic test pattern is displayed Upon completion of the test verify that TAS SYSTEM TEST is heard over the cockpit speaker NOTE This annunciated traffic system test message may be different from the traffic system installed on subject aircraft 6 Open the TRFC circuit breaker on the avionics circuit breaker panel On verify that NO DATA is displayed in yellow after several seconds 7 Close the TRFC circuit breaker on the avionics circuit breaker panel and verify that NO DATA is removed after several seconds If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 31 190 00915 01 Revision 9 7 14 Stormscope Functional Check Reference Section 3 31 Stormscope WX 500 Configuration for configuring Stormscope This procedure assumes familiarity with the set up and operation of the WX PA portable analyzer kit l Apply power to
246. flagged invalid v If problem persists replace GRS 77 or GRS 7800 HDG FAULT AHRS2 magnetometer fault has occurred Perform Calibration Procedure E Magnetometer Interference Test Difference the heading sensors reference Section 5 and Procedure HDG MISCOMP is greater than 6 degrees GRS 77 or GRS 7800 and GMU 44 Magnetometer Calibration reference Section 7 Page 5 72 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 15 4 Calibration Procedure E Magnetometer Interference Test A magnetometer interference test is available for troubleshooting and or verifying a magnetically clean installation of the GMU 44 This test exercises various devices on the aircraft that could potentially affect the magnetic field as measured by the GMU 44 NOTE This test is used to validate that no electronic device or magnetized components produce a magnetic field sufficient to interfere with the operation of the GMU 44 magnetometer It is highly recommended that this test be performed after installation or maintenance of electrical components on the aircraft and or for troubleshooting the GMU 44 COPHENCATIGA STATU Um annm DILIBATIU PROCEDURE test Select TEST COMPLETE vin Finished Tie sintas il then be Aled Figure 5 7 Magnetometer Interference Test l Initiate the AHRS magnetometer interference test procedure by per
247. forming the following steps 2 OnPFDI enter Configuration Mode and go to GRS GMU Calibration page as shown in Figure 5 7 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 73 190 00915 01 Revision 9 3 This page is protected and requires keystroke password to perform this test Press the following softkeys in sequence as counted from left to right on lower bezel of MFD e softkey 9 e softkey 10 e softkey 11 e softkey 12 4 Select MAG INTERFERENCE TEST and press the PFD1 ENT key 5 Follow the checklist items displayed on the and press the ENT key as each one is completed or confirmed NOTE The 3 item on the checklist instructs the operator to prepare a detailed test sequence with precise start and stop times for exercising all electronic devices The list of relevant electronic devices are given in Table 5 5 Begin test with flaps retracted flight controls in a neutral position all lights selected OFF Elapsed Time since Start of Test TUR min secs 0 00 Test begins 0 05 Tail Flood lights on 0 10 Tail Flood lights off 0 20 Navigation lights on 0 30 Navigation lights off 0 40 Landing lights on 0 50 Landing lights off 1 00 Taxi lights on 1 20 Taxi lights off 1 40 Strobes on 1 50 Strobes off 2 00 Recognition lights on 2 10 Recognition lights off 2 20 Beacon on 2 30 Beacon off 2
248. ft flight envelope This envelope is defined by pitch roll and airspeed This feature is only active when in flight and the autopilot is off There are two versions of the ESP option available ESP with Angle of Attack AOA modes and ESP without Angle of Attack AOA modes The ESP option with AOA modes requires a new lift computer The ESP option without AOA modes uses the existing lift computer Underspeed Protes n Underspeed Protection USP is available when the optional ESP system is installed and the autopilot is on It is designed to discourage aircraft operation below minimum established airspeeds When the aircraft decelerates to stall warning the autopilot will provide input causing the aircraft to pitch down and G1000 700 System Maintenance Manual 200 B200 Series King Air Page 2 1 190 00915 01 Revision 9 wings to level The pitch down force will continue until the aircraft reaches a pitch attitude at which IAS equals the IAS at which stall warning turns off plus two knots 21 2 GDU 1040A PFD 2 amp GDU 1500 MFD Two Garmin GDU 1040A displays and one GDU 1500 display are installed in the King Air instrument panel The GDU 1040A units 10 4 inch LCD displays with 1024x768 resolution are configured as PFD 1 and PFD 2 the GDU 1500 unit a 15 inch LCD display with 1024x768 resolution is configured as a MED All displays provide control and display of nearly all functions of the G1000 integrated cockpit system The
249. fy the clutches are engaged and resist movement of the control wheel Press and hold the CWS switch and verify the control wheel moves freely when moved manually Verify the green at the top of PFD1 and PFD2 is replaced by a white CWS 6 Release the CWS switch and press the AP YD DISC TRIM INTRPT switch on the pilots control wheel Verify the autopilot disengages with a flashing amber annunciation on PFD1 and PFD2 accompanied by an aural alert Verify that the control wheel is free in pitch and roll axes 7 Engage the autopilot again by pressing the key on the AFCS mode controller Open AFCS SERVOS circuit breaker Verify the autopilot disconnects and the abnormal disconnect is provided consisting of a continuous aural alert and a flashing red white annunciation Verify no AFCS annunciations e g AFCS PFT Mistrim remain on PFD1 or PFD2 Press the AP YD DISC TRIM INTRPT switch to cancel the abnormal alert Close the AFCS SERVOS circuit breaker to restore power to the system and wait for completion of the pre flight test sequence 8 Engage the autopilot again by pressing the AP key on the AFCS mode controller Ensure the autopilot is coupled to GIA by verifying the arrowhead next to key on the AFCS mode controller is pointing to the pilot s side If the arrowhead points to the copilot s side press the key Open GIAI primary and secondary circuit breakers Ver
250. gh speed Too Low Gear voice TAWS Caution alert GPWS mode 4A B Flight into terrain gear not extended Too Low Flaps voice TAWS Caution alert GPWS mode 4B Flight into terrain flaps not extended Sink Rate voice TAWS Caution alert GPWS mode 1 Excessive Descent Rate Pull Up voice TAWS Warning alert GPWS mode 1 or 2 Excessive Descent Rate Or Excessive Closure Rate Don t Sink voice or Too Low Terrain voice TAWS Caution alert GPWS mode 3 altitude loss after takeoff or go around Glide Slope voice or Glide Path voice TAWS Caution alert GPWS mode 5 Glide Slope Path deviation Five Hundred voice or Four Hundred voice or Three Hundred voice or Two Hundred voice or One Hundred voice TAWS voice callout GPWS mode 6 voice callout as appropriate per altitude aution Obstacle Caution Obstacle voice or Obstacle Ahead Obstacle Ahead voice TAWS Caution alert Reduced required obstacle clearance Or Imminent impact with obstacle Obstacle Obstacle Pull Up Pull Up voice or Obstacle Ahead Pull Up Obstacle Ahead Pull Up voice TAWS Warning alert Imminent impact with obstacle A System Failure voice TAWS status alert Terrain failure AWS Not Available voice Terrain not available TAWS System Test OK voice If passed
251. ghlight the BEFORE CALIBRATION window 8 Follow the checklist items displayed the PFD and press the ENT key as each step is completed or confirmed 9 When the CALIBRATE field is blinking press the ENT button to begin the procedure 10 After several seconds a new checklist appears in the lower half of the PFD Press the ENT key as each step is confirmed When the CONFIRM AIRCRAFT IS LEVEL field is blinking press the ENT key to continue 11 The result of the pitch roll offset compensation is displayed on the PFD If successful the AHRS records the required pitch and roll offsets informs the operator of a successful conclusion and returns to normal operation 12 Press the ENT key on the PFD to conclude this procedure for GRS 1 13 Repeat steps 1 through 13 for GRS 2 with PFD 2 Page 7 20 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 7 3 Compass Rose Evaluation of Magnetic Disturbances for Magnetometer Calibration Procedure Optional NOTE The Magnetometer Calibration Procedure that follows in Section 7 7 4 Calibration Procedure B must be carried out at a site that is determined to be free of magnetic disturbances If it is unsure whether the site is clean the technician should verify that the site is clean by following the guidance provided in Section 7 7 3 The technician may skip Section 7 7 3 if the site condition is acceptable Typically a compa
252. he following e Green PASS in the Configuration and Software columns for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor Page 3 50 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 33 ESP Support no AOA Option Configuration This section applies only to installations with the ESP option without AOA modes available in software version 0985 04 and later The original Safe Flight lift computer is used for this configuration The procedures outlined in this section must be followed to load the necessary configuration files required to enable ESP messages and functions An Enhanced AFCS unlock card is also required for this option see Section 3 44 Coordinate this configuration with Section 7 26 ESP Functional Check NOTE If the ESP Support with AOA Option Configuration was previously loaded see Section 3 32 the baseline configuration must be reloaded before proceeding with this procedure Reload the baseline configuration for the specific airframe and all applicable options as described in Section 3 9 Reloading the baseline configuration disables all previously enabled options 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob PFDI 2 Activate cursor and rotate
253. he G1000 system is now powered in the normal mode In the normal operating mode data fields that are invalid have large red X s through them A valid field does not display a red X Allow the displays to initialize for approximately one minute The GDC 74Bs requires a longer initialization period than do the other LRUs During normal operation this causes the airspeed altitude vertical speed and OAT fields to be invalid during the first 40 60 seconds of PFD power up The PFDs and MFD will function as specified in the G1000 200 B200 Series Cockpit Reference Guide when the system has been correctly installed and configured Figure 3 7 Normal Mode G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 5 190 00915 01 Revision 9 3 6 Reversionary Mode Reversionary mode allows for display of information related to safe flight in the event of a display communication or hardware failure For software version 0985 04 and later the pilot s PFD automatically goes into reversionary mode when communication to the MFD is lost Manual reversionary mode allows the operator to force the pilot or copilot s PFD into reversionary mode by pressing the large red button labeled DISPLAY BACKUP on the respective GMA 1347D audio panel NOTE When the DISPLAY BACKUP button is pushed to exit reversionary mode there is a 5 second debounce or the GDU waits for 5 consecutive seconds and then returns to normal mode if no
254. he PFD press the ALERTS softkey on the PFD to view the Alerts Window Table 5 2 SVS Related Alert Messages Solution Geographical operation limitations are defined in the AFMS listed in Table 1 2 Ensure that operations are within this geographic area SVS is disabled because the aircraft exceeded the boundaries of the loaded terrain database SVS SVS DISABLED Terrain DB resolution too low Ensure the P N 010 00330 43 Terrain Cards are installed in the lower slot of each display If terrain data has been recently updated ensure that the correct 9 Arc Second databases were used SVS is disabled because a 9 Arc Second or better database is not currently loaded Page 5 30 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 5 5 1 General Troubleshooting The following annunciations may appear in the AFCS Annunciation field Table 5 3 AFCS Annunciation Troubleshooting Annunciation Condition AFCS System Failure Confirm Servos circuit breaker IN Ensure that the G1000 system is in proper working order Check that no red X s are present on the MFD and PFD Check that no related alert messages are present on the lt Go to the AUX SYSTEM STATUS page on the MFD and In Configuration mode review 700 equipment Reload software configuration and certification gains to the Check the
255. he aircraft to a properly calibrated compass rose At the compass rose align the aircraft to a heading of magnetic north 5 CAUTION Calibration Procedure B must be carried out on a compass rose in order to guarantee measurements free of environmental magnetic disturbances Attempting to carry out this maneuver on a typical ramp area may not yield a successful calibration The accuracy of the AHRS cannot be guaranteed if this calibration is not performed on a magnetically clean compass rose or equivalent If the compass rose condition is not known it is recommended that the technician follow the guidance in Section 7 7 3 NOTE This procedure provides instructions for calibrating both GRS AHRS separately It is acceptable to calibrate both GRS AHRS simultaneously by putting both PFD 1 and PFD 2 in configuration mode and following the procedure below using PFD 1 to calibrate GRS 1 and PFD 2 to calibrate GRS 2 Restart PFD 1 in configuration mode Go to the GRS Page Group on the PFD Select the GRS GMU Calibration page and enter the following softkey password 9 10 e 1 12 far right softkey Use the FMS small knob to highlight GRS for calibration and press the ENT key The SELECT PROCEDURE field is not blinking Using the FMS small knob select MAGNETOMETER Press the ENT button Use the cursor to highlight the BEFORE CALIBRATION window Follow the checklist items displayed on the PFD and press the ENT key as each one i
256. he airplane 3 Remove the center aisle floorboards and covers as necessary to gain access to the power distribution panel A145 4 Remove the left isolation limiter F131 5 Apply external power Turn BATT and AVIONICS MASTER switches to ON position 6 Bus voltage SHOULD be present on the right isolation bus W109 Verify that the GDL69 FAIL alert message is NOT shown on the PFD Operation of the GDL 69A verifies continuity of the right isolation limiter F132 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 39 190 00915 01 Revision 9 7 By observing the following annunciators power to each of the four buses will be verified L FUEL PRESS R FUEL PRESS L BL AIR FAIL and R BL AIR FAIL If any of the annunciators fail to illuminate the associated limiter F148 F149 F150 or F154 one of the four dual bus feeder diodes CR2 or dual bus circuit breakers RH NO 1 RH NO 2 RH NO 3 or RH NO 4 is open If failure of an annunciator is apparent reset or replace the faulty component and repeat the test 8 Units on the No 1 avionics bus SHOULD NOT operate Verify COM 2 is not powered by observing red X is displayed in COM 2 tuning window If COM 2 is powered at least one of the dual bus feeder diodes is shorted Detection of the shorted diode diodes may be accomplished by opening the following dual bus feeder circuit breakers LH NO 1 LH NO 2 LH NO 3 or LH NO 4 After replacement of t
257. he pitot static test set to simulate an airspeed of 95 kts for ADCI and 85 kts for ADC2 Verify the autopilot does not disconnect and amber comparator window text IAS 5 is displayed on PFD 1 and PFD2 12 Reduce ADCI and ADC2 airspeeds to 0 kts 13 Slowly rotate AHRSI along the lateral pitch axis to a pitch attitude of greater than 5 degrees verify the following AHRS2 pitch attitude does not change An amber PIT MISCOMP is annunciated PFD1 and PFD2 Autopilot disconnects at approximately 5 deg AHRS1 AHRS2 miscompare The autopilot disconnect audio alert two hi low tones sounds red flashing AP annunciator on PFDI and PFD2 Flight director command bars remain in view with autopilot in HDG and ALT mode G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 33 190 00915 01 Revision 9 14 Replace AHRSI to normal attitude and verify that attitude display on PFD1 displays current aircraft attitude 15 Use the AFCS mode controller to re engage autopilot 16 Slowly rotate AHRSI along the longitudinal roll axis to a roll attitude of greater than 5 degrees verify the following AHRS2 roll attitude does not change An amber ROL MISCOMP is annunciated on PFD1 and PFD2 e Autopilot disconnects at approximately 5 deg AHRS1 AHRS2 miscompare e The autopilot disconnect audio alert two hi low tones sounds red flashing annunciator on PFD1 and PFD2
258. he shorted diode diodes the test should be repeated 9 Remove all electrical power from the airplane 10 Reinstall the left isolation limiter F131 Remove the right isolation limiter F132 11 Apply external power Turn BATT and AVIONICS MASTER switches to ON position 12 Bus voltage SHOULD be present on the left isolation bus W108 Units on the No 1 avionics bus SHOULD operate Verify COM 2 is powered by observing a frequency is displayed in COM 2 tuning window Operation of COM2 will verify continuity of the left isolation limiter F131 13 By observing the following annunciators power to each of the four buses will be verified L FUEL PRESS R FUEL PRESS L BL AIR FAIL and R BL AIR FAIL If any of the annunciators fail to illuminate the associated limiter F145 F146 F147 or F153 one of the four dual bus feeder diodes CR1 or dual bus circuit breakers RH NO 1 RH NO 2 RH NO 3 or RH NO 4 is open If failure of an annunciator is apparent reset or replace the faulty component and repeat the test 14 The GDL 69 SHOULD NOT operate Verify that the GDL69 FAIL alert message IS shown on the PFD If the GDL 69A DOES operate at least one of the dual bus feeder diodes CR2 is shorted Detection of the shorted diode diodes may be accomplished by opening the following dual bus feeder circuit breakers LH NO 1 LH NO 2 LH NO 3 or LH NO 4 After replacement of the shorted diode diodes the test should be repeated 15 Re
259. heading Simulate a Localizer Glideslope signal Tune this signal on NAV 1 and NAV 2 receiver Set the PFDI HSI to LOCI and PFD2 HSI to LOC2 by pressing CDI soft key until and LOC2 is selected Use the test equipment to center the deviation bars localizer and glideslope on PFD1 and PFD2 Press the APR key on the AFCS mode controller Verify that the LOC and PIT annunciations are green and ALTS and GS are white on PFDI and PFD2 Apply right left and up down localizer glideslope signals using the test equipment Verify that the Flight Director and flight controls respond appropriately Couple FD to PFDI by pressing the XFR button on the AFCS mode controller Verify FD is coupled to PFD1 as indicated by a left pointing arrow on the AFCS mode controller next to button Repeat step 9 while coupled to PFDI If no other service is to be performed continue to the return to service checks in Section 8 Page 7 8 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 4 GEA 71 Engine Airframe Unit Original GEA 71 Reinstalled No software or configuration loading is required if the removed GEA 71 is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the return to service checks in Section 8 Original GEA 71 Installed in Opposite Locations for Troubleshooti
260. her GIA 63W Continue to Section 8 2 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 8 9 190 00915 01 Revision 9 8 222 AFCS Switch Checks Verify that the AFCS system buttons and switches are operating correctly by performing the following l Actuate both sections of the PITCH TRIM NOSE UP NOSE DN switch to activate Manual Electric Pitch Trim MEPT Verify the trim clutch engages and the trim wheel drives in the requested direction Check operation in both the up and down direction 2 Press the AP YD DISC TRIM INTRPT switch and hold while actuating the manual electric trim switch Verify trim does not run and the trim wheel rotates freely when moved manually Release the AP YD DISC TRIM INTRPT button and PITCH TRIM switch 3 Engage the autopilot by pressing the AP key on AFCS mode controller Press and hold the left section of the manual electric trim switch Verify the Autopilot disengages normally with an aural alert and the trim wheel rotates freely when moved manually 4 Engage the autopilot again by pressing the AP key on the AFCS mode controller Verify the pitch and roll clutches engage and resist movement of the control wheel Press and hold the CWS switch and verify the control wheel moves freely when moved manually Verify the green at the top of PFD1 and PFD2 is replaced by a white CWS 5 Release the CWS switch and press the key on the AFCS mode controller Veri
261. ht Deck via the GDL69A using HSDB The GDL 59 is located in the aft cabin floor area just forward of the cabin door or on the upper avionics equipment shelf in the tail section The GDL 59 is powered from the Avionics No 2 bus Figure 2 13 GDL 59 Wi Fi Datalink G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 9 190 00915 01 Revision 9 2 1 15 GSR 56 Satellite Receiver optional The GSR 56 provides airborne low speed data link and voice communication capability to Garmin Integrated Flight Deck installations The GSR 56 contains a transceiver that operates on the Iridium Satellite network The GSR 56 interfaces directly to the GDL 59 via an RS 232 interface or may be installed as a stand alone unit with an interface to GIA 1 The GSR 56 is located in the aft cabin floor area just forward of the cabin door or on the upper avionics equipment shelf in the tail section The GSR 56 is powered from the Avionics No 2 bus With relocation to the tail section the GSR 56 has an internal heater powered from the Avionics No 2 bus Figure 2 14 GSR 56 Satellite Receiver 2 1 16 GTS 820 850 Traffic System optional The GTS 820 850 is a traffic surveillance system that uses active interrogation of Mode S and Mode C transponders to provide traffic advisories to the pilot The GTS 820 is a TAS unit the GTS 850 is a TCAS I unit The installation includes a top directional antenna GA 58 paired with a GPA 65 power ampl
262. ibration Section 7 7 4 New Repaired or Exchange GMU 44 is Installed If a new repaired or exchange 44 is installed then software must be loaded Continue to Section 3 9 for software loading then continue to the GRS GMU Calibration Procedures Section 7 7 1 Page 7 18 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 77 1 GRS GMU Calibration Procedures GRS GMU Recalibration Criteria The following calibration procedures are provided for the GRS and GMU 44 Pitch Roll Offset Procedure Al PROVIDED IN SECTION 7 7 2 Magnetometer Calibration Procedure B PROVIDED IN SECTION 7 7 4 e Engine Run Up Vibration Test Procedure D PROVIDED IN SECTION 7 7 5 Magnetometer Interference Test Procedure E PROVIDED IN SECTION 5 15 4 Follow the steps given for each procedure on screen at the GRS GMU CALIBRATION page Note that the CALIBRATE command cannot be selected and activated until the installer acknowledges all required steps have been carried out by pressing the ENT key on each step Table 7 7 Required GRS GMU Calibrations Condition Either GMU 44 was removed and reinstalled no change in serial number Calibrations Required Procedure A1 GRS 77 or GRS 7800 Pitch Roll Offset Continue to GRS GMU Test section Procedure B GRS GMU Magnetic Calibration None Required Procedure D Engine Run up Vibration Test GMU 44 was rep
263. icated airspeed of 200 knots with the static system vented to ambient pressure conditions ground Pitot leak rate is not to exceed 1 knot in 1 minute b Forthe static leak check set the air data test set to 30 000 feet and an indicated airspeed of 120 knots Static leak rate is not to exceed 300 feet in 1 minute 2 Connect the pitot static tester to the aircraft left and right pitot and static ports Note that the standby altimeter and airspeed indicator are connected to the copilot side pitot and static lines G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 13 190 00915 01 Revision 9 8 9 Verify that the PFD1 altimeter baro setting is set to 29 92 in Hg 1013 25 mb Start PFD1 in configuration mode and navigate to the GRS page The values for altitude and airspeed are shown on the AHRS AIR DATA INPUT table as B ALT and IAS for both AIR DATA and AIR DATA 2 Simulate the altitudes and airspeeds for each condition shown in Table 7 5 Wait for ADTS to report that target values have been achieved On Table 7 5 record the altitude ALT displayed on PFD1 for AIR DATA 1 and AIR DATA 2 for each condition On Table 7 5 record the airspeed IAS displayed PFD1 for AIR DATA 1 and AIR DATA 2 for each condition Verify that the indicated altitudes and airspeeds are within allowable tolerances File the results with the aircraft maintenance records If either the pilot or copilot air data system
264. ific Alerts The following alerts are configured specifically for the King Air 200 B200 installation ANNUNCIATION ADVISORY Alerts Message Advisory TAWS GEAR FAULT Landing Gear detected in the DOWN position Solution Check the gear down wiring input to the GIAs Refer to G1000 GFC 700 Wiring Diagram listed in Table 1 2 TAWS FLAP FAULT Flaps detected in the LDG position e Check the flap full down wiring input to the GIAs Refer to G1000 GFC 700 Wiring Diagram listed in Table 1 2 WOW Invalid e Ensure that the GIA1 PRI and SEC and GIA2 circuit breakers are closed Check weight on wheels switch inputs to GIA1 and GIA2 Refer to G1000 GFC 700 Wiring Diagram listed in Table 1 2 WOW Fault lt Ensure that the GIA1 PRI and SEC and GIA2 circuit breakers are closed Check weight on wheels switch inputs to GIA1 and GIA2 Refer to G1000 GFC 700 Wiring Diagram listed in Table 1 2 1 FAN FAIL Avionics cooling fan 1 is inoperative 2 FAN FAIL Avionics cooling fan 2 is inoperative PFD 1 FAN FAIL PFD 1 cooling fan is inoperative PFD 2 FAN FAIL PFD 2 cooling fan is inoperative MFD FAN FAIL MFD cooling fan is inoperative e Ensure that the PFD GIA FAN LEFT and RIGHT and MFD FAN circuit breakers are closed Check cooling fan wiring Refer to G1000 GFC 700 Wiring Diagram listed in Table 1 2 Replace cooling fan Refer to Sec
265. ifier low noise amplifier PA LNA unit and a bottom unamplified GA 58 antenna The GTS 820 850 is located in the nose avionics bay on the top left shelf The GPA 65 is located in the left sidewall area just in front of the most forward cabin window The GTS 820 850 traffic system is powered from the Avionics No 2 bus Figure 2 15 GTS 820 850 Traffic System 2 1 17 GTS Traffic Processor The GTS Traffic Processor is a microprocessor based Line Replaceable Unit that uses active interrogations of Mode 5 and Mode A C transponders to provide Traffic Advisories and Resolution Advisories GTS 8000 only to the pilot When installed the GTS Processor can be configured as TAS GTS 825 TCAS I GTS 855 or TCAS II GTS 8000 The GTS traffic processor is installed in the nose avionics bay The GTS interfaces to the GASS traffic antennas which are mounted on the upper and lower fuselage The GTS traffic processor also interfaces with the GTX 3000 through ARINC 429 digital data lines The GTS traffic processor is powered from the Avionics No 2 Bus Page 2 10 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 Figure 2 16 GTS Traffic Processor 2 1 18 Weather Radar The GWX 68 or optional GWX 70 Airborne Weather Radar provides weather radar data output to the GDU 1500 MFD The GWX is mounted forward of the forward bulkhead at F S 30 Power to the GWX is received from the Avionics No 1 bus Data
266. ify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor 3 29 1 GRA Software Installation 1 Goto www garmin com and click on the Dealer Resource Center link in the lower portion of the home page Enter username and passwoi Sign In Username 9 g username mail com Password Ey signing in you agree to the Garmin Confidentiality Agreement 2 Select Technical Tools then select Software Downloads 3 Inthe Keyword s filter enter GRA and click on the Go button 4 A screen similar to the one shown below will appear The numbers shown are for example only G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 43 190 00915 01 Revision 9 Software Downloads Fiterino Options Al lets Subeatogoy 1 Fiter by Market 5 Show AllResulis DateRange e Gne 23 documents found Displaying 10 document s iom 11910 ResutsPerPaue Save Name Type DociD Publish Date GRA 5500 Sensor System Sofware Version Software Updates Jul 25 2013 B 205 a GRA 5500 Stem Sofware Version Software Updates Jule 2013 g 205 a 5 Click on the download symbol for the appropriate Sensor and Main software version part numbers based upon the inf
267. ify the autopilot disconnects with a continuous aural alert and a flashing red white AP annunciation Press the AP YD DISC TRIM INTRPT switch to cancel the alert and annunciation Close the GIAI primary and secondary circuit breakers and wait for completion of the pre flight test sequence 9 Press XFR key on the AFCS mode controller and engage the autopilot by pressing the key on the AFCS Mode Controller Press the AP YD DISC TRIM INTRPT switch on the pilot side to disconnect the autopilot verify the flashing amber alert is displayed on PFD1 and PFD2 10 Press the GO AROUND button on the left throttle Verify is annunciated on PFD1 and PFD2 for both PITCH and ROLL modes and the command bars should be at 8 degrees nose up and wings level 11 Press the Flight Director FD key on the AFCS mode controller to deactivate the GA mode Press the AP key to engage the autopilot Press the CWS button for a minimum of 5 seconds and release verifying there is no residual force on the control stick for the pitch axis 12 Disengage the autopilot by pressing the AP YD DISC TRIM INTRPT switch on the co pilot s control wheel Engage VS mode by pressing the VS key on the AFCS mode controller Verify PFD1 and display VS in green and indicates a pitch reference of 0 FPM 13 Press FLC key on the AFCS mode controller and verify that FLC is annunciated on PFD1 and PFD2 in green with a refe
268. iguration module 1 in position 3 Insert connector into configuration module 1 4 Assembly of the connector is the reverse of disassembly Page 6 10 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 Continue to Section 6 16 3 6 16 2 GRS 7800 Configuration Module Removal amp Replacement The GRS 7800 configuration module is located on the LRU harness connector strain relief Refer to the Master Drawing List listed in Table 1 2 for specific installation drawings 3 2x WASHERS RING TERMINALS Figure 6 3 GRS 7800 Configuration Module Installation Table 6 2 GRS 7800 Configuration Module Parts Item Description Qty Needed Part Number Vendor 4 Configuration Module Circular Connector 1 011 02582 00 Garmin 5 Socket Contact 4 M39029 56 348 Best Source Removal 1 Disconnect connector 1 from LRU 2 Remove2 screws 3 washers ring terminals and configuration module 4 from strain relief 2 3 Disconnect the strain relief 2 from the connector 1 4 Remove the 4 configuration module contact pins from the connector 1 5 Remove the configuration module 4 Installation 1 Inspect connector 1 for damaged pins Install 4 contact pins 5 on the new configuration module 4 wires Install the 4 configuration module contact pins 5 into the connector 1 Assembly of the connector and strain relief is the reverse of the disassembly
269. in Table 1 2 4 Engage the autopilot by pressing the AP key on the AFCS mode controller Actuate and hold the manual electric trim switch in either the up or down direction to disconnect the autopilot Verify that the trim wheel moves smoothly in both directions throughout the entire trim range during manual electric trim operation If the trim wheel hesitates this may indicate that the pitch trim clutch is slipping and proper clutch setting or clutch cartridge and cable tension should be verified Refer to the King Air 200 Series Maintenance Manual and Pitch Trim Servo Install drawing listed in Table 1 2 for clutch settings and cable tensions If both clutch setting and cable tension are within tolerance check the aircraft pitch trim system for excessive friction Refer to the King Air 200 Series Maintenance Manual listed in Table 1 2 8 2 4 Manual Electric Pitch Trim Speed Check 1 Run MANUAL ELECTRIC PITCH TRIM in one direction until it runs against the mechanical stop 2 Run the trim in the opposite direction and using a stop watch or equivalent device time the trim speed to the opposite mechanical stop Verify the elapsed time for full travel measures 13 3 seconds G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 8 11 190 00915 01 Revision 9 8 2 5 Autopilot Operation Checks NOTE For aircraft with software version 0985 03 and the Electronic Stability and Protection ESP option an airspeed of 200 kn
270. in Table 1 2 4 Reinstall cabin interior ceiling panel 5 Test the GTS 820 850 or GTS Processor per Section 7 27 6 33 GDL 59 Wi Fi Datalink Removal 1 Gain access by removing the cabin center floor panel at the main entry door 2 Detach the two rack mount angles from the remote equipment shelf Retain all mounting hardware 3 Remove the Philips head screw which holds the locking lever down 4 the locking lever up to unlock the unit from the mounting rack 5 Remove the unit from the mounting rack Reinstallation 2 4 Visually inspect the connectors to ensure there no bent or damaged pins Repair any damage Insert the unit into the installation rack Do not use excessive force when inserting the GDL 59 into the rack This may cause damage to occur to the connectors unit and or unit rack If heavy resistance is felt during installation stop Remove the GDL 59 and identify the source of resistance rear plate is designed to float in the unit rack Check to ensure the rear plate is not bound by the connector harness Lock the GDL 59 in place using the lever locking handle Fasten the handle to the GDL 59 body using the provided Phillips screw CAUTION Start the handle screw into the hole carefully to avoid cross threading Do not apply torque in excess of 14 in Ibs to the handle screw The application of torque exceeding 14 in Ibs to this screw will damage the LRU case and or retaining hardware Rei
271. in Table 1 2 Pay particular attention to possible areas of chafing such as the middle shelf feed through hole wheel well protrusion etc _ Inspect Ground blocks for security of attachment corrosion or other defects d Ensure connectors are securely fastened Page 4 12 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Table 4 5 Pilot s Compartment Visual Inspection Procedure Item Description Procedure Initials Locate equipment in the aft pedestal for the following inspection Inspect the GCU 477 unit and connector for corrosion or other defects Check the GCU 477 integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment a Inspectthe ADF control unit and connector for corrosion or other defects Check integrity of the SHIELD ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment ADF control unit relocated by STC Inspect visible wire harness for chafing damage proper routing of wire bundles Pedestal Wiring and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Cabin Wire Harness Routing drawing listed in Table 1 2 a Inspect the GTP 59 units and connectors for corrosion or other defects Check the integr
272. ing the 28 VDC AP DISC power switch open or other fault MONITOR CONTROL BOARD STATUS Shows the condition of various monitor board components SERVO PROGRAM 1 3 Servo program discretes are used to determine the HW strapping for each GSA to define the servo type This information can be cross referenced against the system interconnects to verify proper servo grounding AP DISCONNECT Same as GIA Status Indicates whether the pre flight test has passed or failed HIGH RES amp HIGH RNG LOAD CELL CAL Shows the condition of the high resolution and high range load cells on the monitor board If box is black this indicates a corrupt or missing load cell calibration return the servo to Garmin DRIVE SERVO Allows the technician to enter a desired RPM at which to manually drive the selected servo Direction of rotation is controlled by the polarity of the RPM or After the speed is entered the technician may use the ENG CLCH and DRV SRVO sofikeys to drive the servo NOTE Be especially certain that the flight controls are clear and safe to operate before manually driving the servo Page 5 34 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 SERVO DATA Shows real time reported data including servo voltage speed motor current load cell torque and clutch solenoid status A green box indicates the servo clutch is engaged SLIP CLUTCH TEST RESULTS This window is used d
273. installed use two MS3367 7 1 cable ties through the retained phenolic wire guard to secure the guard and connector harness to the GMU 4 Ensure the MS35489 4 grommet is installed on the unit pigtail harness and secured in the slot in the aft side of the GMU adapter plate assembly 5 Use the orientation marks on the GMU adapter plate assembly to align the adapter plate assembly to the flux mounting dish and reinstall the three screws washers attaching the adapter plate 6 Ensure there is a gap of at least 0 2 inch between the unit pigtail harness and the flux valve access cover 7 Reinstall the screws and flux valve access cover on the upper side of horizontal stabilizer 8 Connect the GMU pigtail harness to the electrical wiring harness 9 Reinstall the inspection access panel second from inboard on the lower side of the horizontal stabilizer 10 Calibrate and test the GMU 44 according to Section 7 7 Page 6 6 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 6 10 GDL69A Removal 1 Gain access by removing the right side GDU 1040A display unit see Section 6 1 2 Unlock the GDL 69A handle by loosening the Phillips screw on the handle 3 Pull the handle upward to unlock the GDL 69A Gently remove the unit from the rack Reinstallation Visually inspect the connectors to ensure there are bent damaged pins Repair any damage 2 Gently insert the GDL 69 i
274. inued Airworthiness 4 1 Airworthiness Limitations The G1000 Integrated Flight Deck including the GFC 700 AFCS is airworthy when installed configured and maintained in accordance with this section The G1000 and GFC 700 systems possess the following maintenance airworthiness limitations The intervals for the airworthiness limitations are shown in maximum number of hours between checks as required for certification Table 4 1 aligns these requirements with the King Air Phase Inspection Program These limitations were derived from the certification data GFC 700 Limitations Every 220 hours perform a Trim Annunciator Check per Section 4 12 e For installations with the GSM 85A Servo Gearbox every 420 hours perform a GSM 85 Slip Clutch Torque Check per Section 4 9 e For installations with the GSM 86 Servo Gearbox every 3 000 hours perform a GSM 86 Slip Clutch Torque Check per Section 4 9 1000 Limitations Every 220 hours perform a Weight on Wheels and Low Speed Awareness Band Check per Section 7 23 e Every 220 hours perform G1000 Redundant Connection Check per Section 4 10 For aircraft equipped per MDL 005 00421 00 Rev 15 or previous revisions and not modified Garmin Service Bulletin 1375 Every 220 hours perform a G1000 Cooling Fan Fail Annunciation Check per Section 8 1 4 See Note 1 e Every 620 hours perform a Power Bus Feeder Check per Section 4 17 1 e For aircraft equipped per MDL 005 00421 00 Re
275. ion 1 Reinstallation of the Sandia GDU cooling fan is the reverse of the removal Reference the Main Instrument Panel Installation drawing listed in Table 1 2 for more details 2 Iffurther maintenance is not required proceed to Section 8 6 30 GTS 820 850 Traffic Unit CAUTI After any maintenance or modification is made to the GTS 820 850 TAS TCAS cables such as replacing a connector or entire cable be sure to adhere to all of the specifications and limitations such as minimum and maximum cable attenuation attenuation balance between cables phase matching etc Removal 1 Gain access to the left forward avionics compartment in the nose of the aircraft 2 Disconnect the eight coax quick lock connectors 3 Disconnect the three electrical connectors 4 Unlock the unit from the rack by loosening the ratcheting latch mechanism 5 Remove the unit from the rack Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage Insert the unit into the installation rack Lock the unit into the rack by using the ratcheting latch mechanism Reconnect the eight coax quick lock connectors and the three electrical connectors Close access to the left forward avionics compartment Configure the GTS 820 850 per Section 3 12 and test per Section 7 27 d ET ak adil on 6 31 GPA 65 PA LNA Unit Removal 1 Remove cabin interior to access FS 158 at WL 119 on the left side of the fuselage
276. ion to provide power to the new Standby Instrument Bus and the new Essential bus Dual fed Buses The electrical distribution uses four individual dual fed buses referred through this document as Dual Fed No 1 Bus Dual Fed No 2 Bus Dual Fed No 3 Bus and Dual Fed No 4 Bus Each of these dual fed buses are powered from the Left and the Right Generator buses Avionics Buses The No 1 Avionics bus is powered from the Left Generator Bus via the Avionics No 1 relay The No 2 Avionics bus is powered from the Right Generator Bus via the Avionics No 2 relay Both Avionics relays are controlled using the Avionics Master Switch Left and Right Engine Instrument Buses On serial numbers BB 1484 1486 and subsequent the electrical system includes the L ENG INSTR and R ENG INSTR buses This STC relocates these two buses such that they are powered from Dual Fed Bus No and No 2 respectively Prior to these serial numbers these two buses are not installed and engine instruments are powered directly from the dual fed buses Figure 2 1 shows the system with these buses installed and relocated Essential Bus The Essential bus is a new bus added by this STC It is powered from Dual Fed No 1 bus and the Isolation bus Standby Instrument Bus The Standby Instrument bus is a new bus added by this STC It is powered by the Isolation bus and provides one source of power to the standby attitude indicator and standby altimeter vibrator Entertainment Bu
277. ir Revision 9 190 00915 01 17 Verify on PFD 1 and PFD 2 that there is an ESP OFF and for installations with AOA mode an ESP DEGRADE alert message ESP 29 ESP DEGRADE inoperctive 18 Remove the cover from both GPS1 and GPS2 antennas P AQA mode is 19 Remove power to the aircraft and avionics systems by placing the aircraft AVIONICS MASTER PWR and BATT switches to OFF 20 Wait 1 minute before re applying aircraft power 21 Apply power to the aircraft and avionics systems by placing the aircraft AVIONICS MASTER PWR and BATT switches to ON 22 During power up and GPS satellite acquisition verify PFD1 and PFD2 the ESP Roll Indices are displayed at 45 on the roll indicator on the Attitude Display 23 Once AFCS PFT is complete and GPS has acquired satellites verify on PFDI and PFD2 the ESP Roll Indices are not displayed at 45 on the roll indicator on the Attitude Display 24 On the GCU rotate the inner FMS knob to activate the AUX SYSTEM SETUP page G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 59 190 00915 01 Revision 9 25 On MFD AUX SYSTEM SETUP page press the SETUP 2 softkey 26 Verify that on the MFD SETUP 2 page there is a window for Stability amp Protection and the status is ENABLED status 27 Verify on PFD and PFD 2 that there are no ESP FAIL ESP OFF or ESP DEGRADE alert messages 28
278. ircraft maintenance records Manually select 0 00 rpm for the Drive Servo and press ENT Allow the servo to stop Firmly grasp the aircraft control under test and press the DIS CLCH softkey Press the STP SRVO softkey Repeat steps 2 through 18 for each servo axis shown Verify that the minimum and maximum torque values measured are within the Minimum and Maximum torque values allowed for the given axis listed in Table 4 10 Min Measured Max Measured Min Allowed Max Allowed Axis Direction Torque in Ibs Torque in Ibs Torque in ibs Torque in lbs 28 GSM 85A 38 GSM 85A 24 GSM 86 40 GSM 86 116 GSM 85A 161 GSM 85A 99 GSM 86 168 GSM 86 78 GSM 85 107 GSM 85A 66 GSM 86 112 GSM 86 52 GSM 85A 71 GSM 85A 45 GSM 86 76 GSM 86 Table 4 10 Measured Torque NOTE If the GSM 85A or GSM 86 measured values exceed the limits in Table 4 10 the servo gearbox must be removed from the aircraft and tested adjusted per the Servo Gearbox Adjustment Fixture Procedure in Section 4 9 3 Page 4 24 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 4 9 3 Servo Gearbox Adjustment Fixture Procedure This test is an alternative to the automated and manual slip clutch test procedures Only the GSM 85A servo gearbox slip clutch can be adjusted The GSM 86 servo gearbox does not have an adjustable slip clutch h
279. ircraft only This tool is available from Hawker Beechcraft Any alternate tool authorized in the King Air 200 Series Maintenance Manual for RVSM static port measurements may be substituted for this tool Refer to Chapter 34 10 00 of the King Air 200 Series Maintenance Manual for more details Page 4 4 Revision G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 9 190 00915 01 4 3 Maintenance Intervals Table 4 1 shows systems and items installed by this STC which must undergo tests or checks at specific intervals If the interval is shown to be in flight time as well as calendar months the first interval reached should be used as the limit The inspection time tables used for this STC are aligned with the existing maintenance 200 hr phase inspection program used in the current King Air 200 Series Maintenance Manual A complete inspection cycle for the King Air 200 B200 is 800 hours or 24 calendar months divided into the following four pha Inspection Phase 1 To be performed at 200 hours and every 800 hours thereafter Inspection Phase 2 To be performed at 400 hours and every 800 hours thereafter Inspection Phase 3 To be performed at 600 hours and every 800 hours thereafter Inspection Phase 4 To be performed at 800 hours and every 800 hours thereafter Those inspections that are based on flight time calendar elapsed time or cycles shall have specific intervals stated in Table 4 1 IMPORTANT As allo
280. is needed troubleshooting autopilot faults the Maintenance logs can be downloaded to an SD card as a text file txt and emailed to Garmin Aviation Product Support Please call Garmin Aviation Product Support before you send a Maintenance Log to notify them you are sending it to prevent a delay in response You may download multiple GIA and GSA Maintenance Logs to the same file however in your email to Garmin you must furnish the order in which they were downloaded i e GIA1 then GIA2 then SRVO PTCH MON then SRVO PTCH CTL etc Insert a FAT 32 formatted SD card into the top slot of the PFD before turning on the displays Power up PFD1 PFD2 and in the configuration mode On the PFDI in the System page group use the small FMS knob to scroll to the Diagnostics Terminal page Press the LG2CRD softkey at the bottom of the PFD1 Verify that the sofikey text grays out This indicates the recording function is active and all text that is displayed in the OUTPUT window will be saved to the card Enable the cursor by pressing the FMS knob select GIA1 in the LRU drop down menu and then press the ENT key to select it Skip the SERVO box and move the cursor to the COMMAND box and select View Maintenance Log in the drop down menu then press the ENT key The error log data will be displayed in the OUTPUT box If you see the more press any key to continue text at the bottom of the screen you may need to reselect
281. is not monitored A white N A box is normal GIA1 GTX 33 or GTX 3000 1 data path is functioning Green correctly GIA1 GTX 33 or GTX 3000 1 data path is not functioning correctly e Load GIAI and GTX 33 or GTX 3000 1 configuration files GTX e Swap GIAI and GIA2 reconfigure both GIA s to their new CHNL 5 33ES 3000 Red locations to confirm if the problem is in the original GIAI 1 w TIS o Replace original GIAI if box turns green after swapping units e Check the GIA1 GTX 33 or GTX 3000 1 interconnect wiring for faults Replace GTX 33 or GTX 3000 1 if problem remains GIA1 GTX 33 or GTX 3000 1 data path functionality is Amber unknown Reload GLAT configuration files G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 11 190 00915 01 Revision 9 RS 232 continued Channel LRU Indicator Status CHNL 6 GRS 77 or GRS 7800 1 Green GIAI GRS 77 or GRS 7800 1 data path is functioning correctly Red GIAT GRS 77 or GRS 7800 1 data path is not functioning correctly e Load GIAI configuration files e Swap GIAI and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIAI o Replace original GIAI if box turns green after swapping units e Swap GRSI and GRS2 no reconfiguration required to confirm if the problem is in the original GRS1 o Replace original GRS1 if box turns green afte
282. ition 8 Verify the STALL WARN circuit breaker on the copilot circuit breaker panel is set WARNING Make sure that all personnel are clear of the flap area before proceeding with these procedures 9 Flaps retracted calibration a Run the flaps to the FULL UP position G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 51 190 00915 01 Revision 9 b Using the force applicator deflect the transducer vane forward UP to the Pot 0 TG force measured in step 10 in Section 7 25 1 If the stall warning horn is already ON turn Pot 0 CCW until the horn is OFF and then slowly turn the Pot 0 CW until the horn is ON again Press down on the vane until the horn is OFF and slowly release the vane If the horn is not ON when the vane is released turn the Pot 0 until the horn is ON c Reduce the force on the vane to 0 TG and reposition the force applicator to apply a downward force on the vane d Calculate the Pot 3 TG force by adding 10 TG to the Pot 0 TG force Example If the Pot 0 force is 4 TG add 10 TG and the Pot 3 force is 6 TG e Install voltmeter leads between TP18 Lo and TP19 Hi of the SK100360 Breakout Box f Apply the calculated Pot 3 TG force to the vane with the force applicator g Adjust the Pot 3 on the lift computer until the voltage output from TP18 Lo and TP19 Hi reads 2 2 0 2 VDC on the voltmeter h Return the force on the force applicator to 0 TG
283. itude FT Airspeed K1 AIRDATA 1 AIR DATA2 An DATA 1 AIRDATA2 Nominal AL Altitude Tolerance Tolerance Tolerance Tolerance Li Actual Actual Actual Actual 29000 m m H2 a Ti 28999 29000 m en a 12 30 282 29000 m m H2 a 150 28967 29000 m n a 2 fool 28953 29000 m m H2 28946 29000 m m H2 a 28937 29000 m m H2 a 96 28028 35000 2787 a H2 a 35016 35000 2 87 EX H2 a i 549 35000 EX a H2 EE 34978 35000 87 187 2 a far 34961 35000 EX a H2 a se 34053 35000 87 187 2 2 oa 34946 35000 EX am H2 EE 191 34939 Aircraft S N Date Operator ADTS Make Model Model Model P N P N SIN SIN E Cal Date Cal Date Cal Date Leak Check Static System at 30 000 ft 300 kts pass if lt 300 ft in 1 min Pil Feet Min Copilot Feet Min Leak Check Pitot System at 200 kts pass if lt 1 KIAS in 1 min Pilot KIAS Min Copilot KIAS Min Page 7 16 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 7 6 2 Static Port Vertical Speed Rate of Climb Test 1 Command ADTS to change the altitude at the rates shown in the table below 2 Wait for ADTS to report that target rates have been achieved 3 Verify that the Rate of Climb reported by the Vertical Speed
284. ity of the SHIELD ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment b Inspect wire harness for chafing damage proper routing of wire bundles and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Cabin Wire Harness Routing drawing listed in Table 1 2 GTP 59 Qty 2 Inspect that all required placards are installed on the left and right control wheels Placards Placards must be legible secure and in good condition Refer to the Control Wheel Modification drawing listed in Table 1 2 Table 4 6 Instrument Panel G1000 Equipment Visual Inspection Procedure Initials Gain access to behind the instrument panel by removing the PFDs and MFD see below Gain access to circuit breaker panels by removing the screws which fasten the edgelit overlays to the panels Inspect the PFDs and MFD for any visual damage to the display screens or bezels including buttons and control knobs b Remove the MFD and PFDs as described in Section 6 GDU 1040A PFD c _ Inspect the mounting surface and connector for corrosion heavy oxidation or other Qty 2 amp GDU 1500 damage Check the integrity of the SHIELD BLOCK ground attachments to the MFD harness connector assembly as well as the integrity of the individual shields and their attachment d Do not reinstall GDUs at this time GDU cutouts provi
285. l aircraft and avionics systems to complete their initialization and begin operating normally Verify there are WOW INVALID or WOW FAULT messages Refer to Section 5 3 to troubleshoot messages Verify the Low Speed Awareness band red band is NOT displayed on PFD1 and PFD2 airspeed tapes see Figure 7 8 NOTE This portion of the check can be accomplished in conjunction with the Landing Gear Aural Alert and XM Audio Suppression Test in Section 7 2 2 Place the airplane on jacks Ref King Air 200 Series Maintenance Manual Chapter 7 00 00 with the wheels clear of the ground Verify there are no WOW INVALID or WOW FAULT messages Refer to Section 5 3 to troubleshoot messages Verify the Low Speed Awareness band red band appears at the low end of the Air Speed Tape on the PFDI and PFD2 see Figure 7 8 Remove airplane from jacks If no other service is to be performed continue to the return to service checks in Section 8 Figure 7 8 Low Speed Awareness Band Symbolization Page 7 42 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 24 7 24 1 RVSM Checks The following are required initial and continued airworthiness checks to verify proper configuration for operation in RVSM airspace RVSM operations are prohibited until the all of the RVSM checks are completed successfully Any changes to the aircraft external configuration such as the installation of addition
286. l change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number l The entire G1000 system must be re configured Insert the correct G1000 software loader card into PFD 1 2 Start the G1000 in configuration mode Go to the System Upload Page on PFD 1 3 See Section 3 9 for instructions on how to use the System Upload page Check all configuration files and reload them 4 After reloading configuration files examine the G1000 installation for any installed configuration options Options are listed in Section 3 9 Load optional files as necessary 5 Continue to Section 8 and conduct the return to service checkout Page 6 12 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 6 17 71 Backshell Thermocouple Removal amp Replacement The GEA 71 has a K Type thermocouple Item 1 shown below installed its backshell in addition to the configuration module The thermocouple is used in conjunction with the configuration module temperature sensor to compensate for temperature probe errors resulting from the dissimilar metals at the pin contacts Figure 6 4 GEA Backshell Thermocouple Table 6 3 Thermocouple Kit 011 00981 00 Item Desc Qty Needed Garmin Part Number 1 3 Thermocouple K type 1 925 L0000 00 2 Pins 22 AWG 2 336 00021 00 3 Screw 1 211
287. l quality is adequate Verify communication between GSR 56 and the display control device Verify subscription with Garmin Connext reference Section 7 28 5 28 GTS 820 850 Troubleshooting Problem Cause Solution Unit does not power up Data failed message Improper wiring circuit breaker open Ensure power is properly wired to the GTS 820 850 and the TRFC circuit breaker is closed Improper configuration Verify that the GTS 820 850 is configured correctly for the desired display Traffic Display erroneously indicates TA at own ship position Suppression bus fault Check the mutual suppression line to ensure it is connected to the correct pins at the GTS 820 850 as well as the installed transponder Ensure there are no fractures in the wire and that the suppression line is functioning properly No Audio alerts Improper wiring Volume not set correctly Ensure the audio is properly wired from the GTS 820 850 and volume is not set too low Calibration Fault Factory calibration invalid If the unit fails to go into operate mode then return to Garmin for service Configuration Fault Both internal and external configuration checks failed Verify the configuration Verify wiring to the configuration module and replace if necessary FPGA Fault Internal Fault Return to Garmin for service ROM Fault Internal Fault Return to Garmin for service
288. laced with new unit New serial number x GRS AHRS was removed and or replaced The mounting tray was NOT removed and the mounting tray bolts were NOT loosened Continue to GRS GMU Test section None Required GRS AHRS was removed and or replaced The mounting tray WAS removed and or mounting tray bolts WERE loosened x x x GRS AHRS Configuration Module was replaced x x x G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 19 190 00915 01 Revision 9 77 22 Procedure 1 GRS 77 or GRS 7800 Pitch Roll Offset Calibration This procedure must be performed for both GRS units installed in the aircraft This first procedure must be carried out with the engine off Level the aircraft to within 0 25 of zero pitch and zero roll using a digital level Follow instructions in King Air 200 Series Maintenance Manual listed in Table 1 2 for leveling 2 Start PFD 1 in Configuration mode 3 Go to the GRS Page Group and select GRS GMU Calibration page at the PFD This page is protected and the following softkey password must be entered at the PFD to continue 49 4 10 el e 12 Far Right softkey GRS GMU CALIBRATION coreunroarion STATUS 4 Ensure that the No 1 GRS is selected in the SELECT GRS UNIT window on the PFD 5 Activate the cursor and highlight the SELECT PROCEDURE window and select PITCH ROLL OFFSET 6 Press the ENT key 7 Use the cursor to hi
289. lation l Install antenna using retained mounting screws Connect the antenna coaxial cable Fillet seal around antenna Refer to the Antenna Install drawing listed in Table 1 2 Reinstall cabin interior ceiling panel M dicat AK Proceed to Section 7 3 1 GPS Signal Acquisition for testing 6 19 Diversity Transponder Antenna Removal l Gain access to the antenna coaxial cable connector and mounting hardware by removing the cabin interior ceiling panel Refer to the Antenna Install drawing listed in Table 1 2 2 Disconnect the antenna coaxial cable 3 Remove the two nuts and washers securing the antenna 4 Remove antenna Reinstallation l Install antenna using retained hardware Connect the antenna coaxial cable Fillet seal around antenna Refer to the Antenna Install drawing listed in Table 1 2 Reinstall cabin interior ceiling panel Proceed to Section 7 5 2 for testing of the GTX33D or GTX 3000 y oe GR CE 6 20 Iridium Antenna Removal l Gain access to the antenna coaxial cable connector by removing the aft cabin ceiling panel Refer to the Antenna Install drawing listed in Table 1 2 2 Disconnect the antenna coaxial cable 3 Remove the antenna mounting screws Page 6 14 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 4 Remove antenna Reinstallation 1 Install antenna using retained mounting screws 2 Connect the antenna coaxial cable 3
290. layed PFD 1 and PFD 2 6 Press the GCU MENU button again and select Enable TAWS from the pop up menu and press ENT on the GCU Verify the TAWS INH annunciation on the PFDs has extinguished 7 Press the GCU MENU button again and select Inhibit GPWS from the pop up menu and press ENT on the GCU Verify GPWS INH is displayed on PFD 1 and PFD 2 8 Press GCU MENU button again and select Enable GPWS from the pop up menu and press ENT on the GCU Verify the GPWS INH annunciation on the PFDs has extinguished 9 Press the GCU MENU button again and select Flap Override from the pop up menu and press ENT on the GCU Verify FLAP OVR is displayed on PFD 1 and PFD 2 10 Press the GCU MENU button again and select Disable Flap Override from the pop up menu and press ENT on the GCU Verify the FLAP OVR annunciation on the PFDs has extinguished 11 With a GPS position acquired shield or disconnect the GPS antennas to remove the GPS signal Verify LOI shows on the and the TAWS N A and LOT annunciations show on the PFDs 12 Reconnect or remove the shield from the GPS antennas and verify the MFD LOI indication and PFD TAWS N A and LOT annunciations are removed once the GPS satellites are acquired 13 Pull the RADIO ALTM circuit breaker Verify GPWS FAIL is displayed on PFD1 and PFD2 14 Resetthe RADIO ALTM circuit breaker Verify GPWS FAIL annunciations are removed 1
291. le 7 3 Oil Pressure Indication Test Equipment Table 7 4 Oil Pressure Test Points Table 7 5 Air Data System Tes Table 7 6 Vertical Speed Table Table 7 7 Required GRS GMU Calibrations Table 7 8 RVSM Required Avionics Table 7 9 In Flight Altitude Hold Performance Test G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page vii 190 00915 01 Revision 9 This page intentionally left blank Page viii G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 1 INTRODUCTION 1 Content Scope Purpose This document provides Instructions for Continued Airworthiness ICA for the Garmin G1000 Integrated Flight Deck including the GFC700 Automatic Flight Control System AFCS as installed in the Hawker Beechcraft Model 200 B200 series King Air under STC SA01535WI D This document satisfies the requirements for continued airworthiness as defined by 14 CFR Part 23 1529 and Appendix G Information in this document is required to maintain the continued airworthiness of the G1000 and GFC700 1 1 1 Applicability This document applies to all Model 200 B200 series King Air aircraft equipped with the G1000 and GFC700 AFCS systems Modification of an aircraft by this Supplemental Type Certificate STC obligates the aircraft operator to include the maintenance information provided by this document in the operator s Aircraft Mainte
292. leak and accuracy check per Section 7 6 of this manual Determine which instrument is outside limits and replace Advisory 0720 Both units may individually be in spec but show a difference in altitude If the GDC 74B cannot be adjusted within the limits per Garmin Service Advisory 0720 replace the unit 200 B200 contains error correction at 19 000 feet and above The standby altimeter does not contain any correction Replace GDC 74B configuration module If problem persists replace GDC 74B configuration module wire harness 5 16 2 GDC 74B GDC 7400 Alerts Failure Message Cause Solutions MANIFEST GDC1 software mismatch Communication halted The system has detected an Load correct software version I incorrect software version loaded See Section 3 9 for the Software MANIFEST GDC2 software in the specified GDC Load Procedure mismatch Communication halted Page 5 76 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 17 GWX 68 or GWX 70 Troubleshooting 5 17 1 GWX 68 or GWX 70 Alerts and Problems WARNING Before energizing the equipment be sure microwave radiation safety precautions including both fuel and personnel safety considerations have been observed These include clearing all personnel to an area beyond the maximum permissible exposure level MPEL boundary The MPEL for the GWX 68 is 11 feet and GWX 70 is 10 feet Failure Message Cau
293. li volts Page 4 18 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 4 5 4 Phase 4 Electrical Bonding Procedure 1 Connect the positive lead of the power supply to the engine compartment grounding bracket battery negative connection to the airframe Connect touch the positive lead of the voltmeter to the same point NOTE Ensure that the voltmeter and power supply probes do not touch so as not to induce contact resistance 2 Touch negative lead of power supply to each of the test points listed while performing Step 3 At each point configure the power supply to produce 1 amp before measuring voltage Use an ammeter to ensure current is within 1 amp 100 milli amp at each point 3 Set the voltmeter to measure milli volts and null the reading Measure the voltage from the engine grounding bracket step 1 to each of the following points and record the voltage Perform Step 2 at each point to ensure that 1 amp 100 milli amp is present before measuring Nose Section e GWX 68 or GWX 70 body milli volts Nose Avionics Compartment e GIA top milli volts e GIA 2 top milli volts e GRS 77 or GRS 7800 1 metal bas milli volts e GRS 77 or GRS 7800 2 metal base milli volts e Standby battery milli volts Rear Fuselage and Empennage e GMU 44 1 metal base milli volts e GMU 44 2 metal base milli volts GSA 80 Pitch Servo body milli volts GSA 80 Pitch Trim Servo
294. lick on Tools gt Preferences gt Advanced Tab gt Select Allow Airframe Options Airframe Options window will be visible under the configuration tab Select Option 1 and Option 2 Note Aircraft option 1 4 dB cables Aircraft option 2 NCD curve adjusted for 3 foot installs Click Save Configuration to Unit On the Status Tab click Initiate Calibration Procedure Verify that the GRA 5500 Retrofit Installation Tool display a progress dialog during the calibration procedure and automatically close once the calibration procedure is completed 10 Verify that the information displayed in the status bar indicates 0 ft and Normal G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 45 190 00915 01 Revision 9 3 30 Non Garmin Traffic System Option Configuration Follow this procedure to enable a non Garmin traffic system function for the G1000 system if required NOTE The G1000 can only be configured for TIS or TAS but not both Performing this procedure will automatically disable the TIS function Coordinate this configuration with section 7 13 Non Garmin Traffic System Functional Check 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the System Upload page on using the small FMS knob 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Airframe Option
295. ling fan installation applicable for this maintenance interval 01000 Cooling Fan Verify the operation of the fan power and fan Fail Annunciation speed monitoring circuits for PFD1 fan 8 1 4 820 hours max Check fan and PFD2 fan and fan fail messages For aircraft equipped per MDL 005 00421 00 Rev 15 or previous revisions and not ied per Garmin Service Bulletin Nose Avionics 1375 Functional test of the GIA1 and 444 Compartment Fans GIA2 ported fans Verify airflow from all g 220 hours max Operational Check fan ports NOTE See Section 6 28 Figure 6 5 for identification of cooling fan installation applicable for this maintenance interval For aircraft equipped per MDL 005 00421 00 Rev 16 or later FAA approved revisions 7 or modified per Garmin Service Bulletin Nose Avionics Compartment Fans 1375 Functional test of the GIAT and GIA 444 820 hours max Operational Check NOTE See Section 6 28 Figure 6 6 for identification of cooling fan installation applicable for this maintenance interval Instrument Panel Functional test of the PFD1 MFD and Fans Operational PFD2 cooling fans Verify airflow from each 415 820 Check fan Denotes Airworthiness Limitation Maintenance Requirement See Section 4 1 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 4 7 Revision 9 Section No Interval Item Description Proc
296. lled must be engaged throughout these tests On the MAP TRAFFIC MAP page of the MFD press the softkey sequence 3 4 4 3 The GND TEST softkey will appear Press the GND TEST softkey to activate Ground Test mode This simulates the GTS 8XX to be airborne at 50 000 feet with a magnetic heading of 0 degrees To exit the Ground Test mode press the GND TEST softkey again To perform these tests for the GTS 8000 traffic system the aircraft must be in a simulated in air condition To accomplish this place the aircraft on jacks or actuate the weight on wheels switches on both L H and R H main landing gear OT OW io fea 4 A 18 18 TEST FLT ID ALT MODE Figure 7 17 GTS 820 850 or GTS Processor GND TEST softkey 7 27 1 Antenna Verification The following test assures the antennas and coaxial cables are properly connected The GTS 8XX must be in Ground Test mode 1 the MAP TRAFFIC MAP page of the MED press the OPERATE softkey for GTS 8XX or press TA ONLY softkey for GTS 8000 A self test of the antenna circuit is initialized If the MFD displays FAILURE at the upper left corner of the traffic display area it will be necessary to recheck the coaxial connections If MFD displays OPERATE FOR GTS 8XX OR TA ONLY G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 61 190 00915 01 Revision 9 FOR GTS 8000 without indicating a fault proceed to the next step of antenna
297. loaded to the display and the following screen is displayed DO YOU WANT TO UPDATE THE CUSTOM GRAPHIC FILES EG SPLASH SCREEN INO WILL BE ASSUMED IN 30 SECOND 9 Press the softkey labeled NO Note that the splash screen will need to be loaded after all software and configuration loading is completed 10 When complete the display starts in configuration mode displaying the System Status page Do not remove power 11 Remove the Loader Card from the display and insert it into the top card slot on another display if desired Repeat Steps 3 through 8 as needed IMPORTANT For the rest of the software configuration procedure do not operate the MFD or PED 2 while loading software or configuration files unless specifically instructed to do so A failed or cancelled load may result Page 3 20 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 9 2 01000 System Software Upload The System Upload page allows a technician to load LRU software and system configuration files individually or in an automated sequence Depending on what maintenance is performed software and or configuration files may need to be reloaded to LRUs Follow the steps below as a guide to use the System Upload page The figures contained in the following sections represent software version 0985 04 and later Earlier software versions are similar IMPORTANT Do not allow power to be removed from the syst
298. longer required post incorporation of this STC It is the responsibility of the installer to ensure that there are no post factory installations that would require these checks to remain Table 4 2 Discontinued Maintenance Intervals Description Procedure Manual interval ke Inverter Operational Check Phase Inspections Phases 1 2 3 amp 4 Du Sus Reeder Inspection of Dual Bus Feeder Diodes 24 50 00 Phases superseded by 4 17 2 IMPORTANT For installed equipment not listed in this maintenance manual use the inspection procedures set forth in Chapter 05 of the King Air 200 Series Maintenance Manual or other appropriate maintenance manual as the requirements set forth by those manuals are still applicable The requirements set forth by this document take precedence over those set forth by the King Air 200 Series Maintenance Manual or other appropriate maintenance manual in cases where the requirements conflict G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 11 190 00915 01 Revision 9 44 Visual Inspection Perform a visual inspection in accordance with requirements in Table 4 1 Check for corrosion damage or other defects for each of the items listed in Table 4 3 through Table 4 8 Replace any damaged parts as required Inspection may require the temporary removal of a unit or units to gain access to connectors Follow guidance in Section 6 for equipment removal and replacement Refer
299. lot of PFD in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight Enhanced SAR and press ENT key on PFD 3 Rotate the small FMS knob to select Enhanced Search and Rescue Press ENT key on PFD 4 Verify Enhanced Search and Rescue is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the SAR Enable card from PFD Page 3 62 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 46 Optional Garmin TCAS Enable From GTS 825 to GTS 855 Follow this procedure to enable TCAS I functionality when installing a GTS Processor A TCAS I Enable Card as specified on the General Arrangement Drawing 005 00421 03 will be required for this procedure NOTE The G1000 has various features that require the use of unlock enable cards to activate the feature Throughout this document these cards are generically referred to as enable cards In some cases the actual label on the phy
300. maged pins Repair any damage 2 Gently insert the GEA 71 into the rack The handle should engage the dogleg track 3 Press down on the handle to lock the unit into place 4 Lock the handle to the GEA 71 body using the Philips screw 5 Configure and test the GEA 71 according to Section 7 4 6 Reinstall the GDU 1040A display unit G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 3 190 00915 01 Revision 9 6 5 GTX 33 or GTX 3000 Transponder 33 Remova 1 Gain access by removing the cabin center floor panel at the main entry door 2 Remove the remote equipment shelf Alternately detach the two rack mount angles from the shelf Retain all mounting hardware 3 Unlock the GTX 33 handle by loosening the Phillips screw on the handle 4 Pull the handle upward to unlock the GTX 33 Gently remove the unit from the rack GTX 33 Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage Gently insert the GTX 33 into its rack The handle should engage the dogleg track Press down on the GTX 33 handle to lock the unit into the rack Lock the handle to the GTX 33 body using the Philips screw Reinstall the remote equipment shelf or two rack mount angles using the retained hardware 6 Reinstall the cabin center floor panel 7 Configure and test the GTX 33 according to Section 7 5 GTX 3000 Removal 1 Gain ac
301. me location as the original lift computer under the forward cabin floor Note this unit is not used for the ESP no AOA option 2 2 G1000 Optional Interfaces Optional equipment interfaces include L 3 WX 500 Stormscope traffic systems radar altimeter ADF systems and DME systems The G1000 also provides a general purpose ARINC bus for use with third party entertainment and cabin equipment Refer to wiring diagram listed in Table 1 2 for specific interface information Page 2 14 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 2 3 Electrical Power Distribution This airplane uses a multi bus system as detailed below and in Figure 2 20 This Figure shows the system post installation of this STC Although this STC made several bussing changes to the distribution system the core electrical generation and distribution system remains unchanged from the basic airplane design Figure 2 21 shows the power sources for all equipment used by this STC Each bus used or modified by this installation is described below Left and Right Generator Buses The left and right generator buses receive power from their respective left and right generators The left and right generator buses also support all four dual fed buses and No 1 and No 2 avionics buses respectively Isolation Bus The Isolation bus is fed by two generator buses and the battery bus The Isolation bus is used in this installat
302. min Aviation Product Support if condition continues after replacing the GRS 77 or GRS 7800 and config module for additional assistance G1000 700 System Maintenance Manual 200 B200 Series King Air Page 5 23 190 00915 01 Revision 9 Associated Invalid Data Field LRU s Solution e Ensure metal objects tool boxes power carts etc are not interfering with the magnetometer and aircraft is not in hangar near other buildings parked over metal drainage culverts or on hard surfaces that may contain steel reinforcements e GMU 44 magnetometers located in the tail cone are vulnerable to magnetized rudder torque tube lower fittings and control rod ends This magnetism may be caused by an improperly functioning aircraft static discharge system which is dependent on static dischargers wicks and electrical bonding of the static dischargers and surrounding structure The bonding straps on the elevators and rudder should be visually inspected to verify they are not missing broken or frayed Refer to the King Air 200 Series Maintenance Manual chapter 23 60 00 to verify the following items are within specification 1 The resistance from the tip to the base of each static discharger 2 The resistance between the base of each static discharger and the surface to which it is attached GRS 77 or 3 The resistance between the elevators rudder and HDG FAIL GRS 7800 the airplane structure amp e Ensure that a
303. mount configuration per section 3 37 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 53 190 00915 01 Revision 9 3 36 GSM 86 Servo Mount Configuration For software versions 0985 04 and later the section 4 9 1 slip clutch torque check procedure requires the correct type of GSM servo gearbox to be configured If a GSM 85A servo gearbox is replaced by a GSM 86 servo gearbox follow the steps below to load the configuration It is not necessary to load this configuration if GSM 86 servo gearboxes are already installed for all servos default configuration 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob PFDI 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight King Air 200 B200 GSM 86 Servo Mounts Press ENT key on PFDI 4 Verify King Air 200 B200 GSM 86 Servo Mounts is displayed in the Item window 5 Deselect any servos that have GSM 85A servo gearboxes installed by scrolling to the servo and pressing ENT key on PFDI 6 When all of the servos that have GSM 86 servo gearboxes are selected press LOAD softkey 7 Monitor load progress Verify software load completes without errors as indicated by the following e Green
304. move all electrical power from the airplane 16 Reinstall the right isolation limiter F132 4 18 Exterior Skin Inspection Around Antennas Perform a visual inspection of the exterior skin for cracks and loose and missing fasteners in an area at least 1 inch around the following antennas GA 36 GPS antenna GA 37 GPS XM antenna GA 58 Traffic Antenna Upper if Garmin traffic system is installed GA 58 Traffic Antenna Lower if Garmin traffic system is installed Transponder Antenna Upper 1 if Garmin GTX 33D or GTX 3000 transponder is installed Transponder Antenna Upper 2 if Garmin GTX 33D or GTX 3000 transponder is installed Iridium Antenna if Garmin GSR 56 satellite receiver is installed Wi Fi Antenna if Garmin GDL 59 wi fi data link is installed The antennas do not need to be removed to perform this inspection Page 4 40 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 duy amas mara age amis eran e iet SUN 4 ui ors i name Dun 4 ams age as tot PR Figure 4 8 Exterior Skin Inspection Around Antennas Should damage be detected in any structural component during this inspection all adjacent structures must be carefully investigated for indications of related damage All damage must be repaired using data obtained from the Structural Inspection and Repair Manual SIRM Beechcraft Repair Design Office RDO or
305. n G S1 receiver Replace GIA1 G S2 SERVICE G S2 needs The system has detected a failure Replace GIA2 G S1 FAIL G S1 is inoperative The system has detected a failure in G S1 receiver Switch GIA and GIA2 to verify location of problem v If problem follows the unit replace GIA Y If problem does not follow unit check G S1 antenna and cabling G S2 FAIL G S2 is inoperative 5 11 4 GPS Alerts The system has detected a failure in G S2 receiver NOTE Switch GIA and GIA2 to verify location of problem v If problem follows the unit replace GIA Y If problem does not follow unit check G S2 antenna and cabling Before troubleshooting ensure that no cell phones or devices using cell phone technology are turned on even in monitoring state in the cabin Failure Message MANIFEST GPS1 software mismatch Communication halted Cause The system has detected an incorrect software version loaded GIAt MANIFEST GPS2 software mismatch Communication halted The system has detected an incorrect software version loaded in GIA2 Solution Load the correct GPS software See Section 3 9 for the Software Loading procedure GPS1 SERVICE GPS needs service Return unit for repair The system has detected a failure in GPS1 receiver GPS2 SERVICE GPS2 needs service Return unit for repair The system has detected a failure in GPS
306. n PFD1 and PFD2 e 1 2 fields remain valid and XPDRs can adjusted via PFD softkeys PFD2 Display Failure Condition 1 Open PFD 2 CB 2 Verify desired results 3 Close PFD 2 CB For a PFD2 failure condition the following shall occur e PFD goes blank e PFD1 and MFD remain in normal display formats The following illuminate on PFD1 NO COMP illuminates on PFD1 e ROLL NO COMP illuminates on PFD1 PIT NO COMP illuminates on PFD1 IAS NO COMP illuminates on PFD1 e ALT NO COMP illuminates on PFD1 2 Fail GMA2 is inoperative 2 Fail XPDR2 is Inoperative PFD1 Display Failure Condition 1 Open PFD 1 PRI and PFD1 SEC circuit breakers 2 Verify desired results 3 Close PFD 1 PRI and PFD1 SEC circuit For a PFD1 failure condition the following shall occur e PFD1 goes blank e PFD2 and MFD remain in normal display formats The following illuminate on PFD2 breakers e NO COMP illuminates on PFD2 e ROLL NO COMP illuminates on PFD2 PIT NO COMP illuminates on PFD2 IAS NO COMP illuminates on PFD2 e ALT NO COMP illuminates on PFD2 e Fail GMAT is inoperative e XPDRI Fail XPDR1 is Inoperative G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 8 3 190 00915 01 Revision 9 8 1 4 01000 Cooling Fan Fail Annunciation Check Do the following to verify the cooling fans and annunciations are functi
307. n slowly turn the Pot 2 CW until the horn is ON again Press down on the vane until the horn is OFF and slowly release the vane If the horn is not ON when the vane is released turn the Pot 2 until the horn is ON c Reduce the force on the vane to 0 TG and reposition the force applicator to apply a downward force on the vane d Calculate the Pot 5 TG force by adding 17 TG to the Pot 2 setting Page 7 52 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Example If the Pot 2 force is 10 TG add 17 TG and the Pot 5 force is 7 TG e Install voltmeter leads between TP18 Lo and TP19 Hi of the SK100360 Breakout Box f Apply the calculated Pot 5 TG force to the vane with the force applicator 8 Adjust the Pot 5 on the lift computer until the voltage output from 18 Lo and 19 Hi reads 2 2 0 2 VDC on the voltmeter h Return the force on the force applicator to 0 TG 12 Place the BATT master switch in the OFF position and remove the external power from the airplane 13 Remove the force applicator from the left wing 14 Remove the breakout box and reconnect the lift computer 15 Install the potentiometer access cover on the lift computer 16 Close all panels opened to access the lift computer G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 53 190 00915 01 Revision 9 STALL WARNING AND LAA ADJUSTMENT POTS WN
308. n were loaded to LAU Refer fo the General Arrangement Drawing and to Section 5 20 1 ALERTS no V CUI EE e Check and ensure that correct Card Loader was MANIFEST bello id used during load process Refer to the General mismatch Communication halted Arrangement Drawing e Reload software to LRU After being in configuration mode the PFD e With the G1000 system powered on open the displays a red AFCS annunciation and cycling of PFD 1 PRI PFD 1 SEC and PFD 2 the transponder field between valid and invalid circuit breakers for approximately 30 seconds states then close the circuit breakers Page 5 80 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 20 1 System Communication Hierarchy The following criteria must be satisfied to be able to perform the desired operation Desired Operation Load Software to MFD or PFD Displays Criteria for Success SW Loader Card must be inserted in top slot for each display to be loaded CLR amp ENT keys must be held during power up of display Power on only one display at a time during software loading Load AIRFRAME SYSTEM PFD 1 PFD 2 and MANIFEST configuration files to MED and PFDs SW Loader Card must be inserted top slot of PFD 1 PFD 1 and MFD must be powered on PFD 1 and MFD must have correct software Load Software Configuration files to GIA 63Ws SW Loader Card
309. nable Follow this procedure to enable the Synthetic Vision option An SVS Pathways Enable Card as specified on General Arrangement Drawing 005 00421 03 will be required for this procedure NOTE The Garmin Synthetic Vision and Pathways feature requires 9 arc second high resolution terrain databases to function Each 81000 display must be equipped with the Terrain Obstacle SafeTaxi database card installed in the lower slot NOTE When the SVS Pathways option is enabled for the first time the G1000 writes its unique system ID to the physical card and locks the files to this unique ID This prevents the SVS Pathways unlock card from ever being used to activate the SVS Pathway feature in other G1000 systems The unlock card is tied to the specific aircraft in which it was used for the first time This card MUST be kept with the aircraft for situations where SVS Pathways must be re activated 1 With the SVS Enable card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight Configuration Files and press ENT key on PFD1 3 Rotate the small FMS knob to highlight Enable SVS Dual PFD Press ENT key on PFD1 4 Verify Enable SVS Dual PFD is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify softwar
310. nance Manual and the operator s Aircraft Scheduled Maintenance Program Aircraft modified by this STC have been shown to qualify for operation in Reduced Vertical Separation Minimum RVSM airspace as a group aircraft in accordance with Title 14 of the Code of Federal Regulations 14 CFR Part 91 Appendix G Operations in Reduced Vertical Separation Minimum RVSM Airspace and Federal Aviation Administration FAA Document No 91 RVSM Change 2 dated 2 10 2004 Guidance Material On The Approval Of Operators Aircraft For RVSM Operations This qualification is based on analysis of the configuration and performance of the air data automatic altitude control altitude alerting and altitude reporting systems These systems must be maintained in accordance with the inspections and tests specified in this document and other current maintenance practices to guarantee continued compliance to RVSM specifications 1 1 2 Identifying an STC Configuration Table 1 1 lists the G1000 System Software Version numbers approved for this STC Table 1 1 G1000 System Software Version G1000 System Aura Model Software Version 200 B200 Series King Air Updated GIA software superseded 200 B200 Series King Air 0985 02 Updated GDU and GIA software 200 B200 Series King Air 0985 03 Updated GDU and GIA software 200 B200 Series King Air 0985 04 Updated GDU and GIA software 200 B200 Series King Air 0985 06 Updated GDU and GRS software Updates and adds va
311. nce Manual Check aircraft control cables for proper tension per the King Air 200 Series Maintenance Manual AP DISC Problems For intermittent nuisance disconnects with no AFCS of PFT alert check A P disconnect switch and wiring for intermittent faults If an AFCS or PFT alert is displayed at the time of the disconnect troubleshoot per Section 5 5 Check the GIA AFCS Fault Logs according to Section 5 6 2 If a Mon Prmtr Invalid message is received check for valid true airspeed A faulty GTP 59 OAT probe may cause TAS to become invalid which will flag the Mon Prmtr Invalid message Contact Garmin Product Support for assistance Loss of Manual Electric Trim Check pitch trim servo status Check MET switch discrete inputs to both GIAs by going to the GIA I O Configuration page and selecting DISCRETE IN inputs AutoTrim Inoperative Check flap in motion discrete inputs to both GIAs for proper operation by going to the GIA I O Configuration page and selected DISCRETE IN inputs See Section 4 8 If DATA indicator fails to illuminate or illuminates incorrectly troubleshoot flap motor amp discrete input wiring refer to G1000 GFC 700 Wiring Diagram listed in Table 12 Page 5 32 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 6 GFC 700 AFCS Troubleshooting The GFC 700 is a digital Automatic Flight Control System AFCS which is integrated into
312. nce Manual 200 B200 Series King Air Page 7 25 190 00915 01 Revision 9 7 8 GDL 69A XM Data Link Original GDL 69 is Reinstalled No software or configuration loading is required if the removed GDL 69A is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the GDL 69A Test Section 7 8 1 New Repaired or Exchange GDL 69 is Installed If a new repaired or exchange GDL 69 is installed the correct software and configuration files must be loaded to the unit then the XM Satellite Radio subscription must be reactivated See Section 3 9 and the XM Activation Instructions listed in Table 1 2 Then continue to the GDL 69A Test Section 7 8 1 7 8 1 GDL 69A Test If an XM Satellite Radio subscription has already been activated for the GDL 69A then power up the G1000 and go to the AUX XM INFORMATION page and verify that the GDL 69A is working properly Refer to the Cockpit Reference Guide listed in Table 1 2 for details on XM Radio weather and music operation If the GDL 69 is replaced new unit the owner must re activate the subscription using the new GDL 69A s Radio ID number s Refer to the GDL 69A 69A XM Satellite Radio Activation Instructions listed in Table 1 3 for details on the activation process As a final operations check make sure there are no MANIFEST errors shown on the PFD for the GDL 69A
313. nd 7 and charge the unit for 16 hours The batteries should reach 80 capacity within 1 hour and full charge at 16 hours PS 835 16AWG conductors Power Supply Power Supply 71 pin 7 ground Figure 4 7 Power Supply Connection Page 4 38 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 4 17 Power Bus Check 4 17 1 Power Bus Feeder Check This procedure will verify the availability of the feeders to the essential bus and the No 1 and No 2 dual feed buses 1 Apply external power Turn BATT and AVIONICS MASTER switches to ON position Verify all circuit breakers are closed Observe PFD1 PFD2 and MFD displays and verify all displays are powered and in normal format Verify the absence of red Xs or alert messages Select or verify selected on side sensors for PFD1 and PFD2 Open the ESS BUS PRI circuit breaker Verify the MFD remains powered Open the ESS BUS SEC circuit breaker Verify the MFD is not powered Close the ESS BUS PRI circuit breaker Verify the MFD powers up Close the ESS BUS SEC circuit breaker Open the No 1 dual bus feeder circuit breakers RH NO 1 LH NO 1 Verify PFDI FAN FAIL and GIAI FAN FAIL alert messages are shown on the PFD If the messages are not shown check the dual bus feeder circuit breakers RH NO 1 LH NO 1 and the diode CR1002 between No 1 dual feed bus and the essential bus After replacement of the faulty component the test should
314. ndby Battery Annunciator Switch STBY Battery Switch legends illuminates and reflects STANDBY BATTERY in white ARM in green and ON in amber e For the Prop Synch Annunciator Switch Prop Synch Switch legends illuminates and reflects PROP SYNC in white and ON in green 3 Release cockpit annunciator Press To Test switch 4 If further maintenance is not required proceed to Section 8 6 24 L 3 Avionics BF Goodrich PS 835 C or D Model Emergency Battery Removal 1 Gain access to the forward avionics compartment in the nose of the aircraft 2 Unscrew the knurled hold down nut to allow it to move free of the unit 3 Remove the unit from the rack Reinstallation 1 Install the emergency battery in accordance with the Electrical Equipment Install Nose Bay drawing refer to Master Drawing List listed in Table 1 2 for specific drawing number Refer to the King Air 200 Series Maintenance Manual listed in Table 1 2 for access requirements as needed 2 If further maintenance is not required proceed to Section 8 6 25 Standby Airspeed Indicator Removal 1 Remove MED per Section 6 1 2 Disconnect pitot static plumbing from the back of the standby airspeed indicator Take necessary precautions to prevent foreign object debris from entering the pitot static lines during maintenance 3 Disconnect the electrical connector from the standby airspeed indicator 4 Usea Phillips screwdriver to remo
315. nfiguration and Software columns for each item loaded Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor Page 3 28 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 15 GTX 3000 Configuration This STC only certifies the GTX 3000 interfacing with the Garmin TCAS II The GTX 3000 is compatible with other suppliers TCAS II system but it s not part of this STC and therefore it cannot be installed with a third party TCAS II system Coordinate the GTX 3000 configuration with Section 7 5 GTX 33 or GTX 3000 Transponder 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the System Upload page using the PFD1 small FMS knob 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight King Air GTX 3000 Press ENT key on PFDI 4 Verify King Air GTX 3000 is displayed in the Item window Press LOAD 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration and Software columns for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to ackn
316. ng Joystick Navigation systeme controis Fight management system FMS snos Multifunction softkeys numbered 1 12 left to right Figure 3 1 GDU 1040A Control Interface G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 1 190 00915 01 Revision 9 Moti uncon soars rumored 1 12 eio gt Figure 3 2 GDU 1500 Control Interface 3 14 1 Softkeys Some pages have commands or selections that are activated by GDU 1040 softkeys If a softkey is associated with a command that command will be displayed directly above the key A grayed out sofikey shows a command that is unavailable A sofikey that is highlighted shows the current active selection Figure 3 3 G1000 Softkeys 3 1 2 FMS Knob The FMS knob is the primary control for the G1000 system Operation is similar to the Garmin 400 500 Series units To cycle through different configuration screens To change page groups Rotate the large FMS knob To change pages in a group Rotate the small FMS knob To activate the cursor for a page press the small FMS knob directly in as one would push a regular button To cycle the cursor through different data fields rotate the large FMS knob To change the contents of a highlighted data field rotate the small FMS knob This action either brings up an options menu for the particular field or in some cases allows the operator to enter data for the field To confirm a sele
317. ng No software loading is required if the original GEA units are installed in opposite locations GEA 1 and GEA 2 in opposite unit racks Continue to the GEA 71 Test Section 7 4 1 New Repaired or Exchange GEA 71 Installed If a new repaired or exchange GEA 71 is installed the correct software and configuration files must be loaded to the unit See Section 3 9 and then continue to the GEA 71 Test Section 7 4 1 7 4 1 71 Test On the MFD normal mode check the indication for each of the sensor or monitor inputs with the aircraft engines off In general verify all engine and system instruments show valid static normal values and markings with no red Xs or erratic indications Reference Figure 7 4 for normal engine instrument markings figure may not reflect actual aircraft installation If necessary reference Sections 0 7 4 3 and 7 4 4 for additional tests to verify instrument readings Figure 7 4 Normal Engine Instrument Markings MFD If no other service is to be performed continue to the return to service checks in Section 8 G1000 700 System Maintenance Manual 200 B200 Series King Air Page 7 9 190 00915 01 Revision 9 7 4 22 GEA Engine Indication Checks Perform engine indicating systems checks for the following left and right engine indications Reference King Air 200 Series Maintenance Manual Chapter 77 00 00 Engine Indicating Maintenance Practices ITT NI
318. ng a pitot static ramp tester check airspeed displayed on standby altimeter against airspeed display from ADC2 e Ifthe airspeeds are the same inspect the pitot static ports and associated equipment for faults e If the airspeeds are different replace the standby altimeter or contact the manufacturer for further troubleshooting See Section 6 25 for removal instructions Page 5 89 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 24 Symptom Altimeter lighting is inoperative or malfunctioning Altimeter Vibrator is inoperative or malfunctioning or fail flag is displayed Altitude displayed is incorrect Standby Altimeter Troubleshooting Recommended Action e Perform the Standby Instrument Electrical Power Checks in Section 8 1 5 Remove standby altimeter per Section 6 26 and inspect the electrical connector Check that electrical power is being appropriately supplied to the instrument e If the input electrical power is not adequate troubleshoot the wiring harness e If the input electrical power is appropriate replace the standby altimeter or contact the manufacturer for further troubleshootin e Using a pitot static ramp tester check altitude displayed on standby altimeter Note that PFD2 has error correction above 19 000 ft and will not be the same as the non corrected standby altimeter Inspect the pitot static ports and associated equipment fo
319. ng this test 1 Ensure the G1000 is operating in normal mode 2 Connecta pitot static test set to the aircraft ADCI pitot and static ports Pilot s side Do not connect the pitot static tester to ADC2 ports at this time 3 Set the baro correction on PFD1 and PFD2 to 29 92 4 Onthe AFCS mode controller press the ALT HDG and AP buttons and verify autopilot engages 5 Slowly increase the pitot static test set to simulate an ADCI ADC2 altitude miscompare of greater than 200 ft verify the disconnected ADC altitude does not increase autopilot does not disconnect and amber comparator window text ALT MISCOMP is displayed on PFD1 and PFD2 6 Reduce ADCI altitude to ambient pressure 7 Repeat Step 5 with the pitot static test set connected to the aircraft ADC2 pitot and static ports 8 Use the pitot static test set to simulate an airspeed of 40 kts for ADCI and 55 kts for ADC2 Verify the autopilot does not disconnect and amber comparator window text IAS MISCOMP is displayed on PFD 1 and PFD2 9 Use he pitot static test set to simulate an airspeed of 55 kts for ADCI and 40 kts for ADC2 Verify the autopilot does not disconnect and amber comparator window text IAS MISCOMP is displayed on PFD 1 and PFD2 10 Use the pitot static test set to simulate an airspeed of 85 kts for ADCI and 95 kts for ADC2 Verify the autopilot does not disconnect and amber comparator window text IAS MISCOMP is displayed on PFD 1 and PFD2 11 Use t
320. ngage the lockdown mechanism collars from the GRS 7800 hooks and gently slide the GRS 7800 from the mounting rack If the mounting rack is removed the GRS 7800 must be re calibrated Do not loosen mounting bolts See Section 7 7 GRS 7800 Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Place the GRS 7800 on the mounting rack ensuring the orientation is correct 3 Slide the GRS 7800 back until the feet are fully engaged with the mounting rack 4 Lift the lockdown mechanism collars in place on the GRS 7800 hooks and hand turn lockdown mechanism knobs clockwise until the GRS 7800 is secure Connect the connector to the GRS 7800 6 Calibrate and test the GRS 7800 according to Section 7 7 6 9 GMU 44 Magnetometer Lu NOTE The GMU 44 magnetometers may be located in the tailcone or in the horizontal stabilizer Always use a non magnetic Phillips screwdriver when removing or installing all screws near the magnetometers G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 5 190 00915 01 Revision 9 Reference the Magnetometer Install and Wire Harness Installation Tail drawings listed in Table 1 2 for more details For Tailcone Location Removal 1 Disconnect electrical wiring harnesses and remove the tailcone 2 Remove three screws connecting the unit to the aircraft mounting bracket 3 Remove the cable tie
321. nob select a range of 5000ft or less Verify SafeTaxi display represents the current aircraft location and the airport layout If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 39 190 00915 01 Revision 9 7 19 DME Functional Check This check verifies that the DME to G1000 interface operates correctly 12 13 NOTE Support for a single Collins DME 42 system is provided as an option in the G1000 If the DME option is selected the DME channel one audio level must be adjusted by the procedure contained within Collins DME 42 Transceiver Repair Manual 523 0772458 Maintenance Section 523 0772460 006118 to adjust DME channel one audio level Recommended nominal DME audio output level is 4 46 Vpp 0 10 Vpp Procedure must be accomplished by an approved repair station If DME is not displayed press the PFD sofikeys PFD1 and PFD2 then press the DME softkey Verify the DME window is displayed next to the PFD1 and PFD2 HSI On PFDI and PFD2 press the BACK softkey then select DME softkeys Verify the DME TUNING screen is displayed On PFDI and PFD2 use the large FMS knob to select the NAVI NAV2 and HOLD modes in the DME field Verify that the NAVI NAV2 and HOLD modes can be selected by turning the small FMS knob Set NAVI and NAV2 frequencies to 108 00 and 117 00 respectively On PFDI and PFD2 select the
322. ns 20 Using an air data test set connected to the pilot side pitot static system set an airspeed of at least 190 kts as displayed on PFDI 21 After an alert advisory appears press the softkey directly below the flashing ADVISORY 22 Verify the TAWS FLAP FAULT Flaps detected in the LDG position and TAWS GEAR FAULT Landing Gear detected in the DOWN position messages are present 23 Press the ALERTS softkey to close the alerts window 24 Place the flaps and landing gear in the full up positions 25 Press the ALERTS softkey again to open the alerts window 26 Verify the TAWS FLAP FAULT Flaps detected in the LDG position and TAWS GEAR FAULT Landing Gear detected in the DOWN position messages not present 27 Return air data test set to GROUND 28 Place the landing gear in the down position and remove the aircraft from the jacks If no other service is to be performed continue to the return to service checks in Section 8 Page 7 36 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 16 FliteCharts Functional Check Reference Section 3 32 FliteCharts Configuration for configuring FliteCharts NOTE This test is not required if ChartView is enabled 1 With the G1000 in Normal Mode use FMS knob to select AUX System Status page then select MFDI DB softkey 2 Use the small FMS knob to scroll to CHART 3 Verify FliteCha
323. nstall the two rack mount angles on the remote equipment shelf using retained hardware G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 21 190 00915 01 Revision 9 5 Reinstall the cabin center floor panel 6 Ifnew unit is installed register with Garmin Connext per Section 7 28 7 Configure the GDL 59 per Section 3 33 and 3 17 Test the GDL 59 per Section 7 29 6 34 GSR 56 Satellite Receiver Removal 1 Gain access by removing the cabin center floor panel at the main entry door 2 Detach the two rack mount angles from the remote equipment shelf Retain all mounting hardware 3 Unlock the unit from the rack by loosening the ratcheting latch mechanism 4 Remove the unit from the rack Reinstallation 1 Visually inspect the connectors to ensure there no bent damaged pins Repair any damage 2 Insert the unit into the installation rack CAUTION Do not use excessive force when inserting the GDL 56 into the rack This may cause damage to occur to the connectors unit and or unit rack If heavy resistance is felt during installation stop Remove the GDL 56 and identify the source of resistance 3 Lock the unit into the rack by using the ratcheting latch mechanism 4 Reinstall the cabin center floor panel 5 If new unit i talled register with Garmin Connext per Section 7 28 6 No configuration is required for the GSR 56 Test the GSR 56 according to Section 7 30 6 35 GTS Tr
324. nto its rack The handle should engage the dogleg track 3 Press down on the GDL 69A handle to lock the unit into the rack 4 Lock the handle to the GDL 69A body using the Philips screw 5 Configure and test the GDL 69A according to Section 7 8 6 11 GSA 80 Servos Removal 1 Gain access to the desired servo s 2 Disconnect the servo harness connector 3 Usea socket or open wrench to loosen and remove the servo attachment bolts The Pitch Trim servo bracket will need to be removed to access all the Pitch Trim servo attachment bolts 4 Carefully remove the servo and place a protective cover on the output gear 5 Place a protective cover over the GSM 85A 86 servo gearbox Reinstallation 1 2 Inspect the servo output gear for abnormal wear Using a lint free cloth remove excess grease build up from the servo output gear see Figure 6 1 IMPORTANT It is not necessary to remove all of the grease from the output gear only the excess grease DO NOT USE SOLVENTS TO CLEAN THE OUTPUT GEAR 3 Using a brush or other applicator apply a thin coat of Aeroshell 33MS Lithium complex based grease to the servo output gear N S Figure 6 1 Servo Gear G1000 700 System Maintenance Manual 200 B200 Series King Air Page 6 7 190 00915 01 Revision 9 4 Carefully place the servo into the servo gearbox ensuring proper orientation and alignment 5 Fasten the servo to the servo gearbox using the existing hardware Foll
325. nual 200 B200 Series King Air Revision 9 190 00915 01 COOLING FAN COOLING FAN HOSE TYP NOSE WHEEL WELL HOUSING VIEW OF LEFT SIDE NOSE AVIONICS BAY NOT ALL ITEMS SHOWN FOR CLARITY Figure 6 5 GIA Cooling Fan Installation Configuration applicable to MDL 005 00421 00 Rev 15 or previous FAA approved revisions COOLING FAN 7 COOLING FAN HOSE TYP H FAN INLET DUCT IF INSTALLED Z ES P N 115 00580 02 CIS e NOSE WHEEL WELL HOUSING S VIEW OF LEFT SIDE NOSE AVIONICS BAY NOT ALL ITEMS SHOWN FOR CLARITY Figure 6 6 GIA Cooling Fan Inlet Duct Installation Configuration applicable to MDL 005 00421 00 Rev 16 or later FAA approved revisions or modified per Garmin Service Bulletin 1375 Reinstallation 1 Reinstallation of the avionics cooling fan is the reverse of the removal Reference the Electrical Equipment Install Nose Bay drawing listed in Table 1 2 for more details 2 If further maintenance is not required proceed to Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 19 190 00915 01 Revision 9 6 29 GDU Cooling Fans Removal 1 Remove the display associated with the cooling fan per Section 6 1 2 Disconnect the electrical connector of the cooling fan 3 Use a Phillips screwdriver to remove the attachment screws from the cooling fan 4 Remove the cooling fan tallat
326. o this indicates outside interference is affecting the GPS receivers Find and remove the source of interference i e cell phones FBO datalink antennas etc e If GPS receivers can not aquire position lock troubleshoot per the Will not acquire satellites section G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 63 Revision 9 5 11 5 GIA Cooling Alerts Failure Message GIA1 COOLING GIA1 Cause GIA1 operating temperature is too Solution Allow unit to warm up temperature too low low GIA2 COOLING GIA2 GIA2 operating temperature is too alow unit to warm temperature too low low warm up GIA1 COOLING GIA1 over temperature GIA has exceeded its operating temperature range Check fan wiring and air tubing for proper operation if applicable e Replace cooling fan if unable to determine if operating correctly Replace GIAt e I problem persists contact Garmin Aviation Product Support for assistance GIA2 COOLING GIA2 over temperature GIA2 has exceeded its operating temperature range Check fan wiring and air tubing for proper operation if applicable e Replace cooling fan if unable to determine if operating correctly Replace GIA2 e If problem persists contact Garmin Aviation Product Support for assistance Page 5 64 Revision 9 G1000 GFC 700 System Mainten
327. o XM audio is heard No XM weather information is displayed Recommended Action e Ensure the following items are not preventing the audio panel from distributing XM audio reference applicable G1000 Pilot s Guide Y Verify the XM volume is not muted on the AUX XM RADIO page on the MFD Verify the COM squelch is not open Verify the ICS squelch is not open Verify the marker beacon tones are not being received Y Verify the headphone if equipped volume is turned up e Go to the AUX SYSTEM STATUS page on the MFD and ensure unit is online Y lfaredXis present verify the unit is receiving power at the rack connector e Ensure there are no GDL alerts in the alert window If there is an Alert for software or configuration error or mismatch reload the file noted in the Alert e Restart the PFD s and MFD in configuration mode and go to the GDL page Y Verify unit is active Y Verify the Signal number is 2 or 3 If it is 0 or 1 check the GDL 69 69A antenna and cabling for faults Y Reseat the GDL 69 69A to verify the coax connector is fully seated Y If unit is not active contact XM Customer service to have a refresh signal sent to your unit You will need to provide them the Audio Radio ID and Data Radio ID number for XM weather numbers Also verify with XM that the correct Weather package Aviator Lite or Aviator is on the account and that no traffic service has been activated against that Ra
328. o the GDU TEST page in configuration mode and verify key is stuck if key is stuck the corresponding indicator will be green e Exercise suspected stuck key and reset GDU TEST page to see if indicator remains green without pressing the key v If problem persists replace the display Solution e Ensure a database error has not occurred identified in the ALERTS window on the PFD Ifa database error has occurred correct error before proceeding Check display Ethernet interconnect wiring Replace PFD1 with a known good unit to verify location of problem v If problem persists reinstall original PFD1 and replace PFD2 v If problem persists reinstall PFD2 and replace MFD DATA LOST Pilot stored data lost Recheck settings Pilot stored data has been lost e Ifthe CLR key was held during a power cycle disregard message e Cycle power to PFD1 Y Ensure CLR key is not stuck on the GDU TEST page vf problem persists replace PFD1 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 53 Revision 9 Failure Message Cause Solution MFD1 SERVICE needs service Return unit for repair The G1000 has determined MFD1 needs service e Ensure the MFD connector is fully seated and locked e Ifthe unit was started in a very dark environment the photocells may not have enough light to initially raise the CCFT level Go to th
329. ol Setup Wizard will begin 3 Click Next as prompted by the setup wizard and adjust any settings e g installation directory as needed 4 The last screen of the setup wizard will show Installation Complete Click the Close button to close the setup wizard Page 3 44 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 NOTE Depending on the computer s security settings Windows may prompt the installer to allow the installation software to make changes to the computer The installer will need access to install hardware drivers program files and shortcuts The application may be uninstalled at any time through the Windows Control Panel 3 29 3 GRA 5500 Calibration The following actions must be performed after initial installation of the Garmin GRA 5500 1 Connect a PC that has the GRA 5500 Retrofit Installation Tool installed to the GRA 5500 via USB cable to the installed USB Pigtail located near the GRA 5500 Start the GRA 5500 Retrofit Installation Tool from the Start Menu shortcut or launch the application from its program folder Power up the GRA 5500 by applying aircraft power The connection status in the lower right hand corner of the GRA 5500 Retrofit Installation Tool will transition from Not Connected to Connecting and finally to Connected once the GRA 5500 is powered In the GRA 5500 Retrofit Installation Tool c
330. ollow the procedures outlined in this section to load the necessary configuration files to disable TAWS A voice callouts Coordinate the TAWS A Voice No Callout Option configuration with Section 7 15 TAWS Functional Check 1 With the loader card in the top slot of PFDI and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Airframe Options and press ENT key on PFDI 3 Rotate the small FMS knob to select King Air TAWS A No Voice Callout Installation Option Press ENT key on PFDI 4 Verify the King Air TAWS A No Voice Callout Installation Option is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 39 190 00915 01 Revision 9 3 26 TAWS A Voice Callout Option Configuration This section applies only to installations with the TAWS A option This step is necessary only if TAWS A voice callouts 400 300 200 100 have been disabled and are now desired TAWS
331. ommended Action Set up a NAV COM Ramp Test Set to radiate a test signal Switch GIA and GIA2 to verify location of problem v If problem follows unit replace GIA v If problem does not follow unit check NAV antenna coupler and cabling for faults Weak G S receiver G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 57 190 00915 01 Revision 9 5 10 4 GPS Symptom Will Not Acquire Satellites Recommended Action e Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin e Using the MFD AUX GPS Status page verify the signal strength bars are not erratic If so this indicates outside interference is affecting the GPS receivers Find and remove the source of interference i e cell phones FBO datalink antennas etc e Check date and time on Date Time Setup Page Y If date and time are incorrect enter the correct date and time e Switch GIA1 and GIA2 to verify location of problem Y f problem follows unit clear the GPS almanac by performing the following steps o Using the PFD in config mode go to the GIA RS 232 ARNIC 429 Config Page o Atthe top of the screen select the GIA that can not acquire satellites GIA1 or GIA2 and press the ENT key o Pressthe CLR NV softkey at the bottom of the screen o Select OK the Clear GIA nonvolatile memory pop up window o Next reloa
332. on press the HDG and ALT buttons on the mode controller and center the heading bug 26 Engage the autopilot and turn the heading knob to set the heading bug to the right of center Hold the control yoke centered for approximately 10 seconds Verify that the amber AIL annunciator is displayed on both PFD 1 and PFD 2 Page 4 32 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 27 Turn the heading knob to set the heading bug to the left of center Hold the control yoke centered for approximately 10 seconds Verify that the amber AIL annunciator is displayed on both PFD and PFD 2 28 Disengage the autopilot and clear all modes 29 Ensure the aircraft is on the ground and the nose wheel is approximately straight 30 Engage the yaw damper and apply firm load on the right rudder pedal for approximately 20 seconds 31 Verify that the amber RUD annunciator is displayed on both PFD and PFD 2 32 Apply firm load on the left rudder pedal for approximately 20 seconds 33 Verify that the amber RUD annunciator is displayed on both PFD and PFD 2 34 Disengage autopilot 35 The Trim Annunciator Check is complete 4 13 01000 Miscompare Checks This procedure will check the AHRS airspeed and altitude miscompare monitors Accomplish the following checks with the aircraft positioned where it can receive GPS signals and magnetic heading Access to AHRSI and AHRS2 will be required duri
333. on verify servo PFT is complete This step is checking to make sure that all servos have completed their own PFT This does not check whether the servo PFT passed or failed It verifies that the servo PFT is no longer in progress PFT step 6 Verify cross GIA is initialized This step is checking to make sure the other GIA is also on step 6 PFT If this step fails try cycling power on GIAI GIA2 and all servos If PFT still fails at step 6 then you will need to go check the PFT status of the other GIA and see what step it is failing it should be prior to step 6 NOTE PFT status is communicated between GIA and GIA2 using HSDB a result both the PFD and MFD must be powered for this state to pass PFT step 7 Verify servo type This step is checking to make sure the Servos are the correct type torque and speed If this step fails make sure the Servo configuration on the GFC configuration page matches the Servos installed in the aircraft PFT step 8 Verify servo first certification data This step is checking to make sure the servos have the same certification gains loaded in them as the GIAs have If this step fails reload the certification gains in GIAI GIA2 and all servos PFT step 9 Verify servo second certification data This step is checking to make sure the servos have the same certification gains loaded in them as the GIAs have If this step fails reload the certification gains GIAI GIA2
334. on 5 20 1 are fulfilled for the applicable situation FILE UPLOAD FATL e Ensure that LRU is reporting data on System Status page LRU is ONLINE Check data path wiring as needed e Retry software file load or try using a different card Ensure that the is not touched during the loading process Ensure that LRU part number is compatible with software version and Card Loader Refer to the General Arrangement Drawing and to Section 3 8 of this document e Replace LRU e Ensure that the criteria listed in Section 5 20 1 are fulfilled for the applicable situation CONFIGURATION UPLOAD Ensure that LRU is reporting data on System Status page LRU is ONLINE Check data path wiring as needed e Retry configuration file load or try using a different card Ensure that the MFD is not touched during the loading process Ensure that LRU part number is compatible with Card Loader Refer to the General Arrangement Drawing and to Section 3 8 of this document Replace LRU GIA and or GIA2 to LRU data path not e Ensure that the criteria listed in Section 5 20 1 are fulfilled for the applicable situation Configuration file load fai working e Ensure GIA1 and GIA2 are configured correctly e Check wiring connectors amp pins as needed Software File Mismatch Alert appears in lower Ensure that proper software file part number and right corner of PFD when started in normal mode versio
335. on if GPS can not acquire a position lock for troubleshooting Check corresponding GPS antenna and cable for faults Check Ethernet interconnect between the PFD1 to GIA1 or PFD2 to GIA for faults Swap GIA1 and GIA2 to verify location of problem Y If problem follows the GIA replace the GIA Y If problem persists replace the PFD1 or PFD2 XPDR FAIL GTX 33 or GTX 3000 Check GTX 33 33D 3000 configuration settings for GIA1 and GIA2 Check GTX 33D 3000 and GIA1 interconnect Check GTX 33D 3000 and GIA2 interconnect Perform a SET gt ACTV configuration reset on the GTX Config page for each GTX and verify the aircraft registration is present Replace GTX 33 33D 3000 Y If problem persists replace GIA TAS FAIL AIRSPEED FAIL ALTITUDE FAIL VERT SPEED FAIL GDC 74B Or GDC 7400 Inspect GDC 74B GDC 7400 pitot static plumbing integrity Inspect pitot static ports and associated equipment for faults For TAS failure also check GTP 59 probe Check GDC 74B GDC 7400 configuration settings for the PFDs MFD GIA1 and GIA2 Y f PFDs MFD and GIA configuration settings are correct replace the GDC configuration module GDC 74B only Y If problem persists replace the GDC 74B GDC 7400 GTP 59 Check OAT probe wiring and connectors for faults Check configuration module wiring for damage replace if any is found GDC 74B only Replace configuration module GDC 74B only Replace GDC 7
336. on method allows multiple grounds to be terminated directly to a block mounted to the connector backshell assembly Shielding and grounding requirements for all other LRUs and connectors are shown in the respective install drawings 2 6 G1000 GFC700 Block Diagram No TGA BIW 0 0 GDC 74 Integrated Avionics Unit ir lt Integrated Avionics Unit Syston Heo Seen Figen Feet proe p Wes serion versie NES Figure 2 23 G1000 GFC 700 Block Diagram G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 19 190 00915 01 Revision 9 This page intentionally left blank Page 2 20 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 G1000 Control amp Operation All control and operation of G1000 equipment as normally used flight occurs through PFDs GMC 710 GCU 477 and GMA 1347D audio panel Figure 3 1 through Figure 3 6 identify various interface buttons for these units 3 1 GDU 1040A and GDU 1500 Displays Figure 3 1 and Figure 3 2 provide identification of the GDU 1040A PFD and GDU 1500 MFD controls COM frequency Nav frequency Foedus toggle key GARMIN COM volumer squelch knab ident knob Nav frequency pee COM frequency Selector knob Baro selector knob Map panni
337. on should be considered unreliable until the source of magnetic interference is identified and remedied When the magnetometer interference test fails record the three magnetometer maximum deviation values and their corresponding timestamps Reference the appropriate installation manual for the GRS 77 190 00303 10 and GRS 7800 190 01091 00 for acceptable magnetic interference limits Compare the corresponding timestamps with the prepared test sequence to identify which action produced the problem Contact Garmin for assistance in resolving the problem NOTE Three common reasons for a failed magnetometer interference test are 1 rudder bellcrank or other structure has become magnetized 2 new equipment is installed in close proximity to the GMU 44 magnetometer and 3 an existing or new electronic device has become grounded through the aircraft structure instead of via the proper ground wire in a twisted shielded pair 10 Press the ENT key on the PFD to conclude this procedure G1000 700 System Maintenance Manual 200 B200 Series King Air Page 5 75 190 00915 01 Revision 9 5 16 GDC 74B GDC 7400 Troubleshooting 5 16 1 Air Data Common Problems Symptom Altitude shown on PFD is different than standby altimeter GDC 74B Configuration file does not load Recommended Action Note The GDC 74B may be field adjusted per Garmin Service Note The GDC 74B and GDC 7400 software configuration for the Perform a pitot static
338. oning properly Step Desired Result Cooling Fan Failure Conditions For the cooling fan failure conditions after a 30 1 Ensure the G1000 is in normal mode and second delay verify that the following alert messages verify that there are no fan related alert are displayed messages displayed in PFD1 or PFD2 AVN FAN 1 FAIL Avionics cooling fan 1 is Alerts Window inoperative 2 Pullthe following cooling fan circuit x d breakers e FAN 2 FAIL Avionics cooling fan 2 is a PFD GIA FANS LEFT inoperative b PFD GIA FANS RIGHT e PED 1 FAN FAIL 1 cooling fan is c MED inoperative e PFD 2 FAN FAIL PFD 2 cooling fan is inoperative e FAN FAIL MED cooling fan is inoperative Fan Failure reset and acknowledgement Verify the above alerts extinguish 1 Reset all cooling fan circuit breakers 2 Acknowledge alerts by pressing the ALERTS softkey on PFD1 8 1 5 Standby Instrument Electrical Power Checks This section tests the standby electrical power for the standby attitude indicator the standby altimeter and the standby airspeed indicator The magnetic compass is tested in each Phase inspection during the cockpit lights check in the King Air 200 Series Maintenance Manual listed in Table 1 2 Step Desired Result 1 Remove or ensure external aircraft power Verify the STANDBY BATTERY is removed Set main battery switch to annunciator switch is not illuminated OFF
339. ons for Troubleshooting If the original GMA 1 and GMA 2 are installed in opposite locations configuration loading is required See Section 3 9 and then continue to the GMA 1347D Test Section 7 2 1 New Repaired or Exchange 1347D Installed If a new repaired or exchanged GMA 1347 is installed the correct software and configuration files must be loaded to the unit See Section 3 9 and then continue to the GMA 1347D Test Section 7 2 1 7 21 GMA 1347D Test Except for marker beacon operation an in aircraft checkout may be performed in the aircraft with known good microphone headset and speaker ICS Check 1 Ensure that the MAN SQ key is off no light 2 Adjust GMA1 and GMA2 ICS volume to a comfortable level 3 Plug in a headset at each COCKPIT ICS position One at a time plug a headset into each left and right CABIN ICS jack location if installed one headset on right one headset on left 4 Verify the following e Two way communication between each CABIN ICS jack position CABIN ICS position cannot hear the pilot and copilot e CABIN ICS positions cannot be heard by the pilot or copilot 5 On GMA select COMI and AUDIO 6 Ensure INTR COM is deselected on GMAI or GMA2 Verify an active green COMI frequency is displayed on both PFDs 7 OnGMAI or 2 select and verify the PA select annunciator is illuminated on GMA1 and GMA2 Verify COMI active frequency is display
340. ormation provided in Garmin GA Drawing 005 00421 03 and save the files to the local hard drive NOTE A standard USB A plug to USB B plug commercial cable not provided is required to interface between a personal computer USB A receptacle and the GRA 5500 USB B receptacle installed in the wiring harness 3 29 2 Downloading and Installing the GRA 5500 Retrofit Installation Tool GRA 5500 configuration calibration diagnostics and software upgrades are performed in retrofit non GIFD installations using a personal computer installed with Microsoft Windows XP or later and the GRA 5500 Retrofit Installation Tool Garmin part number 006 A0451 00 This tool is also used to assist in the diagnosis and resolution of asserts found in the GRA 5500 assert log during the installation process and during post installation flight operation The tool is available for download from the Dealer Resource Center portion of the Garmin website www garmin com See the accompanying readme file in the tool s installation directory for the latest instructions NOTE A standard USB A plug to USB B plug commercial cable not provided is required to interface between a personal computer USB A receptacle and the GRA 5500 USB B receptacle installed in the wiring harness Installation 1 Once downloaded launch the installation file from the directory which it is stored or use the web browser s download shortcuts 2 The GRA 5500 Retrofit Installation To
341. ort at avionics Garmin com G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 45 190 00915 01 Revision 9 5 7 Backup Communications Path Checks 5 7 1 Overview The G1000 system architecture is designed with redundant communication ports for several LRUs so that critical information can continue to be displayed in the event of an equipment or wiring failure Of most importance is flight attitude heading and air data information The GRS 77 7800 and GDC 74B GDC 7400 each have four separate ARINC 429 data lines which are all capable of sending data to the displays The GEA 71 GTX 33 D or GTX 3000 and GMA 1347D each have two redundant serial communication paths for the same purpose See Figure 2 23 for a basic G1000 block diagram depicting this architecture Several other diagrams are shown later in this section for illustrative purposes When troubleshooting refer to the G1000 GFC 700 Wiring Diagram listed in Table 1 2 NOTE Refer to Section 8 1 6 for procedures on checking the status of each configured G1000 GFC 700 backup data path 5 7 2 Data Path Failures Failure Message Determine which data path has failed See Section 8 1 6 FAILED PATH A data path has communications data path failed status is not being received by the Check wiring continuity for the failed 91000 path Swap or replace the affected LRU Page 5 46 G1000 GFC 700 System Maintenance Man
342. ots must be input using a pitot static test set 1 Engage the Autopilot by pressing the AP key on the AFCS mode controller Push the HDG knob to synchronize the heading bug to the current aircraft heading Select HDG mode by pressing the HDG key on the AFCS mode controller Verify the command bars are level and the control wheel is stationary There may be some roll motion in the yoke if the aircraft not perfectly level 2 Turn the HDG knob to the left and right and check that the command bars move in the correct direction and the control wheel follows the command bars 3 Push and hold the CWS button and pull the control wheel to the center of the pitch control range Release the CWS button Verify the autopilot clutches re engage and hold the wheel stationary 4 Holding the control wheel lightly rotate the NOSE UP DN wheel on the AFCS mode controller two clicks UP to increase the pitch reference Verify the command bars move up degree and the control wheel begins moving aft In some aircraft the down spring may require manual assistance to get aft control stick movement 5 While holding the control wheel firmly press and hold the CWS button to re synchronize the pitch reference Re center the control wheel to wings level and mid range elevator travel Release the CWS button and check that servo clutches re engage before releasing the control wheel 6 Rotate the NOSE UP DN wheel on the AFCS mode controller two clicks DOWN to decrease th
343. ow the installation instructions provided in the respective servo installation drawing s listed in Table 1 2 6 Inspect the harness connectors and check that no pins are bent or otherwise damaged Connect the harness and secure it appropriately 7 further maintenance is required continue to Section 7 9 6 12 GSM 85A 86 Servo Gearbox Removal 1 Remove the desired servo s per Section 6 11 2 For the Roll Pitch and Yaw Servos remove the servo bridle cables from the control cable clamps For the Pitch Trim Servo disconnect the servo cable at the forward turnbuckle and aft terminal 3 Use a socket or open wrench to loosen and remove the servo attachment bolts 4 Carefully remove the servo gearbox es 5 Remove the cable retention pins and ring or cover and then remove the servo cable from the capstan Reinstallation 1 Ensure cable retention pins are oriented correctly Follow the installation instructions provided in the respective servo installation drawing s listed in Table 1 2 2 Ifno other maintenance is to be performed reinstall the servo s per Section 6 11 6 13 GCU 477 Removal 1 Use a 3 32 hex drive tool to turn each of the four locking sockets 1 4 turn counterclockwise until they reach their stops 2 Disconnect backshell assembly from unit Reinstallation 1 Inspect connector s for damaged pins 2 Connect backshell assembly to unit 3 Hold unit flush with the pedestal ensuring
344. owever the torque value can be measured using this procedure IMPORTANT This adjustment requires the use of the Garmin servo adjustment fixture P N T10 00110 01 For detailed operating instructions for the fixture refer to GSASX GSMSS A Installation Manual listed in Table 1 3 It is highly recommended that the following test be performed at temperatures between 50 F and 120 Remove the GSM 85A or GSM 86 servo gearbox as per Section 6 12 2 Place the GSM 85A or GSM 86 servo gearbox on the slip clutch adjustment fixture and secure with the toggle clamps Install the fixture cable between the capstan under test and the fixture capstan Remove the slack in the cable using the tension adjustment knob Tighten the two wingnuts on bottom of fixture while holding the top thumbscrews 3 Attach a socket to a calibrated torque wrench of appropriate range and place on top of the fixture capstan Adjust the wrench support fixture so that it contacts the handle in the appropriate location 4 Connect a2 Amp 24 V DC power supply to the fixture 5 Place the solenoid switch to on and move the direction switch to the clockwise or counter clockwise position Allow the clutch to rotate at least one revolution in each direction note the capstan itself is fixed 6 Observe the torque reading for at least two full revolutions in each direction Ensure the minimum and maximum torque readings are within the tolerance specified
345. owledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 29 190 00915 01 Revision 9 3 16 GDL 59 Wi Fi Data Link Option Configuration Follow this procedure to enable the optional GDL 59 Wi Fi data link function If the GDL 59 option is reloaded for any reason the GSR 56 option must also be reloaded per Section 3 17 Coordinate the GDL configuration with Section 7 29 GDL 59 Wi Fi Data Link Functional Check 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob PFDI 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key PFD1 3 Rotate the small FMS knob to highlight King Air GDL 59 Press ENT key on PFDI 4 Verify King Air GDL 59 is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration columns for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor Page 3 30 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 17 GSR 56 Satellite
346. p 24 V DC Power Supply Calibrated torque wrench capable of measuring 0 70 in Ibs Standard sockets amp wrenches 3 8 9 16 and 13 16 Calibrated digital thermometer suitable for measuring ambient temperature Laptop with RS232 emulation software M22885 108T8234 extraction tool An 0 060 6 Spline wrench G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 4 3 Revision 9 4 2 3 Special Tools The following tools are needed to perform maintenance tasks on G1000 equipment and or installation GSM 85A Servo Gearbox Slip Clutch Adjustment Tool Garmin P N T10 00110 01 WX PA portable analyzer kit Part Number 78 8060 5791 1 If Stormscope is installed Gauging Equipment Tool SPF 4 AIM BCH GE Lift Computer Breakout Box P N SK100360 or equivalent if ESP with AOA option is installed Lift Transducer Force Applicator Kit Safe Flight P N 1952 1 3 5 if ESP with AOAoption is installed For software loader code 0985 07 GRA 5500 Sensor and Main Software If GRA 5500 is installed Garmin P N per GA Drawing 005 00421 03 obtained from www garmin com web site from instructions in Section 3 29 1 For software loader code 0985 07 GRA 5500 Retrofit Tool If GRA 5500 is installed Garmin P N 006 A0451 00 obtained from www garmin com web site from instructions in Section 3 29 1 The gauging equipment tool is used for the static port inspection for RVSM compliant a
347. paired or exchange GDC unit is installed the correct software and configuration files must be loaded to the unit See Section 3 9 and then continue to GDC 74B or GDC 7400 Test Section 7 6 1 New GDC 74B Configuration Module is Installed The correct configuration files must be loaded if the GDC 74B configuration module has been replaced See Section 3 9 and then continue to GDC 74B or GDC 7400 Test Section 7 6 1 7 6 1 Air Data Test GDC 74B or GDC 7400 The G1000 system must be maintained in accordance with the G1000 System Maintenance Manual listed in Table 1 3 and appropriate regulations When the GDC unit is tested in accordance with 14 CFR Part 43 Appendix E note the following exceptions e For paragraph b 1 i Scale Error use Table 7 5 of this section instead of Appendix E Table I Do not perform paragraph b 1 iv Friction Do not perform paragraph b 1 vi Barametric Scale Error The following Air Data Test is to be performed in addition to or in conjunction with any other regulated tests This test must be performed on both pilot and copilot systems with a calibrated Air Data Test Set ADTS with a combined accuracy repeatability specification of less than 20 feet for the test altitude range 1 Perform pitot static system leak check of each system as described the King Air 200 Series Maintenance Manual 34 00 00 with the following changes a For the pitot leak check set the air data test unit to an ind
348. part number units to be installed with certain hardware software combination restrictions Refer to the applicable Garmin Equipment Software List contained in the General Arrangement drawing for details G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 1 190 00915 01 Revision 9 6 1 GDU 1040A 1500 Removal 1 Using a 3 32 hex tool rotate all four 4 turn fasteners counter clockwise until they reach their stops 2 Carefully remove the display from the panel 3 While supporting the display disconnect the connector Reinstallation 1 Visually inspect the connector and pins for signs of damage Repair any damage While supporting the display connect the connector to the rear of the unit 2 Carefully insert the display into the panel cutout ensuring that all 4 4 turn fasteners align with the corresponding holes 3 Seat the display in the panel cutout Do not use excessive force while inserting the display 4 Once seated rotate all four 4 turn fasteners clockwise to lock the display to the panel 5 Configure and test the MFD and or PFD according to Section 7 1 6 2 GMA 1347D Audio Panel Removal 1 Using 3 32 hex tool turn the hex nut counter clockwise until the GMA 1347D is unlocked from its location 2 Carefully remove the GMA 1347D from its rack Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Gently inser
349. path is functioning correctly PFD2 GMC 710 data path is not functioning correctly e Verify GMC 710 is powered on o If GMC 710 will not power on remove unit and verify power and ground are present at the GMC connector If power or ground is not present troubleshoot aircraft wiring for faults If power and ground are present replace CHNL2 GMC 710 GMC 710 e Load PFD2 and GMC 710 configuration files e Swap PFD2 and PFD to confirm if the problem is in the original PFD2 o Replace original PFD2 if box turns green after swapping displays e Check the PFD2 GMC 710 interconnect wiring for faults Replace GMC 710 if problem remains A PFD2 GMC 710 data path functionality is unknown Reload mber PFD2 configuration file Page 5 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 PFD 2 ARINC 429 Channel L Indicator Status PFD2 GRS 77 GRS 7800 2 data path is functioning correctly PFD2 GRS 77 or GRS 7800 2 data path is not functioning correctly e Verify GRS77 7800 2 status is OK using the System Status page on the MFD If it is not correct condition before proceeding reference GRS troubleshooting sections o Swap GRSI and GRS2 no reconfiguration required to confirm if the problem is in the original GRSI o Replace original GRS1 if box turns green after swapping units INI EUM Red Load PFD2
350. persists replace master configuration module check config module harness for faults and replace if necessary NOTE New Terrain Obstacle cards Jeppesen Aviation Database and other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed 01000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number Page 5 66 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 5 13 GTX Troubleshooting 5 13 1 GTX Alerts Failure Message Cause Solutions MANIFEST GTX1 software mismatch Communication halted MANIFEST GTX2 software mismatch Communication halted The system has detected an incorrect software version loaded in the specified GTX 33 or GTX 3000 Reload software See Section 3 9 for the Software Load Procedure XPDR1 CONFIG XPDR1 configuration error Config service req d XPDR2 CONFIG xPDR2 configuration error Config service req d The system has detected a configuration mismatch for the specified GTX 33 or GTX 3000 e Perform a SET ACTV configuration reset on the GTX Config page and verify the aircraft registration is present e If error is still present reload config files from a loader card v If problem persists re
351. place master configuration module check config module harness for faults and replace if necessary NOTE New Terrain Obstacle cards Jeppesen Aviation Database and other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work they will remain locked to the old System ID number XPDR1 SRVC XPDR1 needs service Return unit for repair XPDR2 SRVC XPDR2 needs service Return unit for repair The G1000 has detected a failure in the specified GTX 33 or GTX 3000 e Replace GTX 33 or GTX 3000 XPDR1 FAIL XPDR 1 is inoperative XPDR2 FAIL XPDR 2 is inoperative The specified GTX 33 or GTX 3000 is not responding Check wiring between GIA s and GTX e Replace GTX 33 or GTX 3000 XPDR1 ADS B FAIL XPDR 1 unable to transmit ADS B message XPDR 2 ADS B FAIL XPDR 2 unable to transmit ADS B message The specified GTX 3000 transponder is not able to transmit ADS B data e Check wiring between GIA s and GPS antenna e Check wiring between GIA s and GTX G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 67 Revision 9 5 14 GDL 69A Troubleshooting 5 14 1 GDL 69A Common Problems Symptom N
352. ply 0 30 VDC 20A capacity DVM Fluke Model 8050A Load Resistor 1 250 watt Stopwatch Capable of measuring to the minute Figure 4 6 Standby Battery Page 4 36 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 4 16 2 Capacity Test NOTE The PS 835 Emergency Power Supply must have completed a full charge prior to any discharge testing This test is performed with the battery removed from the aircraft Press and hold TEST SWITCH Figure 4 6 Item 4 and observe the OUTPUT VOLTAGE MONITOR LED s 1 Ifthe 24VDC OUTPUT VOLTAGE MONITOR LED comes on proceed with Discharge Test procedure 2 If OUTPUT VOLTAGE MONITOR LED s do not come on check fuses at bracket next to battery and replace if blown Perform Cell Isolation Test if no fuses are blown B Discharge Test Load Resistor 1 Prepare for test by first constructing an X Y graph similar to the one shown below If possible use pre printed graph paper to create a record of the discharge period along the X axis and voltage readings along the Y axis NOTE m THESE ARE TYPICAL CURVES AND MAY VARY DUE PS 890A C8 E TO TEMPERATURE TEST EQUIPMENT 251 TYPICAL OUTPUT USING INTERNAL 24 HEATER 7 4 OHMS AS LOAD TYPICAL OUTPUT USING 7 OHM 1 LOAD PIN 11 TO 12 GND REFERENCE MINIMUM ACCEPTABLE 21 DISCHARGE CURVE l I 0 5 10 809 5 35 4 65 Time minute
353. pressing the AP DISC button 14 Hold the control yoke in the forward position and center the pitch trim wheel 15 Engage the autopilot maintain the control yoke in the forward position and keep the pitch trim wheel from rotating for approximately five seconds 16 Quickly release the trim wheel and verify that the red PTRM annunciator is displayed on both PFD 1 and PFD 2 17 Disengage the autopilot and use the pitch trim switch or the pitch trim wheel to trim full down 18 Hold the control yoke in the full forward position 19 Engage the autopilot apply firm aft pressure on the control yoke for approximately 10 seconds allowing the pitch trim wheel to move freely Verify that the amber ELE annunciator is displayed on both PFD 1 and PFD 2 20 Disengage the autopilot and use the pitch trim switch or the pitch trim wheel to trim full up 21 Move the control yoke to the full aft position and hold 22 Press the Go Around button on the throttle and engage the autopilot Apply firm forward pressure on the control yoke for approximately 10 seconds allowing the pitch trim wheel to move freely Verify that the amber ELE annunciator is displayed on both PFD 1 and PFD 2 23 Disengage the autopilot NOTE If the ELE annunciation appears during any of the following steps reset the trim wheel and repeat the test step 24 Use the pitch trim switch or the pitch trim wheel to trim full down 25 Hold the elevator in the neutral positi
354. r Replace GIA2 NAV1 RMT XFR NAV1 remote transfer key is stuck The NAV external remote transfer switch is stuck in the enabled or pressed state Press the NAV1 external remote transfer switch again to cycle its operation Check remote transfer switch and wiring Switch GIA1 and GIA2 to identify whether the unit or connectors wiring is at fault Both GlAs must be configured when swapped see Section 3 9 v If problem follows unit replace GIA1 v If problem persists continue to troubleshoot remote transfer switch amp wiring NAV2 RMT XFR NAV2 remote transfer key is stuck The NAV2 external remote transfer switch is stuck in the enabled or pressed state Press the NAV2 external remote transfer switch again to cycle its operation Check NAV2 remote transfer switch and wiring Switch GIA1 and GIA2 to identify whether the unit or connectors wiring is at fault Both GIAs must be configured when swapped see Section 3 9 Y If problem follows unit replace GIA1 v If problem persists continue to troubleshoot remote transfer switch amp wiring G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 61 Revision 9 5 11 3 Glideslope Alerts service Return unit for repair in G S2 receiver Failure Message Cause Solution G S1 SERVICE G S1 needs The system has detected a failure service Return unit for repair i
355. r swapping units Check the GIA l GRS 77 GRS 7800 1 interconnect wiring for faults Amber GIAT GRS 77 GRS 7800 1 data path functionality is unknown Reload GIAI configuration files CHNL 7 GMA 1347 1 Green GIAI GMA 1347D 1 data path is functioning correctly Red 1347D 1 data path is not functioning correctly e Load GIAI and 13470 1 configuration files e Swap 1347D 1 and GMA 1347 2 reconfigure both GMA s to their new locations to confirm if the problem is in the original GMA 1347D 1 o Replace original GMA 1347D 1 if box turns green after swapping units e Swap GIAI and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIAI o Replace original GIAI if box turns green after swapping units Check the 1 1347D 1 interconnect wiring for faults Amber GIA1 GMA 1347D 1 data path functionality is unknown Reload GIA configuration files Page 5 12 Revision 9 G1000 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 GIA1 ARINC 429 Channel IN2 INS LRU GRS 77 or GRS 7800 2 GDC 74 1 Or GDC7400 1 Indicator Green Status GIAI GRS 77 or GRS 7800 2 data path is functioning correctly Red GIAT GRS 77 or GRS 7800 2 data path is not functioning correctly e Reload GIAI configuration file S
356. r a minimum flight segment of 30 minutes in length The maximum altitude deviation shown on the display throughout the test should not exceed 65 feet If the aircraft fails to hold altitude to this tolerance repeat the test ensuring that the airspeed remains constant and the air remains stable during the entire test If the test still fails have maintenance checks performed on the GFC 700 system then repeat the test RVSM operations are prohibited until the autopilot is capable of maintaining altitude within 65 feet of the selected cruise altitude Aircraft s n Date Enroute To Pilot Time Pilot hr min Altitude Airspeed ft kt Copilot Altitude Airspeed ft kt 0 00 0 05 0 10 0 15 0 20 0 25 0 30 0 35 0 40 0 45 0 50 0 55 1 00 Table 7 9 In Flight Altitude Hold Performance Test Page 7 48 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 25 Safe Flight Lift Computer Ground Calibration NOTE This procedure is required only for aircraft with the optional Electronic Stability and Protection ESP feature with Angle of Attack AoA modes and the Safe Flight Lift Computer p n C 05606 1 Prior to removal of the lift computer it is recommended that Section 7 25 1 be accomplished to record the existing stall warning points for Pots 0 1 and 2 Original C 05606
357. r connectors wiring is at fault Both GIAs must be configured when swapped see Section 3 9 v If problem follows the unit replace GIA v If problem persists replace defective GMA 1347D 1 2 PTT COM push to talk key is stuck The COM external push to talk PTT switch is stuck in the enabled or pressed state Press the push to talk switch s again to cycle its operation Check push to talk switch s and wiring Check GIA2 GMA 13470 2 interconnect Switch GIA1 and GIA2 to identity whether the unit or connectors wiring is at fault Both GIAs must be configured when swapped see Section 3 9 v If problem follows the unit replace GIA2 v If problem persists replace defective GMA 1347D 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 59 Revision 9 Failure Message Cause Solutions Press the COM1 external remote transfer switch again to cycle its operation Check COM1 external remote transfer switch and wiring Switch GIA1 and GIA2 to identify The COM1 external remote whether the unit or connectors wiring is RMT remote transfer switch is stuck in the at fault Both GlAs must be configured y 2 enabled or pressed state when swapped see Section 3 9 Vf problem follows the unit replace GIA1 v If problem persists continue to troubleshoot remote transfer Switch amp wiring Press the 2 exte
358. r faults Replace the standby altimeter or contact the manufacturer for further troubleshooting See Section 6 26 for removal instructions lt 5 25 Safe Flight Lift Computer Troubleshooting Symptom Recommended Action Stall Warning System is not working properly or is invalid Stall Warning Mounting Plate or Vane Heater Inoperative Only Pot 0 provides any adjustment for Stall Warning points Stall Warning Self Test Will Not Work Properly Troubleshoot in accordance with the King Air 200 Series Maintenance Manual listed in Table 1 2 section 27 31 00 Troubleshoot in accordance with the King Air 200 Series Maintenance Manual listed in Table 1 2 section 27 31 00 Troubleshoot in accordance with the King Air 200 Series Maintenance Manual listed in Table 1 2 section 27 31 00 Troubleshoot in accordance with the King Air 200 Series Maintenance Manual listed in Table 1 2 section 27 31 00 Flap Information to the computer is not working properly Display of ESP Alpha Floor Symbology is inoperative or erratic or Advisory Alert ESP DEGRADE ESP AOA Mode is inoperative Troubleshoot in accordance with the King Air 200 Series Maintenance Manual listed in Table 1 2 section 27 31 00 e Insure power is removed from the Stall Warning System e With the aircraft on the ground install the SK100360 Breakout Box per Figure 7 15 Breakout Box and perform the following re
359. ration files GIA Gains file and GSA CANA GEC 900 Red software and gains file if LRU and Card versions are different Reference GFC section for further troubleshooting GIA2 GFC 700 data path functionality is unknown Reload Amber uds GIA2 configuration files Page 5 20 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 22 System Failure Troubleshooting The following table provides basic troubleshooting guidance for LRU failures Refer to G1000 GFC 700 Wiring Diagram listed in Table 1 2 as needed to verify interconnects Invalid Data Field Associated LRU s Solution Low Speed Awareness Band permanently displayed GDU With aircraft weight on wheels and the G1000 in Configuration Mode check that the RH GEAR ON GROUND Discrete In indication for GIA2 on GIA I O CONFIGURATION page is illuminated With aircraft weight on wheels and the G1000 in Configuration Mode check that the LH GEAR ON GROUND Discrete In indication for GIA1 on GIA CONFIGURATION page is illuminated If both indications are illuminated Green switch GIA1 and GIA2 to verify location of problem Y If problem is resolved replace defective unit Y If indication is not illuminated check for wiring faults between the GIAs and aircraft squat switch System Low Speed Awareness Band permanently inhibited GDU With aircraft weight on wheels and the G1000 in Config
360. ration problem is identified and remedied In the event of repeated failure of the engine run up test record the values that are reported to be out of range for future reference The following are potential causes for failure of the engine run up test a Vibration motion of GRS and or GMU44 caused by neighboring equipment and or supports b Mounting screws and other hardware for GRS and or GMU44 not firmly attached c GRS connector not firmly attached to unit d Cabling leading to GRS or GMU44 not firmly secured to supporting structure An engine propeller that is significantly out of balance 7 Press the ENT key on the PFD to conclude this procedure 8 Repeats steps 1 through 7 for GRS 2 and and PFD 2 then proceed to Section 7 7 6 7 7 6 GRS GMU Test The aircraft can now be taxied back and the engine can be shut down for final testing Restart the displays in normal mode to conduct final system checks When the PFDs power up in normal mode the AHRS attitude and heading information displayed should become valid within 1 minute of power up as shown in Figure 7 7 provided both GPS receivers have a valid position if GPS is unavailable AHRS initialization may take as long as 2 minutes m 110 90 110 30 xj apos ALERTS Figure 7 7 Normal Mode AHRS Check If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintena
361. re all configured Servos are communicating by checking for Servo product data in configuration mode PFT step 1 System initialization verify GIA audio is valid This step is checking to make sure that the GIA audio region has been loaded and configured If this step fails load GIA audio region and audio configuration PFT step 2 System initialization verify required servos are configured This step is checking to make sure the current Servo configuration matches the Servo configuration specified in the certification gain file If this step fails then make sure the Servo configuration on the GFC configuration page matches the Servo configuration specified in the configuration gain cgn file PFT step 3 System initialization verify selected side This step is checking to make sure the PFD1 is online and sending the selected AFCS side data over HSDB to GIAI If this step fails then make sure the PFD is powered up and there is an Ethernet connection from the PFD to the GIA PFT step 4 System initialization verify AHRS monitor This step is checking to make sure the AHRS monitor is valid and not reporting an AHRS failure NOTE AHRS monitor will be assumed valid if on the ground If this step fails then make sure the AHRS and ADC is powered up and sending valid attitude data to the G1000 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 37 190 00915 01 Revision 9 PFT step 5 System initializati
362. re condition the following shall occur NAV2 and COMM tuning fields on PFD1 and PFD2 are invalid red X L R engine data remains valid XPDR2 is Inoperative GMAe 15 Inoperative AHRS2 is using backup GPS source AHRS not receiving backup GPS Information An amber ON 51 is displayed on PFD1 and PFD2 AHRS and ADC data remain valid on PFD1 and PFD2 Dual GIA Failure Condition 1 Open GIA1 primary and secondary CBs and GIA 2 CB 2 Check for desired results 3 Restore power to both GIA units For a dual GIA failure the following shall occur COM1 NAV1 amp COM2 NAV2 fields flag invalid GPS CDI flags LOI on PFD NAV1 amp NAV2 CDI loses deviation bar XPDR field flags invalid on PFD Engine Instrument field flags invalid on MFD All AHRS amp ADC fields remain valid Red AFCS status annunciation given TAWS FAIL annunciation given ADF DME windows flag invalid Page 8 2 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 8 1 3 Display Failure Test Step Desired Result MFD Failure Condition 1 Open MFD CB 2 Verify desired results 3 Close MFD For an MFD failure condition the following shall occur e goes blank e All PFD1 and PFD2 primary flight information is retained COM 1 2 and 1 2 tuning fields remain valid and can be tuned by rotating the tuning knobs o
363. re not covered under warranty NOTE Garmin recommends the use of SanDisk or Toshiba brand SD cards to load G1000 software and configuration files If another brand of card is used and software loading problems occur replace the card with a SanDisk or Toshiba brand card and reattempt the software load WARNING Connect a ground power unit to the aircraft for software loading Do not rely on only the aircraft batteries to prevent loss of power during the software loading process DO NOT ALLOW POWER TO BE REMOVED FROM THE SYSTEM WHEN LOADING SOFTWARE Remove power only when told to do so by the following procedure general rule all displays should be in the same mode configuration or normal unless instructed differently 7 1 GDU 1040 1500 MFD amp PFD Original lay Reinstalled If the removed display s are re installed in their original positions no software or configuration loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the PFD MFD Test procedure Original PED Displays Installed in Opposite Locations for Troubleshootin If the PFD 1 and PFD 2 are installed in opposite positions no software or configuration loading is required Continue to the PFD MFD Test procedure New Repair or Exchange Display s Installed If a new repaired or exchange GDU 1040A or GDU 1500
364. re that the vane is free to move with the force applicator 7 Apply external power to the aircraft 8 Place the BATT master switch to the ON position 9 Verify the STALL WARN circuit breaker on the copilot circuit breaker panel is set WARNING Make sure that all personnel are clear of the flap area before proceeding with these procedures 10 Flaps retracted Pot 0 measurement a b d Run the flaps to the full UP position Install voltmeter leads between TP5 Hi and TP2 Lo TP6 Hi and TP2 Lo on the SK100360 Breakout Box Ensure that 28 VDC is not present If the flap information is incorrect troubleshoot in accordance with King Air 200 Series Maintenance Manual procedure 27 31 00 Using the force applicator slowly apply a negative Tip Gram TG force forward UP on the vane until the stall warning horn sounds Record the flaps retracted Pot 0 TG value Return the force on the vane to 0 TG 11 Approach Flaps Pot 1 measurement a b Run the flaps to the APPROACH position Install voltmeter leads between 5 Hi and TP2 Lo 6 Hi and TP2 Lo of the SK100360 Breakout Box Ensure that 28 VDC is ONLY present between 5 and TP2 If the flap information is incorrect troubleshoot in accordance with King Air 200 Series Maintenance Manual procedure 27 31 00 Using the force applicator slowly apply a negative TG force forward UP on vane until the stall warning horn sounds Record the
365. received from the GWX is routed through the GDL 69 data link unit to the MFD via high speed data bus Ethernet Figure 2 17 Weather Radar 2 1 19 GSA 80 Servos and GSM 85A 86 Servo Gearboxes 4 The Garmin GFC 700 AFCS uses GSA 80 high torque servos to automatically control aircraft pitch roll yaw damper turn coordination and pitch trim The pitch trim variant of the GSA 80 is a high speed servo actuator The GSA 80 contains a motor control and monitor circuit board as well as a solenoid and a brushless DC motor The GSA 80 servo receives serial RS 485 data packets from the GIA 63Ws The roll servo is located in the forward cabin lower fuselage at F S 185 The pitch yaw and pitch trim servos are located in the tail Power to the servos is received from the avionics No 2 bus All servos mount to a Garmin GSM 85A or GSM 86 Servo Gearbox The GSM 85A 86 is responsible for transferring the output torque of the GSA 80 servo actuators to the mechanical flight control surface linkage The GSM 85A has a slip clutch that can be adjusted to a desired torque value The GSM 86 has a clutch cartridge that cannot be adjusted to a different torque value Figure 2 18 Servo G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 11 190 00915 01 Revision 9 2 1 20 GRA 5500 Radar Altimeter The GRA 5500 Garmin Radar Altimeter is designed to calculate the height Above Ground Level AGL of the aircraft which is displaye
366. red more than once for a given station the operator should begin turning to the next station approximately 30 A minimum of 2 successful stations per quadrant is required where a successful station is a full 18 second countdown followed by instruction to move Ensure that at least 2 stations per quadrant are completed Thus it may sometimes be required to dwell at a station after a countdown restart A maximum of 30 stations is allowed for the entire calibration procedure If too many countdown restarts are encountered the calibration will fail with the message TOO MANY STATIONS 14 Repeat the turn and stop process until the PFD advises that a successful calibration is complete The GRS AHRS then enters its normal operational mode Press the ENT button on the PFD to conclude this procedure 15 Repeat steps 4 through 14 for GRS 2 and PFD 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 23 190 00915 01 Revision 9 7 7 5 Procedure D Engine Run Up Vibration Procedure m NOTE Calibration Procedure D is performed in order to guarantee that the AHRS mounting is sufficiently rigid and insensitive to vibration This procedure must be performed for both GRS units installed in the aircraft Calibration Procedures A1 and B Sections 7 7 2 and 7 7 4 respectively are not required prior to this procedure GRS GHU CALTERATION CALTERATE Figure 7 6 Engine Run Up Test Page Restart PFD 1 in con
367. rence of 100 KTS Page 8 10 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 14 Press the ALT key on the AFCS mode controller and verify that the ALT annunciation is displayed in green on PFDI and PFD2 with an altitude reference equal to the aircraft altitude within the nearest 20 feet 15 Press the FD key and verify that the mode annunciations and command bars are removed from the display 8 2 3 Autopilot Clutch Overpower Check NOTE The GFC 700 uses electronic torque limiting as well as mechanical slip clutches to limit the maximum servo effort When the system is on the ground the electronic torque limiting is removed allowing manual checks of the slip clutch settings 1 Engage the Autopilot by pressing the AP key on the AFCS mode controller 2 Manually overpower the autopilot clutches in pitch roll and yaw If the Autopilot clutches cannot be overpowered check the GSM 85 clutch torque settings or GSM 86 clutch cartridge Refer to the servo installation drawing listed in Table 1 2 as applicable 3 Actuate and hold PITCH TRIM switch in either the NOSE UP or NOSE DOWN direction to disconnect the autopilot While the trim is running restrain the aircraft pitch trim wheel and verify that the trim clutch can be overpowered If it cannot be overpowered check the GSM 85A clutch torque setting or GSM 86 clutch cartridge Refer to the pitch trim servo installation drawing listed
368. ring for damage inside the GDU connector backshell Y Replace master configuration module wiring and pins Y f problem persists replace master configuration module NOTE New Terrain Obstacle cards Jeppesen Aviation Database and other optional features TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number CNFG MODULE PFD 1 configuration module is inoperative The PFD master configuration module has failed G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 49 Revision 9 Failure Message Cause Solution Reload the display configuration files from SD Loader Card e Reload system configuration files by pressing the UPDT CFG 4 Upload Page in the PFD1 System 7909 Page Group to load configuration files into the configuration module V If message persists check PFD1 config module wiring for faults and replace if necessary Ifissue continues replace PFD1 master configuration A configuration mismatch has module PFD 1 CONFIG PFD 1 occurred between the display and V If problem persists replace the configuration error Config service the Master Configuration Module display req d
369. rious G1000 LRU hardware and software 200 B200 Series King Air 0985 07 This STC allows multiple configurations for the King Air 200 B200 series The correct configuration for a particular aircraft is loaded by choosing the applicable airframe engine propeller configuration Refer to Table 6 of the General Arrangement Drawing Garmin Part Number 005 00421 03 for configuration information for eligible engine and propeller combinations G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 1 1 190 00915 01 Revision 9 IMPORTANT If the technician is unsure of an aircraft s STC configuration perform the following After acknowledgement of the splash screen use the FMS knob on the GCU 477 controller to go to the AUX SYSTEM STATUS page on the In the AIRFRAME section upper right corner the display shows the current G1000 airframe configuration and system software version number The airframe configuration is shown in the AIRFRAME field and the system software version number is shown in the following format SYS SOFTWARE VERSION XXXX XX It correlates to the software image used to load the software to the system EXAMPLE System Software Version 0985 01 Software Image P N 006 B0985 01 Restart the MFD in configuration mode see section 3 7 and use the FMS knob on the GCU 477 controller to go to the GDU AIRFRAME CONFIGURATION page In the AIRFRAME section upper right corner verif
370. rmat on the SD card Ensure files are not necessary or card is empty before proceeding 3 61000 Software Update This wizard will guide you through the process of updating the software in your 51000 integrated cockpit Airframe King Air B200 8300 Version of card Version 098504 4 being created Please enter your SD card in the card programmer and then click New to proceed B Enter SD card Click next once card is inserted Page 3 14 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 8 Ensure the card and correct drive letter is used and click next 51000 Software Update Choose the appropriate drive below and click Nest ror drive is not listed plug it in and click Find ive Storage Card Reader Select the drive letter used by your storage card reader Removable Disk gt Find Drive Select drive ET 9 A window will pop up onto the screen to indicate file progress Transferring Data Copying E aud ran UC Copy of files to selected drive 1000 700 System Maintenance Manual 200 B200 Series King Air Page 3 15 190 00915 01 Revision 9 10 Once successfully completed the following message window will pop up Click Finish to finalize SD card 2 51000 Software Update SGARMIN The update was successfully transferred to your card To complete
371. rming these checks should be thoroughly familiar with the G1000 and 700 Information on the installation and operation of 700 can be found by referring to Sections 6 11 0 and the G1000 in King Air 200 B200 Cockpit Reference Guide listed in Table 1 2 NOTE In the sections that follow an Autopilot disconnect should be accompanied by an aural alert two second tone unless otherwise specified 8 2 1 Pre Flight Test 1 Ifselected ON select the BATT and AVIONICS MASTER PWR switches and ground power unit to OFF After 30 seconds select the ground power unit and BATT and AVIONICS MASTER PWR switches to ON Verify the GFC 700 begins an automatic pre flight test after AHRS and ADC parameters become valid 2 Verify that a white annunciation is displayed PFD1 and PFD2 as shown in Figure 8 4 NN E ET 1209 27 Figure 8 4 Pre Flight Test NOTE A momentarily red annunciation displayed before PFT starts is acceptable 3 Upon successful completion of the test an aural alert will sound and the annunciation will clear The aural alert is generated by either GIA 63W 1 or GIA 63W 2 alternately with each system power up Thus the PFT sequence must be run twice to verify both GIA units are providing the correct aural alert NOTE If the PFT annunciation turns red the test has failed Return to Section 5 for troubleshooting 4 Repeat Steps 3 to test the PFT aural alert for the ot
372. rnal remote transfer Switch again to cycle its operation Check COM2 external remote transfer switch and wiring Switch GIA1 and GIA2 to identify The 2 external remote whether the unit or connectors wiring is COM RMT 2 remote transfer switch is stuck in the at fault Both GIAs must be configured y enabled pressed state when swapped see Section 3 9 v If problem follows the unit replace GIA2 v If problem persists continue to troubleshoot remote transfer switch amp wiring COMI TEMP over temp Check fan wiring and air tubing for proper operation if applicable Reducing tr nemit r power The specified COM transceiver Replace cooling fan if unable to ls reporting a high temperature determine if operating correctly condition and is reducing Replace GIA COM2 TEMP 2 over temp transmit power to prevent Reducing transmitter power damage e if problem persists contact Garmin Aviation Product Support for assistance Page 5 60 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 11 2 NAV Alerts Failure Message NAV1 SERVICE NAV1 needs service Return unit for repair Cause The system has detected a failure in NAV1 receiver Solution Replace GIAt NAV2 SERVICE NAV2 needs service Return unit for repair The system has detected a failure in NAV2 receive
373. rossing Descend voice TCAS Resolution Advisory Descend at the rated depicted by the olid green bar on the vertical speed tape on the PFD Safe separation achieved by descending through the threat s flight path Maintain Vertical Speed Maintain voice TCAS Resolution Advisory Maintain the existing climb or descent rate as depicted by the solid green bar on the vertical speed tape on the PED Safe separation is achieved by not altering the existing vertical speed Maintaing Vertical Speed Crossing Maintain voice TCAS II Resolution Advisory Maintain the existing climb or descent rate as depicted by the solid green bar on the vertical speed tape on the PFD Safe separation is achieved by not altering the existing vertical speed and climbing or descending through the threat s flight path Increase Climb Increase Climb voice TCAS II Resolution Advisory Climb at the rate depicted by the solid green bar on the vertical speed tape on the PFD Received after a CLIMB resolution advisory and indicates additional climb rate is required to achieve safe vertical separation from the maneuvering threat aircraft Increase Descent Increase Descent voice TCAS II Resolution Advisory Descent at the rate depicted by the solid green bar on the vertical speed tape on the PFD Received after a DESCEND resolution advisory and indicates additional Descent rate is required to achieve saf
374. rsity interface with a transponder antenna mounted to the bottom of the fuselage Each GTX diversity transponder GTX33D and GTX 3000 interfaces to a transponder antenna mounted to the top of the fuselage GTX 330 GTX 3000 TU Figure 2 5 Transponder Page 2 4 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 2 1 GIA 63W Integrated Avionics Unit 2 Two Garmin GIA 63W Integrated Avionics Units IAUs contain the VHF COM NAV receivers WAAS GPS receiver Flight Director and system integration microprocessors The GIAs also serve as a communication interface to all other G1000 LRUs in the system Each GIA 63W communicates directly with the on side GDU 1040A display using HSDB Ethernet connection Both GIAs are located remotely in the nose equipment bay GIA 1 receives primary electrical power from the Essential Bus and a secondary electrical power supply from Dual Fed Bus No 1 GIA 2 receives electrical power from Dual Fed Bus No 2 The GIA 175 COMM power supply COMM 1 is provided by the Essential Bus GIA 275 COMM power supply COMM 2 is provided by Avionics Bus No 1 Therefore both GIAs power up immediately with external or aircraft power or battery operation with the exception of COMM 2 operation which will become active after selection of Avionics Master on Both GIA 63Ws interface to the following equipment Existing VOR LOC Glideslope Antenna System
375. rts is displayed in blue text adjacent to CHART 4 Verify the FliteCharts database cycle number is displayed in blue text and the FliteCharts database is current 5 Deactivate the cursor and use the GCU large FMS knob to select the Navigation Map Page then press the SHW CHRT softkey 6 Verify the airport chart is displayed and the following softkeys are displayed some softkeys may be grayed out CHRT DP STAR APR WX NOTAM e 7 Press CHRT OPT softkey and verify the following softkeys are displayed some softkeys may be grayed out ALL HEADER e PLAN PROFILE e MINIMUMS FIT WDTH e FULL SCN BACK If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 37 190 00915 01 Revision 9 7 17 ChartView Functional Check ChartView must be enabled using a ChartView Enable Card as specified in the General Arrangement Drawing listed in Table 1 2 and a current ChartView database Reference section 3 39 ChartView Configuration for enabling procedures NOTE The required ChartView databases are subscription based and are to be procured by the aircraft owner directly from Jeppesen 1 With the G1000 in Normal Mode use the GCU FMS knob to select AUX System Status page then select MFD1 DB softkey 2 Use the small
376. ry or the configuration module fail loss of some or all air data outputs will result GDC 748 Internal Memory Contains internal sensor calibration data that is not installation specific Data is stored from factory calibrations GDC 7400 The GDC 7400 stores GDC configuration file internally The GDC 7400 also stores factory calibration data internally Should internal memory fail loss of some or all air data outputs will result GDC 7400 Internal Memory Contains internal sensor calibration data that is not installation specific Data is stored from factory calibrations Figure 3 15 GRS GDC Configuration Settings Storage Page 3 18 G1000 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 3 9 G1000 Software Configuration Procedure This section summarizes the procedures required to load software and configuration files to the G1000 It is intended to work as a central guide for technicians to use while performing maintenance on the aircraft In sections of this manual where software is required to be reloaded these sections will make reference back to this Section for instructions The technician should use proper judgment regarding the context of maintenance required while following this section The following diagram depicts an overview of the software configuration sequence for the G1000 system This applies mostly to a new G1000 system which ha
377. s PS 835B D amp F 25 _ TYPICAL OUTPUT USING INTERNAL 227 HEATER 7 4 OHMS AS LOAD TYPICAL OUTPUT USING 7 OHM 1 LOAD PIN L 11 TO 12 GND REFERENCE MINIMUM ACCEPTABLE 2 DISCHARGE CURVE aL Ld 0 10 20 30 409 60 70 Time minutes 2 Position all INDIVIDUAL CELL DIP SWITCHES Figure 4 6 Item 5 to the ON position If the INDIVIDUAL CELL MONITOR LED DS12 is the only LED not illuminated proceed to the Cell Isolation Test 3 Connect Digital Voltmeter leads to J1 connector pins 11 and 7 4 Connect the Load Resistor across J1 connector pins 11 and7 and start timing the discharge period with a stopwatch G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 37 190 00915 01 Revision 9 5 Monitor and plot voltage values at 10 minute intervals 6 Note voltage on Digital Voltmeter at 48 0 minutes PS 835D or at 20 0 minutes PS 835C This voltage must be greater than 20 0 Vdc All INDIVIDUAL CELL MONITOR LED s Figure 4 6 Item 1 must remain on b Any LED that does go OFF will represent a defective individual cell which must be replaced 7 Remove the Load Resistor from J1 connector pins 11 and 7 8 Position all INDIVIDUAL CELL DIP SWITCHES Figure 4 6 Item 5 to the OFF position 9 Compare the voltage vs time plot created during this test to that of curve identified as typical for the External Load test method on the chart
378. s The Entertainment Bus is a new bus added by this STC It is powered from the No 2 Avionics bus via a newly installed Entertainment Bus relay This relay is controlled via the existing Cabin Furnishing switch so that bus can be easily shed by pilot using single switch action along with the other cabin equipment Emergency Standby Battery The Standby Emergency Battery STBY BATT system in the King Air 200 B200 is designed to provide uninterrupted DC power to the Standby Attitude indicator including gyro motor and internal instrument lighting the Standby Altimeter including vibrator and internal instrument lighting and the Standby Airspeed Indicator internal instrument lighting from the L 3 PS 835 C or D Model Emergency Standby Battery This standby battery power is independent from the normal electrical system and provides redundant power for the standby instruments in the event that all other electrical power is lost G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 15 190 00915 01 Revision 9 i Figure 2 20 200 B200 Electrical
379. s and press ENT key on PFDI 3 Rotate the small FMS knob to highlight King Air Traffic System Option Press ENT key on PFDI 4 Verify the King Air Traffic System Option is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor Page 3 46 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 34 Lightning System Option Configuration Follow this procedure to enable the lightning system option WX 500 for the G1000 system if required Follow Section 3 31 1 once the following steps are complete 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the System Upload page using the PFD1 small FMS knob 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Airframe Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight King Air Lightning System Option Press ENT key on PFDI 4 Verify the King Air Lightning System Option is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify
380. s King Air Page v 190 00915 01 Revision 9 Figure 4 5 Ambient Temperature Conversion Chart Figure 4 6 Standby Battery Figure 4 7 Power Supply Connection Figure 4 8 Exterior Skin Inspection Around Antennas Figure 5 1 AUX System Status Page Figure 5 2 Alerts amp Annunciations Figure 5 3 ADVISORY Softkey Annunciation Figure 5 4 System Annunciations Figure 5 5 AFCS Annunciation Field Figure 5 6 Status Page Figure 5 7 Magnetometer Interference Test Figure 5 8 GIA 63W Backplate Connectors Figure 5 9 GEA 71 Backplate Connectors Figure 5 10 GMA 1347D Backplate Connectors Figure 5 11 GTX 33 33D Backplate Connectors Figure 5 12 GTX 3000 Connectors P3301 and P3302 Figure 5 13 GDU 1040A 1500 Backshell Connector P10401 or P15001 Figure 5 14 GRS 77 Backshell Connector 771 Figure 5 15 GRS 7800 Backshell Connector P78001 Figure 5 16 GDC 74B Backshell Connector 74 1 Figure 5 17 GDC 7400 Mating Connector P74001 Figure 5 18 GDL 69A Backplate Connector P69A 1 Figure 5 19 GCU 477 Backshell Connector P4751 Figure 5 20 GMC 710 Backshell Connector P7101 Figure 5 21 GWX 68 Backshell Connector P681 Figure 5 22 GWX 70 Backshell Connector P751 Figure 5 23 GTS 820 850 Mating Connectors P8001 and P8002 Figure 5 24 GTS 820 850 Mating Connector P8003 Figure 5 25 GTS Processor Connector P8001 Figure 5 26 GPA 65 Mating Connector P651 Figure 5 27 Signal Conditioner
381. s completed or confirmed When the CALIBRATE field is blinking press the ENT key to begin the procedure The PFD display advises the operator when to turn the aircraft when to stop and when to turn again Upon instruction to turn taxi the aircraft in a right turn After approximately 25 to 30 of turn from the last heading the PFD display advises the operator to stop the aircraft NOTE Due to the difficulties in executing smooth accurate turns the PFD may incorrectly interpret a station and instruct to HOLD POSITION prior to full completion of a 30 turn If this scenario is encountered it is best for the operator to ignore the HOLD POSITION command and instead use outside references to complete the approximate Page 7 22 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 30 turn Instead of using the PFD instruction to turn as a real time indication of when to turn simply judge the 30 59 turn increments of the aircraft by using the compass rose radials Dwelling at these 30 increments for the time recommended by the PFD should result in successful calibration 13 The PFD guides the operator to dwell at multiple headings around a complete circle NOTE Due to high winds or excessive airframe vibration the operator may encounter a condition where the PFD restarts the 18 second countdown without full completion of the previous countdown If this is encounte
382. s not previously been powered up and is for informative purposes only GDU 1040A PFDs GDU 1500 MFD Software Load Software is first loaded to the MFD and PFDs From the factory G1000 units do not contain useable software or configuration settings Load software to PFD2 first then MFD and finally to PFD1 G1000 System Upload Selection After software is loaded to the MFD and PFDs the displays should be placed in configuration mode Using PFD1 the technician goes to the System Upload page From the System Upload page software files are selected to create an automated profile to load Once all desired files are checked the G1000 automatically loads the selected files in the correct sequence to the LRUs G1000 System Software Verification After software is loaded to the system the technician verifies that each LRU reports the correct version and software part number G1000 System Configuration Upload Selection Following G1000 system software upload and verification the aircraft specific configuration files as defined in the general arrangement drawing are loaded The aircraft general arrangement drawing will define the configuration files appropriate to the specific aircraft serial number STC modifications and applicable AFMS G1000 Configuration Verification After system configuration files are loaded the technician verifies that the correct configuration on the Airframe Configuration page
383. s on own aircraft at a rate of 0 1 NM sec Verify that only a single target is displayed in the expected quadrant The intruder should transition from Other Traffic displayed as an open diamond with 03 displayed above to proximate traffic displayed as a filled white diamond with 03 displayed above to a Traffic Advisory TA alarm yellow filled circle with 03 displayed above For GTS 8000 installations with TCAS II the following applies The intruder should transition from a Traffic Advisory displayed as a solid yellow circle with 03 displayed above to a Resolution Advisory RA alarm red filled square with 03 displayed above Additionally a Resolution Advisory is displayed on the vertical speed tape of PFDI and PFD2 indicating guidance to the crew solid red bar with vertical speeds to avoid and solid green bar with suggested vertical speeds An audible Resolution Advisory i e DESCEND DESCEND is heard over cockpit speakers and headphones NOTE The aural TA annunciations are muted if the gear is extended and the Radar Altimeter indicates below 400 feet For GTS 8000 to generate the DESCEND resolution advisory the WOW actuators must be in set in air position and the Radar Altimeter must be set to greater than 2 000 ft e g disconnect receive antenna coaxial cable from the GRA 5500 At the end of these tests engage the Radar Altimeter circuit breaker if installed if disengaged at the beginning o Section 8 7
384. s the FPL key to open the ACTIVE FLIGHT PLAN page Press the FPL key again to close it 18 Press the PROC key to open the PROCEDURES page Press the PROC key again to close it 19 Press the MENU key to open the MENU page Press the MENU key again to close it 20 Press the COMM keyuntil 1 is lit Verify the tuning box is present around the COMM 1 frequency UNO Me A on PFDI 21 Using GCU477 keypad enter a frequency of 123 450 Verify COMMI frequency changes as entered 22 Press the COMM keyuntil 2 is lit Verify the tuning box is present around the COMM 2 frequency on PFDI 23 Using GCU477 keypad enter in a frequency of 123 450 Verify COMM frequency changes as entered 24 Press NAV key until 1 is lit Verify the tuning box is present around the NAV 1 frequency on PFDI 25 Using GCU477 keypad enter in frequency of 108 00 Verify NAVI frequency changes as entered G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 27 190 00915 01 Revision 9 26 27 28 29 30 31 Press the NAV key until 2 is lit Verify the tuning box is present around the NAV 2 frequency on PFDI Using GCU477 keypad enter in a frequency of 108 00 Verify NAVI frequency changes as entered Press the XPDR key until the light to the left of the button is lit Verify a flashing box appears in the XPDR 1 code window Using GCU477 keypad enter in a code of 1234 Verify XPDRI shows a code of
385. s the integrity of the Cabin Location individual shields and their attachment GSR 56 a Inspect the GSR 56 unit if installed shelf brackets and connectors for iridium option only corrosion or other defects Check the integrity of the shield block ground attachments to the harness connector assembly as well as the integrity of the Cabin Location individual shields and their attachment a Using flashlight inspect the roll servo servo gearbox connectors support structure and control cables to ensure that no corrosion chaffing cracks or other defects exist b IfGSM 86 servo gearbox is installed check that the retaining bolt for the slip clutch cartridge is not damaged or loose an assistant manually move the aileron control surfaces from stop to stop and visually observe the servo and control cabling chain Ensure there is no binding in the control cabling or chain and that the capstan sprocket rotates freely GFC 700 Equipment d Check the servo control cables in accordance with AC 43 13 1B Chapter 7 Section 8 Paragraph 7 149 to ensure no fraying corrosion or other damage exists If the condition of any cable is questionable replace it with a new one e Check the tension on the control cables Refer to the Roll Servo Install drawing listed in Table 1 2 for cable tension specifications f Ensure that each cable is correctly attached to the clamps g Follow recommended checks for checking main
386. s to confirm if the problem is in the original GIA2 o Replace original GIA2 if box turns green after swapping units e Swap GRSI and GRS2 no reconfiguration required to confirm if the problem is in the original GRS1 o Replace original GRS1 if box turns green after swapping units e Check the GIA2 GRS 77 GRS 7800 1 interconnect wiring for faults Amber Green GIA2 GRS 77 or GRS 7800 1 data path functionality is unknown Reload GIA2 configuration files GIA2 GDC 2 data path is functioning correctly Red GIA2 GDC 2 data path is not functioning correctly e Load GIA2 and GDC 2 configuration files e Swap GIA2 and GIAI reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA2 o Replace original GIA2 if box turns green after swapping units Check the GIA2 GDC 2 interconnect wiring for faults Replace GDC 2 if problem remains Amber GIA2 GDC 2 data path functionality is unknown Reload GIA2 configuration files G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 17 190 00915 01 Revision 9 G GIA2 GRS 77 or GRS 7800 2 data path is functioning correctly GIA2 GRS 77 or GRS 7800 2 data path is not functioning correctly e Load GIA2 configuration files e Swap GIA2 and GIAI reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA2 ade Ge
387. s to confirm if the problem is in the original GIAI o Replace original GIAI if box turns green after we GRS 77 or Bed swapping units GRS 7800 1 e Swap GRSI and GRS2 no reconfiguration required ref GRS Configuration and Testing sections to confirm if the problem is in the original GRSI Replace original GRS1 if box turns green after swapping units Check the GIAI GRS 77 or GRS 7800 1 interconnect wiring for faults Amber GIAI GRS 77 GRS 7800 1 data path functionality is unknown Reload GIAI configuration files Page 5 14 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 GIA2 RS 232 Channel CHNL 1 2 CHNL 5 LRU GDC 74B 2 Or GDC 7400 2 GRS 77 or GRS 7800 1 output only GTX 33ES 3000 2 w TIS Indicator Green Status GIA2 GDC 2 data path is functioning correctly Red GIA2 GDC 2 data path is not functioning correctly e Load GIA2 and GDC 2 configuration files e Swap GIA2 and GIAI reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA o Replace original GIA2 if box turns green after swapping units e Check the GIAI GDC 2 interconnect wiring for faults Replace GDC 22 if problem remains Amber White N A Green GIA2 GDC 2 data path functionality is unknown Reload GIA2 configuration files GIA2 GRS 77 or GRS 7800 1 output data path is not monitored
388. sages are played e Too Low Terrain e Sink Rate e Pull Up e Don t Sink e Five Hundred Caution Terrain 2X Terrain 2X Pull Up 2X Caution Obstacle 2X Obstacle 2X Pull Up 2X e Terrain Ahead 2X e Terrain Ahead Pull Up 2X Obstacle Ahead 2X Obstacle Ahead Pull Up 2X 11 Pull the PFD1 PRI and PFDI SEC circuit breakers and re power PFDI in normal operating mode If no other service is to be performed continue to the return to service checks in Section 8 Page 7 34 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 15 2 Functional Check for TAWS A 1 With the G1000 in Normal Mode use GCU FMS knob to select the MAP group and TAWS page on the MFD 2 Verify that the title at the top of the page reads MAP TAWS A NOTE If TAWS has not been enabled the title will read MAP TERRAIN PROXIMITY or MAP TERRAIN Refer to section 3 40 for TAWS Configuration for configuring TAWS 3 Press the GCU MENU button and select Test TAWS System from the pop up menu Verify TAWS test annunciation is displayed on the MFD and both PFDs 4 After test has completed verify that System Test Okay is heard over the cockpit speaker if selected and the headsets 5 Press the GCU MENU button again and select Inhibit TAWS from the pop up menu and press ENT on the GCU Verify TAWS INH is disp
389. se Solutions e Load GWX configuration files e Replace GWX e If problem persists replace master configuration module check config module wiring for faults and replace if necessary NOTE GWX CONFIG GWX configuration 01000 has detected a peser Allen Debates Md error Configuration service GWX 68 or GWX 70 required configuration mismatch other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number e Check Ethernet connection The G1000 has detected a between the GWX and GDL69A GWX FAIL GWX is inoperative failure in the GWX 68 or GWX io tats 70 Replace the GWX 68 GWX 70 GWX SERVICE Needs service 01000 has detected a Return unit for repair failure GWX 68 or GWX 70 7 Replace the GWX 68 or GWX 70 The system has detected an MANIFEST GWX software incorrect software version t Load aofiare version mismatch Communication halted loaded in the GWX 68 or GWX Poche oe ee 70 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 77 190 00915 01 Revision 9 5 18 710 Troubleshooting 5 18 1 GMC 710 Alerts and Problems Failure Message
390. series aircraft it is critical that the technician install correct software image part number when servicing the G1000 system Approved software image part numbers are defined on the appropriate General Arrangement drawing see Table 1 2 CAUTION Be cautious when using software loader cards during maintenance The G1000 system immediately initializes the card upon power up On screen prompts must be given careful attention in order to avoid potential loss of data Always read through procedures given in Sections 5 6 and 7 before attempting to use the software loader cards Page 3 12 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 8 2 Loader Card Creation The software image is an executable self extracting file which builds the correct file structure onto an SD card for use loading software to the G1000 and GFC700 To create a software loader card follow the procedures outlined below NOTE In order to create a 200 B200 loader card the individual facility completing these procedures must be an authorized King Air 200 B200 service center to gain access to the necessary data via the Garmin website 1 Goto www garmin com and click on the Dealer Resource Center link in the lower portion of the home page Enter username and password Sign In Username g username mall com Password signing in you agree to the Garmin Conficenselty Agreement
391. sical card may say unlock If uncertain the technician should verify the card part number prior to use Coordinate the GTS Processor TCAS 1 configuration with Section 7 27 GTS Traffic System Functional Check 1 With the TCAS I Enable card in the top slot of in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on MED 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight GTS Processor Enablement and press ENT key on MFD 3 Rotate the small FMS knob to select GTS Processor TAS to TCAS I Enablement Press ENT key on MED 4 Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on MFD to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the TCAS I Enable card from MFD G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 63 190 00915 01 Revision 9 3 47 Optional Garmin TCAS Enable From GTS 825 to GTS 8000 Follow this procedure to enable TCAS function A TCAS II Enable Card as specified on the General Arrangement Drawing 005 00421 03 will be required for this procedure NOTE The G1000 has various features
392. sing GEA Status page Load GIA2 and configuration files Swap GIA2 and GIAI reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA2 o Replace original GIA2 if box turns green after CHNL 1 Red swapping units Swap and GEA2 reconfigure both GEA s to their new locations to confirm if the problem is in the original GEAI o Replace original GEA1 if box turns green after swapping units Check the GIA2 GEAL interconnect wiring for faults A GIA2 GEA data path functionality is unknown Reload GIA2 mber configuration files Green GIA2 GEAQ data path is functioning correctly GIA2 GEAQ data path is not functioning correctly e Verify GEA2 is powered on using GEA Status page Load GIA2 and GEA2 configuration files Swap GIA2 and GIAI reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA2 o Replace original GIA2 if box turns green after CHNL 2 GEA2 Red swapping units Swap GEA2 and reconfigure both GEA s to their new locations to confirm if the problem is in the original GEA2 o Replace original GEA2 if box turns green after swapping units Check the GIA2 GEA2 interconnect wiring for faults GIA2GEA2 data path functionality is unknown Reload GIA2 Amber E configuration files Green GIA2 GFC 700 data path is functioning correctly GIA2 GFC 700 data path is not functioning correctly e Load GIA2 configu
393. sistance measurements per the table below Test Points TP on SK100360 Breakout Box Expected Readings 24 25 140 28 ohms 26 27 320 64 ohms 28 27 320 64 ohms lt Ifthe resistances are not within the ranges specified check the aircraft wiring between the computer and the transducer in accordance with the appropriate Hawker Beechcraft wiring diagram lt Ifthe wiring between the computer and the transducer is good replace the transducer If the resistances are within the ranges specified check that there is a ground on TP 2 e Ifall the resistances are within the ranges specified and there is a ground on TP 2 apply power to the Stall Warning System Lift Computer and check for the presence of 28 VDC from the aircraft circuit Breaker C B on TP 1 Hi and TP 2 Lo Ifthe 28 VDC is missing check the C B lt 28 VDC power to the computer is present check the transducer excitation voltage on TP 24 Hi and TP 25 Lo The voltage should be 10 5 VAC at 720 72 Hz Page 5 90 Revision 9 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 If the excitation voltage is not within the ranges specified replace the computer If the excitation voltage is within the ranges specified check the LAA output on TP 18 Lo and TP 19 Hi The output is a varying DC voltage based on the transducer vane position The output from the computer with the vane in
394. solved simply by pressing the SET gt ACTV softkey which reloads settings to the specific LRU from the PFD Note that this can also be accomplished by reloading the configuration files for the LRU Section 7 describes this process for each LRU Page 3 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 A blank active column as shown in Figure 3 11 represents loss of communication between the display and the particular unit See Section 5 for more details on troubleshooting REZ cm 2 mae Figure 3 11 Loss of Communication 3 7 2 Configuration Prompts When configuration settings are changed the technician receives on screen prompts and or confirmations such as those shown in Figure 3 12 Section 7 shows other prompts encountered during the configuration process CONFIGURING GIA 1 GIA 1 CONFIGURED OK Figure 3 12 Configuration Status 3 7 Data Transmission Indicators Several configuration screens utilize an indicator light system to show discrete ON OFF data and or hardware component status Unless otherwise noted the following applies to all such status indicators e Green Checkmark Expected data is successfully received and is ON A green check could also indicate that the parameter component is working correctly Red X Expected data is not received red X could also indicate tha
395. ss rose is an acceptable location to perform the magnetometer calibration procedure However because not all compass roses are well maintained even an existing compass rose should be regularly evaluated using the method described here to determine if it is free of magnetic disturbances If evaluation of an existing compass rose indicates that magnetic disturbances are present then an alternative location must be found to perform the Magnetometer Calibration Procedure A G1000 equipped airplane that has completed the pitch roll offset compensation procedure Procedure A 1 Section 7 7 2 can be used to evaluate a candidate site for magnetic disturbances and determine whether it is a suitable location to perform the magnetometer calibration procedure The magnetometer calibration procedure itself contains the logic to simultaneously survey the location for magnetic cleanliness while it is computing the magnetometer calibration parameters In order to evaluate a candidate site the Magnetometer Calibration Procedure must be performed twice once turning clockwise around the site and once turning counter clockwise Both times the procedure should be conducted as described in Section 7 7 4 of this document with the exception of the direction of turns around the site NOTE Although Section 7 7 4 indicates that the Magnetometer Calibration Procedure should be performed by making a series of clockwise turns around the site the procedure can also b
396. t and retain the ground strap and associated hardware for reinstallation on the new unit Reinstallation 1 2 Reinstallation of the Signal Conditioners is the reverse of the removal Note that the p n 85 292 2 and 85 292 4 units are interchangeable Reference the Main Instrument Panel Installation drawing listed in Table 1 2 for more details Proceed to Section 7 4 1 for testing G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 15 190 00915 01 Revision 9 6 23 Instrument Panel Annunciators Prop Synch and Standby Battery Removal 1 Remove from the instrument panel as per Section 6 1 2 Using a M22885 108T8234 extraction tool disconnect connector from the back of the switch 3 Pull the pushbutton cap fully out of the switch body and allow the cap to rotate 90 where it is held by the retaining element 4 While holding the retaining sleeve back side of the instrument panel loosen the two screws inside the switch body until the switch is free to come out 5 Remove the mounting sleeve and switch from the instrument panel Reinstallation 1 Reinstallation of the Prop Synch and Standby Battery switches is the reverse of the removal Reference the Main Instrument Panel Installation drawing listed in Table 1 2 for more details 2 Press and hold the cockpit annunciator Press To Test switch located to the left of the annunciator panel and verify the following e For the Sta
397. t a parameter component is invalid e White N A Expected data is OFF or no data is expected GDU STATUS XILINK BASE MAP ETHERNET 2 ETHERNET 3 ETHERNET 4 RS 232 1 RS 232 2 IRDA Figure 3 13 Data Transmission Indicators G1000 700 System Maintenance Manual 200 B200 Series King Air Page 3 9 190 00915 01 Revision 9 3 7 4 Configuration Mode Navigation Using the FMS knob as described in Section 3 1 2 a user can navigate through different pages and page groups in the Configuration Mode For complete description and breakdown of each page refer to the G1000 System Maintenance Manual listed in Table 1 3 S 2 3 4 system Page Group System Status Time Configuration Lighting Configuration System Audio 5 System Upload 9 System Data Path Configuration 6 Diagnostics Terminal 10 System Setup 7 OEM Diagnostics 11 Manifest Configuration 8 System Configuration 12 Maintenance Log System Page Group Aircraft equipped with GDU v13 06 or later 1 System Status 6 Aircraft Configuration 11 System Data Path Configuration 2 Time Configuration 7 File Manager 12 System Setup 3 Lighting Configuration 8 Diagnostics Terminal 13 Manifest Configuration 4 System Audio 9 OEM Diagnostics 14 Maintenance Log 5 System Upload 10 System Configuration GDU Page Group 1 Serial Configuration 5 Ethernet Test 9 Airframe Configuration 2 CDU Status Page 6 Video Test 10
398. t each marker audio signal is present over the pilot and co pilot headphones and speaker 2 Verify that the outer middle and inner annunciations appear PFD 1 and PFD 2 when the corresponding signal is applied Marker beacon annunciations appear at the upper left corner of the altitude indicator on the PFD Figure 7 2 Operate the MKR MUTE key on the 1 and 2 GMA 1347D and ensure that the audio signal is muted If no other service is to be performed continue to the return to service checks in Section 8 Page 7 4 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 2 2 Landing Gear Aural Alert Check This check should be conducted in conjunction with the Phase 2 and Phase 4 Landing Gear Retraction Warning Horn check in the existing King Air Maintenance Program NOTE This procedure is applicable only to aircraft equipped with a tone generator as part of the aircraft audio system Refer to the appropriate aircraft wiring diagrams to determine if a tone generator is installed This check can be accomplished in conjunction with the Weight on Wheels and Low Speed Awareness Band Test in Section 7 23 1 Conduct the Landing Gear Retraction Warning Hom check as stated the King Air 200 Series Maintenance Manual listed in Table 1 2 2 Verify that the aural tone is played through the G1000 audio system and through both cockpit speakers 7 2 3 XM Audio Suppression Check This proce
399. t the GMA 1347D into the rack until the locking tab engages the rack 3 Begin to turn the hex nut clockwise This draws the unit into the rack until seated Do not over tighten the nut 4 Configure and test the GMA 1347D according to Section 7 2 Page 6 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 6 3 GIA 63W Integrated Avionics Units Removal 1 Gain access to the forward avionics compartment in the nose of the aircraft 2 Unlock the GIA 63W handle by loosening the Phillips screw on the handle 3 Pull the handle upward to unlock the GIA 63W Gently remove the unit from the rack Reinstallation 1 Visually inspect the connectors to ensure there no bent or damaged pins Repair any damage Gently insert the GIA 63W into its rack The handle should engage the dogleg track Press down on the GIA 63W handle to lock the unit into the rack Lock the handle to the GIA 63W body using the Philips screw Configure and test the GIA 63W s according to Section 7 3 De dE GBD 6 4 GEA 71 Engine Airframe Unit Removal 1 Gain access by removing the appropriate GDU 1040A display unit see Section 6 1 2 Unlock the GEA 71 handle by unscrewing the Phillips screw 3 Firmly grasp the GEA 71 handle and pull it up vertically This unlocks the unit from the rack 4 Gently remove the GEA 71 from its rack Reinstallation 1 Visually inspect the connectors to ensure there are no bent or da
400. tance if needed MFD1 DB ERR MFD1 obstacle database error exists The MFD has encountered an error in the obstacle database PFD 1 DB ERR PFD 1 obstacle database error exists PFD 2 DB ERR PFD 2 obstacle database error exists The specified PFD has encountered an error in the obstacle database Confirm supplemental data card is inserted fully Reload the database or replace the supplemental datacard Contact Garmin product Support for further assistance if needed MFD1 DB ERR MFD1 airport terrain database error exists The MFD has encountered an error in the airport terrain database PFD 1 DB ERR PFD 1 airport terrain database error exists PFD 2 DB ERR PFD 2 airport terrain database error exists The specified PFD has encountered an error in the airport terrain database Confirm supplemental data card is inserted fully Reload the database or replace the supplemental datacard e Contact Garmin product Support for further assistance if needed DB MISMATCH Aviation database version mismatch Xtalk is off The system has found the Jeppesen aviation database cycles in the PFDs and or MFD do not match Load current aviation database versions to all displays DB MISMATCH Aviation database type mismatch Xtalk is off The system has found the Jeppesen aviation database types in the PFDs and or MFD do not match i e differ
401. te illuminated arrowhead points in the opposite direction Verify the green arrow displayed at the top of PFD 1 also points in the same direction 4 Rotate the ALT SEL knob and verify the altitude bug displayed on PFD 1 altitude tape moves 5 Rotate the UP DN wheel and verify the flight director moves in the vertical direction 6 Press the HDG key and verify the white illumination appears next to the key Rotate the HDG knob and verify the heading bug displayed on PFD 1 compass card moves and the flight director follows 7 Press the HDG knob and verify the heading bug centers 8 Press the YD key and verify the white illumination appears next to the key 9 Press the VS key and verify the white illumination appears next to the key 10 Press the FLC key and verify the white illumination appears next to the key If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 29 190 00915 01 Revision 9 7 12 GWX 68 or GWX 70 Weather Radar Original GWX 68 or GWX 70 Reinstalled No software or configuration loading is required if the removed GWX 68 or GWX 70 is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the GWX 68 or GWX 70 Test Section 7 12 1 New Repaired or Exchange GWX 68 or GWX 70 Installe
402. th is not functioning correctly e Verify GCU 477 is powered on o If GCU 477 will not power on remove unit and verify power and ground are present at the GCU connector f power or ground is not present troubleshoot aircraft wiring for faults If power and ground are present replace GCU 477 Load and GCU 477 configuration files Check MFDI GCU 477 interconnect wiring for faults Replace GCU 477 Replace MFD if problem remains Amber MFDI GCU data path functionality is unknown Reload MFDI configuration file Page 5 10 Revision 9 G1000 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 5 2 1 2 GIA RS 232 ARINC 429 CONFIG Page RS 232 Channel 1 Indicator Status Green GIA1 GDC 1 data path is functioning correctly GIAI GDC 1 data path is not functioning correctly e Load GIAI and GDC 1 configuration files e Swap GIAI and GIA2 reconfigure both GIA s to their new GDC 74 1 ENS locations to confirm if the problem is in the original GIAI CHNL 1 Or o Replace original GIAI if box turns green after GDC7400 1 swapping units Check the GIA L GDC 1 interconnect wiring for faults Replace GDC 1 if problem remains GIA1 GDC 1 data path functionality is unknown Reload amber GIAI configuration files GRS 77 or CHNL 2 GRS 7800 2 White N A output only GIAT GRS 77 or GRS 7800 2 output data path
403. that require the use of unlock enable cards to activate the feature Throughout this document these cards are generically referred to as enable cards In some cases the actual label on the physical card may say unlock If uncertain the technician should verify the card part number prior to use Coordinate the GTS Processor TCAS II configuration with Section 7 27 GTS Traffic System Functional Check 1 With the TCAS II Enable card in the top slot of MFD in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on MFD 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight GTS Processor Enablement and press ENT key on MFD 3 Rotate the small FMS knob to select GTS Processor TAS to TCAS II Enablement Press ENT key on MFD Press LOAD softkey 4 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 5 Press ENT key on MFD to acknowledge upload complete 6 De activate the cursor 7 Power down the system and remove the TCAS II Enable card from MFD Page 3 64 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 48 Aircraft Registration Number Entry NOTE This section is only applicable to those aircraft that
404. the ENT key d The log will appear in the OUTPUT box It will scroll to the end automatically When it is complete repeat steps a c for the other servos in the aircraft Be sure to note the order the servos were downloaded in including the Monitor or Control logs to email to Garmin Product Support Without knowing the order in which the logs were downloaded Garmin will be unable to process them and will ask for another full download Press the LG2CRD softkey to turn off the recording function Wait 1 minute for the system to save the data from the download to the SD card Page 5 44 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 12 While you are waiting for the data to be saved to the SD card record the order of the LRU s and or Servos were downloaded so that you can provide that information to Cessna or Garmin to help decipher the order of the error data 13 Power down the G1000 System and remove the SD card 14 Insert the SD card in the card reader of a laptop or desktop computer and open the buf log txt file from the SD card using the WordPad program Verify that all of the fault logs were downloaded by checking for the End of Fault Log message at the end of the GIA data and that the last servo log entry has the current date 15 Insert the fault log as an attachment to an email and include the LRU order how the data was downloaded and send to Garmin Aviation Product Supp
405. the primary control interface to the GDU 1500 MFD The GCU 477 provides alphanumeric softkey and flight planning function keys used to interface with the G1000 does not possess any knobs or controls other than softkeys The GCU 477 is powered by the Essential Bus The GCU 477 also provides the crew with the added functionality of tuning their receivers via the GCU as well as the PFD Detailed instructions regarding the controls are discussed in the G1000 Cockpit Reference Guide Figure 2 4 FMS Controller 2 1 6 Transponder 2 The Garmin GTX 33 or GTX 3000 transponders communicates with the on side GIA 63W through RS 232 digital interface This STC installation allows for installation of two GTX 33 non diversity transponders two GTX 33D diversity transponders or one of each type This STC installation also allows for installation of two GTX 3000 diversity transponders Mixing between the GTX 33 and GTX 3000 transponsders is not permissible Additionally for TCAS II operations the GTX 3000 transponder communicates with the GTS Processor through ARINC 429 digital interfaces transmit and receive The transponder units are mounted under the floor in the cabin just aft of fuselage station 246 750 or on the upper avionics equipment shelf in the tail section of the airplane Power is provided by the No 1 GTX from the Essential Bus The No 2 GTX is powered from the Avionics Bus No 1 All GTX transponders non diversity and dive
406. the replaced display were cleared Clear user settings by pressing the CLR key on the replaced display while applying power to it Acknowledge the on screen prompt by pressing the ENT key or the right most softkey Check for GEA related Alert messages on the PFD Correct any Alerts concerning software or configuration errors by reloading software or configuration as noted Verify GEA internal power supply configuration and calibration status in configuration mode Y internal power supply configuration and calibration boxes should be green If they are red replace the GEA 71 Verify internal external and reference voltages listed in the Main Analog and I O A Analog boxes are not dashed out does not include Aircraft Power 1 and 2 Y If any voltages are dashed out replace the GEA Ensure the GEA is online green checkmark on the AUX SYSTEM STATUS Y f GEA is not online verify unit is receiving power at the rack connector Y Check the GIA GEA interconnects for faults Reload configuration files to both GIA s and the GEA If problem persists replace the GEA 71 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 25 190 00915 01 Revision 9 5 23 Engine Airframe Instrument Failures The following table provides guidance for troubleshooting individual engine airframe sensor failures Be sure to also follow previous guidance given for the GEA 71 The technician should
407. the reported software version of the LRU whereas the CARD VERS column shows the LRU software version stored on the Loader Card If an inequality between the LRU VERS and CARD VERS columns is detected the SOFTWARE and CONFIGURATION boxes will be pre selected checked for each LRU reporting a different software version than the one on the card The following softkeys provide an easy way to select files CHK ALL Selects all files both configuration and software CHK SW Selects all SW files only CHK CFG Selects all configuration files only CLR ALL Clears all selections LOAD Starts the software loading process NOTE When loading a new software image or re loading software to a particular LRU it may not be necessary to reload all software and configuration files The technician should be sure of the software requirements and load the appropriate files including any options If there is any doubt the CHK ALL softkey is recommended Except where specifically noted the procedures that follow including subsequent sections are for 0985 07 and later software versions Earlier software versions have similar loading procedures and may use slightly different nomenclature 5 After verifying that the desired software and configuration files are checked press the LOAD softkey The G1000 system automatically begins loading software and default configuration files to the selected LRUs in the proper order AIRFRAME PROP ATRFRANE
408. the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Airframe Options and press ENT key on PFDI 3 Rotate the small FMS knob to highlight King Air ESP Support no AOA Press ENT key on PFDI 4 Verify King Air ESP Support no AOA is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 51 190 00915 01 Revision 9 3 34 POTS Handset Configuration Follow this procedure to enable a POTS handset if installed Note that the GDL 59 wi fi data link option must be loaded per Section 3 33 prior to loading the POTS handset configuration Power up the PFDI in configuration mode On the PFDI select GDL page group using the large FMS knob Using the small FMS knob select the GDL 59 Configuration page Activate the cursor Use the large FMS knob to select POTS CONNECTED in the PHONE SETTINGS field Use the small FMS knob to select YES and press the ENT key 6 After GDL 59 is configured press the ENT key Top M Page 3 52 G1000 700 System Maintenance Manual 2
409. the software update insert this card into your G1000 system 3 83 Software Files Software files are defined by part number and version number on the General Arrangement drawing See Table 1 2 for the correct General Arrangement drawing part numbers Each G1000 GFC 700 LRU reports the software version it currently contains to the user in two places Normal System Mode The AUX SYSTEM STATUS page lists each LRU and the reported software version e Configuration Mode The SYSTEM STATUS page SYSTEM page group reports more detailed LRU information including software version part number and LRU status Software files are loaded to LRUs from the SYSTEM UPLOAD page in configuration mode See Section 3 92 3 84 Configuration File Descriptions There are configuration files for baseline settings and various options Configuration files contain preset selections for input output channels aircraft specific settings and LRU specific settings IMPORTANT Certain software and configuration files are REQUIRED to be re loaded during maintenance that involves removal and replacement of G1000 equipment Refer to Section 7 for re configuration requirements for cach G1000 LRU Pay special attention to the configuration of options for the G1000 Page 3 16 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 8 5 Configuration File Storage The G1000 system is designed to store all config
410. ther optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number MANIFEST GDL software The system has detected an Load correct software version mismatch Communication incorrect software version loaded See Section 3 9 for the halted in the GDL 69A Software Load Procedure G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 69 190 00915 01 Revision 9 5 15 GRS 77 or GRS 7800 and GMU 44 Troubleshooting 5 15 1 AHRS Common Problems Symptom AHRS does not complete initialization Recommended Action Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin Ensure GPS has acquired at least four satellites has a 3D navigation solution and a DOP of less than 5 0 This is particularly important if this issue appears during ground operation only Calibrate the GRS 77 or GRS 7800 Check GRS 77 or GRS 7800 configuration module wiring for damage Check GRS 77 or GRS 7800 connector for bent pins Y f no damage can be found replace GRS 77 or GRS 7800 configuration module v If problem persists replace the GRS 77 or GRS 7800 Attitude appears unstabl
411. tinent Model 4200 11 Electric Attitude Indicator is used as the standby attitude indicator It is connected to the new Standby Instrument Bus and the emergency standby battery Gyro power and internal lighting of this unit is powered from Dual Fed No 1 Bus and the emergency standby battery 2 1 26 L 3 PS 835 C or D Model Emergency Standby Battery In the event of loss of all normal electrical power the battery is designed to provide 24 Vdc nominal emergency power source for the following items e standby attitude indicator operation and internal lighting e standby altimeter vibrator and internal lighting e standby airspeed indicator lighting only e pilot side glareshield lighting The aircraft power buss provides a trickle charge to the PS 835 under normal conditions This battery is installed in the nose avionics bay It is controlled using the standby battery switch indicator on the instrument panel G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 13 190 00915 01 Revision 9 2 1 27 Safe Flight Lift Computer For the optional Electronic Stability and Protection ESP feature with Angle Of Attack modes a new Safe Flight lift computer part number C 05606 1 that is a direct replacement for the existing lift computer is installed to provide an additional Low Airspeed Awareness LAA output to support the Angle of Attack modes of Electronic Stability and Protection The lift computer is located in the sa
412. tion models 200 B200 only DME Option GDL59 ESP Support no AoA GRS77 200 B200 ESP Support with AoA GRS7800 RAD ALT Option Non Garmin GSM 85A Servo Mounts TCAS II System Option Non Garmin GSM 86 Servo Mounts Traffic System Option Non Garmin GSR56 Stand Alone Lightning System Option GTS 820 850 GTS Processor circle TAWS A Support one 825 855 8000 TAWS A Voice No Callout Installation Option GTX 3000 TAWS A Voice Callout Installation Option GTX 33ES V1 Airspeed Option GWX 68 GSR 56 with GDL 59 GWX 70 GDC 7400 models 200 B200 only Page 8 14 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01
413. tions 6 28 and 6 29 ESP FAIL ESP is inoperative Troubleshoot the GFC 700 AFCS Refer to Section 5 5 ESP OFF ESP selected off e Check that the MFD AUX SYSTEM SETUP 2 page shows Stability amp Protection status is ENABLED ESP DEGRADE ESP AOA mode is inoperative lt Ensure GIA units are operational and GPS satellites have been acquired Ensure STALL WARN circuit breaker is closed Troubleshoot Safe Flight lift computer Refer to Section 5 25 ESP DEGRADE ESP IAS mode is inoperative Ensure ADC1 and ADC2 circuit breakers are closed and units are providing valid airspeed data ESP CONFIG ESP config error Config service req d Ensure that the ESP Support Option has been installed per Section 3 32 Ensure that the Enhanced AFCS unlock card has been installed per Section 3 44 e Ifthe ESP option needs to be removed reload the baseline configuration for the specific airframe and all applicable options as described in Section 3 9 Reloading the baseline configuration disables all previously enabled options NOTE From this point forward all message advisory alerts presented are common to all G1000 systems and are not specific to the King Air 200 B200 Messages are grouped according to LRU Page 5 28 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 4 TAWS Troubleshooting Annunciation
414. to the King Air 200 Series Maintenance Manual listed in Table 1 2 for instructions on removing any access panels NOTE It is recommended that the Phase 3 and Phase 4 electrical bonding checks contained in section 4 5 are conducted after the Phase 3 and 4 visual inspections while access to these zones is still open Table 4 3 Nose Section Visual Inspection Procedure Gain access via the Item Description Procedure Initials Radome for the following Inspection Inspect the GWX 68 GWX 70 unit mount and connectors for corrosion or other defects Check the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their GWX 68 GWX 70 attachment b Inspect wire harness for chafing damage proper routing of wire bundles and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Nose Wire Harness Routing drawing listed in Table 1 2 Table 4 4 Nose Avionics Compartment Visual Inspection Procedure Item Description Procedure Initials Gain access via the Nose Equipment Compartment access panel for the following Inspection GRS 77 or GRS 7800 Qty 2 defects Check the integrity of the SHIELD BLOCK ground attachments to the attachment a Inspect the GRS 77 or GRS 7800 units racks and connectors for corrosion or other harness connector assembly as well as the integrity of
415. trol being moved and press the red AP DISC switch on the aircraft control stick If an abnormal disconnect of a servo occurs reset AFCS SERVO circuit breaker and repeat the step 8 Manually select 2 50 rpm for the Drive Servo and press ENT 9 Press the ENG CLCH softkey 10 Press the DRV SRVO softkey 11 Allow the selected servo to drive the control surface to either the NOSE DOWN stop Pitch and Pitch Trim or the LEFT stop Roll and Yaw G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 23 190 00915 01 Revision 9 Allow the servo to continue driving against the control stop for at least 50 seconds Observe the TORQUE values displayed in the Servo Data field and record the maximum and minimum values in Table 4 10 or in the appropriate aircraft maintenance records Manually select 0 00 rpm for the Drive Servo and press ENT Allow the servo to stop Manually select 2 50 for the Drive Servo and press ENT Allow the selected servo to drive the control surface to either the NOSE UP stop Pitch and Pitch Trim or the RIGHT stop Roll and Yaw If the PITCH SERVO is selected firmly hold the control yoke in the full aft position until the NOSE UP portion of the test is completed Allow the servo to continue driving against the control stop for at least 50 seconds Observe the TORQUE values displayed in the Servo Data field and record the maximum and minimum values in Table 4 10 or in the appropriate a
416. troubleshoot to isolate the fault by checking sensor to GEA wiring replacing the suspect sensor and finally by replacing the GEA 71 Replace one part at a time Refer to Section 7 4 1 to check for correct operation of the sensors and GEA 71 after any part has been replaced Refer to G1000 GFC 700 Wiring Diagram and King Air 200 Series Maintenance Manual listed in Table 1 2 as needed Invalid Field Sensor Possible Solutions for applicable engine system Check thermocouple cable e Replace thermocouple cable Replace GEA 71 Check torque transmitter GEA wiring Check power input to torque transmitter TORQUE 15 q Torque FT LB e Replace torque transmitter x100 Replace GEA 71 4 Check prop tachometer Signal Conditioner wiring Check Signal Conditioner GEA wiring Prop RPM Check power input to Signal Conditioner e Replace prop tachometer sensor e Replace Signal Conditioner Refer to Section 6 22 Replace GEA 71 e Check engine speed tachometer Signal Conditioner wiring Check Signal Conditioner GEA wiring Turbine RPM Check power input to Signal Conditioner e Replace engine speed tachometer sensor Signal Conditioner Refer to Section 6 22 Replace GEA 71 Check Signal Conditioner unit wiring Check power input to Signal Conditioner Fuel Flow e Replace fuel flow transmitter e Replace Signal Conditioner Refer to Section 6
417. tware load completes without errors as indicated by the following e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor Page 3 24 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 11 GDC 7400 Air Data Computer Software Configuration ftware version 0985 06 and later follow this procedure to configure the GDC 7400 air data installed Refer to section 3 10 if the GDC 74B air data computers are installed Coordinate the GDC 7400 configuration with Section 7 6 GDC 74B or GDC 7400 Air Data Computer 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key PFDI 3 Rotate the small FMS knob to highlight King Air GDC 7400 models 200 B200 only Press ENT key on PFDI 4 Verify King Air GDC 7400 models 200 B200 only Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following is displayed in the Item window e Green PASS in the Configuration column for each item loa
418. ual 200 B200 Series King Air Revision 9 190 00915 01 5 8 GDU 104X Troubleshooting 5 81 GDU 104X Common Problems Symptom Display is blank Display resets Display flickers Recommended Action e Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin e Cycle power Y f GDU recovers observe display for yellow text containing error information at the top of the screen If message indicates software need to be re loaded then re load software Otherwise replace the GDU e Use a bright light to verify LCD is active Y Adjust avionics dimmer control full clockwise Y Manually turn up backlight on the PFD and load configuration files to the GDU e Ensure slide lock is fully engaged with the locking tabs on the back of the unit Y If slide lock is not fully engaged remove connector and verify the locking tabs on the GDU are perpendicular to the connector If necessary straighten them before reseating connector e Ensure GDU is receiving power If a circuit breaker is tripped determine source of short before resetting breaker e Ensure circuit breakers have not failed and power wire connections secure e Swap PFD1 and PFD2 Y f problem follows unit replace the display Please note the position it failed in PFD1 2 Y f problem does not follow unit troubleshoot aircraft wiring for fault SD card is stuck in GDU e NOT insert a scr
419. ubleshooting Recommended Action e Perform the Standby Instrument Electrical Power Checks in Section 8 1 5 e Remove the unit per Section 6 27 and inspect the electrical connector Check to ensure appropriate electrical power is being supplied to the instrument e If input electrical power is not adequate troubleshoot the wiring harness e If input power is appropriate the unit must be removed and serviced by a qualified service facility See Section 6 27 for removal instructions Contact the manufacturer to find a qualified service facility Unit fails to perform to lt The unit must be removed and serviced by a qualified service facility See Section 6 27 for removal instructions Contact the manufacturer to Airspeed Indicator lighting is inoperative or malfunctioning spacficallone find a qualified service facility 5 28 Standby Airspeed Indicator Troubleshooting Symptom Recommended Action e Perform the Standby Instrument Electrical Power Checks in Section 8 1 5 e Remove standby airspeed indicator per Section 6 25 and inspect the electrical connector Check that electrical power is being appropriately supplied to the instrument e if the input electrical power is not adequate troubleshoot the wiring harness e If the input electrical power is appropriate replace the standby airspeed indicator or contact the manufacturer for further troubleshooting Airspeed displayed is incorrect e Usi
420. umber or other Mode S registration number TRANSPONDER CONFIGURATION RRR ser POR 2 ACTIVE VFR CODE AIRCRAFT WEIGHT lt 15 508 LBS AIRSPEED lt 300 KTS ADDRESS TYPE US US TAIL HODE 5 ADDRESS N N FLIGHT ID SAME AS TAIL SAME AS TAIL FLIGHT ID N N ENHANCED SURVEIL ENABLED ENABLED ADS B TRANSHIT PFD CONFIG PFD CONFIG AIRCRAFT WIDTH 23 MT AIRCRAFT LENGTH 15 MT SURVEIL INTEGRITY lt 1 107 5 ERR HR FLT ERR HR FLT Figure 7 5 Aircraft Registration 5 For US registered aircraft the FLIGHT ID TYPE field should be set to SAME AS TAIL For other aircraft the FLIGHT ID TYPE field should be set to CONFIG ENTRY or PFD ENTRY NOTE The CONFIG ENTRY setting requires the Aircraft Registration ID number to be entered once in the FLIGHT ID field The PFD ENTRY setting allows the pilot to enter the Aircraft Registration ID number from the PFD via the TMR REF softkey 6 After each configuration setting change press the ENT key to configure the transponders 7 Press the ENT key on PFDI to acknowledge prompt 8 After completing transponder configuration deactivate the cursor Page 7 12 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 7 5 2 GTX 33 or GTX 3000 Test Operation of the GTX or GTX 3000 Mode S transponder is accomplished using PFD 1 PFD 2 or the MED Refer to G1000 in King Air 200 B2
421. uration Mode check that the RH GEAR ON GROUND Discrete In indication for GIA2 on GIA CONFIGURATION page is illuminated With aircraft weight on wheels and the G1000 in Configuration Mode check that the LH GEAR ON GROUND Discrete In indication for GIA1 on GIA I O CONFIGURATION page is illuminated If both indications are illuminated Green switch GIA1 and GIA to verify location of problem Y If problem is resolved replace defective unit v If indication is not illuminated check for wiring faults between the GIAs and aircraft squat switch system GIA1 Check configuration settings for GIA1 and PFD1 Swap GIA1 and GIA2 to verify location of problem Y f problem follows GIA1 replace GIA1 Check Ethernet interconnect from GIA1 to PFD1 Y If problem persists replace PFD GIA2 Check configuration settings for GIA2 and PFD2 Swap GIA1 and GIA2 to verify location of problem Y If problem follows GIA2 replace GIA2 Check Ethernet interconnect from GIA2 to PFD2 Y If problem persists replace PFD G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 21 190 00915 01 Revision 9 Invalid Data Field GPS LOI m Associated LRU s GIA1 or GIA2 Solution Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin Check GPS1 and GPS signal strength on AUX page 4 Refer to GIA GPS secti
422. uration settings in various places so that the configuration is retained in the aircraft during maintenance of units During system configuration each file is sent directly to the applicable LRU where it is stored in local LRU memory reference Figure 3 14 Each file is also stored in the PFD internal memory The applicable PFD also sends a copy of all configuration files to the Master Configuration module located in the connector backshell see Section 6 16 If the PFD is replaced the configuration module retains all configuration files in the aircraft The GRS 77 7800 GMU 44 GDC 74B and optional GDC 7400 configuration calibration reference Figure 3 15 is different than the LRU s shown in Figure 3 14 1000 Master Configuration Module located in PFD backshell connector OMETI Master configuration module contains identical oe backup configuration fles of PFD configuration memory PFD crosschecks these backup fles posi against fles contained with PFD memory PFD sett sonfiguraton fles configures to match master configuration module pru i sa lea No 1 GDU 1040A PFD HIGHSPEED DATABUS No 2 GDU 1040A PFD Contains ACTIVE PFD settings O Contains ACTIVE PFD settings Represents SET colum for all ETT Represents SET column for all
423. uring the automatic slip clutch torque measurement check 5 6 2 GIA Fault Log Descriptions The section was created to help determine why the GFC 700 has failed the Pre Flight Test indicated by the red PFT annunciation it defines the PFT sequence for the servos and the 700 system and then provides troubleshooting information to help resolve failures There are 16 steps to the GFC 700 PFT The PFT is performed by both GIA s at startup and needs to pass on both GIA s before the autopilot can be engaged The PFT is only started if the AHRS has aligned the GIA s and servos are configured and the certification gains are valid If the PFT has not completed after one minute from when the initialization started the PFT will fail After the system PFT has passed it will be performed again if a servo resets if the autopilot servo breaker is reset or the cross side GIA restarts it Generally the PFT failure fault is logged in the GIA Maintenance Log and not in the Servo Maintenance Logs unless the GIA log fault identifies a servo problem NOTE Thoroughly understanding the operation of the G1000 system in Configuration mode is recommended before starting this procedure The GFC Status page may be used to check the status of the servos and engage them to aid in troubleshooting To access the GIA and GSA Maintenance Logs perform the following steps l Start the G1000 in Configuration mode Use the FMS knob on PFD to go to the
424. v 15 or previous revisions and not modified per Garmin Service Bulletin 1375 Every 220 hours perform a Nose Avionics Compartment Fans Operational Check per Section 4 14 See Note 1 Every 820 hours perform an Engine Data Check per Section 4 11 Every 820 hours perform the 61000 Miscompare Checks per Section 4 13 At 10 000 cycles and every 1 000 cycles thereafter perform an exterior skin inspection around antennas per Section 4 18 Note 1 See Section 6 28 Figure 6 5 for identification of cooling fan installation applicable for this limitation Other Limitations e Every 220 hours perform the Standby Instrument Electrical Power Checks per Section 8 1 5 e Every 220 hours or 6 Calendar Months whichever occurs first perform Standby Battery Charge Check per Section 4 16 1 There are no other airworthiness limitations associated with this type design change STC SA01535WI D The G1000 GFC 700 King Air 200 B200 Airplane Flight Manual Supplement defines all operating limitations for this STC Airworthiness Limitations section is FAA approved and specifies maintenance required under 43 16 and 91 403 of Title 14 of the Code of Federal Regulations unless an alternative program has been FAA approved 2 08 04 FAA APPROVED Robert Murray Date STC Unit Administrator ODA 240087 CE G1000 700 System Maintenance Manual 200 8200 Series King Air Page 4 1 190 00915 01 Revision 9 42
425. various components of the G1000 This section touches upon key items to note while troubleshooting the GFC 700 Should a problem be encountered during the operation of the GFC 700 the pilot and technician should first evaluate the overall status and condition of the G1000 system at the AUX System Status page on Any alert messages annunciations or other abnormal behaviors should be noted in an effort to pinpoint the fault The object is to locate the fault within a LRU or LRUs in efforts to replace the defective equipment The GFC 700 AFCS Annunciation field is located above the airspeed tape on the PFD as shown Figure 5 5 AFCS Annunciation Field G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 33 190 00915 01 Revision 9 5 6 1 GFC Status Page The GFC Status page is presented in configuration mode and gives status information regarding the GFC 700 GFE STATUS BOARD STATUS HIGH RES LOAD CELL CAL LOAD CALL CAL CONTROL STATUS SERVO PROGRAM 1 SER DATA EN 405047580 sr CAIN Figure 5 6 GFC Status Page GIA STATUS AP DISCONNECT Shows the condition of the AP DISC 28 VDC input to the GIAs and servos which is required for the Autopilot to operate A green status indicator shows the AP DISC switch is closed and the GFC 700 is activly receiving 28 volts A red X indicates the GIAs and servos are no longer receiv
426. ve the attachment screws from the front of the standby airspeed indicator 5 Remove the standby airspeed indicator Page 6 16 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 Reinstallation 1 Reinstallation of the standby airspeed indicator is the reverse of the removal Reference the Main Instrument Panel Installation drawing listed in Table 1 2 for more details 2 If further maintenance is not required proceed to Section 8 6 26 Standby Altimeter Removal 1 Remove per Section 6 1 2 Disconnect pitot static plumbing from the back of the standby altimeter Take necessary precautions to prevent foreign object debris from entering the pitot static lines during maintenance 3 Disconnect the electrical connector from the standby altimeter 4 Use a Phillips screwdriver to remove the attachment screws from the front of the standby altimeter 5 Remove the standby altimeter Reinstallation 1 Reinstallation of the standby altimeter is the reverse of the removal Reference the Main Instrument Panel Installation drawing listed in Table 1 2 for more details 2 If further maintenance is not required proceed to Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 17 190 00915 01 Revision 9 6 27 Standby Attitude Indicator Ensure the standby attitude indicator gyro is not spinning this may take 10 minutes or longer after the
427. wap GIAI and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIAI o Replace original GIAI if box turns green after swapping units e Swap GRSI and GRS2 no reconfiguration required to confirm if the problem is in the original GRS2 o Replace original GRS2 if box turns green after swapping units e Check the GIAI GRS 77 or GRS 7800 2 interconnect wiring for faults Amber Green GIAT GRS 77 or GRS 7800 2 data path functionality is unknown Reload GIAI configuration files GIAI GDC 1 data path is functioning correctly Red GIAI GDC 1 data path is not functioning correctly e Load GIAI and GDC 1 configuration files e Swap GIAI and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIAI o Replace original GIAI if box turns green after swapping units Check the GIAI GDC 1 interconnect wiring for faults Replace GDC 1 if problem remains Amber GIA1 GDC 1 data path functionality is unknown Reload GIAI configuration files G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 13 190 00915 01 Revision 9 A GIAI GRS 77 or GRS 7800 1 data path is functioning reen correctly GIA1 GRS 77 or GRS 7800 1 data path is not functioning correctly e Load GIAI configuration files e Swap GIAI and GIA2 reconfigure both GIA s to their new location
428. wed in the King Air 200 Series Maintenance Manual a tolerance of 20 hours for all phase inspections Special Inspection Items Calendar limited inspections a tolerance of 12 days per 12 calendar months The intention of Garmin is to align this maintenance program as best possible with the existing King Air 200 B200 inspection program For a complete description of the King Air inspection program refer to the King Air 200 Series Maintenance Manual listed in Table 1 2 Table 4 1 Maintenance Intervals Section No Interval Item Description Procedure G1000 GFC700 Equipment Complete Visual Inspection of GWX 68 or GWX 70 Equipment and Wiring located in Phase 4 Nose Section Table 4 3 Complete Visual Inspection of dd G1000 GFC700 Equipment and Wiring Phase 4 located in Nose Avionics Compartment Table 4 4 Complete Visual Inspection of dd G1000 GFC700 Equipment and Wiring Table 4 5 Phase 3 G1000 GFC700 located in Pilots Compartment Ses System Visual Inspections Complete Visual Inspection of P G1000 GFC700 Equipment and Wiring Table 4 6 Phase 3 located on and behind Instrument Panel i Complete Visual Inspection of 24 G1000 GFC700 Equipment and Wiring Phase 3 located in Cabin Table 4 7 Complete Visual Inspection of dd G1000 GFC700 Equipment and Wiring ae Phase 4 located in Rear Fuselage and Empennage Table 4 8 G1000 GFC 700 System Maintenance Manual 200 B200
429. wer STRP CODE Check the connector strap inputs to the unit MET STUCK SWTCH Check the MET switch inputs into the system MET STATUS DIF Check the MET switch inputs into the system G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 41 Revision 9 5 6 3 1 2 Control Processor The control processor contains the logs that are found in these processors 3 Pitch Servo 5 Roll Servo 7 Yaw 9 Pitch Trim Servo There are two main groupings of faults that can occur in the control processor The first grouping of faults can occur during the GSA unit pre flight test PFT If there is a fault during PFT the unit will not be able to transition to normal mode and the only way to clear this state would be to cycle unit power The second grouping of faults can occur during normal mode These faults generally cause a disconnect of power to the GSA and report that a fault has occurred to the GIA The Notes column indicates any actions that can be taken to troubleshoot the problem in the aircraft by the technician Any faults that not listed here indicate an internal problem requiring replacement of the servo If the items in the Notes column check out ok replace the servo Faults CONTROL PFT STEP NOTES INT COMM TEST FAIL Mire result of a failure on the other board check MOT PWR ON FAIL
430. wer up If a database does not activate reload the problem database onto the SD Card or replace the card Display will not track dimmer bus Keyboard will not track dimmer bus Reload GDU configuration files If display is a PFD swap PFD1 and PFD2 to see if problem remains with display Y Replace display if condition remains with the same unit Y If condition remains in original position after swapping displays check GDU dimmer input to verify voltage is present If display is the MFD check dimmer input to verify voltage is present Replace MFD if dimmer voltage is present Page 5 48 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 5 9 GDU 104X Alerts lure Message Software Configuration Alerts Cause Solution SW MISMATCH GDU software version mismatch Xtalk is off The system has found the PFDs and or MFD software versions do not match MANIFEST PFD 1 software mismatch Communication Halted mismatch Communication Halted MANIFEST PFD 2 software The system has detected an incorrect software version loaded in the specified PFD MANIFEST MFD1 software mismatch Communication The system has detected an incorrect software version loaded e Load correct software version See Section 3 9 for GDU 1040 Software Loading procedure Halted in MFD e Check master configuration module connector and wi
431. which are characteristic to the specific installation A copy of this calibration data is stored in the GRS configuration module While performing maintenance on these units re calibration may be required See Section 7 7 1 for more information on re calibration criteria The GDC 74B air data computer configuration file is loaded directly to GDC 74B internal memory A copy of the file is stored in the GDC 74B configuration module The GDC 7400 air data computer configuration file is loaded directly to GDC 7400 internal memory and there is no configuration module for the GDC 7400 GRS 77 7800 Config Module located in GRS backshell connector Stores a copy of AHRS magnetometer calibration values that are recorded upon completion of post installation calibration procedures GDC 74B Config Module located in GDC backshell connector Stores copy of the GDC 74B configuration file GRS 77 7800 AHRS The GRS stores calibration data internally The GRS 77 also stores factory calibration data internally Should internal memory or the configuration module fail AHRS output data flags invalid GRS Internal Memory Contains internal sensor calibration data that is not installation specific Data is stored from factory calibrations GDC 74B The GDC 74B stores GDC configuration file internally The GDC 74B also stores factory calibration data internally Should internal memo
432. without errors as indicated by the following e Green PASS in the Configuration and Software columns for each item loaded e Upload Complete COMPLETE the summary box 6 Press ENT key on PFDI to acknowledge upload complete 7 Deactivate cursor Page 3 26 G1000 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 3 13 GTS Traffic Processor Follow this procedure to enable the GTS Processor traffic system function for the G1000 system if required NOTE Configuration of the GTS Processor will require the GTS system to be configured with the aircraft mode S address Coordinate this configuration with Section 3 48 Aircraft Registration Number Entry The default configuration for the GTS system is TAS See Section 3 46 for TCAS I enable and Section 3 47 for TCAS II enable Coordinate the GTS Processor TAS configuration with Section 7 27 GTS Traffic System Functional Check 1 With the loader card in the top slot of PFD1 and PFDI in configuration mode select the System Upload page on PFD1 using the small FMS knob 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS knob to highlight King Air Garmin Options and press ENT key on PFDI 3 Rotate the small FMS knob to highlight King Air GTS Processor Press ENT key on PFDI 4 Verify the GTS Processor is displayed in the Item window Pr
433. y and secondary CBs and GIA2 CB 8 Verify the following COMI NAVI amp 2 2 fields flag invalid GPS CDI flags DR on PFD NAVI amp NAV2 CDI loses deviation bar XPDR field flags invalid on PFD Engine Instrument field flags invalid on MFD All AHRS amp ADC fields remain valid Red AFCS status annunciation given If equipped with TAWS TAWS FAIL annunciation given If equipped with ADF and or DME ADF DME windows flag invalid 9 Restore power to both GIA units The G1000 Redundant Connections Check is complete Page 4 28 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 4 11 Engine Data Check Accomplish this section to verify the engine data availability and validity for oil pressure ITT and torque Remove the left and right engine cowling Ref King Air 200 Series Maintenance Manual Chapter 71 10 00 to gain access to the engine harness connectors and reinstall cowling when testing is complete Required test equipment is provided in Table 4 12 Any product conforming to the specification listed may be used Test Equipment Requirement Signal Generator 0 10Vde 0 Ik Hz Thermocouple Calibrator K type 200 to 1 200 C Table 4 12 Engine Data Check Test Equipment 4 11 1 Oil Pressure Remove power from aircraft Disconnect the left engine oil pressure transmitter connector P12 Connect the Signal Generator to pins A and B of
434. y self test Ensure that self test occurs in area free of buildings and large objects that can reflect signals Download the assert log and use Assert Log Diagnosis Tool or send to Garmin for diagnosis Return unit to Garmin for service if fault persists Check antenna installation and all cable connections and retry self test Ensure that selft test occurs in area free of buildings and large objects that can reflect signals Download the assert log and use Assert Log Diagnosis Tool or send to Garmin for diagnosis Return unit to Garmin for service if fault persists Baro Altitude Fault Temperature Fault Check wiring to source of barometric altitude and ensure that source is operating Download the assert log and send to Garmin for diagnosis TCAS Equipage Fault Radio Altitude Fault Display Fault Check wiring to TCAS Equuipage data source and ensure that source is operating Check wiring to source of radio altitude and ensure that source operating Check the HSDB connection between the GTS Processor and the display Verify that the display is operational For non HSDB installations ensure that the Traffic Display Status Valid inputs TAS TCAS 1 and RA Display Status Valid inputs TCAS II are wired properly to the Display Status Valid output of the display device G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 95 190 00915 01 Revision 9 This page intentionally
435. y the correct configuration for SERIES ENGINE and PROP EXAMPLE For a configuration that loaded King Air B200 PT6A 42 with a McCauley 3 BLADE propeller the AIRFRAME section should display SERIES B200 ENGINE 42 PROP MCCAULEY 3 Page 1 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 9 190 00915 01 1 2 Organization The following outline briefly describes the organization of this manual Section 2 System Description Provides a complete description of the type design change associated with installing the G1000 integrated cockpit system in the 200 B200 Series King Air An overview of the G1000 and 700 system interface is also provided Section 3 G1000 Control amp Operation Presents basic control and operation information specifically tailored to maintenance practices Basic G1000 Configuration Mode operation is also described Section 4 Instructions for Continued Airworthiness Provides maintenance instructions for continued airworthiness of the G1000 and GFC 700 systems Provides troubleshooting information to aid in diagnosing and resolving potential problems with the G1000 and GFC 700 systems Section 6 G1000 Equipment Removal amp Replacement Gives instructions for the removal and replacement of G1000 and GFC700 equipment Section 7 G1000 Equipment Configuration amp Testing Gives instructions for loading software configuring and testing of

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