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Garmin SA01535Wi_D Instruction Manual

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1. NOTE If TAWS has not been enabled the title will read MAP TERRAIN PROXIMITY or MAP TERRAIN Refer to section 3 37 for TAWS Configuration for configuring TAWS 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 After the TAWS test has completed verify that TAWS System Test Okay is heard over the cockpit speaker if selected and the headsets 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 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 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 Press the 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 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 Press the GCU MENU button again and select Disable Flap Override from the pop up menu and press ENT on the
2. Page 5 12 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 GIA1 ARINC 429 Channel GDC 7400 1 GRS 77 or GRS 7800 1 Indicator Status GIA1 GDC 7400 1 data path is functioning correctly GIA1 GDC 7400 1 data path is not functioning correctly e Load GIA1 and GDC 7400 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 GIA1 o Replace original GIA1 if box turns green after swapping units e Check the GIA1 GDC 7400 1 interconnect wiring for faults Replace GDC 7400 1 if problem remains GIA1 GDC 7400 1 data path functionality is unknown Reload GIA1 configuration files GIA1 GRS 77 or GRS 7800 1 data path is functioning correctly GIA1 GRS 77 or GRS 7800 1 data path is not functioning correctly e Load GIA1 configuration files e Swap GIA1 and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA1 o Replace original GIA1 if box turns green after swapping units Swap GRS1 and GRS2 no reconfiguration required ref GRS Configuration and Testing sections to confirm if the problem is in the original GRS1 o Replace original GRS1 if box turns green after swapping units Check the GIA1 GRS 77 or GRS 7800 1 interconnect wiring for faults GIA1 GRS 77 or GRS 7800 1 data path functionality is unknown
3. 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 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 PFD1 3 Rotate the small FMS knob to highlight King Air GRS 7800 Press ENT key on PFD1 Verify King Air GRS 7800 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 PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 33 190 00716 01 Revision 4 3 20 GWX 68 Software Configuration Follow this procedure to configure the GWX 68 Weather Radar if installed Refer to section 3 21 if the GWX 70 Radar is installed Coordinate the GWX 68 configuration with Section 7 12 GWX 68 or GWX 70 Weather Radar 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 on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu
4. 14 Select the MODE softkey 15 Select the OFF softkey Page 7 30 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 7 13 Non Garmin Traffic System TAS TCAS I Functional Check 1 Select the TRAFFIC MAP page on the MFD 2 Verify that the STANDBY OPERATE TEST and ALT MODE soft keys are available on the bottom of the MFD NOTE If the correct softkeys are not displayed the G1000 has not been properly configured for the traffic system Reference Section 3 10 Non Garmin TAS TCAS I Traffic System Option Configuration to enable the traffic system 3 Verify that FAIL is not displayed in the upper left corner of the traffic map Verify that NO DATA is not displayed in the center of the traffic map over the aircraft symbol 5 Press the OPERATE soft key and verify that OPERATING is displayed in the upper left corner of the traffic map 6 Press the STANDBY soft key and verify that STANDBY is displayed in the upper left corner of the traffic map 7 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 OK is heard over the cockpit speaker NOTE This annunciated traffic system test message may vary 8 Open the TRFC circuit breaker on the avionics circuit breaker panel On the MFD verify that NO DATA is displayed af
5. HDG NO COMP illuminates on PFD2 ROLL NO COMP illuminates on PFD2 PIT NO COMP illuminates on PFD2 IAS NO COMP illuminates on PFD2 ALT NO COMP illuminates on PFD2 GMA1 Fail GMA1 is inoperative XPDR1 Fail XPDR1 is Inoperative Page 8 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 8 1 4 G1000 Cooling Fan Fail Annunciation Check Do the following to verify the cooling fans and annunciations are functioning properly r 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 display cadnie ERD or EROA AVN FAN FAIL Avionics cooling fan 1 is Alerts Window 8 inoperative Pull the following cooling fan circuit e breakers AVN FAN 2 FAIL Avionics cooling fan 2 is a PFD GIA FANS LEFT inoperative b PFD GIA FANS RIGHT PFD 1 FAN FAIL PFD 1 cooling fan is c MFD FAN inoperative PFD 2 FAN FAIL PFD 2 cooling fan is inoperative MFD FAN FAIL MFD 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 st
6. Table 1 3 Reference Publications Part Number Garmin Document Airplane Flight Manual Supplement G1000 GFC 700 Hawker Beechcraft King Air 300 300LW King Air Airplane Flight Manual Supplement G1000 GFC 700 in Hawker Beechcraft King Air B300 B300C King Air 190 01344 00 G1000 Cockpit Reference Guide for the Beechcraft 300 B300 190 00355 04 GDL 69 Series XM Satellite Radio Activation Instructions G1000 G1000H System Maintenance Manual Standard Piston Turboprop Helicopter 190 00303 72 GSA 8X GSM85 A Installation Manual 190 00303 83 GSM 86 Servo Gear Box Installation Manual 190 00303 85 GSA9000 GSM9100 Installation Manual 190 00716 02 190 00716 03 190 00907 00 190 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 website Owner operators may obtain the latest revision of this document from th
7. e XM audio can be heard For aircraft not equipped with a tone generator deselect mute softkey or adjust XM volume to restore XM audio G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 5 190 00716 01 Revision 4 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 GIA1 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 GIA1 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 If a 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 Acquisition GPS SOLUTION POSITION RAIM PREDICTION WAYPOINT TRE ARV TIME ALTITUDE ARY DATE GROUND SPEED TRACK GPS SIGNAL STRENGTH Figure 7 3 AUX GPS STATUS Page MFD
8. 2 Start PFD 1 in Configuration mode 3 Go to the GRS Page Group and select the GRS GMU Calibration page at the PFD This page is protected and the following softkey password must be entered at the PFD to continue e 9 e 10 e il e 12 Far Right softkey GRS GMU CALIBRATION COMMUNICATION STATUS m GPS AIR DATA E MAGNETOMETER Compensation Mode CALIBRATE 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 Use the cursor to highlight the BEFORE CALIBRATION window 8 Follow the checklist items displayed on 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 Page 7 20 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 0
9. 2 1 22 GRA 5500 Radar Altimeter The GRA 5500 Radar Altimeter is designed to calculate height Above Ground Level AGL of the aircraft which is displayed 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 Right Gen Avionics Bus Figure 2 21 GRA 5500 Radar Altimeter 2 1 23 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 2 13 190 00716 01 Revision 4 2 1 24 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 Signal Conditioner p n 85 292 4 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 No 1 Triple Fed Bus and to the No 2 Engine Signal Conditioner from No 2 Triple Fed Bus Both signal conditioners will power up immediately with external or aircraft power or ba
10. 4 3 2 1 Figure 5 26 GDL 59 Backplate Connector P591 Rear View 9 8 7 6 5 4 3 0 0 0 00 0 i 1 2 1 1 15 14 13 12 11 10 0 0 0 ae 30 29 28 27 26 25 24 23 22 21 20 16 o 44 43 42 41 40 39 38 37 36 35 34 33 32 31 00 o N Oc o o Figure 5 27 GSR 56 Backplate Connector P561 Rear View GR RR 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 LR kal RR 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 LR ee E RAR 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 RR RR 2 3 4 5 6 7 17 18 19 20 16 14 15 13 LR 10 11 12 8 9 Figure 5 28 GSD 41 Backplate Connector P411 Rear View Figure 5 29 GSA 9000 Mating Connector P90001 Rear View Page 5 85 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Figure 5 30 GRA 5500 Connector P55001 Page 5 86 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 22 Standby Attitude Indicator Troubleshooting Recommended Action Perform the Standby Instrument Electrical Power Checks in Section 8 1 5 Remove the unit per Section 6 28 and inspect the electrical connector Check to ensure appropriate electrical power is being supplied to the Warning flag pops into view instrument i
11. Access to AHRS1 and AHRS2 will be required during this test 1 Ensure the G1000 is operating in normal mode 2 Connect a pitot static test set to the aircraft ADC1 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 On the 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 ADC1 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 ADC1 altitude to ambient pressure 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 ADC1 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 the pitot static test set to simulate an airspeed of 55 kts for ADC1 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 ADC1 and 95 kts for ADC2 Verify the autopilot does not disconnect and amber comparator window te
12. 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 MFD changes 11 Press the SEL key to select one of the softkeys 12 Press the Dr 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 Press 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 SO Sr 2 on PFD1 21 Using GCU477 keypad enter in a frequency of 123 450 Verify COMM1 frequency changes as entered 22 Press the COMM keyuntil 2 is lit Verify the tuning box is present around the COMM 2 frequency on PFD1 23 Using GCU477 keypad enter in a frequency of 123 450 Verify COMM2 frequency changes as entered 24 Press the N
13. 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 MFD 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 MFD 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 300 B300 Series King Air Revision 4 190 00716 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 On the MFD monitor GPS signal strength bars on the AUX GPS STATUS page 2 Onthe PFD ensure that the CDI is set to GPS If it is not press the CDI softkey until GPS ENR is displayed 3 Verify that the GPS INTEG flag is out of view 4 Select 121 150 MHz on the No 1 COM transceiver 5 Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels 6 During the transmit period verify that the GPS INTEG
14. and press ENT key on PFD1 3 Rotate the small FMS knob to highlight King Air BLR winglet STC model 300 only Press ENT key on PFD1 4 Verify King Air BLR winglet STC model 300 only 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 PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 65 190 00716 01 Revision 4 3 48 Splash Screen Loading When all software and configuration has been loaded the splash screens must be loaded to all display units PFD1 PFD2 and MFD If not applied apply power to the G1000 system Remove power from PFD1 PFD2 and MFD by opening the PFD1 PRI SEC PFD2 and MED circuit breakers NO Re 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 10 Apply power to PFD1 and re
15. 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 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 6 21 190 00716 01 Revision 4 6 33 GA 58 Traffic Antennas Removal 1 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 in Table 1 2 4 Reinstall cabin interior ceiling panel 5 Test the GTS 820 850 or GTS Processor according to Section 7
16. 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 7 Repeat steps 5 and 6 and re transmit while monitoring GPS 2 signal levels on the MFD 8 Repeat steps 4 through 7 for each of the following frequencies e 121 175 MHz e 121 200 MHz e 131 250 MHz e 131 275 MHz e 131 300 MHz 9 Repeat steps 4 through 8 for the No 2 COM transceiver GIA2 10 On the MFD select the AUX SYSTEM SETUP page 11 Under the COM CONFIG field change the COM channel spacing from 25 kHz to 8 33 kHz 12 Go back to the AUX GPS STATUS page 13 Select 121 185 MHz on the No 1 COM transceiver 14 Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels 15 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 16 Repeat steps 14 and 15 and re transmit while monitoring GPS 2 signal levels on the MFD 17 Repeat steps 14 through 16 for each of the following frequencies e 121 190 MHz e 130 285 MHz e 131 290 Mhz 18 Repeat steps 14 through 17 for the No 2 COM transceiver GIA2 19 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 VOR LOC GS Test Check the VOR ILS and Glideslope functions with ramp test equipment Operate the equipment according to the test
17. 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 highlight King Air FDR Option Press ENT key on PFD1 Verify King Air FDR 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 Configuration and Software columns for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 52 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 35 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 3 36 NOTE The G1000 can onl
18. voice or One Hundred voice TAWS voice callout GPWS mode 6 voice callout as appropriate per altitude Caution 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 System Failure voice TAWS Warning alert Imminent impact with obstacle TAWS status alert Terrain failure TAWS Not Available voice TAWS status alert Terrain not available TAWS System Test OK voice If passed or TAWS System Failure voice If test failed TAWS status alert Terrain self test TAWS 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 3 Revision 4 Alert Name Monitor Vertical Speed voice Purpose TCAS II Resolution Advisory Ver
19. 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 TAWS Configuration 3 Key Test 7 Alert Configuration 4 Diagnostics 8 DAT Configuration GIA Page Group 1 Serial Configuration 3 GIA I O Configuration 5 GIA Status Page 2 GIA RS 485 Configuration 4 GIA COM Setup 6 GIA CAN Configuration GSD Page Group 1 GSD ARINC 429 Configuration 3 GSD I O Configuration 2 GSD RS 485 Configuration 4 GSD Status Page 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 GMA Configuration Page 3 10 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 GDL Page Group 1 GDL 69 Configuration
20. A GARMIN G1000 GFC 700 System Maintenance Manual Hawker Beechcraft Model 300 B300 Series King Air Contains Instructions For Continued Airworthiness For STC SA01535WI D enen TI e i ETERA ES 190 00716 01 February 2014 Revision 4 This page intentionally left blank Copyright 2012 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 of 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 In
21. G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 2 21 Revision 4 Pitot Static System The following schematic shows the pitot static system as modified by this installation 2 5 SLYOd OLLWLS HA S1YOd SILVLS HI snaviva Niva veug S 1vO SR 140d OILYLS JLYNHILTV R 3AWA 40199739S OILYLS SLVNYaL IV 3 WOLLOS ddd LO ee S 3g0ud YLYG IV L 1vO TE Niva fan a dOL an a PETEA YaLNanoD f didtodoo II VLVG HIV 2 WOLLOG LIN AgaNvis gt dol G3adSHIV ABGNVLS avaHynina SYNSSaud LV ava Hw1Nd AYNSSAYd GYVMYOsA LSVW LOLId HA LSvVW LOLId H Figure 2 24 Pitot Static System Post G1000 STC G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 2 22 Revision 4 190 00716 01 2 6 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 termination 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 drawing
22. GMA1 FAIL GMA is inoperative DAE N EEE Alerte Softkey EAVIS 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 Softkey Annunciation 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 ADVISORY softkey annunciation acknowledges the presence of the alert and displays the advisory message in the Alert Window ADVISORY Figure 5 3 ADVISORY Softkey 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 300 B300 Series King Air Revision 4 190 00716 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 Minimums Minimums voice Minimums Aural A
23. SET gt ACT VSoftkey ISET gt ACTY ACTV gt SET Configuration Correct Master Configuration Module LRUMemory Master Configuration Module LRUMemory Figure 3 10 SET gt ACTV Diagram Page 3 8 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 When troubleshooting the system technicians can look for inequalities between SET and ACTIVE columns Certain problems can be resolved 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 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 7 RS 232 CHANNEL INPUT OUTPUT CHNL 1 GD 1 GDC74 1 CHNL 2 GIA DEBUG GIA DEBUG CHNL 3 OFF OFF CHNL 4 OFF OFF CHNL 5 GTX 33 1 w TIS GTX 33 CHNL E GR 1 CHNL 7 GMA1347 1 CHNL 8 OFF 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 3 Data Transmission Indi
24. 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 aircraft flight envelope This envelope is defined by pitch roll and airspeed Th
25. cescsscsessesecsseeseeeeceeeeaeeeecesecaeeeneeaes Figure 3 17 Airframe Options 00 ccececcsseesceeeceeeeecesececeeneseeceaeeaceeeeaecaecaeeeneesecaaeeneeeees Figure 3 18 Propeller Options cceceseeseesesseceseeseeeeceaeeseeeeceaecaeeeeeeseceaesaeeeeeaeeaeeeneeaes Figure 3 19 Configuration Software Load Page Figure 3 20 Stormscope Configuration Page Figure 3 21 Stormscope Confgeuraton Figure 3 22 Supplemental Database Synchronization eccceceeseeeececeeeeeeceseeeeeeeeaee Figure 3 23 Aircraft Reestraton Figure 3 24 GDL 69 Cable Loss Figure 3 25 GDL 69 Cable Loss Confeured Figure 3 26 Navigation Database Synchronization eccceseeseeeeceececeeeeeeeceaeeateeeeeaee Figure 4 15 GTA W O Page nn a a E E E a a E E E Figure 4 2 Discrete Valid Invalid Indications 0 cecceeceescesececeeceeeeceeeeseeeeceaeeaeeeeeeaes Figure 4 3 GRC Status Pages nees Sangos kera a e pn AR E ROR G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page v Revision 4 Figure 4 4 Ambient Temperature Conversion Chart 4 27 Figure 4 5 E el EE EE 4 32 Figure 4 6 Power Supply Connecton 4 34 Figure 4 7 Exterior Skin Inspection Around Antenngag 4 36 Figure 5 1 AUX System Status Page 5 1 Figure 5 2 Alerts amp Anmunctatons 5 2 Figure 5 3 ADVISORY Softkey Annunciation ccceceesssesceseeseeeecesesaeeeeceaecaeeeceesecaaeeaeseeceaecaeeereeaeeaee 5 2 Figure 5 4 S
26. 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 as they will remain locked to the old System ID number e Load correct software version See Section 3 9 for the Software Load Procedure G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 67 Revision 4 5 15 GRS 77 or GRS 7800 and GMU 44 Troubleshooting 5 15 1 AHRS Common Problems Symptom 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 EE E 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 v If no damage can be found replace GRS 77 or GRS 7800 configuration module v f problem persists replace the GRS 77 or GRS 7800 Ensure that a cell phone or a device using cell phone technology is not t
27. e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the ChartView Enable card from PFD1 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 53 190 00716 01 Revision 4 3 37 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 00629 02 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 16 TAWS Functional Check 1 With the TAWS B Enable card in the top slot of PFD1 and PFD1 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 King Air Enable TAWS Press ENT key on PFD1 Verify
28. 2 SYSTEM DESCRIPTION btsccssetsciesencecsccsstivscenstveleaeeticsssstecevaveccveeseotteseatececsestettessenscesedsveeseesteeteseats 2 1 2 1 EQUIPMENT DERSCRIPTIONS 2 1 2 2 GI1O00 OPTIONAL DNTERFACES E E E EAA NA 2 14 2 3 ELECTRICAL POWER DISTRIBUTION ees oaae E O AOE N E obs 2 15 2 4 ELECTRICAL LOAD UML ZATON a a a r a a aa Ea oaae Ea a Eaa EE AEAEE 2 18 2S CPITOD STATIC SY STEN ege ee ee eege TETON 2 22 2 6 SHIELD BLOCK OGROUNDS 2 23 2 7 GI1000 GFC700 BLOCK DIAGRAM anlan i aa a E a A aaa a 2 23 3 G1000 CONTROL amp OPERATION eesseoeesseceesseoeessoceessoceesseceesoceessoceessoceesseoeessoceessooeesseceesseceesse 3 1 3 1 GDU 1040A AND GDU 1500 DiSptAxg 3 1 3 22 GCU 477 MFD CONTROLLER akana aA aI LASA ERN EAN RAA NREN 3 3 3 35 OMEC TIO ARCS CONTROES S m s a e a E E E A N TES 3 3 34 GMA TAID AUDIO PANEL 33 cs dit ETA ANE E neath bir ens 3 4 3 5 GIOOOJNORMAL MEss EE EREM bebe ane Ee 3 5 3 65 REVERSIONARY MODE ees eseu ed e 3 6 3 7 CONFIGURATION MODE OVERVIEW i reinriiner tor aE ER A EEE AEAEE 3 7 3 8 G1000 GFC 700 SOFTWARE INFORMATION 3 12 3 9 G1000 SOFTWARE CONFIGURATION PROCEDURE sssssessssseessereessrreessrrerssrrerssrrrtssrrerssrrerssreets 3 19 3 10 NON GARMIN TAS TCAS I TRAFFIC SYSTEM OPTION CONFIOGURATION 3 24 3 11 GTS 820 850 TRAFFIC SYSTEM CONFIGURATION ssssessssseessssetsseretsseretssrretsstrerssrrerssereessees 3 25 3 12 ATES PROCESSOR 57 aE EAEN AREE T ETATE N 3 26 3 13 E EE ER HOCH BE ne EE 3 27 3 1
29. ACTIVE AOUIVE settings Uses settings Uses Contains ce ESAD settings Uses PFD internal PFD iennet ACTIVE RN PFD internal configuration files configuration files settings Uses configuration files configuration files for backup for backup PFD internal for backup for backup configuration files for backup RS 485 GDL 69A GWX 68 70 Contains Contains ACTIVE ACTIVE settings Uses Gi settings Uses PFD internal PFD internal configuration files configuration files for backup for backup Figure 3 14 G1000 LRU Configuration File Storage G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 3 17 Revision 4 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 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 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 u
30. ARINC 429 CONFIG ACTIVE GDC74 1 GIA DEBUG OFF OFF GTX 33 1 w TIS GRS77 1 GMA1347 ei OFF ACTIVE Low Low Low Low Low High Low Low Low Low Low Common OUTPUT SET GDC74 1 GIA DEBUG OFF OFF GTX 33 1 w TIS GRS77 1 GMA1347 1 OFF DATA SET OFF OFF OFF GDC74 1 GRS77 1 OFF OFF OFF OFF OFF ACTIVE GDC74 1 GIA DEBUG OFF OFF GTX 33 1 w TIS GRS7 1 GMA1347 1 OFF ACTIVE OFF OFF DC74 1 RS77 1 Figure 8 2 GIA Data Verification ARINC429 RS 232 13 Activate the cursor and select GIA2 in the SELECT UNIT field and then press the ENT key 14 Repeat Steps 13 and 14 Page 8 8 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 15 On PFD1 go to the CAN RS 485 CONFIGURATION page in the GIA Page Group 16 Verify that GIA1 is selected in the SELECT UNIT field 17 Observe the data indicators for all configured RS 485 channels 18 Verify all DATA indicators are GREEN indicating the channels are receiving data as shown CAN RS 485 CONFIGURATION SELECT GIA UNIT GIA1 CAN CHANNEL INPUT DATA OUTPUT DATA DATA SET ACTIVE ACTIVE CHNL 1 GOFF OFF OFF CHNL 2 EF OFF OFF RS 485 CHANNEL INPUT DATA OUTPUT DATA BATA SET ACTIVE SET ACTIVE CHNL 1 wGEA 1 GEA 1 GEA 1 GEA 1 DN 2 OFF OFF OFF CHNL 3 GOFF OFF OFF CHNL 4 mGFC700 CFC 7G DN 5 GOFF OFF OFF CLOCKED DATA INTERFACE CHANNEL INPUT OUTPUT DATA
31. ENT key to indicate that the process is complete When this is done the TEST COMPLETE field stops blinking 6 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 300 B300 Series King Air Revision 4 190 00716 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 vibration 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 e 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 PFD 2 and GRS 2 and proc
32. NAV 1 1 1 0 A 011 01105 20 Primary power input GIA 63W COM 1 1 4 3 A Max 011 01105 20 Primary power input See Notes 0 3 A Not Transmitting 4 3 A Transmitting GMC 710 AFCS Controller 1 0 16 A 011 01020 10 1 0 3 A GRS 77 Primary power input See Note 011 00868 10 GMU 44 011 00870 10 GRS 77 GMU44 AHRS lor 011 00870 20 GRS7800 GMU44 AHRS 1 1 0 45 A GRS 7800 Primary power input See Note 011 02278 00 GMU 44 011 00870 10 011 00870 20 GDC 7400 1 1 0 230 A 011 02337 00 Primary power input 011 02337 01 GDU 1040A PFD 1 1 2 5 A Max 011 00916 10 Primary power input See Notes 1 3A above 15 C 2 5A below 15 C GMA 1347D 1 Audio Panel 1 1 75 A 011 01257 20 Primary power input Meggitt Sig Cond 1 1 032 A 85 292 4 GEA 71 1 1 0 5A 011 00831 00 No 2 Triple Fed Bus GSA 80 Roll Servo 1 161A 011 00877 20 GSA 80 Pitch Servo 1 161A 011 00877 20 GSA 9000 Yaw Servo 1 1 80 A 011 02213 00 011 02213 10 GSA 80 Pitch Trim Servo 1 161A 011 00877 21 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 2 19 Revision 4 Units Ea Unit Equipment Used Amps DC Part Number Notes MFD Cooling Fan 1 01A 305468 00 Sandia P N or 013 00102 00 Garmin P N GDU 1500 MFD 1 3 2 A Max 011 01108 10 2 0 A Temp above 15 C See Note 3 2 A Temp below 15 C GSD 41 1
33. Page 5 8 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 PFD 2 ARINC 429 Channel 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 GRS 77 or GRS 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 GRS1 o Replace original GRS1 if box turns green after swapping units GRS 77 or Load PFD2 configuration file GRS 7800 2 f Ge Swap PFD2 and PFD1 to confirm if the problem is in the original PFD2 o Replace original PFD2 if box turns green after swapping displays Swap GRS1 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 PFD2 GRS 77 or GRS 7800 2 interconnect wiring for faults PFD2 GRS 77 or GRS 7800 2 data path functionality is unknown Reload PFD2 configuration file PFD2 GDC 7400 2 data path is functioning correctly PFD2 GDC 7400 2 data path is not functioning correctly e Verify GDC 74 2 status is OK using the System Status page on the MFD If it is not correct condition before proceeding reference GDC troubleshooting sect
34. 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 300 B300 Series King Air Page 7 29 190 00716 01 Revision 4 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 Installed 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 300 B300 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
35. 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 REGISTERED in the STATUS window 6 With the REGISTER field highlighted press the ENT key on the GCU 7 Verify that the STATUS field indicates REGISTERED and that the data displayed in the CURRENT REGISTRATION field matches the aircraft information G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 57 190 00716 01 Revision 4 7 29 GDL 59 Wi Fi Data Link Functional Check This check verifies GDL 59 Wi Fi Data Link interface is 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 1 Start the G1000 System in Normal Mode 2 Using the large FMS knob select the AUX page group on the MFD Using the small FMS kn
36. Reload GIA1 configuration files G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 13 190 00716 01 Revision 4 GIA2 RS 232 Channel GDC 7400 2 GRS 77 or GRS 7800 1 output only GTX 33ES or GTX 3000 2 w TIS Indicator Status GIA2 GDC 7400 2 data path is functioning correctly GIA2 GDC 7400 2 data path is not functioning correctly e Load GIA2 and GDC 7400 2 configuration files e Swap GIA2 and GIA1 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 Check the GIA1 GDC 7400 2 interconnect wiring for faults Replace GDC 7400 2 if problem remains White N A GIA2 GDC 7400 2 data path functionality is unknown Reload GIA2 configuration files GIA2 GRS 77 or GRS 7800 1 output data path is not monitored A white N A box is normal GIA2 GTX 33 or GTX 3000 2 data path is functioning correctly GIA2 GTX 33 or GTX 3000 2 data path is not functioning correctly e Load GIA2 and GTX 33 or GTX 3000 2 configuration files Swap GIA2 and GIA1 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 Check the GIA2 GTX 33 or GTX 3000 2 interconnect wiring for faults Replace GTX 33 or GTX 3000 2 if problem remains GIA2 GT
37. Removal 1 Remove MFD 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 5 Remove the standby attitude indicator Reinstallation 1 Ensure the lighting control voltage switches on rear of unit are set for 28V 28V Zl E 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 Page 6 18 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 6 29 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 a Phillips screwdriver to remove the attachment screws and duct if installed from the cooling fan 5 Remove the cooling fan COOLING FAN COOLING FAN HOSE TYP NOSE WHEEL WELL HOUSING VIEW OF LEFT SIDE NOSE AVIONICS BAY NOT AL
38. SEC power sources for GIA 1 GRS 1 PFD 1 and GDC 1 The AHRS and ADC data path to PFD PFD and MFD Ethernet connection includes ARINC connection between ADC and MFD and DISPLAY BACKUP button function 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 2 3 Connect a ground power unit to the external power receptacle and turn on the ground power unit Set the BAT EXT PWR and AVIONICS MASTER PWR switches to ON With the G1000 system in normal mode pull the following circuit breakers on the right hand circuit breaker panel Wait PFD 1 PRI AHRS 1 PRI ADC 1 PRI GIA 1 PRI at least 5 seconds then verify the data on PFD1 remains valid and the following alert messages are not present GIA 1 FAIL or any related message such as COM1 NAV1 XPDR1 GPS1 AHRS 1 FAIL ADC 1 FAIL FAILED DATA PATH Close the circuit breakers listed in step 3 Repeat step 4 Pull the following circuit breakers on the right hand circuit breaker panel Wait PFD 1 SEC AHRS 1 SEC ADC 1 SEC GIA 1 SEC at least 5 seconds then repeat step 4 Close the circuit breakers listed in step 7 B AHRS and ADC data path check l Verify there are no AHRS loss of data messages such as AHRS not receiving any GPS information AHRS not receiving backup GPS information AHRS using backup GPS sou
39. SET ACTIVE CHNL 4 OFF OFF SACHER eege be e Figure 8 3 GIA Data Verification RS 485 19 Activate the cursor and select GIA2 in the SELECT UNIT field and then press the ENT key 20 Repeat Steps 18 and 19 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 8 9 190 00716 01 Revision 4 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 performing these checks should be thoroughly familiar with the G1000 and GFC 700 Information on the installation and operation of the GFC 700 can be found by referring to Sections 6 11 6 14 and the G1000 in King Air 300 B300 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 set the AVIONICS MASTER PWR and EXT PWR switches to OFF After 30 seconds set the EXP PWR 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 PFT annunciation is displayed on PFD1 and PFD2 as shown in Figure 8 4 ew 113 88 118 98 eT wie 133 806 carts w2 115 98 118 98 11x5 123 800 135 325 cre i200 21 PFD BS OO POR IOS TMVREF WAST Figure 8 4 Pre Flight Test NOTE A momentarily red
40. 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 005 00629 00 Master Drawing List Garmin G1000 GFC 700 in Hawker Beechcraft Model 300 B300 Series King Air 005 00629 02 General Arrangement G1000 GFC 700 King Air 300 B300 Series 005 00629 40 Main Instrument Panel Installation King Air 300 B300 005 00629 41 Pedestal Re Configuration King Air 300 B300 005 00629 42 GWX Radar Install King Air 300 B300 005 00629 43 Antenna Install King Air 300 B300 005 00629 44 Electrical Equipment Install Nose Bay King Air 300 B300 005 00629 45 Roll Servo Install King Air 300 B300 005 00629 46 005 00629 48 Yaw amp Pitch Servo Install King Air 300 B300 Pitch Trim Servo Install King Air 300 B300 005 00629 49 Magnetometer Install King Air 300 B300 005 00629 50 OAT Sensor Install King Air 300 B300 005 00629 52 005 00629 54 Optional Equipment Install Tail Shelf King Air 300 B300 Wire Harness Installation Nose King Air 300 B300 005 00629 55 Wire Harness Installation Cabin King Air 300 B300 005 00629 56 Wire Harness Installation Tail King Air 300 B300 005 00629 57 Control Wheel Modi
41. This document applies to all Model 300 B300 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 Maintenance 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 Aircraft Model Software Version Note
42. 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 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 are 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 38 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 PFT Faults MONITOR PFT STEP is a This can sometimes be a result of a failure on the other internal servo ER 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 N
43. configuration has been loaded per Section 3 32 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 26 ESP Functional Check 1 With the Enhanced AFCS Unlock card in the top slot of PFD1 and PFD1 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 Enhanced AFCS and press ENT key on PFD1 3 Rotate the small FMS knob to highlight King Air Enable Enhanced AFCS Press ENT key on PFD1 4 Verify King Air 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 PFD1 to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the Enhanced AFCS Unlock Card from PFD1 Page 3 58 G1000 GFC 700 System Mai
44. if applicable v Replace cooling fan if unable to determine if operating correctly v If problem persists replace the MFD If problem continues contact Garmin Aviation Product Support for assistance PFD 1 COOLING has poor cooling Reducing power usage PFD 1 has exceeded its operating temperature range Check cooling fan and wiring for proper operation if applicable v Replace cooling fan if unable to determine if operating correctly v If problem persists replace the PFD1 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 Check cooling fan and wiring for proper operation if applicable v Replace cooling fan if unable to determine if operating correctly v If problem persists replace the PFD2 If problem continues contact Garmin Aviation Product Support for assistance Page 5 50 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 5 9 4 Key Alerts Failure Message MFD1 key KEYSTK key is stuck The SYSTEM has determined a key is stuck on MFD1 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 The system has determined a key is stuck on the PFD 2 5 9 5 Misc
45. review the GFC 700 equipment status software and certification gains Reload software configuration and certification gains to the GIAs and GSA servos Check the GFC Status page for additional GFC 700 system information Review the fault and assert logs for the GIAs and servos see Section 5 6 3 Isolate the fault to an LRU Replace this LRU and confirm the resolution of the annunciation Pitch Axis Failure Pitch Trim Axis Failure Yaw Axis Failure Roll Axis Failure Check the AUX SYSTEM STATUS page to see if the servo is online green check Check that the affected servo is receiving power Check the servo wiring and connector For pitch trim check pitch trim switch operation to verify switch contacts are not stuck If failure condition still exists remove and replace the affected servo AHRS Monitor Failure If the 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 Elevator Mis Trim Up Aileron Mistrim Right If elevator mistrim annunciations persist check the pitch and pitch trim servos for proper operation Verify that the servo is online at the AUX SYSTEM STATUS page Check the servo wiring and connectors Ensure the servo is receiving power Check the aircraft control adjustments If mistrim con
46. that there is an empty SD card in the card reader and then click Setup WinZip Self Extractor 006 B0985 04 OA exe S G1000 Software Update To install software press Setup c ance WinZip Self Extractor 006 B0985 04_0A exe lt gt G1000 Software Update Es To install software press Setup T ance Unzipping grm_ayvtn_sys gca About 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 format on the SD card Ensure files are not necessary or card is empty before proceeding G1000 Software Update This wizard will guide you through the process of updating the software in your G1000 integrated cockpit Airframe King Air B200 B300 Version of card Version 098504 AT being created Please enter your SD card in the card programmer and then click Next to proceed Enter SD card Click next once card is inserted Page 3 14 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 8 Ensure the card and correct drive letter is used and click next G1000 Software Update amp GARMIN Choose the appropriate drive below and click Next IF your drive is not listed plug it in and click Find Drive Storage Card Reader Select the drive letter used by your storage card reader Removable Disk E e Select drive e 9 A
47. to acknowledge prompt 8 After completing transponder configuration deactivate the cursor Page 7 12 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 7 5 2 GTX 33 or GTX 3000 Test Operation of the GTX 33 or GTX 33D or GTX 3000 Mode S transponder is accomplished using PFD 1 PFD 2 or the MFD Refer to G1000 in King Air 300 B300 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 S 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 7400 Air Data Computer Original GDC 7400 is Reinstalled No software or configuration loading is required if the removed 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
48. 0 5 A 011 01457 00 GEA 71 2 1 0 5A 011 00831 00 No 3 Triple Fed Bus GDU 1040A PFD 2 1 2 5 A Max 011 00916 10 1 3A above 15 C See Notes 2 5A below 15 C 0 3 A Total GRS 77 011 00868 10 GMU 44 GRS 77 GMU 44 AHRS 2 or i i EEN GRS 7800 GMU 44 AHRS 2 045 A Total GRS 7800 011 02278 00 GMU 44 011 00870 10 011 00870 20 GDC 7400 ADC 2 1 0 230 A 011 02337 00 011 02337 01 GIA 63W NAV 2 1 10A 011 01105 20 GCU 477 FMS CTL 1 0 085 A 011 01428 00 Standby Battery 1 See Note 501 1228 03 or 2 5 A for model PS 835C 501 1228 04 5 A for model PS 835D PFD 2 Cooling Fan 1 LIA 305468 00 Sandia P N or 013 00102 00 Garmin P N GIA 2 Cooling Fan 1 0 4 A 305467 00 Sandia P N or 013 00103 00 Garmin P N Meggitt Sig Cond 2 1 032 A 85 292 4 Avionics Bus Triple Fed GTX 33 Transponder 1 16A 011 00779 30 or 1 6 A 011 00779 21 GTX 33D Transponder 1 1 1 6A 011 01997 00 or GTX 3000 Transponder 1 Standby Battery Bus Standby Attitude Indicator 1 0 25 A 4200 11 MOD 2 Standby Altimiter 1 See Note 3A43 22 35F 28 Vibrator 030 A 1 FU Thommen Lighting 096 A P N or 157 A total 16650 1172 Aerosonic P N Page 2 20 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 Aerosonic Corp P N Equipment W i ee Part Number Notes Standby Airspeed Indicator 1 050 A MD25 300 Mid Continent Inst P N or 050 A 25030 0184
49. 0985 07 and Subsequent 1 With PFD1 in configuration mode select the AIRCRAFT CONFIGURATION page on PFD1 2 Activate the cursor to select the AIRCRAFT REGISTRATION field and enter the aircraft s tail number 3 Rotate the large FMS knob to select the ICAO ADDRESS and enter the aircraft s 24 bit ICAO address 4 If applicable rotate the large FMS knob to select the IATA AIRLINE DESIGNATOR field and enter the airline s 2 digit airline designator code 5 Rotate the large FMS knob to 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 GTX1 softkey and acknowledge the PFD1 prompt by pressing the ENT key Press the SET GTX2 softkey and acknowledge the PFD1 prompt by pressing the ENT key Press the SET GTS softkey and acknowledge the PFD1 prompt by pressing the ENT key After completing transponder configuration deactivate the cursor D PND G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 63 190 00716 01 Revision 4 3 46 GDL 69 Alternate Antenna Location Configuration NOTE This section is only applicable to those aircraft that use the alternate location to mount the GPS antennas See drawing 005 00629 43 1 With PFD1 in configuration mode select the GDL69 page 2 Press the GDU softkeys in the numerical sequence of 12 9 6 3 to activate the cursor 3 Highligh
50. 15 Repeat steps 4 through 14 for PFD 2 and GRS 2 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 23 190 00716 01 Revision 4 7 7 5 Procedure D Engine Run Up Vibration Procedure 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 Al and B Sections 7 7 2 and 7 7 4 respectively are not required prior to this procedure GRS GMU CALIBRATION COMMUNICATION STATUS m GPS AIR DATA W MAGNETOMETER CALIBRATE Figure 7 6 Engine Run Up Test Page 1 Restart the PFD 1 in configuration mode 2 Use the FMS small knob to highlight GRS 1 for calibration and press the ENT key The SELECT PROCEDURE field is not blinking 3 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 4 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 5 When the operator has completed the engine run up and the engine is back to an idle setting press the
51. 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 assistance if needed MFD1 DB ERR MED 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 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
52. 27 6 34 GDL 59 Wi Fi Datalink Removal 1 Gain access to the avionics shelf in the tail area 2 Remove the Philips head screw which holds the locking lever down 3 Lift the locking lever up to unlock the unit from the mounting rack 4 Remove the unit from the mounting rack Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Insert the unit into the installation rack CAUTION 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 The rear plate is designed to float in the unit rack Check to ensure the rear plate is not bound by the connector harness 3 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 lbs to the handle screw The application of torque exceeding 14 in lbs to this screw will damage the LRU case and or retaining hardware 4 Ifnew unit is installed register with Garmin Connext per Section 7 28 5 Configure the GDL 59 per Section 3 15 and 3 16 Test the GDL 59 per Section 7 29 Page 6 22 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4
53. 3 29 190 00716 01 Revision 4 3 16 GSR 56 Satellite Receiver with GDL 59 Wi Fi Data Link Option Configuration Follow this procedure to enable the optional GSR 56 Satellite Receiver with GDL 59 Wi Fi data link function NOTE 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 15 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 PFD1 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 PFD1 3 Rotate the small FMS knob to highlight King Air GSR 56 with GDL 59 Press ENT key on PFD1 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 Configuration and Software columns for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 30 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revisio
54. 5 Remove the standby airspeed indicator 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 27 Standby Altimeter Removal 1 Remove MFD 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 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 300 B300 Series King Air Page 6 17 190 00716 01 Revision 4 6 28 Standby Attitude Indicator Ensure the standby attitude indicator gyro is not spinning this may take 10 minutes or longer after the unit has been turned off This unit is very delicate handle with care Refer to the 4200 Series Attitude Indicator Installation Manual listed in Table 1 2 for more handling instructions
55. 77 on the mounting plate ensuring the orientation is correct 3 Fasten the unit to the plate using the Phillips thumbscrews 4 Connect the connector to the GRS 77 5 Calibrate and test the GRS 77 according to Section 7 7 GRS 7800 Removal 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 Disengage 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 a G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 6 5 190 00716 01 Revision 4 6 9 GMU 44 Magnetometer NOTE The GMU 44 magnetometers may be located in the tailcone or in the horizont
56. A58 TRAFFIC ANTENNA UPPEE PTIONAL L Rz Z LS GA ANTENNA V I FI ANTENNA PTIONAL TRANSPONDER ANTENNA UPPER PTIONAL A A37 CPS XM ANTENNA A37 XM ANTENNA PTIONAL LOCATION I TRAFFIC ANTENNA LOWET PTIONAL Figure 4 7 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 other approved sources Page 4 36 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 5 TROUBLESHOOTING This section provides instructions and guidance for G1000 system troubleshooting as installed in the King Air 300 B300 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 t
57. AEE 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 1 for troubleshooting 4 Repeat Steps 1 3 to test the PFT aural alert for the other GIA 63W Continue to Section 8 2 2 Page 8 10 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 8 2 2 AFCS Switch Checks Verify that the AFCS system buttons and switches are operating correctly by performing the following 1 10 11 12 13 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 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 Engage the autopilot by pressing the AP key on AFCS mode controller Press and hold the left section of the manual
58. AIR DATA 2 for each condition 7 On Table 7 5 record the airspeed IAS displayed on PFD1 for AIR DATA 1 and AIR DATA for each condition 8 Verify that the indicated altitudes and airspeeds are within allowable tolerances 9 File the results with the aircraft maintenance records 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 Page 7 14 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 Table 7 5 Air Data System Test Test S R Point Altitude FT Airspeed KIAS AIR DATA 1 AIR DATA 2 AIR DATA 1 AIR DATA 2 Nominal ALT AS Altitude Tolerance Tolerance Tolerance Tolerance Actual Actual Actual Actual 0 20 20 2 2 0 0 0 20 20 2 2 99 0 0 20 20 2 2 132 0 0 20 20 2 2 198 0 1000 20 20 2 2 50 1000 2000 25 25 2 2 50 2000 4000 25 25 2 2 80 4000 8000 30 30 2 2 80 8000 8000 30 30 2 2 260 8000 10000 30 30 2 2 120 0000 11000 35 35 2 2 120 1000 13000 40 40 2 2 150 3000 14000 40 40 2 2 150 4000 16000 45 45 2 2 180 6000 18000 45 45 2 2 210 8000 190
59. Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 24 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 11 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 The G1000 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 45 Aircraft Registration Number Entry 1 With the loader card in the top slot of PED and PFD1 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 PFD1 3 Rotate the small FMS knob to highlight King Air GTS 8XX TAS TCAS1 Press ENT key on PFD1 4 Verify the King Air GTS 8XX TAS TCAS1 is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes
60. GCU 477 FMS controller and may not function prior to software load New software is loaded to the PFD or MFD unit and the following screen is displayed DO YOU WANT TO UPDATE THE CUSTOM GRAPHIC FILES EG SPLASH SCREEN NO WILL BE ASSUMED IN 3 SECONDS Press the softkey labeled YES Note that the splash screen may need to be loaded again after all software and configuration loading is completed When complete the display starts in configuration mode displaying the System Status page Do not remove power Remove the Loader Card from the display and insert it into the top card slot on another display if desired Repeat Steps 5 through 9 as needed IMPORTANT For the rest of the software configuration procedure do not operate the MFD or PFD 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 300 B300 Series King Air Revision 4 190 00716 01 3 9 2 G1000 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 IMPORTANT Do not allow power to be removed from the system when loading software Remove po
61. GEA1 o Replace original GEA 1 if box turns green after swapping units Check the GIA2 GEA 1 interconnect wiring for faults GIA2 GEA1 data path functionality is unknown Reload GIA2 configuration files GIA2 GEA2 data path is functioning correctly GIA2 GEA2 data path is not functioning correctly e Verify GEA2 is powered on using the GEA Status page e Load GIA2 and GEA2 configuration files e Swap GIA2 and GIA1 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 Swap GEA2 and GEA1 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 configuration files GIA2 GFC 700 data path is functioning correctly GIA2 GFC 700 data path is not functioning correctly e Load GIA2 configuration files GIA Gains file and GSA software and gains file if LRU and Card versions are different GFC 700 Reference GFC section for further troubleshooting GIA2 GFC 700 data path functionality is unknown Reload GIA2 configuration files Page 5 18 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 2 2 System Failure Troubleshooting
62. GMC 710 if problem remains PFD1 GMC 710 data path functionality is unknown Reload PFD1 configuration file Page 5 6 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 PFD 1 ARINC 429 Channel GRS 77 or GRS 7800 1 GDC 7400 1 Indicator Status PFD1 GRS 77 or GRS 7800 1 data path is functioning correctly PFD1 GRS 77 or GRS 7800 1 data path is not functioning correctly e Verify GRS77 or GRS 7800 1 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 GRS1 Replace original GRS1 if box turns green after swapping units Load PFD1 configuration file Swap PED and PFD2 to confirm if the problem is in the original PFD1 o Replace original PFD1 if box turns green after swapping displays Swap GRS1 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 PFD1 GRS 77 or GRS 7800 1 data path functionally is unknown Reload PFD1 configuration file PFD1 GDC 7400 1 data path is functioning correctly PFD1 GDC 7400 1 data path is not functioning correctly e Verify GDC 74 1 sta
63. GPS1 receiver GPS2 SERVICE GPS2 needs service Return unit for repair The system has detected a failure in GPS2 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 v If problem follows the unit replace GIA If problem does not follow the unit check GPS antenna and cabling Page 5 60 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Failure Message 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 Solution Verify 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 uscg gov gps gps notices default htm will
64. HSI to LOCI and PFD2 HSI to LOC2 by pressing CDI soft key until LOC1 and LOC2 is selected Use the test equipment to center the deviation bars localizer and glideslope on PFD1 and PFD2 9 Press the APR key on the AFCS mode controller Verify that the LOC and GS annunciations are green on PFD1 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 10 Couple FD to PFD1 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 the XFR button 11 Repeat step 9 while coupled to PFD1 Page 8 14 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 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 Part number of the G1000 software loader card used to perform software loading or software updates e Record part and serial numbers of any LRU which was replaced e Record any database updates which were performed during maintenance e Any other applicable information related to the maintenance work performed on the aircraft Date Aircraft Registration Aircraft Model Aircraft Serial G1000 Loader
65. King Air 190 00716 01 Revision 4 20 19 18 17 16 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1 42 41 40 39 38 37 36 35 34 33 32 31 30 29 28 27 26 25 24 23 22 62 61 60 59 58 57 56 55 54 53 52 51 50 49 48 47 46 45 44 43 P3301 0 0 60 61 62 63 64 65 66 67 68 69 70 71 72 73 LR 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 O 21 22 23 24 25 26 27 28 29 30 31 Sewer eee er eee ee eee ee 1 2 3 4 5 6 7 8 10 11 12 13 14 15 16 17 18 19 20 E ae a z0 20 N d se 20 ze s0 E Si Si co P3302 Figure 5 12 GTX 3000 Connector w een O A SSES SS eves Cre ee e ee e ge 3 Se e e e e ez e e e ee ee er D v2 zi CO CH Figure 5 15 GRS 7800 Mating Connector P78001 Kai Page 5 82 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 Figure 5 19 GMC 710 Mating Connector P7101 1 23 4 5 6 7 8 9 10 1 12 13 14 15 EE ae 17 18 19 20 21 22 23 24 25 26 27 28 29 30 kal A ARA e WR vc 31 32 33 34 35 36 37 38 39 40 41 kl RR 42 43 44 kal RA Figure 5 20 GWX 68 Mating Connector P681 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 83 Revision 4 eee eee o o 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 LR 40 41 42 43 44 45 46 47 48
66. LRU box you may select either GIA1 or GIA2 b Inthe SERVO box choose a servo using the FMS knobs Each servo contains two logs one in the Monitor MON processor and one in the Control CTL processor You must download both for each servo separately c Inthe COMMAND box select View Maintenance Log and press 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 10 Press the LG2CRD softkey to turn off the recording function 11 Wait 1 minute for the system to save the data from the download to the SD card Page 5 42 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 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 diag but og GC file from the SD card using the WordPad progra
67. 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 different regions Americas International Atlantic etc Load same type aviation database to all displays G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 49 Revision 4 Failure Message 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 Failure Message Alerts MFD1 COOLING has poor cooling Reducing power usage The PFDs and or MFD have different terrain database types installed i e different regions Americas International Atlantic etc MFD1 has exceeded its operating temperature range Solution Confirm supplemental data card is inserted fully Reload the database or replace the supplemental datacard Solution Check cooling fan and wiring for proper operation
68. PART NUMBER VER REPORT MAIN SUB SYSTEM GIA1 CLC TSE crswansenane ILL st Wee rr CC wes o O O S cesnricaioncans __ LSeeesrasr Es a o GIA 63W IAU 2 AUDIO GIA2 AUDIO GPS WAAS ENGINE GPS2 COMMUNICATION COM2 NAVIGATION NAV2 wea i CERTIFICATIONGAINS GC CERT GIA2 Pale je LI NI E LI SYSTEM MED GDU 1500 MFD E e Wi WE FPGA MFD FPGA GDC 7400 AIR DATA SYSTEM GDC1 COMPUTER FPGA GDC1 FPGA GDC 7400 AIR DATA SYSTEM LL T Go COMPUTER Foi III op ron GTX 33 33D 3000 TRANSPONDER GTX 33 SYSTEM GTX1 IF INSTALLED GTX 33 33D 3000 TRANSPONDER GTX 33 SYSTEM GTX2 IF INSTALLED Figure 7 9 RVSM Required Avionics Any other transponder that meets or exceeds the requirements of TSO C74c Mode C or TSO C112 Class 2a Mode S may be installed Page 7 44 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 7 25 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 10 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 except as noted below If any da
69. Restart the G1000 in normal mode C PFD and MFD Ethernet connection check includes ARINC connection check between ADC1 and MFD and between GRS1 and MFD and the DISPLAY BACKUP button check 1 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 7 Press the DISPLAY BACK UP button on the Pilot s GMA 1347D audio panel to return to normal mode 8 Close the PFD 2 circuit breaker and wait for PFD 2 to initialize Open the PFD 1 PRI and PFD 1 SEC circuit breakers 10 Press the DISPLAY BACK UP button on the Co pilot s GMA 1347D audio panel 11 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 12 Verify ADC1 data and GRS1 data can be displayed on the MFD 13 Press the DISPLAY BACK UP button on the Co pilot s GMA 1347D audio panel to return to normal mode 14 Close the PFD 1 PRI and PFD 1 SEC circuit breakers and wait for PFD 1 to initialize D Engine data availability to the displays and GPS data availability to the AHRS with either GIA inoperative check 1 Open the GIA1 PRI and G
70. Section 5 5 AP DISC Problems Check the GIA AFCS Fault Logs according to Section 5 6 3 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 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 Loss of Manual Electric Trim 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 AutoTrim Inoperative 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 1 2 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 31 190 00716 01 Revision 4 5 6 2 GFC Status Page The GFC Status page is presented in configuration mode and gives status information regarding the GFC 700 GFC STATUS Sr r SELECT GIA UNIT _ GIA 1 GIA STATUS AP DISCONNECT mm HONITOR BOARD STATUS SERVO PROGRAH 1 2 AP DISCONNECT SERVO PROGRAM 2 PFT HIGH RES LOAD CELL CAL HIGH RNG LOAD CELL CAL m SERVO PROGRAM 1 AP DISCONNECT SERVO PROGRAH Z PFT SERVO PROGRAM 3 g DRIVE SERVO SERVO DATA RPM 0 00rpm Al 0 0
71. 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 1504 5 00 200 4 Observe MFD in normal mode and verify Oil Pressure indications match those values listed in Table 7 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 7 11 Revision 4 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 Troubleshooting 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 5 1 Transponder Configuration 1 Ifnot applied apply power to the G1000 system 2 With PFD in configuration mode select the GTX page group then select the TRANSPONDE
72. 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 Page 7 34 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 7 16 7 16 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 MFD 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 TERRAIN PROXIMITY or MAP TERRAIN Refer to section 3 37 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 TA WS 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 an
73. 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 Associated LRU s Solution Invalid Data Field Low Speed Awareness Band permanently displayed e With aircraft weight on wheels and the G1000 in SS Configuration Mode check that the RH GEAR ON GROUND Discrete In indication for GIA2 on GIA I O CONFIGURATION page is illuminated e 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 GDU CONFIGURATION page is illuminated e f both indications are illuminated Green switch GIA1 and GIA2 to verify location of problem v 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 ee gel Low Speed Awareness Band permanently inhibited e 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 e 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 GDU CONFIGURATION page is illuminated e f both indications are illuminated Green switch GIA1 and GIA2 to verify location of problem v If probl
74. and Pitch Trim 10 If the CLUTCH TEST FAIL message is displayed on the MFD for any axis repeat the test twice in the failed axis If the test does not pass the GSM 86 slip clutch cartridge must be replaced or tested using the Manual Slip Cluch Test Procedure Section 4 9 2 Sey R G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 4 21 190 00716 01 Revision 4 4 9 2 Manual Slip Clutch Test Procedure This test is an alternative to the automated slip clutch test 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 GSA8X GSM85 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 F Remove the GSM 86 servo gearbox as per Section 6 12 2 Place the 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 a 2 Amp 24 V DC
75. and Protection ESP feature 1 Apply power to the aircraft and avionics systems by setting the BAT EXT PWR and AVIONICS MASTER PWR switches to ON Ensure G1000 system and components are powered and operating normally 2 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 PFD1 or PFD2 4 On initial power up verify that the MFD splash screen includes the following graphic 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 indicates which side is coupled No flight director modes should be active at this time 6 On the GCU rotate the inner FMS knob to activate the AUX SYSTEM SETUP page on the MFD 7 On the 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 STABILITY amp PROTECTION STATUS 9 Verify on PFD 1 and PFD 2 that there are no ESP FAIL ESP OFF or ESP DEGRADE alert messages 10 Cover both GPS1 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 Atti
76. 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 4 25 190 00716 01 Revision 4 4 11 Engine Data Check Accomplish this section to verify the engine data availability and validity for ITT and torque Remove the left and right engine cowling Ref Super King Air 300 or B300 Maintenance Manual Chapter 71 10 00 to gain access to the engine harness connectors Required test equipment is provided in Table 4 11 Any product conforming to the specification listed may be used Test Equipment Requirement Signal Generator 0 10Vdc 0 1k Hz Thermocouple Calibrator K type 200 to 1 200 C Table 4 11 Engine Data Check Test Equipment 4 11 1 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 Super King Air 300 or B300 Maintenance Manual Chapter 71 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 and Chromel leads are strictly observed when making connection
77. assembly and the No 1 and No 2 GIA inputs and the air ground status logic Denotes Airworthiness Limitation Maintenance Requirement See Section 4 1 Special 3 000 hrs max Special 20 years max Phase 1 2 3 amp 4 220 hours max G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 4 7 Revision 4 Manual Section No Interval Description Procedure Special Exterior skin Inspect the exterior skin around 10 000 cycles inspection around antennas for cracks and loose and d initial antennas missing fasteners 1 000 cycles repeat Configuration Module Qty 5 GEA 71 Backshell Thermocouple Qty 2 GTP 59 OAT Probe Qty 2 ge Removal amp Replacement On Condition Annunciator Switch 6 24 Emergency Frequency GIA Cooling Fans Qty 2 GDU Cooling Fans Qty 3 6 29 6 30 G1000 Lightning Protection Perform the Phase 3 electrical bonding Electrical Bonding resistance check of G1000 equipment SE Test Perform the Phase 4 electrical bonding resistance check of G1000 equipment GE Lightning Strike to GTP 59 OAT Probe Inspect the antenna probe and surrounding or Antenna installation per Table 4 9 Actual or Suspected Lightning Strike To r 4 4 the Aircraft Inspect the GIA Fan discrete output Table 4 9 On Condition On Condition Page 4 8 G1000 GFC 700 System Maintenance Manual 300 B300 Series K
78. avionics unit 1 e NAVI NAV2 COM1 COM2 ADF and DME 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 GMA 1347D 1 1 Turn the GMA 1347D 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 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 1 circuit breaker to continue testing Failsafe Operation Check GMA 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 COM 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
79. be Fee eS ERR b s Want Eegen ee een 0 10 20 30 40 50 60 70 80 90 100 AMBIENT TEMPERATURE E Figure 4 4 Ambient Temperature Conversion Chart 4 11 2 Torque 1 Remove power from aircraft 2 Disconnect the left engine firewall connector J102 3 Connect the Signal Generator to pins C HI and R LO of J102 4 Apply external power to aircraft and start the G1000 in normal mode 5 Using the Signal Generator inject DC signals specified in Table 4 13 and verify the indications are within the specified tolerances Test Point VDC Torque Indication 0 000 02 0 2 1 035 02 45 2 1 725 02 75 2 2 300 02 100 2 Table 4 13 Torque 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 torque indication remains unchanged Reset the the GIA1 PRI and GIA1 SEC circuit breakers Repeat steps 1 through 5 using right engine firewall connector J103 pins C HD and R LO Pull the GIA 2 circuit breaker and verify the last observed torque indication remains unchanged Reset the GIA 2 circuit breaker 9 Remove power from aircraft and reconnect left and right engine firewall connectors G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 4 27 190 00716 01 Revision 4 4 12 Trim Annunciator Check This procedure checks the pitch trim PTRM annunciation from bot
80. 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 Super King Air 300 or B300 Maintenance Manual A complete inspection cycle for the King Air 300 B300 is 800 hours or 24 calendar months divided into the following four phases 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 allowed in the Super King Air 300 or B300 Maintenance Manual a tolerance of 20 hours for all phase inspections Special Inspection Items Calendar limited inspections have 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 300 B300 inspection program For a complete description of the King Air inspection program refer to the Super King Air 300 or B300 Maintenance Manual listed in Table 1 2 Table 4 1 Maintenance Intervals are Manual Item Description Procedure Section No Interval G1000 GFC700 Equipment Complete Visual Inspection o
81. ccccccccecsseeeseceteceneceseeeseeeseeeseecseeesaeentecsseeeseenseeeas 7 10 Table 7 2 Fuel Flow Test Points cccsscccssscosssssssccecesscecosvesceecesscoccessecceceessecesvvnssccsesssesssvvnsccecesssese 7 10 Table 7 3 Oil Pressure Indication Test Equipment ccccccccssecsseceteceseceeceeecseeeseeeeneeesaecaeenseeneesseenes 7 11 Table 7 4 Oil Pressure Test Points cccscscscccsccsscsseccccccsscsessnseccccessesssesbeceecessecsessnseceecessesvesseveecessecs 7 11 Tablet Ap Data Systemi Pest vss s3 cscstestaczeaccsdessn yebatcetedscvenaheanitesscduves aE ERARE aa RA EEA 7 15 Table 7 6 Vertical Speed Table cscs sceesecvazesets deer Ges dged dees deed Geet 7 17 Table 7 7 Required GRS GMU Cahbrapnons 7 19 Table 7 8 In Flight Altitude Hold Performance Test 7 49 Page viii G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 1 INTRODUCTION 1 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 300 B300 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
82. ceceeceseesceeeceseceeeseesececeeeeeseceaeeaeeeenaeeaeees 6 20 Figure 7 1 G1000 Normal Mode Check 7 2 Figure 7 2 Marker Beacon Svmbologw 7 4 Figure 7 3 AUX GPS STATUS Page NED EE 7 6 Figure 7 4 Normal Engine Instrument Markings MED 7 9 Fuere 7 5 Aarcraft Registration 120 AER ESA 7 12 Figure 7 6 Engine Run Up Test Page 7 24 Figure 7 7 Normal Mode AHRS Check 7 25 Figure 7 8 Low Speed Awareness Band Svmboltzapon 7 43 Figure 7 9 RVSM Required Avionics ccccecsseesseesseesseessecesecesecesecesecseeseeeeeseceseeesaecseecsaecsaecnseeeseesaeeeas 7 44 Figur 7 10 RVSM Critical REGION wiscassressicexcesdeusn de Een EES EES ENEE Ae 7 45 Figure 7 11 Dial Indicator eege Eed Eege date el de casei suas os EENS 7 47 Figure 7 12 Static Port Measurement niesienie e EEE A EEA E E 7 47 Page vi G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 Figure 7 13 Static Port Measurement locations cescesceseeseeesceseeseeeecaecateeeeaecaaeeseeeeesecnaeeneseeeeaeeaeees 7 48 Figure 7 14 Static Port Measurement Log 7 48 Figure 7 15 GTS 8XX GND TEST softkew ccescceceeseesecesesseeeeceaesaeeenceaecaecaeeeceesecaaeeeeeseceaeeaeeeeeeaeees 7 53 Figure 7 16 GSR56 Configuration Page 7 59 Figure 7 17 AUX RE E RE 7 59 Figure 8 1 GDU Data Verification ARINC A0 8 7 Figure 8 2 GIA Data Verification ARINCA7OIRS 23711 8 8 Figure 8 3 GIA Data Verification RS 485 i cic
83. clamp and remove the clamp 4 Carefully remove the unit from its mount Reinstallation 1 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 7400 according to Section 7 6 5 Reinstall the GDU 1040A display unit Page 6 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 6 7 GTP 59 OAT Probe Removal 1 Using a 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 1 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 2 Place the GRS
84. 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 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 AVN 1 FAN FAIL Avionics cooling fan 1 is inoperative AVN 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 MED cooling fan is inoperative ESP OFF ESP selected off 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 Sections 6 29 and 6 30 Check that the MFD AUX SYSTEM SETUP 2 page shows Stability amp Protection status is ENABLED ESP DEGRADE ESP IAS mode is inoperative ESP CONFIG ESP config error Config service req d Ensure ADC1 and ADC2 circuit breakers are closed and units are providing valid airspeed data 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 41 If the ESP option needs to be removed reload the baseline configuration for the spec
85. 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 GMU 44 was replaced with new unit New serial number Calibrations Required Procedure A1 GRS 77 or GRS 7800 Pitch Roll Offset Procedure B GRS GMU Magnetic Calibration None Required Procedure D Engine Run up Vibration Test Continue to GRS GMU Test section X GRS AHRS was removed and or replaced The mounting tray was NOT removed and the mounting tray bolts were NOT loosened None Required Continue to GRS GMU Test section GRS AHRS was removed and or replaced The mounting tray WAS removed and or mounting tray bolts WERE loosened GRS AHRS Configuration Module was replaced G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 7 19 Revision 4 7 7 2 Procedure A1 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 1 Level the aircraft to within 0 25 of zero pitch and zero roll using a digital level Follow instructions in Super King Air 300 or B300 Maintenance Manual listed in Table 1 2 for leveling
86. d Go oe r 5 l d l A fu m S d e IUU 8 PE E 4 D EN IP Ee 5y hf ja 5E Ra F ue Ee ees D oe Figure 2 22 300 B300 Electrical Distribution Post G1000 STC Page 2 16 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 m Si 17 ASUNa 1334 bes 1X3 Sula ONE Y Wy aud Tanda H iy aud Tans 7 1x3 u 9N3 1 INYM ALO Ta 1 WM ALO Tana 1 Io 7a j 40 qana 7 IOL Ts JOL x a x ES IAL aed T la 40 Tans 40 Tans ot BA WO Wy Q wat Wine 1 QL INNd ABLS 1 Q vn Q any iNOS lee ai Twas H Twas T va AMALIE INOD TWNOIS 71 INg Tana 1 JNa 7304 7 334 Bae 1334 3AL 1334 JAHL de 334 JAHL un ld J4 08 74 ZZ L74 qa Laysouly EN HONOHL l4 ease H Ja daveouly lav l4 H IHL 14 Lu Lay ONY qa q4 Ja J4 10014 Lay ANY v4 LavHOMIY lyy dr NIgy qWwanv d S ke Lie ASG Wel a EN Wh d 17 e J19 300W e TEE d Is die Is at La WW VIO Cdel Inn lid ee diva v agal EI IOL Ts Lie Aga iva da IHd NO Ty l ld ld y e l VAD an EENG Ades z E z WOS ONNES Tee IJL73H Aan a a 1 ad d SEA ISNI ANION 7 4S inia Es ji a Md Ile i VW IHY Y z 1 va INGI D idd 8 3 IHY ER TYNI JON any x mu sie 7 d Ba 171 ts e idd af Se 1 au 2 TEET 17 rte 1H 8 IN
87. drive the servo NOTE Be especially certain that the flight controls are clear and safe to operate before manually driving the servo Page 5 32 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 5 6 3 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 GFC 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 Thorough
88. equipment manufacturer s instructions Adjust the RF signal to a level adequate to perform the test Select the appropriate HSI source by using the CDI softkey G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 7 190 00716 01 Revision 4 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 l 10 11 Ensure FD is coupled to PFD1 as indicated by a left pointing arrow next to the AFCS mode controller XFR button Simulate a VOR signal on a radial equivalent to the aircraft heading Tune the NAV and NAV 2 receivers to the simulation frequency Set the HSI on PFD1 to VOR by pressing the CDI soft key until VOR1 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 VOR1 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 VOR 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 control
89. 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 e Every 220 hours perform a Trim Annunciator Check per Section 4 12 e Every 3 000 hours perform a GSM 86 Slip Clutch Torque Check per Section 4 9 e Every 20 years remove the GSM 9100 yaw servo gear box and send to a properly rated FAA Approved Repair Station qualified for servicing of this unit G1000 Limitations e Every 220 hours perform a Weight on Wheels and Low Speed Awareness Band Check per Section 7 24 e Every 220 hours perform a G1000 Redundant Connection Check per Section 4 10 e For aircraft equipped per MDL 005 00629 00 Rev 6 or previous revisions and not modified per Garmin Service Bulletin 1375 Every 220 hours perform a G1000 Cooling Fan Fail Annunciation Check per Section 8 1 4 See Note 1 e For aircraft equipped per MDL 005 00629 00 Rev 6 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 e Every 820 hours perform an Engine Data Check per Section 4 11 e Every 820 hours perform the G1000 Miscompare Checks per Section 4 13 e At 10 000 cycles and eve
90. 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 has 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 SES 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 appli
91. has Verify radar altimeter input is valid occurred Verify baro altitude and vertical speed input are valid G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 27 190 00716 01 Revision 4 5 5 Synthetic Vision and Pathways Troubleshooting The SVS Pathways software feature requires the following G1000 sensors data to be valid e AHRS e Heading e GPS Position e 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 Symptom Recommended Action SYN VIS softkey does not appear on PFD softkey tier Follow the steps in Section 3 40 to reactivate the SVS Pathways feature 3D terrain presentation does not appear on PFD Verify that P N 010 00442 43 terrain datacards are installed in the lower slot of the PFD and MFD Verify that the alert messages shown in Table 5 2 are not displayed on the PFD 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 If a terrain database update has just been pe
92. hour after the request for the refresh has been sent to receive the signal v Alternatively you may also go to XM s website and ente the radio ID s to have a refresh signal sent 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 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 If problem persists replace the GDL 69 69A No XM weather information is displayed Page 5 66 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 14 2 GDL 69A Alerts Failure Message GDL 69 FAIL GDL 69 has failed GDL69 CONFIG GDL 69 configuration error Config service req d MANIFEST GDL software mismatch Communication halted The G1000 has detected a failure in the GDL 69A The G1000 has detected a GDL 69A configuration mismatch The system has detected an incorrect software version loaded in the GDL 69A Solutions Replace GDL 69A Check GDL 69A antenna and cabling Check the GDL 69A and MFD interconnect Reload configuration file See Section 3 9 for the Configuration Procedure If problem persists replace master configuration module
93. in Table 1 2 as needed Invalid Field Sensor Solutions 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 Super King Air 300 or B300 Maintenance Manual listed in Table 1 2 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 Super King Air 300 or B300 Maintenance Manual listed in Table 1 2 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 25 190 00716 01 Revision 4 5 3 300 B300 Specific Alerts The following alerts are configured specifically for the King Air 300 B300 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 Check the flap full down wiring input to the GIAs Refer to G1000 GFC 700 Wiring Diagram listed in Table 1 2 WOW Invalid Ensure that the GIA1 PRI and SEC and GIA2 circuit breakers are
94. 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 in which it is stored or use the web browser s download shortcuts The GRA 5500 Retrofit Installation Tool 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 43 190 00716 01 Revision 4 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 28 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 a USB cable to the installed USB Pigtail located near the GRA 5500 Start the GRA 5500 Retrofit Ins
95. is felt during installation stop Remove the GSD 41 and identify the source of resistance 3 Lock the unit into the rack by using the ratcheting latch mechanism 4 Configure the GSD 41 according to Section 3 34 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 6 23 190 00716 01 Revision 4 6 37 GTS Traffic 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 mechanisms 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 2 Insert the unit into the installation rack 3 Lock the unit into the rack by using the ratcheting latch mechanisms 6 Connect the eight coaxial cable connectors Note the color coded bands which match the mating connectors 4 Connect the three electrical connectors 5 Configure the GTS Processor per Section 3 12 and test per Section 7 27 6 38 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 coun
96. is required for this test If the test fails the installation 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 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 73 190 00716 01 Revision 4 5 16 GDC 7400 Troubleshooting 5 16 1 Air Data Common Problems Symptom Recommended Action e Perform a pitot static leak and accuracy check per Section 7 6 of this manual Altitude is different than standby altimeter 5 16 2 GDC 7400 Alerts e Determine which instrument is outside limi
97. 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 GRT 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 11g Wi Fi protocol The 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 Flight Deck via the GDL69A using HSDB The GDL 59 is located on the upper avionics equipment shelf in the tail section The GDL 59 is powered from the Right Gen Avionics Bus Figure 2 13 GDL 59 Wi Fi Datalink G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 2 9 190 00716 01 Revision 4 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 transce
98. nut inside fuselage milli volts e OAT 2 Probe base nut inside fuselage milli volts e 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 e PFD1 Cooling fan metal base milli volts e PFD2 Cooling fan metal base milli volts e MFD Cooling fan metal base milli volts Cabin Compartment e GSA 80 Roll Servo body 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 1 amp reference current is present TIP If 1 amp reference current cannot be maintained note the difference between the attainable current and 1 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 300 B300 Series King Air Page 4 17 190 00716 01 Revision 4 4 5 4 Phase 4 Electrical Bonding Procedure 1 Connect the positive lead of the power supply to the engine compartment g
99. on 2 30 Beacon off 2 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 3 30 Elevator full nose DN 3 40 Manual electric elevator trim full nose UP 3 50 Manual electric elevator trim full nose DN 4 00 End of test Table 5 5 Magnetometer Interference Test Sequence Page 5 72 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 COMPLETE when finished The calibration status vill then be displayed TEST COMPLETE 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 PFD informs the operator if the installation has passed or failed the magnetometer interference test If the test passes no further action
100. on the GMA CONFIGURATION page for higher noise environments Replace unit only after all possible external sources of noise are eliminated Some buttons are disabled in the GUA CONFIGURATION page by default This is to remove potential sources of audio noise for inputs that are 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 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 V button is active highlight Disable Split COM with the cursor and press the ENT key to turn the box green which will deactivate Split COM mode 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 Reduce ICS Volume Ensure both GMA units are receiving power Ensure both units are properly configured by verifying there are no GMA alert messages Check interconnect wiring between the GMA s for faults Replace GMA1 If problem persists reinstall GMA1 and replace GMA2 G1000 GFC 700 System Maintenan
101. original GRS2 o Replace original GRS2 if box turns green after swapping units Check the GIA2 GRS 77 or GRS 7800 2 interconnect wiring for faults GIA2 GRS 77 or GRS 7800 2 data path functionality is unknown Reload GIA2 configuration files Page 5 16 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 5 2 1 3 GIA CAN RS 485 CONFIGURATION Page GIA1 RS 485 Channel Indicator Status GIA1 GEA1 data path is functioning correctly GIA1 GEA1 data path is not functioning correctly e Verify GEA1 is powered on using the GEA Status page e Load GIAI and GEA1 configuration files e Swap GIA1 and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA1 o Replace original GIA1 if box turns green after swapping units Swap GEA1 and GEA2 reconfigure both GEA s to their new locations to confirm if the problem is in the original GEA1 o Replace original GEA1 if box turns green after swapping units Check the GIA1 GEA1 interconnect wiring for faults GIA1 GEA1 data path functionality is unknown Reload GIA1 configuration files GIA1 GEA2 data path is functioning correctly 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 GIA1 and GIA2 reconfigure both GIA s to their new locations to confirm if the p
102. 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 Record the minimum and maximum torque values When finished remove the fixture cable and then remove the servo gearbox from the fixture 7 Ifthe minimum and maximum torque values are within the specified range in Table 4 10 the slip clutch cartridge is acceptable Reinstall the GSM 86 servo gearbox per Section 6 12 8 Ifthe minimum and maximum torque values are not within the specified range in Table 4 10 the slip clutch cartridge must be replaced NE Dica Min Measured Max Measured Min Allowed Max Allowed Torque in lbs Torque in lbs Torque in lbs Torque in lbs Table 4 10 Measured Torque This value valid only with the GSM86 continuous travel servo gearbox p n 011 01904 01 Page 4 22 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 4 10 G1000 Redundant Connection Check NOTE Throughout this check prior to the 0985 07 software version indicators showing GDC 74 are applicable to the GDC 7400 air data computers Perform the following steps to verify the following A B C D The primary PRI and secondary
103. 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 a 3D navigation solution and a 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 v If problem persists replace GRS 77 or GRS7800 configuration module v Contact Garmin Aviation Product Support if condition continues after replacing the GRS 77 or GRS 7800 and config module for additional assistance G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 21 190 00716 01 Revision 4 Associated LRU s Solution Invalid Data Field e Ensure metal objects tool boxes power carts etc are not interfering with the magnetometer and aircraft is not in hangar near other buildings parke
104. ppm RE KEE mee eng Ee Den een eee Deeg E Een EC Oe EC CA been Een Ke eee ren age OO Geet keen Een EE ees PE re Es Case eren Cem pe EE IER EEN PT Ee DER KEE ECH IECH NEEN KEE ED DEENS IER 9 E Een Een egen A SC EE been emeng EES mme DEn PO SEN men EECH EE EEN DEET PP een Fon pen Deg PE IECH EE FE een RE WE EE GE PH EEN en ESA BESSE Fee mee peace keem We ee Fa Eed Eet Een EES SS WEEN BECH REES ee Pree eren ET ep Ee T En wee maps pe Pei EEN DERES Cie GEN IER tege DEINE SCT GEN MER ES WEST Lode Fee Een t berg ES FE Fee Ee ee e EE DRESCH SE RS EE EE eme Beers Ger 2 WEE EES E 1 Ke KE Een EE EE DEEN EEN E EE EEN WEE EE E DEE ER DEE E t ER ER De Dg mer been EE een een FEH E ER DEE KEE WEE Em Dt ee ee A ES CR en Eege pen emm REH DECH Ee Fame Pm Ee Deen EE En DEn FER DEE Gd PEN FER eem em oe eem FE PS GEET DEEN ET DEE DESEN IER DOEN CES GSE ER WER ECH Ee Segen ECH Dee GE een Enn WEE emer e Wegen Ee Ween ben Ee WEEN EE ET EE EH Date WEEN Ee d SEC Fee weern en EE DE EEN EE DEEN E DEER DEE e E ERR TE Al Fan Wen em een E Ze ee E EE e e E EE E Pe men GE Pre See Deen E WER DES SEN EES PEN pe en Ed ten DECH EE EC EEN Eege aert em Ste Ee D s CS ed ee Een pen emm FER men Ee Seen De E SEN PE Eegen EE AE EE een BET ee Een a LL Femme a VEH m met DECKER Deen men RY FE E pe PE Hien En D SERE Ee E E EE SSS DEE EE EE been ee Ven apen mem ER FE bam De EE ES WEEN DP ae SEE GENE Weem ee EAEE em MENGT EE EH Pas Et Se rer Ee K eege ees Wee e
105. 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 white illuminated arrowhead points in the opposite direction Verify the green arrow displayed at the top of PFD 1 also points in the same direction 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 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 compass card moves and the flight director follows 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 Press the VS key and verify the white illumination appears next to the key 10
106. remove the unit from the rack GTX 33 Reinstallation 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 Configure and test the GTX 33 according to Section 7 5 Ne FO a der GTX 3000 Removal 1 Gain access 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 Place the GTX 3000 on the mounting rack Slide the GTX 3000 back until the foot is fully engaged with the mounting rack 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 3000 according to Section 7 5 T Ee 6 6 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
107. settings for GIA1 and GIA2 e Check GTX 33D or GTX 3000 and GIA1 interconnect e Check GTX 33D or GTX 3000 and GIA2 interconnect XPDR FAIL GTX 33 GTX Go e Perform a SET gt ACTV configuration reset on the GTX Sa Config page for each GTX and verify the aircraft registration is present e Replace GTX 33 33D or GTX 3000 v If problem persists replace GIA TAS FAIL AIRSPEED FAIL ALTITUDE FAIL VERT SPEED FAIL e Inspect GDC 7400 pitot static plumbing integrity e Inspect pitot static ports and associated equipment for faults e For TAS failure also check GTP 59 probe e Check GDC 7400 configuration settings for the PFDs MED GIA1 and GIA2 v If PFDs MED and GIA configuration settings are correct replace the GDC configuration module v If problem persists replace the GDC 7400 GDC 7400 e Check OAT probe wiring and connectors for faults e Check GDC config module wiring for damage replace OAT if any is found SES e Replace GDC config module e Replace GDC 7400 with a known good unit v If problem persists replace the GTP 59 Page 5 20 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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
108. table below 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 H2 Indication PPH 0 0 2 140 100 10 561 400 10 841 600 10 1122 800 10 Page 7 10 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 7 4 4 GEA 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 Hawker Beechcraft King Air 300 300LW or B300 B300C Maintenance Manual Chapter 71 10 00 to gain access to the engine Oil Pressure Transmitter connector P12 z Sin Ww PY NM Apply external power to aircraft Set the BAT EXT PWR 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 output the voltages specified in the table below
109. 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 PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 35 190 00716 01 Revision 4 3 22 GMU 44 Software Configuration Follow this procedure to configure the GMU 44 magnetometers Coordinate the GMU 44 configuration with Section 7 7 GRS 77 or GRS 7800 AHRS GMU 44 Magnetometer 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 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 PFD1 3 Rotate the small FMS knob to highlight King Air GMU 44 Press ENT key on PFD1 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 th
110. to possible areas of chaffing b Inspect edgelit overlay panels for damage or defect c Reinstall the circuit breaker edgelit overlays to the circuit breaker panels Reinstall the MFD and PFDs as described in Section 6 Placards Inspect that all required placards are installed Placards must be legible secure and in good condition Refer to the Main Instrument Panel Installation drawing listed in Table 1 2 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 4 13 Revision 4 Table 4 7 Cabin Area Visual Inspection Procedure ltem _ _ 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 center aisle floorboards in cabin FS 207 for 300 FS 221 for B300 a 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 Using a flashlight inspect the roll servo servo gearbox connectors support structure and control cables to ensure that no corrosion chaffing cracks or other defects exist For the roll servo gearbox c
111. to the General Arrangement Drawing and to Section 3 8 of this document Replace LRU Configuration file load fails 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 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 GIA1 and or GIA2 to LRU data path not Ensure that the criteria listed in Section 5 20 1 are workin fulfilled for the applicable situation 8 Ensure GIA1 and GIA2 are configured correctly 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 version were loaded to LRU Refer to the General Arrangement Drawing and to Section 5 20 1 a Check and ensure that correct Card Loader was ECHT GDC1 software used during load process Refer to the General mismatch Communication halted i ee Arrangement Drawing Reload software to LRU After being in configuration mode the PFD With the G1000 system powered on open the displays a red AFCS annunciation and cycling of MED P
112. to the unit 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 300 B300 Series King Air 190 00716 01 Page 5 41 Revision 4 5 6 4 2 Downloading GIA and GSA Maintenance Logs If additional assistance 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 GIAI 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 MFD in the configuration mode 3 On the PFD in the System page group use the small FMS knob to scroll to the Diagnostics Terminal page 4 Press the LG2CRD softkey at the bottom of the PFD 1 Verify that the softkey 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 5 Enable the cursor by pressing the FMS knob select GIA1 in the LRU drop down menu and then press the E
113. unit replace GIA1 v f problem persists continue to troubleshoot remote transfer switch amp wiring COM2 RMT XFR COM2 remote transfer key is stuck The COM2 external remote transfer switch is stuck in the enabled or pressed state Press the COM2 external remote transfer switch again to cycle its operation Check COM2 external 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 v If problem follows the unit replace GIA2 v If problem persists continue to troubleshoot remote transfer switch amp wiring COM1 TEMP COM1 over temp Reducing transmitter power COM2 TEMP CON2 over temp Reducing transmitter power The specified COM transceiver is reporting a high temperature condition and is reducing transmit power to prevent damage Check fan wiring and air tubing for proper operation if applicable Replace cooling fan if unable to determine if operating correctly Replace GIA If problem persists contact Garmin Aviation Product Support for assistance Page 5 58 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 5 11 2 NAV Alerts Failure Message NAV1 SERVICE NAV1 needs service Return unit for repair The system has detected a failure in NAV1 receiver Solution e Replace GI
114. unit replace GIA v f problem does not follow unit check NAV antenna coupler and 5 10 3 G S cabling for faults Symptom Recommended Action Weak G S receiver e Setup a NAV COM Ramp Test Set to radiate a test signal e Switch GIA1 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 55 190 00716 01 Revision 4 5 10 4 GPS Symptom 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 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 Check date and time on Date Time Setup Page v If date and time are incorrect enter the correct date and time Switch GIA1 and GIA2 to verify location of problem v If 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 Will Not Acquire Satellites At the top of the screen select the GIA that can not acquire satellites GIA1 or GIA2 and press the ENT key Press the CLR NV softke
115. verify on PFD1 and PFD2 the ESP 23 24 25 26 27 28 29 30 Roll Indices are not displayed at 45 on the roll indicator on the Attitude Display On the GCU rotate the inner FMS knob to activate the AUX SYSTEM SETUP page On the MFD AUX SYSTEM SETUP page press the SETUP 2 softkey Verify that on the MFD SETUP 2 page there is a window for Stability amp Protection and the status is ENABLED STABILITY amp PROTECTION STATUS Verify on PFD 1 and PFD 2 that there are no ESP FAIL or ESP OFF alert messages 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 Repeat step 1 thru 27 while coupled to right side Remove power to the aircraft and avionics systems by setting the aircraft AVIONICS MASTER PWR EXT PWR and BAT switches to OFF Wait 1 minute before re applying power for further testing as required Page 7 52 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 7 27 GTS Traffic System Functional Check This section is applicable to the GTS 820 825 TAS GTS 850 855 TCAS I and GTS 8000 TCAS II traffic systems Perfo
116. 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 PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 25 190 00716 01 Revision 4 3 12 GTS 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 45 Aircraft Registration Number Entry The default configuration for the GTS system is TAS See Section 3 43 for TCAS I enable and Section 3 44 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 PFD1 in configuration mode select the System Upload page on PED 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 PFD1 3 Rotate the small FMS knob to highlight King Air GTS Processor Press ENT key on PFD1 Verify the King Air GTS Processor is displayed in the Ite
117. 0 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 300 B300 Series King Air 190 00716 01 Page 5 79 Revision 4 Mating Backplate Connectors 5 21 The following figures depict the mating backplate connectors as viewed with the LRU removed COM ANTENNA CONNECTOR COOLING PORT 0 MAIN SERIAL CONNECTOR P603 COM BOARD CONNECTOR P601 MAIN DISCRETE CONNECTOR P604 GPS ANTENNA CONNECTO UO CONNECTOR 1 P605 UO CONNECTOR 2 P606 J G S ANTENNA CONNECTOR VOR ILS CONNECTOR P60 NAV ANTENNA CONNECTOR Figure 5 8 GIA 63W Backplate Connectors G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 80 Revision 4 190 00716 01 33 34 35 36 37 38 L Figure 5 9 GEA 71 Backplate Connectors 60 61 62 63 64 65 66 67 68 69 70 71 P13472 P13471 GMA 1347D Backplate Connectors 10 Figure 5 COOLING PORT P331 TOP ANTENNA CONNECTOR BOTTOM ANTENNA CONNECTOR Figure 5 11 GTX 33 33D Backplate Connectors Page 5 81 G1000 GFC 700 System Maintenance Manual 300 B300 Series
118. 00 47 47 2 2 138 8983 19000 47 47 2 2 162 8971 19000 47 47 2 2 185 8958 19000 47 47 2 2 209 8947 19000 47 47 2 2 233 8947 19000 47 47 2 2 242 8947 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 7 15 Revision 4 Air Data System Test Continued Test Point Altitude FT Airspeed KTS AIR DATA1 AIR DATA 2 AIR DATA 1 AIR DATA 2 Nominal AL Altitude Tolerance Tolerance Tolerance Tolerance AS Actual Actual Actual Actual 29000 72 72 2 2 111 28999 29000 72 72 2 2 130 28982 29000 72 72 2 2 150 28967 29000 72 72 2 2 169 28953 29000 72 72 2 2 188 28937 29000 72 72 2 2 196 28928 29000 72 72 2 2 212 28925 35000 87 87 2 2 97 35016 35000 87 87 2 2 14 34996 35000 87 87 2 2 30 34978 35000 87 87 2 2 47 34961 35000 87 87 2 2 64 34946 35000 87 87 2 2 71 34939 35000 87 87 2 2 135 34925 Aircraft S N Date Operator ADTS ADC1 ADC2 Make Model GDC 7400 Model GDC 7400 Model P N 011 02337 P N 011 02337 S N S N S N Cal Date Cal Date Cal Date Leak Check S
119. 011 01997 00 or GTX 3000 Transponder 2 GWX 68 Weather Radar 2A 011 00883 20 or 1 GWX 70 Weather Radar 2 5 A 011 01768 00 Right Generator Bus Avionics Right Generator Fed Avionics Bus GDL 69A Data Link 1 0 35 A 011 00987 00 GDL 59 Wi Fi 1 0 572 A 011 01746 00 GTS Processor 25A 011 02571 00 or 1 GTS 820 Traffic Processor 1 6 A 011 01446 00 or GTS 850 Traffic Processor 1 6 A 011 01553 00 GRA 5500 Radio Altimeter 1 0 5A 011 02537 00 GSR 56 Iridium Iridium Heater 1 1 86A 011 02268 00 or 011 02268 01 Center Bus GDU 1040A PFD 1 1 2 5 A Max 011 00916 10 Secondary power input See Notes 1 3A above 15 C 2 5A below 15 C Page 2 18 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Units Ea Unit Equipment Used Amps DC Part Number Notes 0 3 A GRS 77 Secondary power input See Note 011 00868 10 GMU 44 GRS 77 GMU 44 AHRS 1 or a REH SEH 0 45 A GRS 7800 Secondary power input See Note 011 02278 00 GMU 44 011 00870 10 011 00870 20 GDC 7400 ADC 1 1 0 230 A 011 02337 00 Secondary power input See Note 011 02337 01 GIA 63W NAV 1 1 10A 011 01105 20 Secondary power input See Note No 1 Triple Fed Bus PFD 1 Cooling Fan 1 01A 305468 00 Sandia P N or 013 00102 00 Garmin P N GIA 63W 1 Cooling Fan 1 0 4 A 305467 00 Sandia P N or 013 00103 00 Garmin P N GIA 63W
120. 0rpm ISLIP CLUTCH TEST RESULTS CENT ON Oli NOSE UP NOSE DOWN CLUTCH ENGAGE STATUS _ HIN inib e HAX ISVO a ENG CLOH DRV SRVO RST GAIN 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 receiving 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 PFT 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 softkeys to
121. 1 13 Repeat steps 1 through 12 for GRS 2 with PFD 2 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 compass 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 loca
122. 1 amp 2 e GEA7I 1 amp 2 e GDU 1040A 1 amp 2 e GSA 80 e GSA 9000 e GRS77 or GRS 7800 1 amp 2 e Traffic System if installed The GIA 63W 1 interfaces to the following additional equipment e GDC 7400 1 e GTX 33 or GTX 3000 1 e DME 42 if installed e GSR 56 if installed per stand alone configuration The GIA 63W 2 interfaces to the following additional equipment e GDC 7400 2 e GTX 33 or GTX 3000 2 e ADF if installed e Stormscope if installed e Radar Altimeter if installed Figure 2 6 GIA unit G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 2 5 190 00716 01 Revision 4 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 is provided from No 1 Triple Fed Bus and to GEA 2 from No 2 Triple Fed Bus Both GEA units will power up immediately with external or aircraft power or battery operation Each GEA interfaces to the following sensors for its onside engine e Oil P
123. 1 and GMA2 Verify COMI active frequency is displayed white 8 Initiate passenger address using pilot s headset boom mic by keying the pilot s PTT Verify the following e 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 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 e 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 300 B300 Series King Air Page 7 3 190 00716 01 Revision 4 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 NAV1 NAV2 COM1 COM2 ADF and DME and check for audio over the pilot s headset 2 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
124. 1 has low voltage Reducing power usage The MFD supply voltage is low Check input voltage to MFD If input voltage is ok replace MED Page 5 52 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 5 9 6 GMA Common Problems Recommended Action Symptom Failure Message Noise in Audio Buttons Do Not Work COM Bleedover Speaker Cuts Out Mic Audio Heard in Speaker GMA XTALK GMA crosstalk error has occurred 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 v If the 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 v If the 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 Ensure the marker beacon audio is not active Ensure the ICS squelch is not open v Master squelch level can be adjusted
125. 1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 Table 4 8 Rear Fuselage and Empennage Visual Inspection Procedure Description Procedure Initials Wi fi Antenna Inspect the external wi fi antenna if installed for leading edge erosion and condition of wi fi option only base seals Remove access panel to gain access to the tail area for the following inspections Refer to the servo installation and equipment tail shelf drawings and the Super King Air 300 or B300 Maintenance Manual listed in Table 1 2 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 Tail Wiring Harness Paragraph 11 96 and the Tail Wire Harness Routing drawing listed in Table 1 2 Pay particular attention to possible areas of chaffing Verify security of aft bulkhead connectors Inspect the GTX 33 or GTX 3000 units 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 shields and their attachment Inspect the GDL 59 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 shields and their attachment Inspect the GSR 56 uni
126. 1347D 1 Indicator Status GIA1 GRS 77 or GRS 7800 1 data path is functioning correctly GIA1 GRS 77 or GRS 7800 1 data path is not functioning correctly e Load GIA1 configuration files e Swap GIA1 and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA1 o Replace original GIA1 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 Check the GIA1 GRS 77 or GRS 7800 1 interconnect wiring for faults GIA1 GRS 77 or GRS 7800 1 data path functionality is unknown Reload GIA1 configuration files GIA1 GMA 1347D 1 data path is functioning correctly GIA1 GMA 1347D 1 data path is not functioning correctly e Load GIA1 and GMA 1347D 1 configuration files e Swap GMA 1347D 1 and GMA 1347D 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 GIA1 o Replace original GIA1 if box turns green after swapping units Check the GIA1 GMA 1347D 1 interconnect wiring for faults GIA1 GMA 1347D 1 data path functionality is unknown Reload GIA1 configuration files
127. 190 00716 01 6 35 GSR 56 Satellite Receiver Removal 1 Gain access to the avionics shelf in the tail area 2 Unlock the unit from the rack by loosening the ratcheting latch mechanism 3 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 Insert the unit into the installation rack CAUTION Do not use excessive force when inserting the GSR 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 GSR 56 and identify the source of resistance 3 Lock the unit into the rack by using the ratcheting latch mechanism If new unit is installed register with Garmin Connext per Section 7 28 Configure the GSR 56 per Section 3 17 if installed in the stand alone configuration Test the GSR 56 according to Section 7 30 6 36 GSD 41 Data Concentrator Removal 1 Gain access to the avionics shelf in the tail area 2 Unlock the unit from the rack by loosening the ratcheting latch mechanism 3 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 Insert the unit into the installation rack CAUTION Do not use excessive force when inserting the GSD 41 into the rack This may cause damage to occur to the connectors unit and or unit rack If heavy resistance
128. 2 15 are only applicable to Model 300 aircraft Place the L BLEED AIR CONTROL SWITCH in the PNEU amp ENVIR OFF position Verify RUD BOOST OFF annunciator illuminates Place the L BLEED AIR CONTROL SWITCH in the OPEN position Verify RUD BOOST OFF annunciator extinguishes Place the R BLEED AIR CONTROL SWITCH in the PNEU amp ENVIR OFF position Verify RUD BOOST OFF annunciator illuminates Place the R BLEED AIR CONTROL SWITCH in the OPEN position Verify RUD BOOST OFF annunciator extinguishes 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 4 35 190 00716 01 Revision 4 IRIDIUM ANTENNA PTIONAL TRANSPONDER ANTENNA UPPER PTIONAL A PS ANTENNA PTIONAL LOCATION H
129. 2 GRA 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 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 7 23 Non Garmin Radar Altimeter Check This check verifies that the G1000 radar altimeter interface is operates correctly 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 Navigate to the AUX SYSTEM STATUS page on the MFD 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 PFD1 and PFD 2 5 Pull the RADIO ALTM circuit breaker Verify on PFD 1 and PFD 2 th
130. 2X Pull Up 2X e Two Hundred e Terrain 2X e One Hundred e Caution Obstacle 2X e Glide Slope e Obstacle 2X Pull Up 2X e Glide Path Pull the PFD1 PRI and PFD1 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 Place the airplane on jacks Ref Super King Air 300 or B300 Maintenance Manual Chapter 7 00 00 with the wheels clear of the ground Ensure all equipment and personnel are clear of the flaps and landing gear Place the flaps and landing gear in the full down positions 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 PFD1 After an alert advisory appears press the softkey directly below the flashing ADVISORY 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 Press the ALERTS softkey to close the alerts window Place the flaps and landing gear in the full up positions Press the ALERTS softkey again to open the alerts window 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 Re
131. 3 GDL 59 Configuration 5 GSR 56 Configuration 2 GDL 59 Status 4 GDL 59 Report Configuration SW version 0985 06 and prior RMT Page Remote Controller Status GWX Page Group 1 GWX Configuration GTS Page GTS Configuration OTHER Page Stormscope CAL Page Group 1 Fuel Tank Calibration 3 HSCM Calibration 2 Flaps amp Trim Calibration 4 DAT Configuration Appears only if option is installed G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 11 190 00716 01 Revision 4 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 G1000 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
132. 3 1B Chapter 11 Section 8 Paragraph 11 96 and the Nose Wire Harness Routing drawing listed in Table 1 2 Description Procedure Nose Equipment Compartment access panel for the following Inspection Inspect the GRS 77 or GRS 7800 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 Initials GIA 63W Qty 2 Inspect the 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 Inspect the standby battery fuses and associated bracket for corrosion or other defects GIA Cooling Fan Qty 2 Inspect remote cooling 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 ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment LMD Rack and Modules Inspe
133. 4 GTX 3000 CONFIGURATION ccccccccesssscccsessccecsessececsesceecsesseeecsesseeecseseeecsesseeecseseeeesenseeeees 3 28 3 15 GDL 59 WI FI DATA LINK OPTION CONFEIOURATION 3 29 3 16 GSR 56 SATELLITE RECEIVER WITH GDL 59 WI FI DATA LINK OPTION CONFIGURATION 3 30 3 17 GSR 56 SATELLITE RECIEVER STAND ALONE OPTION CONPIOURATION 3 31 3 18 GRS 77 AHRS SOFTWARE CONFIGURATION ssssssssssseessereesseetssrretsseretssreetssrrerssrrerssrreessees 3 32 3 19 GRS 7800 AHRS SOPTwWARPICONFIOGURATION 3 33 3 20 GWX 68 SOETWAREICONEIOURATION 3 34 3 21 GWX 70 SBOETWARRICONEIOURATION 3 35 3 22 GMU 44 SOFTWARE CONFIGURATION ssssssssssesssesetsseretssreesstretssrtetssrretssrtetssrretssrretssrreessee 3 36 3 23 TAWS A SUPPORT CONFIGURATION rieira EEE T ACT EEREN EEN 3 37 3 24 TAWS A VOICE NO CALLOUT OPTION CONFIOGURATION 3 38 3 25 TAWS A VOICE CALLOUT OPTION CONFIOURATION 3 39 3 26 ADF OPTION CONFIGURATION moin E EEA A EAR 3 40 3 27 DME OPTION CONFIGURATION oA a TE AE AT ETE E A S A 3 41 3 28 RAD ALT OPTION CONFIGURATION arianen aOR Eas A a E OA RARA 3 42 3 29 NON GARMIN TCAS II TRAFFIC SYSTEM OPTION CONFIOURATION 3 45 3 30 LIGHTNING SYSTEM OPTION CONFIOGURATION 3 46 3 31 LIGHTNING SYSTEM OPTION CONFIGURATION LOAD CONFIRMATION 3 47 3 32 ESP SUPPORT OPTION CONFIGURATION serris riietes rrira s Een EE eK ELA RETEA EEEE AEK KLEES EEE eaS iNi 3 49 3 33 POTS HANDSET CONFIGURATION rcir a E E ANORA 3 50 G1000 GFC 700 System Maintenance Manual 300 B300 S
134. 4 OHMS AS LOAD 23 TYPICAL OUTPUT USING gt 7 OHM 1 LOAD PIN 22 11 TO 12 GND REFERENCE MINIMUM A ACCEPTABLE DISCHARGE CURVE 21 20 0 10 20 30 40 50 60 70 80 90 Time minutes 2 Position all INDIVIDUAL CELL DIP SWITCHES Figure 4 5 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 300 B300 Series King Air Page 4 33 190 00716 01 Revision 4 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 a All INDIVIDUAL CELL MONITOR LED s Figure 4 5 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 5 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 above If the plot reveals a discharge curve that meets or excee
135. 49 50 51 52 53 54 55 56 57 58 59 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 LR 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Figure 5 21 GWX 70 Backshell Connector P751 KA RRE 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 LR 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 LR e 00900090000099 21 22 23 24 25 26 27 28 29 30 1 32 33 34 35 36 37 38 39 1 2 3 A 5 6 7 8 9 10 II 12 1 17 18 19 20 o P8003 Figure 5 22 GTS 820 850 Mating Connectors Rear View KA RK 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 G R RR 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 LA RR 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 KA RK 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Figure 5 24 GPA 65 Mating Connector P651 Rear View Page 5 84 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 Figure 5 25 Signal Conditioner Mating Connector PVIB1 Rear View LR 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 ee0e0002020000080808008080 o 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 LR LR 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 CR 13 14 15 16 17 18 19 12 20 11 10 9 8 7 6 5
136. 5 28 5 6 GEC 700 AFCS TROURLESHOOTING srira aae A AE T 5 29 ST BACKUP COMMUNICATIONS PATH CHECKS a a NE EEA E A ETELE EEE E AEAN 5 44 5 8 GDU 104X TROUBLESHOOTING nie in rA E E EAT STE T A 5 45 KEE IR IEN EC KE 5 47 5 10 GIAL6 35 TROUBLESHOOTING Yor scescetesadetedvacthadeotsideeretatuneuripdedtavtncastevivnde deer 5 55 5 11 GTA ALERT MESSAGES dee ae AEA ae 5 57 5 12 GEA TROUBLESHOOTING 5 AR rR AEA eebe 5 64 5 13 OGTXTROUpLESHOOTINO Vre errn A EA Er ENEI E AEAEE E ERA 5 65 5 14 GDI 69A TROUBLESHOOTING sssecceaivcicesdesap SERIES E aa SEENEN SE 5 66 Page ii G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 15 GRS 77 OR GRS 7800 AND GMU 44 TpOoUpLESHOOTINO 5 68 5 16 GDC 7400 TROUBLESHOOTING EE 5 74 5 17 GWX 68 GWX I0TROUPBLESHOOTINO ECE En in EE EET EENE FENETRE 5 75 5 18 GMC 71O FROUBEESHOOTING ae TEE A N A 5 76 5 19 GCW4T7 TROUBLESHOOTING cair AEE E AEA 5 77 5 20 SOFTWARE CONFIGURATION TROUBLESHOOTINO 5 78 5 21 MATING BACKPLATE CONNBCTORS n o e A E AA AA ARA aaa 5 80 5 22 STANDBY ATTITUDE INDICATOR TROUBLESHOOTINO 5 87 5 23 STANDBY AIRSPEED INDICATOR TROUBLESHOOTINGO 5 87 5 24 STANDBY ALTIMETER TROUBLESHOOTING cccccccecssssssececececsessnsssececesecseseseseseeeeecsesentaaees 5 88 5 25 GDIb59 TROUBLESHOOTING ege eege dees 5 88 5 26 GSR56 TROUBLESHOOTING fo sss cesdisesces pines RA RAA RR 5 89 5 27 GTS 820 850 TROUBLESHOOTING ccccccecssscecssssececeessececse
137. 56 and the display control device Verify subscription with Garmin Connext reference Section 7 28 5 27 GTS 820 850 Troubleshooting Probem___ Cause Solution S Unit does not power up Data Improper wiring circuit breaker open Ensure power is properly wired to the failed message 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 Suppression bus UO fault Check the mutual suppression line to indicates TA at own ship position 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 Verify the configuration checks failed 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 Execution Fault Internal Fault Return to Garmin for service Electrical Fault Internal Fault Return to Garmin for service Whisper Shout Fault Interna
138. 59 OAT Probes provide the GDC 7400 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 300 B300 Series King Air Page 2 7 190 00716 01 Revision 4 2 1 11 Attitude amp Heading Reference System 2 The Garmin GRS 77 or GRS 7800 AHRS units provide attitude and heading information to the G1000 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 2 GRS AHRS units can provide heading data to an approved third party TCAS II device through an ARINC 429 digital interface Additionally the GRS 7800 AHRS provides heading with or without the aiding of the 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 No Triple Fed Bus and a secondary power supply from the Center Bus GRS 2 receives electrical power from No 3 Triple Fed Bus GRS 77 G
139. 8 Remove airplane from jacks If no other service is to be performed continue to the return to service checks in Section 8 TAS KT TAS KT Figure 7 8 Low Speed Awareness Band Symbolization G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 43 190 00716 01 Revision 4 7 25 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 additional 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 7 25 1 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 By visual inspection of the units verify hardware part number matches the information in the General Arrangement drawing listed in Table 1 2 Record the results in Figure 7 9 HARDWARE SOFTWARE SYSTEM STATUS DESCRIPTION PART NUMBER DESCRIPTION
140. 8 006 B0544 37 E ARAARA 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 PFD1 ENT key to acknowledge the Upload Complete box Page 3 22 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 1 Start the G1000 system in Configuration Mode as described in Section 3 7 2 Press the small FMS knob to activate the cursor on the System Status page of the PFD or MFD 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 listed in Table 1 2 IMPORTANT It is essential that the software versions be checked and matched against the listed versions in the General 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 ma
141. 80 capacity within hour and full charge at 16 hours Ji pin 11 PS 835 Power Supply Power Supply Figure 4 6 Power Supply Connection Page 4 34 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 4 17 On ER a En 12 13 14 15 4 18 Rudder Boost Operational Check Place the RUDDER BOOST switch to the OFF position For Model 300 aircraft set the left and right bleed air control switches to the OPEN position Verify the amber RUD BOOST OFF annunciator on the aircraft s caution and advisory panel is illuminated Place the RUDDER BOOST switch to the RUDDER BOOST position Verify the amber RUD BOOST OFF annunciator on the aircraft caution and advisory panel is extinguished Pull GIA1 primary and secondary circuit breakers Verify RUD BOOST OFF annunciator is extinguished Pull GIA2 circuit breaker Verify RUD BOOST OFF annunciator illuminates Reset GIA1 and GIA2 circuit breakers Verify RUD BOOST OFF annunciator extinguishes Pull the AFCS SERVO circuit breaker Verify RUD BOOST OFF annunciator illuminates Reset AFCS SERVO circuit breaker Verify RUD BOOST OFF annunciator extinguishes Press and hold the AP DISC switch on the pilot s control wheel and verify RUD BOOST OFF annunciator illuminates Release the AP DISC switch and verify the RUD BOOST OFF annunciator extinguishes 11 Repeat steps 9 10 for the copilot s control wheel NOTE Steps 1
142. 90 00716 01 3 25 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 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 Callout Option configuration with Section 7 16 TAWS 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 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 highlight 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 e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System
143. A1 NAV2 SERVICE NAV2 needs service Return unit for repair The system has detected a failure in NAV2 receiver e Replace GIA2 NAV1 RMT XFR NAV1 remote transfer key is stuck The NAV1 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 NAV1 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 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 v If problem follows unit replace GIA1 v If problem persists continue to troubleshoot remote transfer switch amp wiring G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 59 Revision 4 5 11 3 Glideslope Alerts Failure Message G S1 SERVICE G S1 needs service Return
144. ANDBY BATTERY legend on the standby battery switch is illuminated full bright Verify the following ON annunciation should extinguish on the STANDBY BATTERY switch 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 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 Verify the following 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 Page 8 6 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 8 1 6 G1000 Backup Path Test 1 With the G1000 in configuration mode go to the GDU Page Group on PED On PFD1 activate the cursor and select PFD1 in the SELECT UNIT field and press ENT Obs
145. AV key until 1 is lit Verify the tuning box is present around the NAV 1 frequency on PFD 1 25 Using GCU477 keypad enter in a frequency of 108 00 Verify NAVI frequency changes as entered G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 27 190 00716 01 Revision 4 26 Press the NAV key until 2 is lit Verify the tuning box is present around the NAV 2 frequency on PFD1 27 Using GCU477 keypad enter in a frequency of 108 00 Verify NAVI frequency changes as entered 28 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 29 Using GCU477 keypad enter in a code of 1234 Verify XPDR1 shows a code of 1234 in the window 30 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 31 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 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 7 11 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
146. Aircraft Make Engine Prop Card Version Installed Enabled Installed Enabled Unit Option check if installed or Unit Option check if installed or configured configured ADF Option GSR 56 with GDL 59 DME Option GDL59 ESP Support no AoA GMU 44 FDR Option GRS77 RAD ALT Option Non Garmin EE TCAS II System Option GSR 56 Stand Alone Non Garmin Traffic System Option GTS 820 850 Non Garmin BLR Winglet STC Ge EES 825 855 8000 Lightning System GTX 3000 Option TAWS A Support GTX 33ES TAWS A Voice No Callout Installation GWX 68 Option TAWS A Voice Callout GWX 70 Installation Option G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 8 15 190 00716 01 Revision 4 This page intentionally left blank Page 8 16 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01
147. CWS button for a minimum of 5 seconds and release verifying there is no residual force on the control stick for the pitch axis 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 PFD2 display VS in green and indicates a pitch reference of 0 FPM Press the FLC key on the AFCS mode controller and verify that FLC is annunciated on PFD1 and PFD2 in green with a reference of 100 KTS G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 8 11 190 00716 01 Revision 4 14 Press the ALT key on the AFCS mode controller and verify that the ALT annunciation is displayed in green on PFD1 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 Engage the Autopilot by pressing the AP key on the AFCS mode controller 2 Manually overpower the autopilot clutches in pitch and roll Ifthe Autopilot clutches cannot be overpowered check the GS
148. DU 1500 MFD The GCU 477 provides alphanumeric softkey and flight planning function keys used to interface with the G1000 the MFD does not possess any knobs or controls other than softkeys The GCU 477 is powered by No 3 Triple Fed 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 on the upper avionics equipment shelf in the tail section of the airplane Power is provided by the No 1 GTX from Triple Fed Avionics Bus The No 2 GTX is powered from Left Gen Avionics Bus All GTX transponders non diversity and diversity interface with a transponder antenna mounted to the bottom of the fuselage Each diversity tran
149. E 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 14 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 12 DIAL INDICATOR GAGING ASSEMBLY STATIC PORT FUSELAGE SKIN aa H L EE IT Figure 7 12 Static Port Measurement 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 13 Record the measurements in the measurement log Figure 7 14 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 14 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 G1000 GFC 700 System M
150. FD 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 78 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 MED PFD 1 PFD 2 and MANIFEST configuration files to MED and PFDs SW Loader Card must be inserted in 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 Load Software Configuration files to GMA 1347D 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 in 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 SW Loader Card must be inserted into PFD 1 top slot G100
151. Failure Message MAG VAR WARN Large magnetic variance Verify all course angles PIT MISCOMP ROL MISCOMP 5 15 3 GMU Alerts Failure Message MANIFEST GMU1 software mismatch Communication halted MANIFEST GMU2 software mismatch Communication halted Magnetic variance value from GMU 44 is not accurate Difference in the pitch sensors is greater than 5 degrees Difference in the roll sensors is greater than 6 degrees The system has detected an incorrect software version loaded in the specified GMU 44 Solutions 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 Perform Calibration Procedure A1 GRS 77 or GRS 7800 Pitch Roll Offset Calibration reference Section 7 Perform Calibration Procedure A1 GRS 77 or GRS 7800 Pitch Roll Offset Calibration reference Section 7 Solutions Load the correct software version See Section 3 9 for the Software Load Procedure HDG FAULT AHRS1 magnetometer fault has occurred HDG FAULT AHRS2 magnetometer fault has occurred A fault has occurred in the specified magnetometer heading will be flagged invalid e Check GMU 44 GRS 77 or GRS 7800 interconnect for faults v Replace GMU 44 v If p
152. Figure 2 20 GSA 9000 GSM 9100 EE Figure 2 21 GRA 5500 Radar Altimeter cececeecceseeceeeecescesecaeeeeeesecaeeeneeeecneeeaeeeees Figure 2 22 300 B300 Electrical Distribution Post G1000 STO esssssessssseesessee Figure 2 23 G1000 Component Power Sources Figure 2 24 Pitot Static System Post G1000 STC ccccccsecsceteceteceteceseesteeseeeeseeeaes Figure 2 25 G1000 GFC 700 Block Dageram Figure 3 1 GDU 1040A Control Interface seeseseeeeeesesseseseessstseesessestsrrsesseseesesessesee Figure 3 2 GDU 1500 Control Interface Figure 3 3 G1000 Softkeys ccccccsccesccssscseeceeseeeseeeseeeseeeseecseecsaecsecesecesecseeseeeseeeseneeags Figure 3 4 MFD Controls GCU 477 showmn Figure 3 5 AFCS Controls GMC 710 sbown Figure 3 6 GMA 1347D Controls Fig re 3 7 Normal Mode 2eeeebb isdedeiebfh ZeeChe ENEE Figure 3 8 Automatic Reversion with MED failure eeeeceeseeeececeeeeeeceaeeneeeneeaes Figure 3 9 Manual Reversion with pilot PFD fue Figure 3 10 SET gt ACTV Dagram inaen ea aaao aa SEa a ire Figure 3 11 Loss of Communication sesessseseesseseseseesessssesstssstsessesssesesessesessesessesee Figure 3 12 Configuration Stats Figure 3 13 Data Transmission Indiceators Figure 3 14 G1000 LRU Configuration File Storage cccccccscesseesteeeteeeeeeeseeseeeees Figure 3 15 GRS GDC Configuration Settings Storage cccesccesceseceeeeeeeeeeseeseeeees Figure 3 16 Software Configuration Overview
153. G REF DISABLED 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 the PFD1 STORMSCOPE DATA Figure 3 21 Stormscope Configuration G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 47 190 00716 01 Revision 4 3 Verify that the DATA window shows the following Hdg None J3 1 Jumper J3 2 Jumper Hdg Valid No Fla Flag Flag Sense invld J3 4 Open lt aircraft Hdg Value headings Inhibit off Line Antenna Mount Bottom J3 3 Open 4 Deactivate the cursor NOTE The DATA window is only updated once every five seconds Page 3 48 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 32 ESP Support Option Configuration This section applies only to installations with the ESP option 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 41 Coordinate this configuration with Section 7 26 ESP 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 on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop do
154. GCU Verify the FLAP OVR annunciation on the PFDs has extinguished 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 LOT annunciations show on the PFDs 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 Pull the RADIO ALTM circuit breaker Verify GPWS FAIL is displayed on PFD1 and PFD2 Reset the RADIO ALTM circuit breaker Verify GPWS FAIL annunciations are removed Pull PFD1 PRI and PFD1 SEC circuit breakers Re power PFD1 in configuration mode and use the PFD1 FMS knob to select the Audio Alert Configuration page Page 7 36 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 16 17 18 19 20 21 22 23 24 25 26 2h 28 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 e Too Low Terrain e Terrain Ahead 2X e Too Low Flaps e Terrain Ahead Pull Up 2X e Too Low Gear e Obstacle Ahead 2X e Sink Rate e Obstacle Ahead Pull Up 2X e Pull Up e Five Hundred e Don t Sink e Four Hundred e Caution Terrain 2X e Three Hundred e Terrain
155. 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 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 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 Select the BACK softkey 8 Select the VERTICAL softkey Select the TILT softkey to activate the cursor in the TILT field 10 On the GCU turn the small FMS knob to select the desired antenna tilt angle Press the GCU 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 the GCU 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 the GCU select the GAIN softkey again to recalibrate the gain Verify CALIBRATED is displayed in the GAIN field
156. HRS GMU 44 MAOGN TOMETER 7 18 Teo GDL69A XM DATA LINK aa a EEN ARATE E is deeb R 7 26 LEQ AGSAs8O 9000 SERVOS EE 7 26 7 10 GCUAT7 FMS CONTRO LER bei AEN EA TT N TERON 7 27 7 11 GMC TIO ARCS CONEROLLER e ARNE E N OAR E AAR 7 29 7 12 GWX 68 OR GWX 70 WEATHER RADAREN 7 30 7 13 NON GARMIN TRAFFIC SYSTEM TAS TCAS I FUNCTIONAL CHECK 7 31 7 14 NON GARMIN TRAFFIC SYSTEM TCAS IT FUNCTIONAL CHECK 00 e ceccceessessseeteeetseesseesees 7 32 7 15 LIGHTNING SYSTEM FUNCTIONAL CHECK 7 33 7 16 ALA W S RUNCTIONAL HECE EE 7 35 7 17 FLITECHARTS FUNCTIONAL CHECK 7 38 7 18 CHART VIEW FUNCTIONAL CHECK 1 ccccccccssssceessssscecsesccecsesseeecsesseeecsesseeecseseeecsenteceeseneeeeees 7 39 7 19 SAFETAXI FUNCTIONAL CHECK ccccccccssssscecsssececssssececsssesecssssececssssesecsssseseessssssecssssseeseuss 7 40 7 20 DME FUNCTIONAL CHECKE Ee r SEA EAR EE 7 41 7 21 ADF FUNCTIONAL CHECK ees eege cob svat eebe ng eebe 7 42 T22 GRA 5500 RADAR ALTIMETER FUNCTIONAL CHECK 7 42 7 23 NON GARMIN RADAR ALTIMETER CHECK 7 42 7 24 WEIGHT ON WHEELS AND LOW SPEED AWARENESS BAND CHECK 7 43 71 25 IRVSM e EE 7 44 7 26 ESP FUNCTIONAL CHECK eer eet ees eege ee 7 50 7 27 GTS TRAFFIC SYSTEM FUNCTIONAL CHECK 7 53 7 28 ACTIVATION OF GARMIN CONNENT urtee nET E EE EEN 7 56 7 29 GDL 59 WI FI DATA LINK FUNCTIONAL CHECK u ccccccccssssscecsessececesssceecsesceecssnseeecseneeeees 7 58 7 30 GSR 56 SATELLITE RECEIVER FUNCTIONAL CHECK 7 59 7 31 SEARCH AND RESC
157. IA1 SEC circuit breakers 2 Verify the following e NAV 1 and COMM tuning fields on PFD 1 and PFD 2 are invalid red X e L R engine data remains valid e XPDR1 is Inoperative e GMAIL is Inoperative AE Page 4 24 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 AHRS 1 is using backup GPS source AHRS2 not receiving backup GPS Information An amber BOTH ON GPS2 is displayed on PFD 1 and PFD 2 AHRS and ADC data remain valid on PFD 1 and PFD 2 3 Close the GIA1 PRI and GIA1 SEC circuit breakers Allow system to re acquire satellites and return to normal display modes Open GIA2 CB 5 Verify the following NAV2 and COMM tuning fields on PFD 1 and PFD 2 are invalid red X L R engine data remains valid XPDR2 is Inoperative GMA2 Is Inoperative AHRS2 is using backup GPS source AHRS not receiving backup GPS Information An amber BOTH ON GPS is displayed on PFD 1 and PFD 2 AHRS and ADC data remain valid on PFD 1 and PFD 2 6 Close GIA2 CB Allow system to re acquire satellites and return to normal display modes 7 Open GIA1 primary and secondary CBs and GIA2 CB 8 Verify the following COMI1 NAV1 amp COM2 NAV2 2 fields flag invalid GPS CDI flags LOI 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
158. 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 each G1000 LRU Pay special attention to the configuration of options for the G1000 Page 3 16 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 8 5 Configuration File Storage The G1000 system is designed to store all configuration 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 and GDC 7400 configuration calibration reference Figure 3 15 is different than the LRU s shown in Figure 3 14 G1000 Master Configuration Module located in PFD backshell connector GMC 710 z SE Contains Master configuration module contains identical ACTIVE backup configuration files of PFD configuration settings Uses memory PFD cross checks th
159. ISC 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 Engage the autopilot again by pressing the AP key on the AFCS mode controller Ensure the autopilot is coupled to GIA1 by verifying the arrowhead next to the XFR key on the AFCS mode controller is pointing to the pilot s side If the arrowhead points to the copilot s side press the XFR key Open GIA1 primary and secondary circuit breakers Verify 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 GIA1 primary and secondary circuit breakers and wait for completion of the pre flight test sequence Press the XFR key on the AFCS mode controller and engage the autopilot by pressing the AP 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 AP alert is displayed on PFD1 and PFD2 Press the GO AROUND button on the left throttle Verify TO is annunciated on PFD1 and PFD2 for both PITCH and ROLL modes and the command bars should be at 10 degrees nose up and wings level 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
160. King Air Enable TAWS 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 e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete De activate the cursor 8 Power down the system and remove the TAWS B Enable Card from PFD1 Page 3 54 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 38 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 00629 02 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 10 Ensure that the RAD ALT Option Configuration has been loaded per Section 3 28 Coordinate this configuration with Section 7 16 TAWS Functional Check 1 With the TAWS A Enable card in the top slot of PFD1 and PFD1 in configuration mode sele
161. L ITEMS SHOWN FOR CLARITY Figure 6 6 GIA Cooling Fan Installation Configuration applicable to MDL 005 00629 00 Rev 6 or previous FAA approved revision G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 6 19 190 00716 01 Revision 4 COOLING FAN COOLING FAN HOSE TYP FAN INLET DUCT IF INSTALLED P N 115 00580 02 NOSE WHEEL WELL HOUSING VIEW OF LEFT SIDE NOSE AVIONICS BAY NOT ALL ITEMS SHOWN FOR CLARITY Figure 6 7 GIA Cooling Fan Inlet Duct Identification Configuration applicable to MDL 005 00629 00 Rev 7 or later FAA approved revision 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 6 30 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 Reinstallation 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 If further maintenance is not required proceed to Sectio
162. M 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 86 clutch cartridge Refer to the pitch trim servo installation drawing listed 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 Ifthe 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 Super King Air 300 or B300 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 Super King Air 300 or B300 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 i
163. Maintenance Manual 300 B300 Series King Air Page 3 39 190 00716 01 Revision 4 3 26 ADF Option Configuration This section loads the necessary configuration files for those aircraft equipped with an ADF Coordinate the ADF configuration with Section 7 21 ADF 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 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 ADF Option Press ENT key on PFD1 Verify the King Air ADF 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 PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 40 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 27 DME Option Configuration This section loads the necessary configuration files for those aircraft equipped with a DME Coordinate the DME configuration with Section 7 20 DME Functional Check 1 With the lo
164. NC 429 pitch or roll angle has not been received Exceeded Attitude Limits The pitch or roll angle has exceeded the engagement limits Cross Hdg Accel Fail Cross heading acceleration monitor failed Vert Accel Fail Vertical acceleration monitor failed Fitrd Cross Hdg Accel Fail Filtered cross heading acceleration monitor failed Fltrd Vert Accel Fail Filtered vertical acceleration monitor failed smo moan E 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 A MET switch in the specified axis is stuck Check the MET trim switches for proper operation e 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 lt PARAMETER has become invalid The following is a list of some of the possible values for lt PARAMETER 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 34 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 6 4 GIA Pre Flig
165. NT key to select it 6 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 7 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 8 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 9 Ifyou 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
166. OIAY INOIAY fl INOIAT 1 in 1_SOINOIAV 1 1 1 1 SOINGIAY 1 SOINOIAY 134 Jal 1334 JIL 333 Se 333 IAL 1B4 NBO ot JOLVYENSS LHOR 133 NBO 7 Figure 2 23 G1000 Component Power Sources Page 2 17 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 2 4 Electrical Load Utilization The following chart lists the electrical equipment and their associated loads for each of the standard and optional items installed on the King Air 300 series airplanes with the installation of G1000 The loads specified are used to verify the electrical buses generating system and batterys are operated within their limits and capacity For electrical load test procedure and electrical load test report refer to Garmin documents 190 00716 00 Post Installation Checkout Procedure King Air 300 B300 Series and 005 00629 22 Electrical Load Test Report G1000 integrated Avionics System Hawker Beechcraft Model 300 B300 King Air respectively Table 2 1 Electrical Loads Units Ea Unit Equipment Used Amps DC Part Number Notes Battery Bus Left Generator Bus Avionics Left Generator Bus GIA 63W COM 2 1 4 3 A Max 011 01105 20 0 3 A Not Transmitting See Note 4 3 A Transmitting GMA 1347D 2 Audio Panel 1 1 75 A 011 01257 20 GTX 33 Transponder 2 1 6 A 011 00779 30 or 1 1 6 A 011 00779 21 GTX 33D Transponder 2 1 6A
167. On Condition G1000 Cooling Fan Fail Annunciation Check For aircraft equipped per MDL 005 00629 00 Rev 6 or previous revision and not modified per GarminService Bulletin 1375 Verify the operation of the fan power and fan speed monitoring circuits for GIA1 fan and GIA2 fan NOTE See Section 6 29 Figure 6 6 for identification of cooling fan installation applicable for this maintenance interval 220 hours max G1000 Cooling Fan Fail Annunciation Check G1000 Cooling Fan Fail Annunciation Check For aircraft equipped per MDL 005 00629 00 Rev 7 or latest FAA approved revision or modified per Garmin Service Bulletin 1375 Verify the operation of the fan power and fan speed monitoring circuits for GIA1 fan and GIA2 fan NOTE See Section 6 29 Figure 6 7 for identification of cooling fan installation applicable for this maintenance interval Verify the operation of the fan power and fan speed monitoring circuits for PFD1 fan MFD fan and PFD2 fan and fan fail messages 820 hours max 820 hours max Nose Avionics Compartment Fans Operational Check For aircraft equipped per MDL 005 00629 00 Rev 6 or previous revision and not modified per Garmin Service Bulletin 1375 Functional test of the GIA1 and GIA2 ported fans Verify airflow from all fan ports NOTE See Section 6 29 Figure 6 6 for identification of cooling fan installation applicable for this maintenance interval 220 hours max Nose Av
168. PROP EXAMPLE For a configuration that loaded King Air B300 PT6A 60A the AIRFRAME section should display SERIES B300 ENGINE PT6A 60A PROP HARTZELL 4 Page 1 2 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 300 B300 Series King Air An overview of the G1000 and GFC 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 Section 5 Troubleshooting 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 G1000 equipment Section 8 System Return to Service Procedure Spec
169. R CONFIGURATION page on PFD1 3 The ADDRESS TYPE default is US TAIL To enter a non US Mode S registration number set the ADDRESS TYPE 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 XPDR 1 ACTIVE XPDR 2 ACTIVE VFR CODE 1200 1200 AIRCRAFT WEIGHT lt 15 500 LBS lt 15 500 LBS MAX AIRSPEED lt 300 KTS lt 300 KTS ADDRESS TYPE US TAIL US TAIL MODE S ADDRESS N N FLIGHT ID TYPE SAME AS TAIL SAME AS TAIL FLIGHT ID N N ENHANCED SURVEIL ENABLED ENABLED ADS B TRANSMIT PFD CONFIG PFD CONFIG AIRCRAFT WIDTH lt 23 MT lt 23 MT AIRCRAFT LENGTH lt 15 MT lt 15 MT SURVEIL INTEGRITY lt 1x10 5 ERR HR FLT lt 1x10 5 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 PED
170. RS 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 N D U t Figure 2 11 Magnetometer Page 2 8 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 2 1 13 GDL 69A Datalink The GDL 69A provides 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 69A 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 Right Gen Avionics Bus The GDL 69A sends weather data through the HSDB bus to the MFD where the data link interface is controlled Digital audio
171. 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 GWX 68 Press ENT key on PFD1 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 PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 34 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 21 GWX 70 Software Configuration Follow this procedure to configure the GWX 70 Weather Radar if installed Refer to section 3 20 if the GWX 68 Radar is installed Coordinate the GWX 70 configuration with Section 7 12 GWX 68 or GWX 70 Weather Radar 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 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 PFD1 3 Rotate the small FMS knob to highlight King Air GWX 70 Press ENT key on PFD1 Verify King Air GWX 70 is displayed in
172. SWITCH ANNUNCIATOR PROP SYNCH AND STANDBY BATTERY 6 16 6 24 EMERGENCY FREQUENCY BWITCHIANNUNCIATOR 6 16 6 25 STANDBY BATTER Yossie eebe eeh hee 6 17 6 26 STANDBY AIRSPEED INDICATOR cccccccssssscecssssececsesseeecscsseeecsesseeecessseecesesseeeesesseeecseseeeeseuss 6 17 6 27 STANDBY ALTIMETER au da icceisesSeccasel aA EES 6 17 6 28 STANDBY ATTITUDE ANDICATOR eg Aere Ae AE 6 18 6 29 CTA COOLEIN GRAINS is 535 053 le neko ce Sas avon less a eebe eee Ava AAA vik Oa AoA asi 6 19 6 30 GDU COOLING EEN 6 20 6 31 GES 820 850 TRARFIG CR EE 6 20 6 32 GAC 65 PALNA UNIT foc Ee A EE EE 0s ANGERS sa EE 6 21 6 33 GA S8 TRABFIG ANTENNAS eegene geseet Ee eege SA 6 22 6 34 GDE S59 WIEEEFDATALINK oer eee eegene geen AR 6 22 6 35 GSR S6 SATELEITE RECEIVER zacierania RSE eg Ed EES De ed Ee 6 23 6 36 GSD 41 DATA CONCENTRATOR araar AE EAE AEA AE E ERIA ARAARA EFRA 6 23 6 37 GTS FRAFEIG PROCESSOR EE 6 24 6 38 GRA 5500 RADAR ALTMEIER 6 24 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page iii 190 00716 01 Revision 4 7 G1000 EQUIPMENT CONFIGURATION amp TESTING cccssssscssesssrsscssecsscssesssessessssseeses 7 1 7 1 GDU 1040A 1500 MFD amp PED 7 1 72 GMAI1347D AUDIO PANEL a Ta EEE E TE NEE 7 3 7 3 GTA 63W INTEGRATED AVIONICS UNITA 7 6 7 4 GEA 71 ENGINE AIRFRAME UNITA 7 9 7 5 GTX 33 OR GTX 3000 TRANSPONDER eein nernet ine i e 7 12 7 6 GDC 7400 AIR DATA COMPUTER 7 13 7 7 GRS 77 OR GRS 7800 A
173. The following tools are needed to perform maintenance tasks on G1000 equipment and or installation 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 Al1M BCH GE 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 28 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 28 2 The gauging equipment tool is used for the static port inspection for RVSM compliant aircraft only This tool is available from Hawker Beechcraft Any alternate tool authorized in the Super King Air 300 or B300 Maintenance Manual for RVSM static port measurements may be substituted for this tool Refer to Chapter 34 10 00 of the Super King Air 300 or B300 Maintenance Manual for more details G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 4 3 190 00716 01 Revision 4 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
174. U 44 according to Section 7 7 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 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage Gently insert the GDL 69A into its rack The handle should engage the dogleg track Press down on the GDL 69A handle to lock the unit into the rack Lock the handle to the GDL 69A body using the Philips screw Configure and test the GDL 69A according to Section 7 8 Sne eS 6 11 GSA 80 and GSA 9000 Servos Removal 1 Gain access to the desired servo s 2 Disconnect the servo harness connector 3 Use a socket or open wrench to loosen and remove the 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 86 or GSM 9100 servo gearbox Reinstallation 1 For GSA 80 servos only perform the following steps a Inspect the servo output gear for abnormal wear b 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 c Using a brush or other appl
175. UE FUNCTIONAL CHECK 7 60 8 SYSTEM RETURN TO SERVICE PROCEDURE esseseesseceesseceessoceessoceesscocecssoceesseoeessoceesseceessooe 8 1 SL BACKUP PATH SYSTEM TESTING ENEE NEE e e Eegen 8 2 SZ GFCO GROUND CHECKOUT geeiert Eege AA E Digg 8 10 SA MAINTENANCE RECORDS anurio Dees eege eene 8 15 Page iv G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 LIST OF ILLUSTRATIONS FIGURE Figure 2 1 Display Units deefe Suedel ee ee Figure 22 Audio Baelen ee tisha ade ee Figure 2 3 ARCS Controller EE Figure 2 4 FMS Controller ccecescesscssscecesesecececenccececonseaesnesecsenceeesesentenaeeesoneeaeenees Figure 2 5 BEL Figure 26 GTA Umit seslen aele ea eE EE EE EEE A EEE A E EE EE aeaa Fig re 2 7 GEA MUI acess ecs eoruin aa a a aetna Figure 2 8 Air Data Computer Figure 2 9 OAT pr b se eiiis araa a aa eave A E a A E E E Figure 2 11 Magnetometeny tocan a a DEN E Ee Figure 2 12 GDL 69A Datalink sseseeeseeeeeseseseesessssesrssssesestestssesessessstsessesessesesseserees Figure 2 13 GDL 59 Wi Fi Datalink 0 0 ceececeecceseeseeeeeeseceeceeeeeeesecaeeaeeeeeeaeeateeeeeaes Figure 2 14 GSR 56 Satellite Recetwer ec eceseescesesseeeeceseceeeeeeesecaeeaeeeceaeeaeeeneeaeeaee Figure 2 15 GSD 41 Data Concentrator 0 eccecesseeeceeeseeeecesecaeeeeeeaecaeeeneesecaeeaeeeeenees Figure 2 17 GTS Traffic Drocessor isseire rsitirpiiiiye ensien sioner ii reiia Figure 2 19 GSA EE
176. X 3000 1 w TIS Indicator GIA1 GDC 7400 1 data path is functioning correctly GIA1 GDC 7400 1 data path is not functioning correctly e Load GIA1 and GDC 7400 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 GIA1 o Replace original GIA1 if box turns green after swapping units e Check the GIA1 GDC 7400 1 interconnect wiring for faults Replace GDC 7400 1 if problem remains White N A GIA1 GDC 7400 1 data path functionality is unknown Reload GIA1 configuration files GIA1 GRS 77 or GRS 7800 2 output data path is not monitored A white N A box is normal GIA1 GTX 33 3000 1 data path is functioning 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 Swap GIA1 and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA1 o Replace original GIA1 if box turns green after swapping units 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 unknown Reload GIA1 configuration files G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 11 Revision 4 GIA1 RS 232 continued Channel GRS 77 or GRS 7800 1 GMA
177. X 33 or GTX 3000 2 data path functionality is unknown Reload GIA2 configuration files Page 5 14 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 GIA2 RS 232 continued Channel GRS 77 GRS 7800 2 GMA 1347D 2 Indicator Status 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 GIA1 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 GRS1 no reconfiguration required to confirm if the problem is in the original GRS2 o Replace original GRS2 if box turns green after swapping units Check the GIA2 GRS 77 or GRS 7800 2 interconnect wiring for faults 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 GIA2 GMA 1347D 2 data path is not functioning correctly e Load GIA2 and GMA 1347D 2 configuration files e Swap GMA 1347D 2 and GMA 1347D 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 GIA1 reconfigure both GIA s to their new locations to con
178. XPIRES and DISABLES dates of the subscription appear in blue text 3 Use the FMS knob on the GCU to select MAP Navigation Map page On the GCU press MENU With Map Setup highlighted press ENT on the 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 SAFETAXI Turn the GCU small FMS Knob to display the range of distances 7 Turn the 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 knob 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 Page 7 40 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 7 20 DME Functional Check This check verifies that the DME to G1000 interface operates correctly 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 Vp
179. ader card in the top slot of PFD1 and PFD1 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 highlight King Air DME Option Press ENT key on PFD1 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 PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 41 190 00716 01 Revision 4 3 28 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 22 GRA 5500 Radar Altimeter Functional Check 1 6 7 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 on PFD1 Activate cursor and rotate the small FMS knob to display the drop down m
180. age 3 37 190 00716 01 Revision 4 3 24 TAWS A 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 follow 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 16 TAWS 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 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 highlight King Air TAWS A No Voice Callout Installation Option Press ENT key on PFD1 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 PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 38 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 1
181. age 4 10 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 4 4 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 to the Super King Air 300 or B300 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 Description Procedure Radome for the following Inspection Initials GWX 68 or GWX 70 Item Gain access via the GRS 77 or GRS 7800 Qty 2 a Inspect the GWX 68 or 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 attachment Inspect wire harness for chafing damage proper routing of wire bundles and security of attachment in accordance with AC 43 1
182. aintenance Manual 300 B300 Series King Air Page 7 47 190 00716 01 Revision 4 6 Calculate the ANGLE for each static port by subtracting the smallest of the A B C or D measurements from the largest of the A B C or D measurements Record the ANGLE in the measurement log Figure 7 14 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 13 Static Port Measurement locations AVERAGE ANGLE A B c D A B C D 4 Largest Smallest UPPER LEFT LOWER LEFT UPPER RIGHT LOWER RIGHT Aircraft s n Date Figure 7 14 Static Port Measurement Log 7 25 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 Page 7 48 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 7 25 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 Mainte
183. al stabilizer Always use a non magnetic Phillips screwdriver when removing or installing all screws near the magnetometers 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 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 harnesses 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 mount
184. alid XPDR1 is Inoperative GMA1 Is Inoperative AHRS 1 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 2 Open GIA1 primary and secondary CBs 3 Verify desired results 4 Close GIA1 primary and secondary CBs Allow system to re acquire satellites and return to normal display modes GIA 2 Failure Condition For a GIA 2 failure condition the following shall Open GIA 2 CB occur Verify desired results Close GIA 2 CB Allow system to re acquire satellites and return to normal display modes Dual GIA Failure Condition 1 Open GIA1 primary and secondary CBs and GIA 2 CB Check for desired results Restore power to both GIA units If equipped NAV2 and COMM2 tuning fields on PFD1 and PFD2 are invalid red X L R engine data remains valid XPDR2 is Inoperative GMA2 Is Inoperative AHRS2 is using backup GPS source AHRS1 not receiving backup GPS Information An amber is displayed on PFD1 and PFD2 AHRS and ADC data remain valid on PFD1 and PFD2 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 an
185. amage 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 chaffing Reinstall the GMU 44 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 shields and their attachment GRA 5500 Radar Altimeter G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 4 15 190 00716 01 Revision 4 Table 4 9 Lightning Strike Inspection Procedure Description Procedure Initials 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 installation to ensure GTP 59 OAT Probe that there is no structural damage around the areas where lightning may have attached If or Antenna 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 suspected or actual GMU 44 Qty 2 lightning strike A li
186. ance Manual 300 B300 Series King Air Revision 4 190 00716 01 7 30 GSR 56 Satellite Receiver Functional Check 1 Power up the PFD1 in configuration mode On the PFD1 select GDL page group using the large FMS knob Using the small FMS knob select the GSR56 Configuration page Verify the page can be displayed and information is available GSR56 CONFIGURATION PERMISSION LEVEL ACTIVE VOICE DATA SMS NONE ENABLED FUNCTIONALITY SETTINGS DEFAULT INTERNATIONAL CODE VOICE PRIORITIZED OVER DATA Figure 7 16 GSR56 Configuration Page 4 Restart 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 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 the 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 P t wg COCKPIT IRIDIUH 1 Figure 7 17 AUX TELEPHONE 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 300 B300 Series King Ai
187. 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 Page 5 54 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 5 10 GIA 63 Troubleshooting 5 10 1 COM Symptom Recommended Action Weak COM transmit power e Switch GIA1 and GIA2 to verify location of problem v If problem follows unit replace GIA v If problem does not follow unit check COM antenna and cabling for faults Weak COM receiver e Switch GIA1 and GIA2 to verify location of problem v If problem follows unit replace GIA v If problem does not follow unit check COM antenna and cabling for faults No COM sidetone 5 10 2 NAV e Switch GIA1 and GIA2 to verify location of problem v If problem follows unit replace GIA v If problem persists replace GMA1 with a known good unit v If problem persists reinstall original GMA1 and replace GMA2 Symptom Recommended Action Weak NAV receiver e Setup aNAV COM Ramp Test Set to radiate a test signal e Switch GIA1 and GIA2 to verify location of problem v If problem follows
188. andby 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 Super King Air 300 or B300 Maintenance Manual listed in Table 1 2 r 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 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 8 5 190 00716 01 Revision 4 s Leite Besch Verify the following 5 Select depress the STANDBY BATTERY switch 6 Activate aircraft power by selecting the on position of the BATTERY switch Deselect the STANDBY BATTERY switch Remove aircraft power by selecting the battery switch to OFF position 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 STBY attitude STBY Altimeter STBY Airspeed indicators are illuminated full bright Amber ON is annunciated full bright on the STANDBY BATTERY switch White ST
189. anual 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 other input is received If the DISPLAY BACKUP button is pushed again during this 5 second interval the timer will repeat the count 132 825 124 588 cons 119 158 conz EEEE 19 150 Page 3 6 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 external power then set the BAT EXT PWR and AVIONICS MASTER PWR switches to ON Pull the MFD PFD1 PRI PFD1 SEC and PFD2 circuit breakers 3 Press and hold the ENT key on PFD2 co pilot while applying power using the PFD2 circuit breaker Release the ENT key after INITIALIZING SYSTEM ap
190. 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 e 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 H PFT FAIL Timeout lt STEP 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 e 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 STEP 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 M AHRS MON invalid lt STATE gt The AHRS monitor has detected that the AHRS data is invalid The possible values for lt STATE gt are a Mon Prmtr Invalid The ARINC 429 data used by one of the monitors has not been received Attitude Prmtr Invalid The ARI
191. apable of measuring to the minute MERGENCY POWER SUPPLY J Figure 4 5 Standby Battery Page 4 32 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 A Press and hold TEST SWITCH Figure 4 5 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 IfOUTPUT 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 THESE ARE TYPICAL CURVES AND MAY VARY DUE PS 835A C amp E TO TEMPERATURE TEST EQUIPMENT ETC 25 TYPICAL OUTPUT USING INTERNAL 24 Be HEATER 7 4 OHMS AS LOAD x TYPICAL OUTPUT USING 7 OHM 1 LOAD PIN 2 11 TO 12 GND REFERENCE MINIMUM ACCEPTABLE lt 21 DISCHARGE CURVE 20 0 5 10 15 20 25 30 35 40 45 Time minutes PS 835B D amp F 25 TYPICAL OUTPUT USING INTERNAL 24 a HEATER 7
192. armin GMA 1347D Audio Panel integrates NAV COM digital audio intercom system and marker beacon controls The 300 B300 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 IAUs Electrical power to GMA 1 is provided from No Triple Fed Bus Electrical power to GMA 2 is provided from Left Gen Avionics Bus 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 2 1 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 300 B300 Series Cockpit Reference Guide The GMC 710 is powered by No 1 Triple Fed Bus Figure 2 3 AFCS Controller G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 2 3 190 00716 01 Revision 4 2 1 5 GCU 477 FMS Control Unit The GCU 477 functions as the primary control interface to the G
193. ashing 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 51 Clearing Default User Settings 1 Remove power from PFD1 PFD2 and MFD by pulling the PFD1 PRI PFD1 SEC PFD2 and MFD circuit breakers While holding the CLR button on PFD1 reset PFD1 PRI and PFD1 SEC circuit breakers 3 While holding the CLR button on PFD 2 reset the PFD2 circuit breaker While holding the second key from the right side of the MFD beginning on the right side of the MED count 2 keys to the left reset the MFD circuit breaker 5 When prompted to clear user settings select the YES softkey on each unit G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 69 190 00716 01 Revision 4 This page intentionally left blank Page 3 70 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 4 Instructions for Continued 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
194. at an RA FAIL message is displayed 6 Reset the RADIO ALTM circuit breaker a a ee If no other service is to be performed continue to the return to service checks in Section 8 Page 7 42 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 7 24 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 BAT EXT PWR and AVIONICS MASTER PWR switches to ON and wait for all aircraft and avionics systems to complete their initialization and begin operating normally 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 is NOT displayed on the 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 Super King Air 300 or B300 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 PFD1 and PFD2 see Figure 7
195. ately 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 Ifthe bearing is not as anticipated or multiple targets are displayed 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 e 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 to assure proper operational and surveillance functions The GTS 8XX must be in Ground Test mode 1 Onthe MAP TRAFFIC MAP page of the MFD press the OPERATE softkey for GTS 8XX or TA RA softkey for GTS 8000 For GTS 8000 only change BARO setting to 29 92 in Hg on PED and PFD2 3 Position ramp tester at 90 degrees Select the following on the ramp tester Intruder type ATCRBS Intruder Start Distance 15 nm Intruder Start Altitude GTS 8XX 50 300 ft Intruder Start A
196. attery 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 300 B300 Series King Air Page 2 15 190 00716 01 Revision 4 p 1 T z 2 a 13 28 2 l l Be irs d V A aw 5 Be PEF 8 H 3 EZ bes ee za e SZ aoli S E e z E 2 l Kabel T i 5 E l B ao o a aa x an z a a l p E ia a x Ze S gt H R H gt GE l gt KI EN aa gt ek l D z l H A R A w E x aa Ge E SE k gt te g ol l v a E d x t Dg S x i we 5 R 5 S A 3 g i ei le i H H Ly F Se R LC bas 2 o ER 5 E g l ER ER 4 d a RN i 1 ol Yy d z SI a y E a w y 8 a gt o 5 ne a gt e m R 2 E T 2 ae D Rz I g ZQ T ER RE z d G Z SS Ss LG ER a a H H rm bi Bs i a 3 ege E E eege
197. 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 4 Remove antenna Reinstallation 1 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 Reinstall the aft cabin ceiling panel 5 Test the GSR 56 according to Section 7 30 6 21 Wi Fi Antenna Removal 1 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 1 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 Test the GDL 59 according to Section 7 29 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 Condition
198. cable AFMS Ba G1000 Configuration Verification After system configuration files are loaded the technician verifies that the correct configuration on the Airframe Configuration page Figure 3 16 Software Configuration Overview G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 19 190 00716 01 Revision 4 3 9 1 MFD amp PFD Software Load Follow this procedure to load software to either PFD or the MFD l 2 3 Connect a ground power unit to the external power receptacle and turn on the ground power unit Set the BAT EXT PWR and AVIONICS MASTER PWR switches to ON With the G1000 system powered on pull the MFD PFD 1 PRI PFD 1 SEC and PFD 2 circuit breakers Insert the software loader card into top card slot in the desired PFD or MFD See Section 3 8 2 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 Start the PFD or MFD in configuration mode as described in Section 3 7 Press the ENT key or the sofkey labeled YES to acknowledge the following prompt see also note below for MFD 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 6 The ENT key for the MFD is located on the
199. cators 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 e Red X Expected data is not received A red X could also indicate that a parameter component is invalid e White N A Expected data is OFF or no data is expected GDU STATUS XILINX BASE MAP ETHERNET 1 ETHERNET 2 ETHERNET 3 ETHERNET 4 RS 232 1 RS 232 2 IRDA Figure 3 13 Data Transmission Indicators G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 9 190 00716 01 Revision 4 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 System Page Group 1 System Status 5 System Upload 2 Time Configuration 6 Diagnostics Terminal 3 Lighting Configuration 7 OEM Diagnostics 4 System Audio 8 System Configuration 9 System Data Path Configuration 10 System Setup 11 Manifest Configuration 12 Maintenance Log System Page Group Aircraft equipped with GDU v13 06 or later
200. ce Manual 300 B300 Series King Air Page 5 53 190 00716 01 Revision 4 5 9 7 GMA Alerts Failure Message GMA1 SERVICE GMA1 needs service Return unit for repair GMA2 SERVICE GMA2 needs service Return unit for repair The system has determined that the specified GMA 1347D needs service Solution Replace GMA GMA1 FAIL GMA1 in inoperative GMA2 FAIL GMA2 in inoperative The system has detected a failure in the specified GMA 1347D Ensure GMA1 is receiving power Ensure both GIAs are receiving power Ensure all GDUs are receiving power Ensure the GMA GIA RS 232 data lines are working properly Ensure the GIA GDU Ethernet data lines are working properly Replace GMA1 MANIFEST GMA1 software mismatch Communication Halted MANIFEST GMA2 software mismatch Communication Halted 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 GMA1 CONFIG GMA1 configuration error Config service req d GMA2 CONFIG GMA2 configuration error Config service req d The system has detected a GMA 1347D configuration mismatch for the specified unit e Load GMA configuration files see Section 3 9 e Replace GMA e f problem persists replace master configuration module check config module wiring for faults
201. ch 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 PFD1 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 King Air Enable SVS Dual PFD Press ENT key on PFD1 4 Verify King Air Enable SVS Dual PFD 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 PFD1 to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the SVS Enable card from PFD1 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 57 190 00716 01 Revision 4 3 41 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 00629 02 will be required for this procedure Ensure that the ESP Support no AOA
202. ch located to the left of the annunciator panel and verify the following e legends illuminate and reflect EMERG FREQ in white and 121 5 in white 3 Release cockpit annunciator Press To Test switch 4 If further maintenance is not required proceed to Section 8 Page 6 16 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 6 25 Standby 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 battery from the rack Reinstallation 1 Install the standby 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 Super King Air 300 or B300 Maintenance Manual listed in Table 1 2 for access requirements as needed 2 If further maintenance is not required proceed to Section 8 6 26 Standby Airspeed Indicator Removal 1 Remove MFD 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 Use a Phillips screwdriver to remove the attachment screws from the front of the standby airspeed indicator
203. compare monitors function properly 820 hours max G1000 Alerts Check for and troubleshoot any alerts provided in the alert window per the referenced manual section On Condition GPS WAAS Antennas Diversity Transponder Antenna Iridium antenna Wi Fi Antenna GA 58 Traffic Antennas Removal amp Replacement Refer to Master Drawing List listed in Table 1 2 for installation drawings On Condition On Condition On Condition On Condition On Condition Flaps in motion Discrete Input Check Test the Flaps in motion discrete inputs to the G1000 to verify proper operation Phase 1 2 3 amp 4 GSA 80 and GSA 9000 Servos GSM 86 and GSM 9100 Servo Gear Box Removal amp Replacement Refer to Master Drawing List listed in Table 1 2 for installation drawings Removal amp Replacement Refer to the servo install drawings listed in Master Drawing List listed in Table 1 2 On Condition On Condition GSM 86 Slip Clutch Torque Check GSM 9100 Servo Gear Box Rudder Boost Operation Check WOW and Low Speed Awareness Band Check Verify that the pitch roll and pitch trim GSM 86 slip clutch torque values are within acceptable limits Remove the GSM 9100 yaw servo gear box and send to Garmin for servicing Verify the Rudder Boost operation and annunciation Verify the integrity of the wiring interface between the landing gear safety switch
204. 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 HW MISMATCH GIA hardware mismatch GIA1 communication halted HW MISMATCH GIA hardware mismatch GIA2 communication halted The G1000 has detected a non WAAS GIA 63 Replace GIA with a WAAS unit GIA1 SERVICE GIA1 needs service Return unit for repair GIA2 SERVICE GIA2 needs service Return unit for repair The G1000 has detected a failure in the specified GIA Replace suspect GIA G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 63 Revision 4 5 12 GEA Troubleshooting 5 12 1 GEA Alerts Failure Message Solution MANIFEST GEA1 software mismatch Communication l halted The system has detected an Load the correct software verion See incorrect software version loaded Section 3 9 for GEA 71 Software Load MANIFEST GEA2 software in the specified GEA 71 Procedure mismatch Communication halted GEA1 CONFIG GEA1 e Load GEA configuration files See configuration error Config service Section 3 9 for GEA 71 req d Configuration Procedure If problem persists replace master configuration module check config module harness for faults and replace if necessary NOTE N
205. contains magnetic disturbances that are too large G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 21 190 00716 01 Revision 4 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 1 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 the 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
206. craft 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 6 1 190 00716 01 Revision 4 6 1 GDU 1040A and GDU 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 dis
207. csesensaeeeeeeecsesensaaeas 4 1 d SERVICING INFORMATION nieerrer eker EAEE E EERE EREN 4 2 4 3 lt MAINTENANGE INTERVALS eener NENEN NE E UR 4 4 AA MISUALAINSPECTION ed E N E E EN 4 11 d ELECTRICAL BONDING TEST ra nern rE ARA AA AEEA 4 16 4 6 GRS 77 OR GRS 7800 EARTH MAGNETIC FIELD UppATEs 4 19 4 7 GSA 80 GREASING DROCEDURE ROA SE Aa AREE ROAR 4 19 4 8 FLAPS IN MOTION DISCRETE INPUTCHRBCK 4 20 4 9 GSM 86 SLIP CLUTCH TORQUE CHECK PROCEDURE 4 21 4 10 G1000 REDUNDANT CONNECTION CHECK 4 23 4 11 ENGINE DATA CHECK ee Eet eet EES 4 26 4 12 ERIM ANNUNCITATOR CHECK i 2 s asszeaescoczscsteucsitiues ctddeab EENS EE 4 28 4 13 G1000 MISCOMPARE CHECKS anarien rea aE EEA A aAA AASE ANTRENA A aA iaa AAE RATAA Ea 4 30 4 14 GIA COOLING FANS OPERATIONAL CHECK 4 31 4 15 GDU COOLING FANS OPERATIONAL CHECK 4 31 4 16 STANDBY BATTERY PERIODIC CHECKS irena ieronsri ienee ians a taeae aoe iaon iaten ieas 4 32 4 17 RUDDER BOOST OPERATIONAL CHECK 4 35 4 18 EXTERIOR SKIN INSPECTION AROUND ANTENNAS 4 35 5 TROUBLESHOOTING wesissssesccscsscivescecstvescecccvssessctcsscesstvesssdsevssescccessnscctesssedvcvessscaevesescceessescctesdecste 5 1 531 41000 ALERTING SYSTEM WEE EE 5 2 5 2 SYSTEM ANNUNGIATIONS 5 335 cotati Beggen Sharan aie 5 5 Sa 300 B300 SPECIFIC ALERTE 5 26 9 45 STA WS TROUBLESHOOTING ee dee dE EE EE suits 5 27 5 5 SYNTHETIC VISION AND PATHWAYS TROUBLESHOOTING ssssssssssssssssesesetssssssrrersrssssssrreesrs
208. ct 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 King Air Enable TAWS A Press ENT key on PFD1 Verify King Air Enable TAWS 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 e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete De activate the cursor 8 Power down the system and remove the TAWS A Enable Card from PFD1 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 55 190 00716 01 Revision 4 3 39 Supplemental Database Loading 1 Open PFD1 PFD2 and MFD 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 Reinsert the SD card containing the current supplemental databases into the Jower slot of the MFD 5 Close PFD1 PFD2 and MFD circuit breakers The system will
209. ct 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 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 in Table 1 2 Pay particular attention to possible areas of chaffing such as the middle shelf feed through hole wheel well protrusion etc Inspect Ground blocks for security of attachment corrosion or other defects Ensure all connectors are securely fastened G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 4 11 Revision 4 Table 4 5 Pilot s Compartment Visual Inspection Procedure Description Procedure Initials 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 Locate equipment in the aft pedestal for the following inspection a 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 Inspect the ADF control un
210. d Use the small large FMS knobs to enter the US aircraft registration number or other Mode S registration number TRANSPONDER CONFIGURATION XPDR 1 ACTIVE XPDR 2 ACTIVE VFR CODE 1200 1200 AIRCRAFT WEIGHT lt 15 500 LBS lt 15 500 LBS MAX AIRSPEED lt 300 KTS lt 300 KTS ADDRESS TYPE US TAIL US TAIL MODE S ADDRESS N N FLIGHT ID TYPE SAME AS TAIL SAME AS TAIL FLIGHT ID N N ENHANCED SURVEIL ENABLED ENABLED ADS B TRANSMIT PFD CONFIG PFD CONFIG AIRCRAFT WIDTH lt 23 MT lt 23 MT AIRCRAFT LENGTH lt 15 MT lt 15 MT SURVEIL INTEGRITY lt 1x10 5 ERR HR FLT lt 1x10 5 ERR HR FLT Figure 3 23 Aircraft Registration 4 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 5 After each configuration setting change press the ENT key to configure the transponders 6 Press the ENT key on PFD1 to acknowledge prompt 7 After completing transponder configuration deactivate the cursor Page 3 62 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 45 2 System Software Version
211. d GRA 23 documents found Displaying 10 document s from 1 to 10 Results Per Page 10 B Save Settings Name Type DocID Publish Date gt GRA5500 Sensor System Software Version Software Updates Jul 25 2013 P 2 05 gt GRA 5500 Main System Software Version Software Updates Jul 25 2013 o 2 05 5 Click on the download symbol for the appropriate Sensor and Main software version part numbers based upon the information 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 28 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
212. d over metal drainage culverts or on hard surfaces that may contain steel reinforcements The 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 300 or B300 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 The resistance between the base of each static discharger and the surface to which it is attached The resistance between the elevators rudder and GRS 77 or HDG FAIL GRS 7800 the airplane structure amp Ensure that a cell phone or a device using cell phone HDG GMU 44 technology is not turned on even in a monitoring state in the cabin 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 Perform a Magnetometer Interference Test to check for interference from onboard electrical system components e g NAV lights Pay particular attention to any n
213. d the TAWS N A and LOT 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 PFD1 SEC circuit breakers Re power PFD1 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 messages are played e Too Low Terrain e Sink Rate e Pull Up e Don t Sink e Five Hundred e Caution Terrain 2X e Terrain 2X Pull Up 2X e Caution Obstacle 2X e Obstacle 2X Pull Up 2X e Terrain Ahead 2X e Terrain Ahead Pull Up 2X e Obstacle Ahead 2X e Obstacle Ahead Pull Up 2X 11 Pull the PFD1 PRI and PFD1 SEC circuit breakers and re power PFD1 in normal operating mode If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 35 190 00716 01 Revision 4 7 16 2 Functional Check for TAWS A 1 2 9 10 11 12 13 14 15 With the G1000 in Normal Mode use the GCU FMS knob to select the MAP group and TAWS page on the MFD Verify that the title at the top of the page reads MAP TAWS A
214. de references to complete the approximate 30 turn Instead of using the PFD instruction to turn as a real time indication of when to turn simply judge the 30 45 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 encountered 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
215. dition still exists remove and replace the affected servo Check for possible fuel imbalance Check aileron control adjustments Page 5 30 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Annunciation Condition Resolution Aileron Mistrim If mistrim condition still exists remove and replace the roll Left servo Rudder Mistrim Check rudder control adjustments Right If mistrim condition still exists remove and replace the yaw Se servo Rudder Mistrim Left Allow the system to complete pre flight tests Pre Flight Test The 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 4 for additional PFT diagnostics Table 5 4 AFCS General Troubleshooting 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 Super King Air 300 or B300 Maintenance Manual Check aircraft control cables for proper tension per the Super King Air 300 or B300 Maintenance Manual Poor AP Performance Limited AP Authority 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
216. ds the MINIMUM ACCEPTABLE DISCHARGE CURVE the unit is considered satisfactory 10 Ifunit 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 5 Item 4 Ifno OUTPUT VOLTAGE MONITOR LED s come on 1 Position all INDIVIDUAL CELL DIP SWITCHES Figure 4 5 Item 5 to the ON position 2 Press and hold TEST SWITCH Figure 4 5 Item 4 and observe the INDIVIDUAL CELL MONITOR LED s Figure 4 5 Item 1 a If all INDIVIDUAL CELL MONITOR LED s come on except DS12 the unit is damaged and requires repair at an authorized repair station b If all INDIVIDUAL CELL MONITOR LED s are on 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 a 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 and 7 and charge the unit for 16 hours The batteries should reach
217. 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 PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 27 190 00716 01 Revision 4 3 14 GTX 3000 Configuration This STC only certifies the GTX 3000 interfacing with the Garmin TCAS U 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 PFD1 Verify King Air GTX 3000 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 summa
218. e aircraft the RVSM critical region must meet the following additional visual inspection criteria The fillet seal around the perimeter of the external doubler must be smooth and uniform The protruding head screws must be installed tightly against the cover plate The cover plate must fit smoothly against the external doubler 7 EXTERNAL DOUBLER COVER PLATE l STATIC PORTS LA OXYGEN SERVICING DOOR RH SIDE ONLY L al Figure 7 10 RVSM Critical Region modified 7 25 3 RVSM Static Port Height Inspection The Gauging Assembly p n SPF 4 A1M BCH GE is available from Hawker Beechcraft Any alternate tool authorized in the Super King Air 300 or B300 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 the plunger is free Place the gauging assembly on a flat surface gauge block or equivalent 3 Ensure the smaller needle is at approximately 1 Rotate the dial indicator to set the large needle at 0 as shown in Figure 7 11 Page 7 46 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 DIAL INDICATOR Figure 7 11 Dial Indicator The static port measurements are obtained at four locations on each static port as shown in Figure 7 13 These measurements are used to find an AVERAGE and ANGL
219. e cable Replace thermocouple cable Replace GEA 71 Check torque transmitter GEA wiring Check power input to torque transmitter Replace torque transmitter Replace GEA 71 Torque Check prop tachometer Signal Conditioner wiring Check Signal Conditioner GEA wiring Check power input to Signal Conditioner Replace prop tachometer sensor Replace Signal Conditioner Refer to Section 6 22 Replace GEA 71 Check engine speed tachometer Signal Conditioner wiring Prop RPM 60 a s Check Signal Conditioner GEA wiring Check power input to Signal Conditioner 2 RPM Replace engine speed tachometer sensor Replace Signal Conditioner Refer to Section 6 22 Replace GEA 71 TURB 1007 Turbine RPM Check Signal Conditioner unit wiring Check power input to Signal Conditioner Fuel Flow Replace fuel flow transmitter Replace Signal Conditioner Refer to Section 6 22 Replace GEA 71 Check oil pressure sensor GEA wiring Oil Pressure Replace oil pressure sensor Replace GEA 71 Check oil temperature sensor GEA wiring Oil Temperature Replace oil temperature sensor Replace GEA 71 Page 5 24 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 2 4 ADF DME Failure A DME or ADF failure is represented by the following red X s Refer to G1000 GFC 700 Wiring Diagram and Super King Air 300 or B300 Maintenance Manual listed
220. e 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 MFD 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 weu 113 HD 110 98 IIXD nav2115 98 110 98 Ke d ROL Figure 5 5 AFCS Annunciation Field G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 29 190 00716 01 Revision 4 5 6 1 General Troubleshooting The following annunciations may appear in the AFCS Annunciation field Annunciation AFCS Table 5 3 AFCS Annunciation Troubleshooting AFCS System Failure Confirm AFCS Servos circuit breaker IN Ensure that the G1000 system is in proper working order Check specifically for proper operation of the v GIA 63 Integrated Avionics Units v GRS 77 AHRS Units v GDC 7400 Air Data Computers v All GSA 80 Servos Check that no red X s are present on the MFD and PFD displays Check that no related alert messages are present on the PFD displays press the ALERTS softkey Go to the AUX SYSTEM STATUS page on the MFD and verify that all LRUs have a green check see Section 5 In Configuration mode
221. e 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 300 B300 Series King Air Revision 4 190 00716 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 e Yaw Damper e Electronic Stability and Protection optional Flight Director 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 between flight director 1 GIA 1 and flight director 2 GIA2 Autopilot
222. e summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 36 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 23 TAWS A 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 38 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 on PFD1 2 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small FMS to highlight King Air Airframe Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight King Air TAWS A Support Press ENT key on PFD1 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 PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air P
223. eccesceseeseeseceseeseesecaesaeeseessecaeeeeeeneeseceaeeaeseecaeeaeeeneeaeease 8 9 Figure 8 4 Pre Pl ght Let eebe ee suuedlcacens ony a e i i a e E 8 10 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page vii 190 00716 01 Revision 4 LIST OF TABLES TA BL DE PAGE Table 1 1 G1000 System Software Version ccccccccsscessscessceeecsseeseceeeseeeseeeseecsaecsaecaeceseceseceeeseeeseeesaees 1 1 Table 1 2 Re guired DOCUMENTS sonis a a a Fastadend has busdoesadeidibasdas AEE 1 5 Table 1 3 Reference Publications sescreesseeiseesssrsisaeseesssesicasssesssocstaesiesiseeisesasecsscsdsaseosroateessaiseedsocsdsaess 1 6 Table 2 dk Clesen See E EATE nal E AE A A ebe 2 18 Table 3 1 Flight Data Recorder Barameterg 3 51 Table 4 1 Maintenance Intervals cccecccccccccccseessscccccsseesssesessecccusseseseesscesceseesesessssesceeseesseeseeseesees 4 4 Table 4 2 Discontinued Maintenance Intervals cccccccccccceseessssscesccecessesssaescccuseessssssesescesssesesssaseesecs 4 10 Table 4 3 Nose Section Visual Inspection Drocedure 4 11 Table 4 4 Nose Avionics Compartment Visual Inspection Procedure ccccecsceessesteeeteeeteeeteeeeees 4 11 Table 4 5 Pilot s Compartment Visual Inspection Brocedure 4 12 Table 4 6 Instrument Panel G1000 Equipment Visual Inspection Procedure ccsceeseeteeeteeeeeeees 4 12 Table 4 7 Cabin Area Visual Inspection Brocedure 4 14 Table 4 8 Rear Fuselage and Empen
224. ecific to installations with the GTS Processor configured as a GTS 8000 TCAS II unit For installations of other approved TCAS II systems these alerts 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 Increase Climb Increase Climb voice Page 5 4 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 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 4 132 825 124 500 com 121 500 JA conz HDG NO COMP ROL NO COMP PIT NO COMP TAS NO COMP ALT NO COMP XPOR1 2324 STBY LCL 14 29 58 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 MED 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 mes
225. eck 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 Ensure that each cable is correctly attached to the clamps Follow recommended checks for checking main control cables following the instructions in Chapter 27 Flight Controls of the Super King Air 300 or B300 Maintenance Manual listed in Table 1 2 i Reinstall the access panel if no other maintenance is to be performed GTX 33 or GTX 3000 Qty 2 GTX option only GDL 59 wi fi option only GSR 56 iridium option only GSD 41 GSD option only The GMU 44 units are mounted in the tailcone or the horizontal stabilizer Refer to Section 6 9 for details on gaining access to the GMU For each GMU 44 do the following Remove the three Phillips screws holding the GMU to the mounting bracket Be sure to use a non magnetic screwdriver to avoid harming the GMU Carefully remove the assembly taking care not to damage unit or wiring and inspect the GMU 44 and mounting plate GMU 44 Qty 2 Inspect the mounting hardware and GMU 44 for corrosion or other damage Inspect all exposed GMU wiring and ensure no chaffing wear or other d
226. ect GTS Processor TAS to TCAS II Enablement Press ENT key on MED 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 De activate the cursor 1 With the TCAS II Enable card in the top slot of MFD in configuration mode select the 7 Power down the system and remove the TCAS II Enable card from MFD G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 61 190 00716 01 Revision 4 3 45 Aircraft Registration Number Entry NOTE This section is only applicable to those aircraft that use the GTX 33 33D or GTX 3000 transponder configuration loaded per Sections 3 13 or 3 14 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 45 1 System Software Version 0985 06 and Previous 1 With PFD1 in configuration mode select the GTX page group then select the TRANSPONDER CONFIGURATION page on PFD1 2 The ADDRESS TYPE default is US TAIL To enter a non US Mode S registration number set the ADDRESS TYPE field to HEX ID 3 Activate the cursor and highlight the MODE S ADDRESS fiel
227. ection 3 9 3 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 8 1 190 00716 01 Revision 4 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 GPS Failure Test T Destro Res Single GPS Failure Condition 1 Ensure GPS satellites 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 Check for desired results Remove shroud from the GIA 1 GPS antenna and allow system to re acquire satellites Place a shroud over the GPS antenna for GIA 2 to prevent signal reception Verify loss of signal on MFD AUX page 4 Check for desired results Remove shroud from the GIA 2 GPS antenna Dual GPS Failure Condition Ensure GPS satellites are acquired Cover both GPS antennas Verify loss of signal on MFD AUX page 4 Check for desired results Remove shrouds from GPS antennas Allow both receivers to re acquire satellite signals before continuing For each of the single GPS failure conditions the following shall remain valid on the PFD throughout
228. eed mode key mode key mode key ALT ALT SEL BANK PUSH SYNC PUS H DIR PUSH DIA Back Autopilot key ey mads i ackKCOUurse ki Selector TT mode key ai Course 2 Yaw damper key Speed key selector Course Bank AS MACH selector og Nose Up Nose Dn Figure 3 5 AFCS Controls GMC 710 shown G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 3 190 00716 01 Revision 4 3 4 GMA 1347D Audio Panel Figure 3 6 provides the audio panel controls COM1 Transmitters Transceiver Audio Passenger Address Telephone Music Speaker Marker Beacon Mute Marker Beacon Signal Sensitivity Transceiver Audio Aircraft Navigation Radio Audio Manual Squelch Digital Recording Playback Intercom System ICS Cabin Intercom ICS VOL SQ Small Knob Master VOL Large Knob Reversionary Mode DISPLAY BACKUP Figure 3 6 GMA 1347D Controls Page 3 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 and EXT PWR switches to ON The following G1000 equipment is powered PFD displays amp MFD display GRS 77 or GRS 7800 AHRS Units GDC 7400 Air Data Computers GIA 63W Integrated Avionics Units GEA 71 Engine Airframe Units GCU 477 FMS Control Unit GMC 710 Autopilot Control Unit GSA S
229. eed 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 NAVI 118 98 122 500 125 500 con nav2 113 68 gt 118 38 127 250 con2 Ya Nt N PORT Es 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 Maintenance Manual 300 B300 Series King Air Page 7 25 190 00716 01 Revision 4 7 8 GDL 69A XM Data Link Original GDL 69A 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 69A is Installed If a new repaired or exchange GDL 69A 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
230. electric trim switch Verify the Autopilot disengages normally with an aural alert and the trim wheel rotates freely when moved manually 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 AP at the top of PFD1 and PFD2 is replaced by a white CWS Release the CWS switch and press the XFR key on the AFCS mode controller Verify 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 AP at the top of PFD1 and PFD2 is replaced by a white CWS 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 AP annunciation on PFD1 and PFD2 accompanied by an aural alert Verify that the control wheel is free in pitch and roll axes Engage the autopilot again by pressing the AP 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 AP annunciation Verify no AFCS annunciations e g AFCS PFT Mistrim remain on PFD1 or PFD2 Press the AP YD D
231. ellaneous Alerts Failure Message XTALK ERROR A flight display cross talk error has occurred A communication error has occurred between the MFD and or PFDs Solution Go to the GDU TEST page in configuration mode and verify key is stuck if key is stuck the corresponding indicator will be green 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 Ensure a database error has not occurred identified in the ALERTS window on the PFD v 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 If the CLR key was held during a power cycle disregard message Cycle power to PFD1 v Ensure CLR key is not stuck on the GDU TEST page v If problem persists replace PFD1 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 51 Revision 4 Failure Message MFD1 SERVICE needs service Return unit for repair The G1000 has determined MFD1 needs service Solution Ensure the MFD connec
232. em is resolved replace defective unit v If indication is not illuminated check for wiring faults between the GIAs and aircraft squat switch system e Check configuration settings for GIA1 and PFD1 e Swap GIA1 and GIA2 to verify location of problem GIA1 v If problem follows GIA1 replace GIA1 e Check Ethernet interconnect from GIA1 to PFD1 v If problem persists replace PFD NAV2 amp COM2 e Check configuration settings for GIA2 and PFD2 e Swap GIA1 and GIA2 to verify location of problem GIA2 v If problem follows GIA2 replace GIA2 NAV e Check Ethernet interconnect from GIA2 to PFD2 v If problem persists replace PFD G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 19 190 00716 01 Revision 4 Associated Invalid Data Field LRU s Solution 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 GPS LOI Check GPS1 and GPS2 signal strength on AUX wil ing page 4 Refer to GIA GPS section if GPS can not acquire a position lock for troubleshooting GIA1 or GIA2 Check corresponding GPS antenna and cable for faults Check Ethernet interconnect between the PFD1 to GIA1 or PFD2 to GIA2 for faults Swap GIA1 and GIA2 to verify location of problem v If problem follows the GIA replace the GIA v If problem persists replace the PFD1 or PFD2 e Check GTX 33 33D or GTX 3000 configuration
233. enu Rotate the small FMS knob to highlight King Air Airframe Options and press ENT key on PFD1 Rotate the small FMS knob to highlight King Air RAD ALT Option Press ENT key on PFD1 Verify the King Air RAD ALT Option is displayed in the Item window 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 PFD1 to acknowledge upload complete Deactivate cursor 3 28 1 GRA Software Installation 1 2 3 Go to 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 mail com Password By signing in you agree to the Garmin Confidentiality Agreement Sign In Select Technical Tools then select Software Downloads In the Keyword s filter enter GRA and click on the Go button Page 3 42 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 4 A screen similar to the one shown below will appear The numbers shown are for example only Software Downloads Filtering Options Clear All Filters Sub category x Filter by Market X Show All Results z Date Range B
234. equipment manufacturer s instructions Verify that 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 on 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 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 24 1 Conduct the Landing Gear Retraction Warning Horn check as stated in the Super King Air 300 or B300 Maintenance Manual listed in Table 1 2 2 Verify that the aural tone is played through the G1000 audio system and through both cockpit s
235. er 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 unit and retain the ground strap and associated hardware for reinstallation on the new unit Reinstallation 1 Reinstallation of the Signal Conditioners is the reverse of the removal Reference the Main Instrument Panel Installation drawing listed in Table 1 2 for more details 2 Test the signal conditioners according to Section 7 4 1 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 6 15 190 00716 01 Revision 4 6 23 Instrument Panel Switch Annunciator Prop Synch and Standby Battery Removal 1 Remove MFD 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 Instr
236. eries King Air Page i 190 00716 01 Revision 4 3 34 FLIGHT DATA RECORDER OPTION CONFIOGURATION 3 51 3 35 FLITECHARTS CONFIGURA TIONG ed eieresesedg B rer Fak desis aaae aascech dek Ea aena aaia aeee Eai 3 53 3 36 OPTIONAL CHARTVIEW ENABLE ssssssssesssssssessseosssssseseretsessssereretsssssserersrssssssreeetssssesreresrsss 3 53 3 37 STANDARD TAWS B ENABLE oi a A E E a E ETEA 3 54 3 38 OPTONAL TAWS A ENABLE E 3 55 3 39 SUPPLEMENTAL DATABASE LOADING cccccccssssscecesssececeessececseseeccsesseeccsessesecsesseeecsesseeeeseuss 3 56 3 40 OPTIONAL SVS PATHWAYS ENABLE o oueienn e A EA T EA EEREN 3 57 3 41 OPTIONAL ESP ENABLE oaa A ANA 3 58 3 42 OPTIONAL SEARCH AND RESCUE ENARLE 3 59 3 43 OPTIONAL GARMIN TCAS I ENABLE FROM GTS 825 roOTSgant 3 60 3 44 OPTIONAL GARMIN TCAS II ENABLE FROM GTS 825 TO GTS 000 3 61 3 45 AIRCRAFT REGISTRATION NUMBER ENTRN 3 62 3 46 GDL 69 ALTERNATE ANTENNA LOCATION CONEFIOURATION 3 64 3 47 BLR WINGLET OPTION MODEL 300 ONLY 3 65 3 48 SPLASH SCREEN LOADING ain RA RA TERRA ERAO ege ee 3 66 3 49 NAVIGATION DATABASE LOADING a a a E AE E E n 3 67 3 50 CONFIGURATION OF NAVIGATION MAP FOR TRAFFIC RNSTEM 3 69 3 51 CLEARING DEFAULT USER SETTINGS mereerin caged deaaueate dacs SEENEN ENEE SE 3 69 4 INSTRUCTIONS FOR CONTINUED AIRWORTHINESG csssscccssssscccssssccccssssccccsssscceeees 4 1 4 1 AIRWORTHINESS LIMITATIONS cccccessscccececssssssccececececsenssececececsesensnseseeece
237. erve the GRS 77 or GRS 7800 and GDC 74 DATA indicators in the ARINC 429 window Verify both indicators are GREEN indicating the channels are receiving data as shown below Pr i RS 232 CHANNEL DATA CHNL 1 CHNL 2 ARINC 429 CHANNEL DATA ACTIVE ACTIVE IN1 High GRS77 1 IN2 Low GDC74 1 Figure 8 1 GDU Data Verification ARINC 429 5 On PFD activate the cursor and select PFD2 in the SELECT UNIT field and press the ENT key 6 Repeat Steps 5 and 6 7 On PFD activate the cursor and select MFD1 in the SELECT UNIT field and press the ENT key 8 Repeat Steps 5 and 6 9 On PFD1 go to the GIA Page Group Go to the RS 232 ARINC 429 CONFIG page 10 Verify that GIA1 is selected in the SELECT UNIT field 11 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 8 7 190 00716 01 Revision 4 12 Verify all DATA indicators are GREEN indicating the channels are receiving data as shown in the following image SELECT UNIT GIA1 CHANNEL CHNL 1 IN 1 IN 2 IN 3 IN 4 IN 5 ING IN 7 IN 8 OUT 1 OUT 2 OUT 3 SDI DATA INPUT SET GDC74 1 GIA DEBUG OFF OFF GTX 33 1 w TIS GRS77 1 GMA1347 1 OFF SPEED SET Low Low Low Low Low High Low Low Low Lov Low Common SET gt ACTY ACTY gt SET RS 232
238. ervos GMA 1347D Digital Audio Panel 1 GSD 41 Data Concentrator Optional 2 Set the AVIONICS MASTER switch to ON The following G1000 equipment is powered GMA 1347D Digital Audio Panel 2 GDL 69A Datalink Unit GWX 68 or GWX 70 Weather Radar Unit GTS 820 850 Traffic System or GTS Traffic Processor Optional GTX 33 or GTX3000 Mode S Transponders Optional GDL 59 GSR 56 Wi Fi Satellite Optional GRA 5500 Radar Altimeter optional The 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 7400s require 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 300 B300 Series Cockpit Reference Guide when the system has been correctly installed and configured G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 5 190 00716 01 Revision 4 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 The pilot s PFD automatically goes into reversionary mode when communication to the MFD is lost M
239. es 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 GWX FAIL GWX is inoperative The G1000 has detected a failure in the GWX 68 or GWX 70 Check Ethernet connection between the GWX and GDL69A for faults Replace the GWX 68 or GWX 70 GWX SERVICE Needs service Return unit for repair The G1000 has detected a failure in GWX 68 or GWX 70 Replace the GWX 68 or GWX 70 MANIFEST GWX software mismatch Communication halted The system has detected an incorrect software version loaded in the GWX 68 or GWX 70 Load correct software version See Section 3 9 for the Software Load Procedure G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 75 Revision 4 5 18 GMC 710 Troubleshooting 5 18 1 GMC 710 Alerts and Problems Failure Message Solutions Load GMC configuration files Replace GMC 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 GMC 710 configuration other optional features i e mismatch TAWS unlock card wi
240. ese backup files PED internal against files contained with PFD memory PFD self configuration files configures to match master configuration module for backup d RS 232 RS 232 No 1 GDU 1040A PFD HIGH SPEED DATABUS Contains ACTIVE PFD settings Represents SET column for all Gees LRUs Stores all configuration files in GDU 1500 MFD internal memory Uses master Contains ACTIVE configuration module for backup MFD settings The MED uses PFD 4 internal configuration files for backup No 2 GDU 1040A PFD Contains ACTIVE PFD settings Represents SET column for all LRUs Stores all configuration files in internal memory Uses master configuration module for backup PE GMA 1347D GMA 1347D RS 232 Contains ACTIVE GMA settings Uses RS 232 No 1 GIA 63W Contains ACTIVE settings Uses PFD No 2 GIA 63W Contains ACTIVE settings Uses PFD Contains ACTIVE GMA settings Uses PFD internal int fi ti h int fi ti PFD internal configuration files for in lec ea oaa ion 2 in N DE ion configuration files for backup iles for backup iles for backup backup No 1 GEA 71 No 1 No 2 No 2 GEA 71 Contains GTX 33 3000 GTX 33 3000 Contains PEINT Contains ACTIVE Ge Contains
241. etention 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 Page 6 8 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Revision 4 6 13 GCU 477 Removal 1 Use a 3 32 hex drive tool to turn each of the four locking sockets Lo 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 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 1 4 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 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
242. ew Terrain Obstacle cards The system has detected a Jeppesen Aviation Database and configuration mismatch in the other optional features i e TAWS GEA1 CONFIG GEA2 specified GEA 71 unlock card will need to be configuration error Config service replaced if the master configuration req d 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 Page 5 64 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 13 5 13 1 GTX Alerts Failure Message MANIFEST GTX1 software mismatch Communication halted MANIFEST GTX2 software mismatch Communication halted GTX Troubleshooting The system has detected an incorrect software version loaded in the specified GTX 33 or GTX 3000 Solutions 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 Perform a SET gt ACTV configuration reset on the GTX Config page and verify the aircraft registration is present If error is still present reload config files from a loader card v If proble
243. ew electrical devices that have been installed since the aircraft was new Correct any discrepancies that do not allow this test to pass before continuing Ensure GRS 77 or GRS 7800 and GMU 44 connectors are secure Check the wiring and any inline connectors between the GRS and GMU for faults Recalibrate the GMU 44 Load configuration files to the PFD1 PFD2 GIA1 and GIA2 v If problem persists replace the GMU 44 v If problem persists replace the GRS 77 or GRS 7800 Page 5 22 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 Associated LRU s Solution Invalid Data Field E L e GRS 77 or GRS 7800 If this message persists longer than five minutes amp perform AHRS calibration procedures as described in GMU 44 Section 7 7 3 If software was loaded to a new GDU display be sure that the user settings for the replaced display Engine Airframe Sensors All were cleared Clear user settings by pressing the Invalid 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 My Correct any Alerts concerning software or fat configuration errors by reloading software or We configuration as noted Verify GEA internal power supply configuration and calibration status in configuration mode GEA 71 v The internal power s
244. f GWX 68 or 44 GWX 70 Equipment and Wiring located in i Nose Section Table 4 3 Phase 4 Complete Visual Inspection of 4 4 G1000 GFC700 Equipment and Wiring T ble 4 4 located in Nose Avionics Compartment able 4 4 Phase 4 Complete Visual Inspection of 4 4 G1000 GFC700 Equipment and Wiring Tabk 4 5 located in Pilot s Compartment SE Phase 3 G1000 GFC700 System Visual Inspections Complete Visual Inspection of 4 4 G1000 GFC700 Equipment and Wiring located on and behind Instrument Panel Table 4 6 Phase 3 Complete Visual Inspection of G1000 GFC700 Equipment and Wiring located in Cabin 4 4 Table 4 7 ee Complete Visual Inspection of 44 G1000 GFC700 Equipment and Wiring located in Rear Fuselage and Empennage Table 4 8 ere Page 4 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 GFC700 Periodic Check TAWS Functional Check GDU 1040A PFD Qty 2 GDU 1500 MFD GMA 1347D Qty 2 GIA 63W IAU Qty 2 GEA 71 EAU Qty 2 GTX 33 or GTX 3000 Transponder Qty 2 GDC 7400 Qty 2 RVSM checks GRS 77 or GRS7800 AHRS Qty 2 GMU 44 Magnetometer Qty 2 GDL 69A Description Procedure Verify proper operation of the GFC700 by performing the following Pre Flight Test AFCS Switch Checks Autopilot Operation Checks Autopilot Clutch Overpower Check Periodic TAWS function check Removal amp Re
245. 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 of this section If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 190 00716 01 700 System Maintenance Manual 300 B300 Series King Air Page 7 55 Revision 4 7 28 Activation 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 e 1 913 440 1135 worldwide Have the following information ready prior to calling e If activating services for a GDL 59 only installation o Aircraft tail number serial number manufacturer and model o GI1000 system ID number e If activating services for a GDL 59 and GSR 56 installation Aircraft tail number serial number manufacturer and model GSR 56 unit serial number G1000 system ID number Name of aircraft owner and contact information O O Oo O Credit card information Garmin Connext will provide additional information for activati
246. fferent replace the standby altimeter or contact the manufacturer for further troubleshooting See Section 6 26 for removal instructions G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 87 190 00716 01 Revision 4 5 24 Standby Altimeter Troubleshooting Symptom Recommended Action Perform the Standby Instrument Electrical Power Checks in Section 8 1 5 Altimeter lighting is inoperative or Remove standby altimeter per Section 6 27 and inspect the electrical malfunctioning connector Check that electrical power is being appropriately supplied to the instrument If the input electrical power is not adequate troubleshoot the wiring Altimeter Vibrator is inoperative or harness malfunctioning or fail flag is r displayed If the input electrical power is appropriate replace the standby altimeter or contact the manufacturer for further troubleshooting 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 for faults Replace the standby altimeter or contact the manufacturer for further troubleshooting See Section 6 27 for removal instructions Altitude displayed is incorrect 5 25 GDL 59 Troubleshooting Symptom Recommended Action heck iri i f GDL it E with EDL Se e Check power w
247. fication King Air 300 B300 005 00629 59 Circuit Breaker Panel Modification King Air 300 B300 005 00629 61 101 590097 9 Lighting Modification King Air 300 B300 005 W0226 00 Wiring Diagram G1000 GFC 700 King Air 300 B300 Hawker Beechcraft Document Super King Air 300 and 300LW Maintenance Manual 101 590097 15 Super King Air 300 and 300LW Wiring Diagram Manual 101 590097 161 Super King Air 300 Airworthiness Limitations Manual 130 590031 7 Super King Air B300 and B300C Electrical Wiring Diagram Manual 130 590031 11 130 590031 197 Super King Air B300 and B300C Maintenance Manual Super King Air B300 and B300C Avionics Wiring Diagram Manual Proline 21 130 590031 211 Super King Air B300 and B300C Airworthiness Limitations Manual 101 590097 13 King Air Series Component Maintenance Manual 98 39006 King Air Structural Inspection and Repair Manual Other Documents 85 292 1 1033 Signal Conditioner Installation Manual Meggitt Sensing Systems 9016182 Mid Continent Instruments Installation Manual and Operating Instructions 4200 Series Attitude Indicator TP 336 L 3 Avionics Systems Emergency Power Supply Installation Manual PS 835 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 1 5 Revision 4 The following publications are recommended to be on hand during the performance of maintenance activities
248. firm if the problem is in the original GIA2 o Replace original GIA2 if box turns green after swapping units Check the GIA1 GMA 1347D 2 interconnect wiring for faults GIA1 GMA 1347D 2 data path functionality is unknown Reload GIA2 configuration files G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 15 190 00716 01 Revision 4 GIA2 ARINC 429 Channel GDC 7400 2 GRS 77 or GRS 7800 2 Indicator Status GIA2 GDC 7400 2 data path is functioning correctly GIA2 GDC 7400 2 data path is not functioning correctly e Load GIA2 and GDC 7400 2 configuration files e Swap GIA2 and GIA1 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 e Check the GIA2 GDC 7400 2 interconnect wiring for faults Replace GDC 7400 2 if problem remains GIA2 GDC 7400 2 data path functionality is unknown Reload GIA2 configuration files GIA2 GRS 77 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 GIA1 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 e Swap GRS2 and GRS1 no reconfiguration required to confirm if the problem is in the
249. g Connectors 0 cccecesccesseseeesceseeseeseeeeceaecaeeecesecaaeeaeeeecaeeaeeeeeaeeaeees 5 84 Figure 5 23 GTS Processor Connector P8001 eeceseesssseceseeseeseeeecaesaeeeeceaecaeseneesecaaeeneesecaeeaeeeeeeaeees 5 84 Figure 5 24 GPA 65 Mating Connector Peoal 5 84 Figure 5 25 Signal Conditioner Mating Connector DNIBI 5 85 Figure 5 26 GDL 59 Backplate Connector Da091 5 85 Figure 5 27 GSR 56 Backplate Connector P561 ccccccsccessceseceseceeceeeceeeeeeseeeseeeseecaeecsaecsseceseeneeeeeeeses 5 85 Figure 5 28 GSD 41 Backplate Connector PAI 5 85 Figure 5 29 GSA 9000 Mating Connector POoOO01 ceccescceseceseceeeceeeceeeeeeseeesecsaecaeceseeeaeeneeseeeeseeeass 5 85 Figure 5 30 GRA 5500 Connector Daa00 1 5 86 Figure6 1 GSA 80 S ervo Geal Seier che aetes E ETE EE EEEE AEE ETE EE EET ave sisives 6 8 Figure 6 2 GSM 9100 O TI yenienn eE a EE E A EE E EE EEE AEN 6 8 Figure 6 3 Configuration Module Installation ssseseseeeseseesssseseesessesestsessesesresesseseesesssseseesessesesnesesss 6 10 Figure 6 4 GRS 7800 Configuration Module Installation cccceeccesseeeseeeseeeseeeeeeeeeseceseeeeeeeeeeseneeses 6 11 Figure 6 5 GEA Backshell Thermocouple ecescceseeseseeceseeseeeceaeeaeeeceaecaesenesecaaeeaeesecaeeaeeesenaeeaeees 6 13 Figure 6 5 GIA Cooling Fan Installaton eccescceeeseeeeceseeseeseceaecaesseceaecaeeeceeaecaaeeaeeceesecaeeaeenaeeaeees 6 19 Figure 6 6 GIA Cooling Fan Inlet Duct Identification 00 00
250. gen Eet EE Em er Ee E egen eee eme Fee LU 1 ES em pen pen VEER Pe femme A eet beet Segen E vg eegen Den ee geet e Mee Se KEEN Fan SEH ECH een bom FE Een EC oi FE Een Reien Gen EE Deem Ee be Ep E EC ege PER Kee ey Fee Den ee Een Fe ER EH Se OE E Eer Ren be WEE Ern pen men EECHER E EEN FER DEER EE IS EE EE FE IN Ge Emtee Een SE epes mea pen Dsg Deeg ENN EEN KEES DEE DES ED a GE eme ES EN GEN EE A EEN EE ALE EH eh EEA aen Een CHE ECH FER bag Femmes pe GER WE EE EE EEN We egent eee Fee Ee zem Reese pes gegen E IECH beem Fee Ka DR WENN ER ER FEH EEN EN eg ee SY BS Ee Kr egen em RON DEEN EE bere Dee om Eege Erem een Fe EE Pen Weg DEE FE PEN er D r pen pe CHEN Em Ee IEN WE DE beem Em men Ke ER IER Wena Deeg Ve EEN er ena pen CRA OS AONE ASRS WEE KC EE WEE WE SEA SEH EE emt ER Wem DEN Ee ee ST en EEN EEN EH BES IT One CREE ey Ce OE WEE mp Toe WEE Weem Ee ee E F n WEE Ee SE een DEE EE d DESEN rem een IER RE ene D mme ben Deem Feet ERR be ee EE EEN EH IER Een Een a PE Weg KEES Eet E ve Een am Een I EE EE FEH EEN EECH V Fa Eege Leen CE we Geng Pa EE er ep Cen Femme E eet ED beet Eege Een Een E EE IEN een Ee tte Freen mee FER CSR Een Wee een CH Beem EE Ee EEN DEEN REN EE PE ER S Eege Fee Een Ree DEE NEE og tee Een eet Wee ER Eet pen ER EE mm Deem Cen pen seen Deeg en Ween men Pe Pe Eee SE Em Eegen Ree eeng pen Wm FR REH Dee BEEN CN E een Ewen Pen FE EE E E E r Ken Be Een KE EES E RE Wee Een Fe Gen CT 3 baten Deen Een me DEE ge DEE
251. ghtning 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 GIA Fans Verify the GIA fan DISC out is correctly annunciating when the FAN is not working by performing tests per section 8 1 4 4 5 Electrical Bonding Test The following bonding tests are provided for G1000 equipped 300 B300 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 procedures in Sections 4 5 3 and 4 5 4 as required and in accordance with the Super King Air 300 or B300 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 valid calibration records 4 5 3 Phase 3 Electrical Bo
252. gine instruments 8 De activate pilot side reversion mode by pushing the DISPLAY BACKUP button Verify PFD 1 and MFD return to normal display modes 9 Repeat Step 1 using GMA2 Ensure that PFD 2 and MFD enter reversion mode and MFD displays valid altitude airspeed vertical speed COMM1 COMM2 NAV1 NAV2 and engine instruments 10 De activate co pilot s side reversion mode by pushing the DISPLAY BACKUP button Verify PFD 2 and MFD return to normal display modes 11 Select the TAWS page on the MFD 12 Verify that the title at the top of the page reads MAP 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 the TAWS test has completed verify that TAWS 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 300 B300 Series King Air Revision 4 190 00716 01 7 2 GMA 1347D Audio Panel Original GMA 1347D 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 c
253. h 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 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 5 Release the switch and wait for the PTRM annunciation to clear 6 Repeat Steps 2 through 5 for the right part of the pilot s pitch trim switch 7 Repeat Steps 2 through 6 for the copilot s pitch trim switch 8 Select copilot side by pressing the XFR key on the mode controller changes active GIA to GIA 2 9 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 pressing the AP DISC button 14 Hold the control yoke in the f
254. have notices posted 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 If GPS receivers can not aquire a position lock troubleshoot per the Will not acquire satellites section G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 61 Revision 4 5 11 5 GIA Cooling Alerts Failure Message GIA1 COOLING GIA1 temperature too low GIA1 operating temperature is too low Solution Allow unit to warm up GIA2 COOLING GIA2 temperature too low GIA2 operating temperature is too low Allow unit to warm up GIA1 COOLING GIA1 over temperature GIA1 has exceeded its operating temperature range Check fan wiring and air tubing for proper operation if applicable Replace cooling fan if unable to determine if operating correctly Replace GIA1 If 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 Replace cooling fan if unable to determine if operating correctly Replace GIA2 If problem persists contact Garmin Aviation Product Support for ass
255. he 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 300 B300 Series King Air Page 5 35 190 00716 01 Revision 4 PFT step 5 System initialization 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 of its PFT If this step fails try cycling power on GIA1 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 The PFT status is communicated between GIA1 and GIA2 using HSDB As 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 certif
256. he 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 ALRFRANE RFRAHE OH IHAIL VLIGLON CONFIGURATION ID CRO PART HUMBER RRTM TN CHECKLIST NAVIGATION INTERHAL REGION WAF FFECTIVE NIC SI ANDBY BOTTOM LARD REGION 2YCLE SFFPCTTUF XPIRES BaSBiP BOTTOM CARD oooooo08 ARFRM ANN TEST RA TEST Figure 5 1 AUX System Status Page The AUX System Status page displays the following information for each LRU and sub function e Status A green check is displayed for properly operating LRUs A 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 e 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 e 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 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 1 190 00716 01 Revision 4 5 1 G1000 Alerting System System Annunciators FAILED DATE EN Alerts failed E Window GMA2 FAIL GMAZ2 is inoperative
257. he 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 Rotate the NOSE UP DN wheel on the AFCS mode controller two clicks DOWN to decrease the 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 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 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 8 13 190 00716 01 Revision 4 8 2 6 VOR LOC GS Test Perform the following test using ramp test equipment Operate the equipment according to the test equipment manufacturer s ins
258. he 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 MFD 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 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
259. heck that the retaining bolt for the slip clutch cartridge is not damaged or loose Have 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 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 Check the tension on the control cables Refer to the Roll Servo Install drawing listed in Table 1 2 for cable tension specifications Ensure that each cable is correctly attached to the clamps Follow recommended checks for checking main control cables following the instructions in Chapter 27 Flight Controls of the Super King Air 300 or B300 Maintenance Manual 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 Inspect the GPA 65 PA LNA unit if installed 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 GPA 65 a GTS 820 850 traffic option only Page 4 14 G
260. hecks in Section 8 Original GMA 1347D Installed in Opposite Locations 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 GMA 1347D Installed If a new repaired or exchanged GMA 1347D 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 2 1 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 Intercom System ICS Check 1 Ensure that the MAN SQ key is off no light Adjust GMA1 and GMA2 ICS volume to a comfortable level 3 Plug ina 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 e CABIN ICS position cannot hear the pilot and copilot e CABIN ICS positions cannot be heard by the pilot or copilot 5 OnGMAI select COM1 MIC and AUDIO 6 Ensure INTR COM is deselected on GMA1 or GMA2 Verify an active green COM1 frequency is displayed on both PFDs 7 On GMA or 2 select PA and verify the PA select annunciator is illuminated on GMA
261. ht 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 sure 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 GIA1 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 t
262. ication gains loaded in them as the GIAs have If this step fails reload the certification gains in GIA1 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 in GIA1 GIA2 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 36 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 PFT step 12 Verify AP disconnect enabled This step is checking to make sure GIA1 GIA2 and all servos have are connected to a 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 a
263. icator apply a thin coat of Aeroshell 33MS Lithium complex based grease to the servo output gear see Figure 6 1 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 6 7 190 00716 01 Revision 4 Figure 6 1 GSA 80 Servo Gear Figure 6 2 GSM 9100 O ring For GSA 9000 yaw servo only install a new o ring p n AS568 043 on the GSM 9100 servo 2i gearbox see Figure 6 2 3 Carefully place the servo onto the servo gearbox ensuring proper orientation and alignment 4 Fasten the servo to the servo gearbox using the existing hardware Follow the installation instructions provided in the respective servo installation drawing s listed in Table 1 2 5 Inspect the harness connectors and check that no pins are bent or otherwise damaged Connect the harness and secure it appropriately 6 Ifno further maintenance is required continue to Section 7 9 6 12 GSM 86 and GSM 9100 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 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 r
264. if necessary If issue continues replace PFD1 master configuration A configuration mismatch has module PFD 1 CONFIG PFD 1 occurred between the display and If problem persists replace the configuration error Config service the Master Configuration Module display req d 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 a new number when installing a new req d 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 48 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 The MFD or specified PFD has encountered an error in the Jeppesen aviation database Solution Reload aviation database into the display Contact Garmin Technical Support for assistance MFD1 DB ERR MED 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
265. ific 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 300 B300 Messages are grouped according to LRU Page 5 26 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 4 TAWS Troubleshooting Annunciation Solution If message occurred on the first power up after unlocking TAWS cycle power to initialize TAWS Ensure each GDU contains the correct database data card Ensure the G1000 is configured for TAWS A TAWS system failure has v If the system is not configured TAWS FAIL occurred for TAWS reconfigure per Section 3 9 6 Verify GIAs are online Ensure a database or GDU SW mismatch has not occurred v Hamematch has occurred load correct database software files or replace the terrain card TAWS system is currently N A Test will be conducted up to two being tested minutes Enable TAWS system alerting by pressing the INHIBIT softkey on the TAWS system alerting is disabled MAP TAWS page 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 Troubleshoot GIAs Verify GIAs are online A GPWS system failure
266. ifies return to service procedures to be performed upon completion of maintenance of the G1000 system G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 1 3 190 00716 01 Revision 4 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 MFD 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 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 1 4 Publications
267. ify vertical speed is out of the solid red 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 Crossing Climb 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 Crossing Descend voice TCAS II Resolution Advisory Descend at the rated depicted by the solid green bar on the vertical speed tape on the PFD Safe separation is achieved by descending through the threat s flight path Maintain Vertical Speed 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 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
268. ig module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number GCU CNFG GCU Config error Config service req d Check wiring for faults ref Failed Path troubleshooting section Replace the GCU 477 The system has detected an Load the correct software version incorrect software version See Section 3 9 for the Software loaded in GCU 477 Load Procedure The G1000 has detected a GCU FAIL GCU is inoperative failure in the GCU 477 MANIFEST GCU software mismatch Communication halted G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 77 190 00716 01 Revision 4 5 20 Software Configuration Troubleshooting Problem Solutions MED or PFD displays do not power up Ensure that the criteria listed in Section 5 20 1 are fulfilled for the applicable situation Ensure power is present at display backshell connector Troubleshoot per the Blank Display GDU section Software file load fails Ensure that criteria listed in Section 5 20 1 are fulfilled for the applicable situation FILE UPLOAD FAIL Ensure that LRU is reporting data on System Status page LRU is ONLINE Check data path wiring as needed Retry software 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 software version and Card Loader Refer
269. in reversion mode 3 OnPFD1 go to the GFC Page Group and select the GFC STATUS page using the FMS knobs GFC STATUS SELECT GIA UNIT SELECT SERVO AXIS GIA 1 PITCH SERV GIA STATUS AP DISCONNECT L p MONITOR BOARD STATUS SERVO PROGRAM 1 1 AP DISCONNECT SERVO PROGRAM 2 z PFT A SERVO PROGRAH 3 HIGH RES LOAD CELL CAL m HIGH RNG LOAD CELL CAL y CONTROL BOARD STATUS SERVO PROGRAM 1 AP DISCONNECT SERVO PROGRAM 2 PFT ORIVE SERVO _ SERVO DATA RPM D reg VOLTAGE CURRENT BIR CLUTCH TEST RESULTS NOSE UP NOSE DOWN rh _in lb CLUTCH ENGAGE STATUS TEST SVO TEST ALL 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 Use the FMS knob to select the desired servo Pitch Roll or Pitch Trim Yaw is not tested 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 TEST SVO softkey on 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 a servo occurs reset the AFCS SERVO circuit breaker and repeat the test 8 When test is completed verify the CLUTCH TEST PASS message is displayed on the MFD Repeat steps 3 through 7 for each servo axis Pitch Roll
270. in Section 8 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 39 190 00716 01 Revision 4 7 19 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 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 e Inset map e Weather Datalink Page e Airport Information Page e Intersection Information Page e NDB Information Page e VOR Information Page e User Waypoint Information Page e Trip Planning Page e Nearest Pages 1 Use the FMS knob on the 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 E
271. 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 69A 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 If no other service is to be performed continue to the return to service checks in Section 8 7 9 GSA 80 9000 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 appr
272. ing e Green PASS in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box Press ENT key on MFD to acknowledge upload complete De activate the cursor 1 With the TCAS I Enable card in the top slot of MFD in configuration mode select the SYSTEM 8 Power down the system and remove the TCAS I Enable card from MFD Page 3 60 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 44 Optional Garmin TCAS Il Enable From GTS 825 to GTS 8000 Follow this procedure to enable TCAS II 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 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 IJ configuration with Section 7 27 GTS Traffic System Functional Check 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 sel
273. ing Air Revision 4 190 00716 01 Hem Description Procedure Manual Section No Interval Engine Airframe Sensors ITT Thermocouple Cable Qty 2 Oil Pressure Sensor Qty 2 Oil Temperature Sensor Qty 2 Torque Transmitter Qty 2 Fuel Flow Transmitter Qty 2 Prop Tachometer Qty 2 Engine Speed Tachometer Qty 2 Signal Conditioners Qty 2 Annunciator Switch Prop Sync Other Equipment Standby Airspeed Indicator Removal amp Replacement Refer to Super King Air 300 or B300 Maintenance Manual listed in Table 1 2 Removal amp Replacement Removal amp Replacement On Condition On Condition On Condition Static pressure system test according to 14 CFR 91 411 and Part 43 Appendix E 24 Calendar Months Standby Altimeter Standby Attitude Indicator Standby Battery Standby Battery Charge Check Standby Instrument Electrical Power Checks Annunciator Switch Standby Battery Removal amp Replacement On Condition Test according to 14 CFR 91 411 and Part 43 Appendix E 24 Calendar Months Removal amp Replacement On Condition Removal amp Replacement Capacity test of standby battery On Condition 12 Calendar Months Verify the standby battery is being charged Verify STBY ATT amp STBY ALT vibrator operate and STBY ATT STBY ALT amp STBY A S illumination function on aircraft power and standby batter
274. ing dish 6 Remove three screws connecting the GMU to the GMU adapter plate assembly 7 Ifthe 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 Ifanew GMU is 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 Page 6 6 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 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 GM
275. ing 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 Calibration Section 7 7 4 New Repaired or Exchange GMU 44 is Installed If a new repaired or exchange GMU 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 300 B300 Series King Air Revision 4 190 00716 01 7 7 1 GRS GMU Recalibration Criteria GRS GMU Calibration Procedures The following calibration procedures are provided for the GRS and GMU 44 e Pitch Roll Offset Procedure Al PROVIDED IN SECTION 7 7 2 e Magnetometer Calibration Procedure B PROVIDED IN SECTION 7 7 4 e Engine Run Up Vibration Test Procedure D PROVIDED IN SECTION 7 7 5 e 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
276. ion 4 190 00716 01 3 34 Flight Data Recorder Option Configuration Follow this procedure to enable the optional GSD 41 Data Concentrator function which is required for interfacing to an existing flight data recorder Table 3 1 provides a list of the parameters output on the ARINC 717 bus of the GSD 41 NOTE Parameters specified in Table 3 1 are contingent upon the current aircraft wiring Additional parameters are available for configuration Table 3 1 Flight Data Recorder Parameters Parameter Name Radio Altitude Throttle Power Lever Position Roll Attitude Air Ground Sensor Ee ne Warning Oil Pressure Manual Radio Transmitter Keying Longitudinal Acceleration Selected Flight Path C ompater Panurge Critical Systems Lateral Acceleration Selected Decision Height Latitude and Longitude EFIS Display Format Drift Angle SE Engine Alerts Autopilot Pagaseient Selected Mach Barometric Pressure Setting Inner Turbine Temperature ITT Selected Vertical Speed Selected Altitude Vertical Speed Comm Active Frequency IMPORTANT A separate approval is required for the installation of a Flight Data Recorder system This configuration option only allows the G1000 to interface to a Flight Data Recorder system G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 51 190 00716 01 Revision 4 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD
277. ion Module Kit 011 00979 00 or 03 Description Qty Needed Garmin Part Number Configuration Module PCB Board Assembly w EEPROM amp Temp Sensor 012 00605 00 or 02 Spacer Config Module 213 00043 00 Cable 4 Conductor Harness 325 00122 00 Pins 22 AWG HD 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 configuration module 1 in position 3 Insert connector into configuration module 1 4 Assembly of the connector is the reverse of disassembly 5 Continue to Section 6 16 3 Page 6 10 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 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 SSE 4x 5 Figure 6 4 GRS 7800 Configuration Module Installation Table 6 2 GRS 7800 Configuration Module Parts Configuration Module Circular Connector 011 02582 00 Garmin Socket Contact M39029 56 348 Best Source Removal 1 Disconnect connector 1 from LRU 2 Remove 2 screws 3 washers ring terminal
278. ionics Compartment Fans Operational Check For aircraft equipped per MDL 005 00629 00 Rev 7 or latest FAA approved revision or modified per Garmin Service Bulletin 1375 Functional test of the GIA1 and GIA2 ported fans Verify airflow from all fan ports NOTE See Section 6 29 Figure 6 7 for identification of cooling fan installation applicable for this maintenance interval 820 hours max Instrument Panel Fans Operational Check Functional test of the PFD1 MFD and PFD2 cooling fans Verify airflow from each fan Denotes Airworthiness Limitation Maintenance Requirement See Section 4 1 820 hours max Page 4 6 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 G1000 Redundant Connection Check Description Procedure 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 Ethernet connections Verify ARINC connection between ADC1 and MFD and between GRS1 and MFD Verify DISPLAY BACKUP button function Manual Section No Interval 220 hours max Engine Data Check Verify engine data is available and accurate with GIA 1 or GIA 2 inoperative 820 hours max Trim Annunciator Check Verify trim annunciators function properly 220 hours max G1000 Miscompare Check Verify AHRS airspeed and altitude mis
279. ions Load PFD2 and GDC 7400 2 configuration files Swap PFD2 and PFD1 to confirm if the problem is in the original PFD2 o Replace original PFD2 if box turns green after swapping displays Check the PFD2 GDC 7400 2 interconnect wiring for faults Replace GDC 7400 2 if problem remains PFD2 GDC 7400 2 data path functionality is unknown Reload PFD2 configuration file GDC 7400 2 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 9 190 00716 01 Revision 4 MFD1 RS 232 Channel Indicator Status MFD1 GCU 477 data path is functioning correctly MFD1 GCU 477 data path 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 If power or ground is not present troubleshoot aircraft wiring for faults oer at If power and ground are present replace GCU 477 e Load MED and GCU 477 configuration files e Check the MFD1 GCU 477 interconnect wiring for faults e Replace GCU 477 Replace MFD if problem remains MFD1 GCU data path functionality is unknown Reload MFD1 configuration file Page 5 10 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 2 1 2 GIA RS 232 ARINC 429 CONFIG Page GIA1 RS 232 Channel GDC 7400 1 GRS 77 or GRS 7800 2 output only GTX 33ES or GT
280. ir 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 300 B300 Series King Air Revision 4 190 00716 01 4 2 2 Required Tools The following tools are needed to perform maintenance tasks on G1000 equipment 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 Amp 24 V DC Power Supply Calibrated torque wrench capable of measuring 0 70 in lbs 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 4 2 3 Special Tools
281. ire 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 1 AHRS2 GPS AHRS2 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 in a 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 Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 69 Revision 4
282. iring ane pin out 9 GDL 59 unit e Ensure GDL 59 configuration option has been loaded Verify that a wi fi network is configured and available Ensure the wi fi antenna is within range of a wi fi network tiaj Remove any obstacles between the aircraft wi fi antenna and the wi fi No or low quality wi fi signal q E 9 network hub that may be blocking the signal Check the wi fi antenna cable and connectors Verify antenna ground plane is adequate Connactstowi tibutcann tsend Activate Garmin Connext reference Section 7 28 Note that a replacement GDL 59 unit must be registered again even if the MFD already shows EES REGISTERED S i i Page 5 88 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 26 GSR 56 Troubleshooting Symptom Recommended Action NS e Check power wiring and pin out of GSR 56 unit No communication with GSR 56 e Ensure GSR 56 configuration option has been loaded Ensure the Iridium antenna has an unobstructed view of satellite constellation Check the Iridium antenna cable and connectors Verify antenna ground plane is adequate Check wiring from GSR 56 toGDL 59 or from GSR 56 to GIA 1 stand No audio output alone as applicable to the installation Verify subscription with Garmin Connext reference Section 7 28 No or low quality Iridium signal Verify signal quality is adequate Unable to make a phone call Verify communication between GSR
283. is 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 Protection Underspeed Protection USP is available when the optional ESP system is installed and the autopilot is on Itis 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 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 2 1 190 00716 01 Revision 4 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 2 1 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 PFD displays are located on either side of the MFD with the stand by instr
284. istance Page 5 62 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 11 6 GIA Configuration Alerts Failure Message MANIFEST GIA1 software mismatch Communication Halted The system has detected an incorrect software version loaded in GIA1 MANIFEST GIA2 software mismatch Communication Halted The system has detected an incorrect software version loaded in GIA2 Solution Load the correct software See Section 3 9 for the Software Loading procedure GIA1 CONFIG GIA1 audio config error Config service req d GIA2 CONFIG GIA2 audio config error Config service req d The GIA s audio configuration files are incorrect or missing Reload audio configuration files GIA1 CONFIG GIA1 configuration error Config service req d 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 If problem 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
285. it and connector for corrosion or other defects Check the 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 all 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 Inspect the GTP 59 units and connectors for corrosion or other defects Check the integrity of the SHIELD ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment 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 Table 4 6 Instrument Panel G1000 Equipment Visual Inspection Procedure Item Description 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 a Inspect the PFDs and MFD for any visual damage to the display screens or bezels including buttons and control knobs Remove the MFD and PFDs as de
286. it breaker panel On the MFD verify that NO DATA is displayed after several seconds 9 Close the TRFC circuit breaker on the copilot circuit breaker panel and verify that NO DATA is removed after several seconds Page 7 32 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 7 15 Lightning System Functional Check Reference Section 3 30 for configuring the optional Stormscope This procedure assumes familiarity with the set up and operation of the WX PA portable analyzer kit 1 Apply power to 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 modes e Access to both 3600 and 1200 weather view modes e All available ranges can be displayed e Access to the cell mode and strike mode e Strike counter is displayed in all weather modes and ranges 3 Key COMI and COM2 several times on different frequencies representing the lower mid and upper portion of the VHF COM frequency band Verify keying of COM1 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
287. itot static plumbing and ensure it is secure and in good condition and routed to provide positive moisture drainage 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 well as the integrity of the individual shields and their attachment Page 4 12 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 GMA 1347D Qty 2 Description Procedure Inspect the GMA 1347D 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 Initials GDU Fans Qty 3 Inspect PFD and MFD fans for accumulation of dirt and other damage Remove excess dirt as required GDL 69A Inspect the GDL 69A 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 GMC 710 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 attachments to the harness connector assembly as well as the integri
288. iver 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 on the upper avionics equipment shelf in the tail section The GSR 56 is powered from Right Gen Avionics Bus Figure 2 14 GSR 56 Satellite Receiver 2 1 16 GSD 41 Data Concentrator optional The GSD 41 interfaces to various airframe discrete outputs to support third party systems such as Flight Data Recorders The GSD 41 is located on the avionics shelf in the tail area The GSD 41 is powered from No 2 Triple Fed Bus Figure 2 15 GSD 41 Data Concentrator Page 2 10 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 2 1 17 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 amplifier 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 Right Gen Avionics Bu
289. k switch s and wiring Check GIA1 GMA 1347D 1 interconnect 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 v If problem follows the unit replace GIA1 v f problem persists replace defective GMA 1347D 1 COM2 PTT COM2 push to talk key is stuck The COM2 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 1347D 2 interconnect 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 v If problem follows the unit replace GIA2 v If problem persists replace defective GMA 1347D 2 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 57 Revision 4 Failure Message COM1 RMT XFR COM1 remote transfer key is stuck The COM1 external remote transfer switch is stuck in the enabled or pressed state 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 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
290. l 300 B300 Series King Air Revision 4 190 00716 01 e Flight director command bars remain in view with autopilot in HDG and ALT mode 17 Replace AHRS1 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 4 14 GIA Cooling 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 fans and hoses is accomplished in Section 4 4 This check requires the G1000 to be powered on 1 Gain access to the nose avionics compartment 2 Disconnect cooling fan hose from the pilot side GIA and verify airflow is present 3 Reconnect the cooling fan hose to the GIA and secure using MS3367 5 9 cable tie 4 Repeat Steps 2 through 3 for the copilot side GIA 5 The GIA Cooling Fans Operational Check is complete 4 15 GDU Cooling Fans Operational Check This procedure will verify that airflow is present from the PFD1 MFD and PFD2 cooling fans The 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 G1000 to be powered on 1 Remove PFD1 as described in Section 6 1 steps 1 and 2 Remo
291. l 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 are connected in their proper place Verify input voltage and if it continues return to Garmin for service G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 89 190 00716 01 Revision 4 1030 MHz Fault Internal Fault 1090 MHz Fault Internal Fault PA LNA Fault Antenna connections or internal fault Receiver Fault Antenna connections or internal fault Transmitter Fault Antenna connections or internal fault Baro Altimeter is not powered on or improper wiring Baro Altitude Fault Improper configuration settings Fan is not operating Poor ventilation at the mounting location Broken wire improper configuration Radar Altimeter is not powered on or improper wiring Improper configuration settings Temperature Fault TCAS Equipage Fault Radio Altitude Fault Red X on a data port on the configuration page Improper wiring wrong port or speed selected 5 28 GTS Traffic Processor Troubleshooting Recommended Action Unit does not power up H Data failed message TREC circuit breaker is closed desired display Traffic Display erroneously indicates TA at own ship position are functioning properly Configuration Data Faul
292. lear Resource Center portion of the web site 4 7 GSA 80 Greasing Procedure The GSA 80 servo greasing procedure is required only when the GSA 80 is removed and reinstalled pitch pitch trim and roll axes Refer to Section 6 11 for details G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 4 19 190 00716 01 Revision 4 4 8 Flaps in motion Discrete Input Check To perform this check all G1000 and GFC 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 checks GIA I 0 CONFIGURATION Eog GIA SS em a CONFIGURATION CHANNEL DATA TYPE INVERTED ACTV DEBNCE ms INACTV DEBNCE ms PIN DATA SET ACTIVE SET ACTIVE SET ACTIVE SET ACTIVE F AUDIO INHIBIT 1 FALSE 300 300 FALSE OFF FALSE AFCS GO AROUND FALSE PLT CTRL WHL FALSE AFCS DISCONNECT II FALSE NS LDG DN TRUE CPLT PIT TRM ARM FALSE PLT PIT TRM ARM FALSE OFF FALSE OFF FALSE GIA 1 FAN TRUE FLAPS 50 FALSE FLAPS 100 FALSE OFF FALSE FLAP EXTEND FALSE FLAP RETRACT FALSE FALSE Ka Di GG GI GA GG GO GIG GI GO GO Di GG GI GO GG GO GN GI GO GH Gi H A A amp A D F D F D F IO IO IO a A A A oO F 0 F 0 F D P o F O F A A O m IO IO IO IO CPLT PIT SETDACTVIACTVDSET Figure 4 1 GIA UO Page Invalid Valid Figure 4 2 Discrete Valid Invalid Indications 1 Verify the DATA indicat
293. led Data Path Failures A communications data path status is not being received by the G1000 Solutions Determine which data path has failed See Section 8 1 6 Check wiring continuity for the failed path Swap or replace the affected LRU Page 5 44 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 5 8 GDU 104X Troubleshooting 5 8 1 GDU 104X Common Problems Symptom 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 Cycle power Display is blank v If 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 Use a bright light to verify LCD is active v Adjust avionics dimmer control full clockwise v Manually turn up backlight on the PFD and load configuration files to the GDU Ensure slide lock is fully engaged with the locking tabs on the back of the unit v 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 Ensure GDU is receiving power If a circuit breaker is tripped determine source of short before resetting breaker Ensure circuit breakers have not failed and power wire co
294. ler 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 LOC1 and PED HSI to LOC2 by pressing CDI soft key until LOC1 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 PFD1 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 PFD1 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 the XFR button Repeat step 9 while coupled to PFD1 If no other service is to be performed continue to the return to service checks in Section 8 Page 7 8 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 a
295. lert Alt Alert aural Altitude Alerting Function Caution 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 B C Flight into terrain takeoff or high 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 Pull Up voice TAWS Caution alert GPWS mode 1 Excessive Descent Rate TAWS Warning alert GPWS mode 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
296. ll 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 GMC CNFG GMC Config error Config service req d Check wiring for faults ref Failed Path troubleshooting section 5 7 Replace the GMC 710 The system has detected an Load the correct software version incorrect software version See Section 3 9 for the Software loaded in the GMC 710 Load Procedure The G1000 has detected a GMC FAIL GMC is inoperative failure in the GMC 710 MANIFEST GMC software mismatch Communication halted Page 5 76 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 19 GCU 477 Troubleshooting 5 19 1 GCU 477 Alerts and Problems Failure Message Solutions Load GCU configuration files Replace GCU 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 GCU 477 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 conf
297. 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 300 B300 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 300 B300 Series King Air Revision 4 190 00716 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 obtain the current file follow the procedures outlined below NOTE In order
298. locking sockets 1 4 turn clockwise This may require applying a small amount of forward pressure to engage the 1 4 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 1 Inspect connector for damaged pins 2 Hold unit flush with the radar mount 3 Use a 3 16 hex drive tool to tighten each of the four mounting screws 4 Connect backshell 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 300 B300 Series King Air Page 6 9 190 00716 01 Revision 4 6 16 Configuration Modules 6 16 1 Configuration Module Removal amp Replacement Configuration modules reference Figure 6 3 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 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 3 Configuration Module Installation Table 6 1 Configurat
299. lowing items standby attitude indicator operation and internal lighting standby altimeter vibrator and internal lighting standby airspeed indicator lighting only pilot side glareshield lighting magnetic compass 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 2 2 G1000 Optional Interfaces Optional equipment interfaces include lightning detection traffic transponder radar altimeter ADF 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 300 B300 Series King Air Revision 4 190 00716 01 2 3 Electrical Power Distribution This airplane uses a multi bus system as detailed below and in Figure 2 22 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 23 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 p
300. ltitude GTS 8000 300 ft above PFD1 PFD2 displayed altitude Vertical Speed 0 fpm Velocity 600 kts Page 7 54 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 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 closes 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 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 PFD1 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
301. ly 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 Start the G1000 in Configuration mode 2 Use the FMS knob on PFD1 to go to the Diagnostics Terminal page in the System group This page allows the technician to view maintenance logs associated with the GFC 700 3 Choose GIA 1 or GIA 2 in the LRU window In the 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 Press the 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 softkey G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 33 190 00716 01 Revision 4 9 The GIA Maintenance Log can record
302. m 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 PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 26 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 13 GTX 33 33D Configuration Do not perform this step if the TCAS II System Option was loaded per Section 3 29 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 on PFD1 Verify King Air GTX 33ES is displayed in the Item window Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the following
303. m 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 Support at avionics Garmin com G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 43 190 00716 01 Revision 4 5 7 5 7 1 Overview Backup Communications Path Checks 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 and 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 and GMA 1347D each have two redundant serial communication paths for the same purpose See Figure 2 25for 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 Failure Message FAILED PATH A data path has fai
304. m 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 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 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 Replace GTX 33 or GTX 3000 XPDR1 FAIL XPDR 1 is inoperative XPDR2 FAIL XPDR 2 is inoperative 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 33 or GTX 3000 is not responding The specified GTX 3000 transponder is not able to transmit ADS B data Check wiring between GIA s and GTX Replace GTX 33 or GTX 3000 Check wiring between GIA s and GPS antenna Check wiring between GIA s and GTX G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 65 Revision 4 5 14 GDL 69A Troubleshooting 5 14 1 GDL 69A Common Problems Symptom Recom
305. m 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 Page 3 56 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 40 Optional SVS Pathways Enable Follow this procedure to enable the Synthetic Vision option A GDUIXXX SVS Enable Card as specified on General Arrangement Drawing 005 00629 02 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 NOTE The Garmin Synthetic Vision and Pathways feature requires 9 arc second high resolution terrain databases to function Each G1000 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 whi
306. mage 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 For model 300 only the ELT access hole cover on the right hand side must be in place he rom Gees SS 7 AFT CORNER MARKING TYPICAL USE CONTRASTING COLOR r 1 12 INCHES e STATIC PORTS 1 ELT ACCESS HOLE F 7 OXYGEN SERVICING DOOR RH SIDE ONLY S Vana RH SIDE ONLY 12 INCHES 10 INCHES 14 INCHES L l Figure 7 10 RVSM Critical Region G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 45 190 00716 01 Revision 4 Note that Model B300 B300C aircraft with installation of the Sierra Nevada Corporation SNC Aircraft Survivability System ASE include a large external doubler and cover plate which are within the RVSM critical region as shown in Figure 7 10 These items are installed by SNC drawing number 01211012 B300 Aft ASE Provisions Installation For thes
307. mended Action No XM audio is heard Ensure the following items are not preventing the audio panel from distributing XM audio reference applicable G1000 Pilot s Guide v 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 Verify the headphone if equipped volume is turned up Go to the AUX SYSTEM STATUS page on the MFD and ensure unit is online v lf ared X is present verify the unit is receiving power at the rack connector 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 Restart the PFD s and MFD in configuration mode and go to the GDL page v Verify unit is active v Verify the Signal number is 2 or 3 If it is 0 or 1 check the GDL 69 69A antenna and cabling for faults v Reseat the GDL 69 69A to verify the coax connector is fully seated 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 Radio ID The unit must be on for approximately one
308. ment 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 or parts are removed or replaced e Section 8 specifies system return to service procedures The beginning of Section 6 provides 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 Repa
309. milar to the following will be displayed on the MFD DO YOU WANT TO UPDATE THE ACTIVE NAVIGATION DATABASE SELECTING YES WILL OUERWRITE THE ACTIVE NAVIGATION DATABASE FROM TO REGION WORLDWIDE WORLDWIDE CYCLE 8984 8985 EFFECTIVE 9 APR 2009 7 MAY 2889 EXPIRES 7 MAY 2089 4 JUN 2889 6 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 7 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 MFD1 DATABASE SYNC STATUS NAV STANDBY NAVIGATION INTERNAL REGION CYCLE EFFECTIVE EXPIRES NAV STANDBY BOTTOM CARD REGION CYCLE EFFECTIVE EXPIRES Figure 3 26 Navigation Database Synchronization G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 67 190 00716 01 Revision 4 8 Ifan error occurs during synchronization one of the following messages will be displayed followed by the affected GDU Err No Space SD card does not con
310. mperature sensor to compensate for temperature probe errors resulting from the dissimilar metals at the pin contacts Figure 6 5 GEA Backshell Thermocouple Table 6 3 Thermocouple Kit 011 00981 00 Description Qty Needed Garmin Part Number 3 Thermocouple K type 925 L0000 00 Pins 22 AWG 336 00021 00 Screw 211 60234 08 Removal 1 Remove GEA 71 per Section 6 4 2 Remove GEA connector backplate 3 Remove connector assembly J711 from the backplate 4 Remove screws item 7 and cover item 6 from the backshell item 5 5 Unscrew thermocouple from boss on backshell Extract the thermocouple pins from the connector G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 6 13 190 00716 01 Revision 4 Replacement l 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 300 B300 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 5 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 indica
311. n 4 190 00716 01 3 17 GSR 56 Satellite Reciever Stand 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 stand alone configuration with Section 7 30 GSR 56 Satellite Receiver 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 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 PFD1 3 Rotate the small FMS knob to highlight King Air GSR 56 Stand Alone Press ENT key on PFD1 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 PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 31 190 00716 01 Revision 4 3 18 GRS 77 AHRS Software Configuration Foll
312. n 8 Page 7 38 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 7 18 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 36 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 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 e CHRT OPT e APR e CHRT e WX e INFO 1 e NOTAM e DP e GO BACK e STAR 7 Press CHRT OPT softkey and verify the following softkeys are displayed some softkeys may be grayed out e ALL e HEADER e PLAN e PROFILE e MINIMUMS e FIT WDTH e FULL SCN e BACK If no other service is to be performed continue to the return to service checks
313. n 8 6 31 GTS 820 850 Traffic Unit CAUTION 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 Page 6 20 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 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 11 and test per Section 7 27 6 32 GPA 65 PA LNA Unit Removal 1 Remove cabin interior to access FS 158 at WL 119 on the left side of the fuselage Reference the Antenna Install drawing listed in Table 1 2 for more details Er ON e Ze 2 Disconnect the eight coax quick lock
314. n 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 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 7 7 1 New Repaired or Exchange GRS is Installed If a 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 7 7 1 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 load
315. n 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 Page 8 12 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 8 2 5 Autopilot Operation Checks 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 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 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 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 While holding the control wheel firmly press and hold the CWS button to re synchronize t
316. n whole or in part of this manual 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 California 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 300 B300 Series King Air Revision 4 190 00716 01 TABLE OF CONTENTS SECTION PAGE RER WARTZ OTI DL e H L EE 1 1 EE CONTENT SCOE PURPOSE Eeer Eege Eege be aa aes 1 1 122 OR LEE EE 1 3 13 DEEINITIONSIABBRENIATIONS re AEE A REA E 1 4 L PURECATON oo aua AA E E ENT A GA AE 1 5 L REVISION AND DISTRIBUTION i scsci2scdecis deene NEE dee 1 6
317. nage Visual Inspection Drocedure 4 15 Table 4 9 Lightning Strike Inspection Procedure 0 cccscecsseessecsteceteceseceeeeseeeseeeseecseecsaecsecnseeeseesaeeees 4 16 Table 4 10 Measured Torgus orein resning e Ao a T aE ERAEN aA A E iin 4 22 Table 4 11 Engine Data Check Test Eoupment ccccccccsccssecessceseceseceeeeeeseeeseeeseecseecsaecaeceseenseenaeenes 4 26 Table 4 12 ITT Indication Test Pomts 4 26 Table 4 13 Torque Indication Test Pomts 4 27 Table 4 14 Standby Battery Required Equipment ccccccccescessceseceeeceeeeeeseeeseeeseeeseecsaeesecsseenseesaeenes 4 32 Table 5 1 SVS Troubleshooting cccecccccssessseeseeeceeeeesseceseceseceseceseeseeseeeseseceaeeeaeecseecsaecseceseeeseenseenas 5 28 Table 5 2 SVS Related Alert Messages 5 28 Table 5 3 AFCS Annunciation Troubleshooting ccccccescesscensceeeceeeceeeeeeceeeseecseecseecsaecsaeceseeneenaeenes 5 30 Table 5 4 AFCS General Troubleshooting ccccccccscesseceseceseceseceseceeeceeceeeseeeseeeseecseecsaeesaecesecneeeeaeenas 5 31 Table 5 5 Magnetometer Interference Test Sequence ccccccscesseceteceseceecesecseeeeeeeeeeeeeseeessenaeenseenaeenes 5 72 Table 6 1 Configuration Module Kit 011 00979 00 or 09 6 10 Table 6 2 GRS 7800 Configuration Module Parts 6 11 Table 6 3 Thermocouple Kit 011 00981 00 ooo ccc ccccsseceteceseceneceseceeeceeeeeeeeceseeeseecseecsaecsaeceseenaeenseenes 6 13 Table 7 1 Fuel Flow Indication Test Equipment
318. nance 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 e Altitude FL290 to FL350 e Altimeter setting 29 92 in Hg 1013 HPA e Autopilot altitude hold engaged e Non turbulent non gust conditions 2 Record the data from the primary cockpit displays as specified by Table 7 8 every 5 minutes for 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 4 Aircraft s n Pilot Copilot 65 feet of the selected cruise altitude Altitude ft Airspeed kt Altitude ft Airspeed kt Table 7 8 In Flight Altitude Hold Performance Test G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 7 49 Revision 4 7 26 ESP Functional Check NOTE This procedure is required only for aircraft with the optional Electronic Stability
319. nd 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 GIA1 GIA2 and all servos If PFT still fails at step 14 then you will need to go check the PFT status of the other GIA and see what step it is failing NOTE The PFT status is communicated between GIA 1 and GIA2 using HSDB As a result both the PFD and MFD 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 300 B300 Series King Air Page 5 37 190 00716 01 Revision 4 5 6 4 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 Monitor Processor The monitor processor contains the logs that are found in these processors 2 Pitch Servo 4 Roll Servo 6
320. nd select speaker to ON Verify that the DME audio can be heard over the cockpit speakers 11 On PFD1 and PFD2 set the DME mode to NAV2 and verify that the DME distance is dashed out 12 Tune NAV 2 to the test set frequency Set NAV 1 to a frequency other than the test set frequency 13 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 41 190 00716 01 Revision 4 7 21 ADF Functional Check This check verifies that the ADF G1000 interface operates correctly 1 Press the PFD softkey on PFD1 and PFD2 Toggle the BRG1 and BRG2 softkey until the ADF bearing is shown on PFD1 and PFD2 Verify that the ADF window is not invalid no red X 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 on GMA1 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 2
321. ndicating that the gyro motor is e If input electrical power is not adequate troubleshoot the wiring not receiving sufficient power to harness Operate If input power is appropriate the unit must be removed and serviced by a qualified service facility See Section 6 28 for removal instructions Contact the manufacturer to find a qualified service facility The unit must be removed and serviced by a qualified service facility See Section 6 28 for removal instructions Contact the manufacturer to find a qualified service facility Unit fails to perform to specifications 5 23 Standby Airspeed Indicator Troubleshooting Symptom Recommended Action Perform the Standby Instrument Electrical Power Checks in Section 8 1 5 Remove standby airspeed indicator per Section 6 26 and inspect the electrical connector Check that electrical power is being appropriately supplied to the Airspeed Indicator lighting is instrument inoperative or malfunctioning e If the input electrical power is not adequate troubleshoot the wiring harness If the input electrical power is appropriate replace the standby airspeed indicator or contact the manufacturer for further troubleshooting Using a pitot static ramp tester check airspeed displayed on standby altimeter against airspeed display from ADC2 e fthe airspeeds are the same inspect the pitot static ports and Airspeed displayed is incorrect associated equipment for faults If the airspeeds are di
322. nding 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 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 Page 4 16 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 Pilot Compartment e Top metal case of PFD 1 milli volts e Top metal case of PFD 2 milli volts e Top metal case of MFD milli volts e Top metal case of GMA 1347D 1 milli volts e Top metal case of GMA 1347D 2 milli volts e Top metal case of GCU 477 milli volts e Top metal case of GMC 710 milli volts e GEA 71 1 body milli volts e GEA 71 2 body milli volts e GDC 7400 1 body milli volts e GDC 7400 2 body milli volts e OAT Probe base
323. netic field file See Section 4 6 GEO LIMITS AHRS1 too far north south no magnetic compass GEO LIMITS AHRS2 too far north south no magnetic compass 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 300 B300 AFMS listed in Table 1 3 AHRS1 TAS AHRS1 not receiving airspeed AHRS2 TAS AHRS2 not receiving airspeed AHRS1 GPS AHRS1 not receiving backup GPS information The specified GRS 77 or GRS 7800 is not receiving airspeed from the GDC 7400 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 Check GRS GDC interconnect for faults Replace the GDC 7400 If problem persists replace the GRS 77 or GRs 7800 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 GPS status for GIA 1 and 2 on MFD AUX GPS STATUS page If one or both GPS receivers cannot acqu
324. nnections are Display flickers secure Swap PFD1 and PFD2 v H problem follows unit replace the display Please note the position it failed in PFD1 2 v H problem does not follow unit troubleshoot aircraft wiring for fault Display resets DO NOT insert a screwdriver of any length into the card slot DO NOT pry against the overlay DO NOT force the SD Card out Use a small screwdriver in the groove on the side of the exposed end of the card to help pull out the card Push the card in further to release the card locking mechanism SD card is stuck in GDU Check SD Card for having more than one label Two or more labels on the card will cause sticking v Remove all but one label 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 Go 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 v If problem is verified replace GDU A button knob joystick does not appear to function G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 45 190 00716 01 Revi
325. ntenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 42 Optional 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 00629 02 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 slot 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 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
326. nunciation given ADF DME windows flag invalid G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 8 3 Revision 4 8 1 3 Display Failure Test Sepe O OOO Desired Best MFD Failure Condition 1 Open MFD CB 2 Verify desired results 3 Close MFD CB PFD2 Display Failure Condition 1 Open PFD 2 CB 2 Verify desired results 3 Close PFD 2 CB PFD1 Display Failure Condition Open PFD 1 PRI and PFD1 SEC circuit breakers Verify desired results Close PFD 1 PRI and PFD1 SEC circuit breakers For an MFD failure condition the following shall occur MFD goes blank All PFD1 and PFD2 primary flight information is retained The COM 1 2 and NAV 1 2 tuning fields remain valid and can be tuned by rotating the tuning knobs on PFD1 and PFD2 XPDR 1 2 fields remain valid and XPDRs can adjusted via PFD softkeys For a PFD2 failure condition the following shall occur PFD2 goes blank PFD1 and MFD remain in normal display formats The following illuminate on PFD1 HDG NO COMP illuminates on PFD1 ROLL NO COMP illuminates on PFD1 PIT NO COMP illuminates on PFD1 IAS NO COMP illuminates on PFD1 ALT NO COMP illuminates on PFD1 GMA2 Fail GMA2 is inoperative XPDR2 Fail XPDR2 is Inoperative For a PFD1 failure condition the following shall occur PFD1 goes blank PFD2 and MFD remain in normal display formats The following illuminate on PFD2
327. ob select the AUX REPORT STATUS page 3 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 5 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 6 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 7 Ifthe selected network is a secure network enter the passcode in the ENTER PASSPHRASE field in the WPA SECURITY SETTINGS pop up window 8 Press the ENT key on the GCU to accept the passcode then press the ENT key on the GCU again 9 When the SAVE SETTINGS pop up window is displayed press the ENT key on the GCU keypad to select SAVE CONNECTION 10 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 11 With the CONNECT button highlighted press the ENT key on the GCU to connect to the network 12 Press the ENT key on the GCU if the verification window Are you sure you want to connect is displayed 13 Verify that the CONNECTION STATUS field on the AUX WI FI SETUP page on the MFD indicates CONNECTED If no other service is to be performed continue to the return to service checks in Section 8 Page 7 58 G1000 GFC 700 System Mainten
328. og and send to Garmin for diagnosis e f upload of FPGA image was recently attempted retry the upload Otherwise return unit to Garmin for service If upload of audio image or IGRF magnetic field image was recently attempted retry the upload Otherwise return unit to Garmin for service Download the assert log and send to Garmin for diagnosis Return unit to Garmin for service if fault persists Download the assert log and send to Garmin for diagnosis Return unit to Garmin for service if fault persists Page 5 90 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Whisper Shout Fault e Check cable loss configuration antenna installation and all cable connections and retry self test e Return unit to Garmin for service if fault persists Transmit Power Fault e Check aircraft power supply e Return unit to Garmin for service if fault persists 1030 MHz Fault e Cycle power and retry self test e Return unit to Garmin for service if fault persists 1090 MHz Fault e Cycle power and retry self test e Return unit to Garmin for service if fault persists Receiver Cal Fault e Check antenna installation and all cable connections and retry self test Ensure that self test occurs in area free of buildings and large objects that can reflect signals e Download the assert log and use Assert Log Diagnosis Tool or send to Garmin for diagnosis e Return unit to Garmin for service if fault pe
329. on of data services To obtain the G1000 system ID number and GSR 56 unit serial number accomplish the following 1 Turn the large FMS knob on the MFD to select the AUX page group 2 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 SYS SOFTWARE VERSION CONFIGURATION ID CRG PART NUMBER SYSTEM ID lt _SYSTEM ID Number Location CHECKLIST Page 7 56 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 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 1 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
330. opriate 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 300 B300 Series King Air Revision 4 190 00716 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 loaded 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
331. ormal Mode Faults MONITOR FAULT 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 DIF Check the MET switch inputs into the system G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 39 190 00716 01 Revision 4 5 6 4 1 1 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 are not listed here indicate an internal problem requiring replacement of the se
332. ors 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 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 Page 4 20 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 4 9 GSM 86 Slip Clutch Torque Check Procedure Perform either the Automated Slip Clutch Test Procedure per Section 4 9 1 or the Manual Slip Clutch Test Procedure per Section 4 9 2 To perform the procedure all G1000 and GFC 700 equipment must be installed and operational 4 9 1 Automated Slip Clutch Test Procedure 1 Power on the sytem with PFD1 in Configuration Mode and with PFD2 and MFD in normal mode 2 Press the red DISPLAY BACKUP button on the pilot s GMA audio panel to place the MFD
333. orward 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 position press the HDG and ALT buttons on the mode controller and center
334. ot 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 PFD1 4 Verify the King Air Lightning 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 in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 46 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 31 Lightning System Option Configuration Load Confirmation Coordinate the StormScope configuration with Section 7 15 Functional Check 1 With PFD1 in configuration mode use the PFD1 large FMS knob to select OTHER and the Stormscope configuration page STORMSCOPE CONFIGURATION DATA STATUS HEADING FLAG DATA MODE HEADING STAB ANT MOUNT HEADING VALID HEADING FORMAT SYNC ANGLE HDG FLAG SENSE SYNC REF MODE STRIKE COUNT STATUS TRIGGER COUNT STORMSCOPE MODE y lt STRIKE RATE HEADING g HD
335. ow this procedure to configure the GRS 77 AHRS if installed Refer to section 3 19 if the GRS 7800 AHRS are installed Coordinate the GRS 77 configuration with Section 7 7 GRS 77 or GRS 7800 AHRS GMU 44 Magnetometer 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 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 PFD1 3 Rotate the small FMS knob to highlight King Air GRS 77 Press ENT key on PFD1 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 PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 32 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 19 GRS 7800 AHRS Software Configuration Follow this procedure to configure the GRS 7800 AHRS if installed Refer to section 3 18 if the GRS 77 AHRS are installed Coordinate the GRS 7800 configuration with Section 7 7 GRS 77 or GRS 7800 AHRS GMU 44 Magnetometer
336. ower from their respective left and right generators The left and right generator buses also support Center Buses and Left Gen and Right Gen Avionics Buses respectively Triple Fed Bus The Triple Fed bus is powered by left and right generator buses and the battery bus Avionics Buses The Left Gen Avionics bus is powered from the Left Generator Bus via the Avionics No 1 relay The Right Gen Avionics Bus is powered from the Right Generator Bus via the Avionics No 2 relay The Triple Fed Avionics Bus is powered from the Triple Fed bus via the Avionics No 3 relay All avionics relays are controlled using the Avionics Master Switch Left and Right Engine Instrument Buses On serial numbers FL 120 FL 122 through FL 380 FL 382 FM 009 through FM 11 the electrical system includes the L ENG INSTR and R ENG INSTR buses On all other serial numbers these two buses are not installed and engine instruments are powered directly from the Triple Fed Buses Emergency Standby Battery The Standby Emergency Battery STBY BATT system in the King Air 300 B300 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 standby airspeed indicator internal instrument lighting and internal instrument lighting for the magnetic compass from the L 3 PS 835 C or D Model Emergency Standby Battery This standby b
337. p 0 10 Vpp Procedure must be accomplished by an approved repair station 1 If DME is not displayed press the PFD softkeys on PFD1 and PFD2 then press the DME softkey Verify the DME window is displayed next to the PFD1 and PFD2 HSI 2 On PED and PFD2 press the BACK softkey then select DME softkeys Verify the DME TUNING screen is displayed 3 On PFD1 and PFD2 use the large FMS knob to select the NAV1 NAV2 and HOLD modes in the DME field Verify that the NAV1 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 5 On PFD1 and PFD2 select the DME NAV1 mode Verify that the DME window display is set to the NAVI frequency of 108 00 6 On PFD1 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 7 On PED 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 8 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 9 Verify that the DME distance on PFD1 and PFD2 match the test set 10 Select or verify selected DME and SPKR buttons on GMA1 and GMA2 audio panels to select the DME audio a
338. peakers 7 2 3 XM Audio Suppression Check This procedure 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 Super King Air 300 or B300 Maintenance Manual Chapter 7 00 00 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 e 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 e landing gear warning horn is not active e 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 GOONS On e Stall warning tone is active e XM audio is muted in the pilot and co pilot stations 9 Release the STALL WARN TEST switch and verify the following e Stall warning tone is not active
339. pears in the upper left corner of PED 5 Press and hold the far right softkey on the MFD or the ENT key on the GCU 477 MFD controller while applying power using the MFD circuit breaker 6 Release the softkey after INITIALIZING SYSTEM appears in the upper left corner of the MFD 7 Press and hold the ENT key on PFD1 pilot while applying power using the PFD1 PRI and PFD1 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 Configura
340. peat steps 5 and 6 SOOO ON rig oem 11 Cycle power to the MFD and splash screen will be present NOTE Any time software and or configuration is loaded to the system the splash screens may need to be reloaded to all three display units Page 3 66 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 49 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 MFD 2 Insert an SD card containing the latest cycle Jeppesen navigation database data supplied by Jeppesen into the top slot of the MFD 3 Apply power to the PFD1 PFD2 and MFD 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 DATABASE WILL BE ACTIVATED UPON THE FIRST ON GROUND POWER CYCLE ON OR AFTER 00 00 SYSTEM TIME ON THE EFFECTIVE DATE FROM TO REGION WORLDWIDE WORLDWIDE CYCLE 0964 8985 EFFECTIVE 9 APR 2009 7 MAY 2889 EXPIRES 7 MAY 2089 84 JUN 2889 Select the YES softkey to confirm the standby navigation database update 5 After the database is updated a prompt si
341. placement Manual Section No Interval Phase 2 and 4 Phase 4 On Condition Removal amp Replacement Removal amp Replacement GMA 1347D Test Landing Gear Aural Alert Check XM Audio Suppression Check Removal amp Replacement Removal amp Replacement On Condition On Condition Phase 2 and 4 Phase 2 and 4 Phase 2 and 4 On Condition On Condition Special Inspection Perform GTX 33 or GTX 3000 test Removal amp Replacement 24 Calendar Months On Condition Special Inspection Perform Air Data Test Special inspection for RVSM compliant aircraft only NOTE These checks required for initial RVSM compliance These checks also required when e a static port is removed installed e the RVSM critical region is repaired or painted Removal amp Replacement GWX 68 or GWX70 GMC 710 GCU 477 GTS 820 850 Traffic Unit GPA 65 PA LNA Unit Magnetic variation database update Removal amp Replacement 24 Calendar Months 24 Calendar Months On Condition see note On Condition G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 4 5 Revision 4 GTS Traffic Processor GRA 5500 GDL 59 Wi Fi Datalink GSR 56 Satellite Receiver GSD 41 Data Concentrator Description Procedure Removal amp Replacement Manual Section No Interval
342. play connect the connector to the rear of the unit 2 Carefully insert the display into the panel cutout ensuring that all 4 1 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 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 a 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 insert 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 300 B300 Series King Air Revision 4 190 00716 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
343. pon completion of post installation calibration procedures GRS 77 7800 AHRS GDC 7400 The GRS stores calibration data internally The GDC 7400 stores GDC configuration file internally The GRS 77 7800 also stores factory calibration data The GDC 7400 also stores factory calibration data internally internally Should internal memory fail Should internal memory or the configuration module fail AHRS loss of some or all air data outputs will result output data flags invalid GRS Internal Memory GDC Internal Memory Contains internal sensor calibration data Contains internal sensor calibration data that is not installation specific Data is that is not installation specific Data is stored from factory calibrations stored from factory calibrations Figure 3 15 GRS GDC Configuration Settings Storage Page 3 18 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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
344. r Page 7 59 190 00716 01 Revision 4 7 31 Search and Rescue Functional Check ie Ga hn D 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 From the Search and Rescue Menu turn the large and small FMS knobs to enter the starting waypoint Press ENT key to complete the selection and move to the next option PATTERN type Use the FMS knob to move to the PATTERN type and select PARALLEL With the FMS knob scroll through the options and change the fields as desired or leave the default entries 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 Page 7 60 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 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 S
345. rce G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 4 23 Revision 4 Place the G1000 in configuration mode 3 Inthe GIA page group go to the GIA RS 232 ARINC 429 CONFIG page With GIA1 selected in the SELECT UNIT window verify the RS232 Channel 1 GDC7400 1 and RS232 Channel 6 GRS77 1 or GRS7800 1 indicators are green Ref Section 5 2 1 2 5 With GIA1 selected in the SELECT UNIT window verify the ARINC 429 IN2 GRS77 2 or GRS7800 2 and ARINC 429 INS GDC7400 1 and ARINC 429 IN6 GRS77 1 or GRS7800 1 indicators are green Ref Section 5 2 1 2 6 With GIA2 selected in the SELECT UNIT window verify the RS232 Channel 1 GDC7400 2 and RS232 Channel 6 GRS77 2 or GRS7800 2 indicators are green Ref Section 5 2 1 2 7 With GIA2 selected in the SELECT UNIT window verify the ARINC 429 IN2 GRS77 1 or GRS7800 1 and ARINC 429 IN5 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 PFD1 selected in the SELECT UNIT window verify the ARINC 429 IN1 GRS77 1 or GRS7800 1 and ARINC 429 IN2 GDC7400 1 indicators are green Ref Section 5 2 1 1 10 With PFD2 selected in the SELECT UNIT window verify the ARINC 429 IN1 GRS77 2 or GRS7800 2 and ARINC 429 IN2 GDC7400 2 indicators are green Ref Section 5 2 1 1 11
346. rds from the lower slot of all displays before loading software into any unit Not removing the cards may corrupt them Replacing corrupted database cards are not covered under warranty 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 As a general rule all displays should be in the same mode configuration or normal unless instructed differently 7 1 GDU 1040A 1500 MFD amp PFD Original Display 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 PFD Displays Installed in Opposite Locations for Troubleshooting If the PFD 1 and PFD 2 are installed in opposite positions no software or configuration loading is required Contin
347. ressure Sensor e Oil Temperature Sensor e Fuel Flow Sensor via onside Signal Conditioner e Turbine Speed Sensor via onside Signal Conditioner e Propeller Speed Sensor via onside Signal Conditioner e Torque Sensor e Interstage Turbine Temperature ITT Sensor Figure 2 7 GEA unit Page 2 6 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 2 1 9 GDC 7400 Digital Air Data Computer 2 The Garmin GDC 7400 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 7400 communicates with the GIA 63W GDU 1040A and GRS 77 using ARINC 429 digital interface The unit is mounted behind the instrument panel GDC 1 receives primary electrical power from No 1 Triple Fed Bus and a secondary power supply from Center Bus GDC 2 receives power from No 3 Triple Fed Bus GDC 1 and GDC 2 connect to existing pitot static ports Refer to Figure 2 24 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 Figure 2 8 Air Data Computer 2 1 10 OAT Probe 2 The Garmin GTP
348. rformed 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 the MFD AUX System Status page The following table provides SVS Pathways specific alert messages which may appear in the Alerts Window on the PFD press the ALERTS softkey on the PFD to view the Alerts Window Table 5 2 SVS Related Alert Messages Failure Message SVS SVS DISABLED Out of available terrain region 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 28 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 5 6 GFC 700 AFCS Troubleshooting The GFC 700 is a digital Automatic Flight Control System AFCS which is integrated into various components of the G1000 This section touches upon key items to note while troubleshooting the GFC 700 Should a problem b
349. rm 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 8XX traffic systems the aircraft must be on 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 XXX must be in Ground Test mode For those tests with the GTS 8000 TCAS II configuration the Radar Altimeter circuit breaker if installed 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 Figure 7 15 GTS 8XX 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 Onthe MAP TRAFFIC MAP page of the MFD press the OPERATE softkey for GTS 8XX or pre
350. roblem is in the original GIA1 o Replace original GIA1 if box turns green after swapping units Swap GEA2 and GEA1 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 GIA1 GEA2 data path functionality is unknown Reload GIA1 configuration files GIA1 GFC 700 data path is functioning correctly GIA1 GFC 700 data path is not functioning correctly e Load GIA configuration files GIA Gains file and GSA software GFC 700 and gains file if LRU and Card versions are different Reference GFC section for further troubleshooting GIA1 GFC 700 data path functionality is unknown Reload GIA1 configuration files G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 17 190 00716 01 Revision 4 GIA2 RS 485 Channel Indicator Status GIA2 GEA data path is functioning correctly GIA2 GEA1 data path is not functioning correctly e Verify GEA1 is powered on using the GEA Status page e Load GIA2 and GEA configuration files e Swap GIA2 and GIA1 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 Swap GEA and GEA2 reconfigure both GEA s to their new locations to confirm if the problem is in the original
351. roblem persists replace GRS 77 or GRS 7800 HDG MISCOMP Difference in the heading sensors is greater than 6 degrees Perform Calibration Procedure E Magnetometer Interference Test reference Section 5 and Procedure B GRS 77 or GRS 7800 and GMU 44 Magnetometer Calibration reference Section 7 Page 5 70 Revision 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 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 GRS GHU CALIBRATION y CONNICATION STATUS 1 as E AIR MTA a rch TIrtEs recse stort ond stop times for eeercising d electronic CALIBRATION PROCEDURE Begin test sequence Select TEST COMPLETE when finished The colferotion siotus vil then be dispioved Se GOR Sa aa eee ee Figure 5 7 Magnetometer Interference Test 1 Initia
352. rounding 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 70 body milli volts Nose Avionics Compartment e GIA 1 top milli volts e GIA 2 top milli volts e GRS 77 7800 1 metal base milli volts e GRS 77 7800 2 metal base milli volts e Standby battery milli volts e GTS Traffic Unit milli volts Rear Fuselage and Empennage e GMU 44 1 metal base milli volts e GMU 44 2 metal base milli volts e GSA 80 Pitch Servo body milli volts e GSA 80 Pitch Trim Servo body milli volts e GSA 9000 Yaw Servo body milli volts e GTX 33 3000 1 top milli volts if installed e GTX 33 3000 2 top milli volts if installed e GSR 56 top milli volts if installed e GDL59 top milli
353. rsists Transmitter Cal Fault e 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 e Download the assert log and use Assert Log Diagnosis Tool or send to Garmin for diagnosis e Return unit to Garmin for service if fault persists Baro Altitude Fault e Check wiring to source of barometric altitude and ensure that source is operating Temperature Fault e Download the assert log and send to Garmin for diagnosis TCAS Equipage Fault e Check wiring to TCAS Equuipage data source and ensure that source is operating Radio Altitude Fault e Check wiring to source of radio altitude and ensure that source is operating Display Fault e Check the HSDB connection between the GTS Processor and the display e Verify the display is operational G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 91 190 00716 01 Revision 4 This page intentionally left blank Page 5 92 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 6 Equipment Removal amp Installation This section describes how to remove and replace equipment in the King Air 300 B300 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 air
354. rvo If the items in the Notes column check out ok replace the servo PFT Faults CONTROL PFT STEP i i This can sometimes be a result of a failure on the other board check AEON TES EAL faults on other processor CTL MOT PWR ON FAIL 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 40 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 CONTROL FAULT GIA DIS FAULT Normal Mode Faults NOTES 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 MET STUCK SWTCH Check the connector strap inputs
355. ry 1 000 cycles thereafter perform an exterior skin inspection around antennas per Section 4 18 Note 1 See Section 6 29 Figure 6 6 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 Airplane Flight Manual Supplements for the King Air 300 and B300 B300C define all operating limitations for this STC The 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 Gs Ad FAA APPROVED Robert Murray Date STC Unit Administrator ODA 240087 CE G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 4 1 190 00716 01 Revision 4 4 2 Servicing Information G1000 GFC 700 LRU maintenance is on condition only No component level overhaul is required for the G1000 GFC 700 installation 4 2 1 On Condition Servicing On Condition replacement and or servicing should occur when an item exhibits conditions symptoms and or abnormalities defined in Section of this manual Replace
356. ry box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 28 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 15 GDL 59 Wi Fi Data Link Option Configuration Follow this procedure to enable the optional GDL 59 Wi Fi data link function NOTE If the GDL 59 option is reloaded for any reason the GSR 56 option must also be reloaded per Section 3 16 Coordinate the GDL 59 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 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 PFD1 3 Rotate the small FMS knob to highlight King Air GDL 59 Press ENT key on PED 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 Configuration and Software columns for each item loaded e Upload Complete COMPLETE in the summary box Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page
357. s 2 7 G1000 GFC700 Block Diagram Diti dl High Speed Data Bus No 1 GIA 63W Integrated Avionics Unit No 2 GIA 63W Integrated Avionics Unit System Inegration Processors GDL 69A System Integration Processors VO Processors XM Satellite Datalink 1 0 Processors amp Radio VHF COM jute ee VHF COM VHF NAVILOC VHF NAVILOC GPS GPS Glideslope Glideslope WAAS e WAAS Wav bh GWX 68 70 AFCS Mode Logic Weather Radar GDL 59 AF CS Mode Logic 1 Flight Director Calculations Wi Fi Data Link 2 Flight Director Calculations Servo Communication ESP USP Servo Communication ESP USP Satellite GSD 41 GTS Data Traffic Concentrator System mmm mm GSR56 1 GEA71 GSA 80 GSA 80 SA 3000 Engine Airrame Pitch Servo Roll Serva EE Engine Airtame SC ESPAS GEN e mmer Unit Figure 2 25 G1000 GFC 700 Block Diagram G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 2 23 190 00716 01 Revision 4 This page intentionally left blank Page 2 24 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 G1000 Control amp Operation All control and operation of G1000 equipment as normally used in flight occurs through the PFDs MFD 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 Di
358. s ei Figure 2 16 GTS 820 850 Traffic System 2 1 18 GTS Traffic Processor The GTS Traffic Processor is a microprocessor based Line Replaceable Unit that uses active interrogations of Mode S 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 GA58 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 Right Gen Avionics Bus Figure 2 17 GTS Traffic Processor G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 2 11 190 00716 01 Revision 4 2 1 19 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 Left Gen Avionics Bus Data received from the GWX is routed through the GDL 69A data link unit to the MFD via high speed data bus Ethernet Figure 2 18 Weather Radar 2 1 20 GSA 80 Servos and GSM 86 Servo Gearboxes 3 The Garmin GFC 700 AFCS uses GSA 80 high torque servos to control aircraft pitch pitch trim and roll The pi
359. s 300 B300 Series King Air 0985 04 Initial approval Adds Vmca for BLR winglets 300 B300 Series King Air 0985 06 Updates GDU and GRS software Updates and adds various G1000 LRU hardware and software 300 B300 Series King Air 0985 07 This STC allows multiple configurations for the King Air series The correct configuration for a particular aircraft is loaded by choosing the applicable airframe engine propeller configuration G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 1 1 190 00716 01 Revision 4 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 MFD 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 04 Software Image P N 006 B0985 04 With the PFD in configuration mode see section 3 7 go to the GDU AIRFRAME CONFIGURATION page In the AIRFRAME section upper right corner verify the correct configuration for SERIES ENGINE and
360. s Apply external power to aircraft and start the G1000 in normal mode Using the Thermocouple Calibrator or equivalent inject the DC signals specified in Table 4 12 and verify the indications are within specified tolerances If the Thermocouple Calibrator is not temperature compensated use the chart shown in Figure 4 4 to convert the ambient temperature to millivolts and subtract from Table 4 12 Test Point degC DC signal mV Indication degC 200 8 137 200 17 400 16 395 400 17 600 24 902 600 12 800 33 277 800 7 1000 41 269 1000 12 1200 48 828 1200 17 Table 4 12 ITT 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 ITT indication remains unchanged Reset the the GIA1 PRI and GIA1 SEC circuit breakers 7 Repeat steps 1 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 Page 4 26 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 y 0 004x 0 7191 Be Fees Geen ra gn Es PE emer pre EE ey n ee DER EE ey ee eee es Ee WEE ee Cam We Ween Ee D bere page eme
361. s 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 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 2 Perform pitot static system leak check of each system as described in the Super King Air 300 or B300 Maintenance Manual 34 00 00 with the following changes a For the pitot leak check set the air data test unit to an indicated 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 For the 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 3 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 1 and AIR DATA 2 5 Simulate the altitudes and airspeeds for each condition shown in Table 7 5 Wait for ADTS to report that target values have been achieved 6 On Table 7 5 record the altitude B ALT displayed on PFD1 for AIR DATA and
362. s 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 2 Install 4 contact pins 5 on the new configuration module 4 wires 3 Install the 4 configuration module contact pins 5 into the connector 1 4 Assembly of the connector and strain relief is the reverse of the disassembly 5 Continue to Section 6 16 3 6 16 3 Configuration Module Checkout Ifa 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 Ifa GEA 71 Configuration Module is replaced Proceed to Section 7 4 1 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 6 11 190 00716 01 Revision 4 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 1 Start the G1000 system in configuration mode 2 Go to the Config
363. s 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 Troubleshooting 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 GEA 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 7 4 2 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 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 9 190 00716 01 Revision 4 7 4 2 GEA Engine Indication Checks Perform engine indicating s
364. sages 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 300 B300 Series King Air Page 5 5 190 00716 01 Revision 4 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 RS 232 Channel GMC 710 Indicator PFD1 GMC 710 data path is functioning correctly PFD1 GMC 710 data path is not functioning correctly e Verify GMC710 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 GMC 710 e Load PFD1 and GMC 710 configuration files e Swap PFD1land PFD2 to confirm if the problem is in the original PFD1 o Replace original PFD1 if box turns green after swapping displays e Check the PFD1 GMC 710 interconnect wiring for faults Replace
365. scribed in Section 6 GDU 1040A PFD 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 Do not reinstall GDUs at this time GDU cutouts provide access for visual inspections below Inspect all fwd bulkhead connectors for security of attachment Inspect all instrument panel 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 Inspect all other exposed G1000 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 G1000 Wiring harness Visually inspect each GDC 7400 unit mount and connector for corrosion or other defects Check the integrity of the SHIELD BLOCK ground attachments to the GDC 7400 Air Data harness connector assembly as well as the integrity of the individual shields and their Computer Qty 2 attachment Visually inspect the p
366. sion 4 Symptom Recommended Action Ensure supplemental data cards are inserted correctly in the lower slots of all three GDU s Terrain Obstacle Safetaxi does Allow the system to verify the data on the cards for approximately five not display minutes after power up If a database does not activate reload the problem database onto the SD Card or replace the card Reload GDU configuration files Display will not track dimmer bus If display is a PFD swap PED and PFD2 to see if problem remains with display v Replace display if condition remains with the same unit v H condition remains in original position after swapping displays Keyboard will not track dimmer check GDU dimmer input to verify voltage is present bus If display is the MFD check dimmer input to verify voltage is present v Replace MFD if dimmer voltage is present Page 5 46 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 9 GDU 104X Alerts 5 9 1 Failure Message SW MISMATCH GDU software version mismatch Xtalk is off Software Configuration Alerts The system has found the PFDs and or MFD software versions do not match MANIFEST PFD 1 software mismatch Communication Halted MANIFEST PFD 2 software mismatch Communication Halted The system has detected an incorrect software version loaded in the specified PFD MANIFEST MFD1 software mismatch Comm
367. splays Figure 3 1 and Figure 3 2 provide identification of the GDU 1040A PFD and GDU 1500 MFD controls COM frequency Nav frequency toggl toggle key oggle key GARMIN COM volume squelch knob Nav volume ident knob Nav frequency tuner knob COM frequency selector knob Baro selector knob Map panning range joystick Navigation systems controls Flight management system FMS knob Multi function softkeys numbered 1 12 left to right Figure 3 1 GDU 1040A Control Interface G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 1 190 00716 01 Revision 4 GARMIN Multi function softkeys numbered 1 12 left to right Figure 3 2 GDU 1500 Control Interface 3 1 1 Softkeys Some pages have commands or selections that are activated by the GDU 1040 softkeys Ifa softkey is associated with a command that command will be displayed directly above the key A grayed out softkey shows a command that is unavailable A softkey that is highlighted shows the current active selection ANLG IN CRNT MNTRENG TEMP BKSHELL ANNUNC DIGITAL DISCRETE COPY VERIFY r en Aa 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 Ro
368. sponder GTX33D and GTX 3000 interfaces to a transponder antenna mounted to the top of the fuselage GTX 33 GTX 3000 DEE Le Figure 2 5 Transponder Page 2 4 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 2 1 7 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 a HSDB Ethernet connection Both GIAs are located remotely in the nose equipment bay GIA receives primary electrical power from No Triple Fed Bus and a secondary electrical power supply from Center Bus GIA 2 receives electrical power from No 3 Triple Fed Bus The GIA 1 s COMM power supply COMM 1 is provided by No Triple Fed Bus GIA 2 s COMM power supply COMM 2 is provided by Left Gen Avionics Bus 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 e Existing VOR LOC Glideslope Antenna System e Existing VHF COM 1 amp 2 Antennas e GA 36and GA 37 GPS WAAS Antennas e GMA 1347D
369. ss 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 for GTS 8000 without indicating a fault proceed to the next step of antenna 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 53 190 00716 01 Revision 4 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 approxim
370. ssceecsesseeecsesseeecseseeeceesteeecsenteeeees 5 89 5 28 GTS TRAFFIC PROCESSOR TROUBLESHOOTING ss ssssssessseseesseretssrirtssrretssrretsstrerssrrerssereessres 5 90 6 EQUIPMENT REMOVAL amp INSTALLATION ccsssscccssssscccssscccsssssccccssssccscssscccscssssccsssssees 6 1 GL GDU 1040A AND GDU KO canieveessevecosddaite l est a die Ed let 6 2 6 2 2 GM Al134 7D AUDIO PANEL deet eigene Eeer EE 6 2 6 3 GIA 63W INTEGRATED AVIONICS UNITg i a i i 6 3 6 4 GEA 71 ENGINE AIRFRAME UNITA 6 3 6 5 GTX 33 OR GTX 3000 TRANSPONDER s ssssssssesessesesresets sterte stestssttstestessesesstsressessssstessesets 6 4 6 6 GDC 7400 AIR DATA COMPUTER 6 4 64 GTP S9 OAT PROBE EE 6 5 OS GRS2 7 OR GRS 800 AHR eege oud teksts EEN 6 5 6 9 GMU 44 MAGNETOMETER ssssssssseseessesetssttttsstttts stets s trots stret s st te PSSE EPES SEEPS SEEE ES SEEE ESSEE esseen sereen 6 6 6 10 ERIC 6 7 6 11 GSA 80 AND GSA 9000 SERVOS vurar a E ERE R A A RARE 6 7 6 12 GSM 86 AND GSM 9100 SERVO ODRARBON 6 8 6 13 EE Re 6 9 6 14 MCT EE 6 9 6 15 CE WEX68 OR GWE TO cee a vs EE EEN AE Ae Shah 6 9 6 16 CONFIGURATION MODULES SEA EE EA A AARAA 6 10 6 17 GEA 71 BACKSHELL THERMOCOUPLE REMOVAL amp RGPLACEMENT 6 13 6 18 GPS WAAS ANTENNAS oein aO a E R A SES ARAC 6 14 6 19 DIVERSITY TRANSPONDER ANTENNA 6 14 6 20 PIDU ANTENNA ee ee EE SE 6 15 6 21 WI FI ANTENNA A N A NAAA 6 15 6 22 SIGNAL C ONDITIONERS o r e E n EE EE A T ES 6 15 6 23 INSTRUMENT PANEL
371. 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 MFD1 DATABASE SYNC STATUS SAFETAXI OBSTACLE NAVIGATION INTERNAL REGION CYCLE EFFECTIVE EXPIRES NAY STANDBY BOTTOM CARD REGION CYCLE EFFECTIVE Figure 3 22 Supplemental Database Synchronization 7 Ifan 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 8 When the synchronization is complete the status is shown as Complete Cycle power to PFD1 PFD2 and MFD 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 PED and confir
372. t FPGA Fault ROM Fault Execution Fault Cycle power and retry self test Electrical Fault Check aircraft power supply Return to Garmin for service Return to Garmin for service Ensure all antenna connections are correct otherwise return to Garmin for service Ensure all antenna connections are correct otherwise return to Garmin for service Ensure all antenna connections are correct otherwise return to Garmin for service Verify that the baro altimeter has power and is properly wired Verify the configuration correct Verify the fan is running and the unit is getting adequate ventilation Verify configuration settings on the transponder and the GTS Ensure proper wiring between the transponder and the GTS Verify that the radar altimeter has power and is properly wired Verify the configuration is correct Ensure the port is properly wired to the GTS 820 850 and the correct settings are selected on the configuration page Ensure power is properly wired to the GTS Traffic Processor and the e Verify that the GTS Traffic Processor is configured correctly for the e Check the mutual suppression line to ensure it is connected to the correct pins at the GTS Processor as well as the installed transponder Ensure there are no fractures in the wire and that the suppression line is Calibration Data Fault e Return unit to Garmin for service e Both internal and external configuration checks failed e Download the assert l
373. t 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 shields and their attachment Inspect the GSD 41 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 shields and their attachment Using a flashlight inspect the servos servo gearboxes attaching hardware connectors support structure and control cables to ensure that no corrosion chaffing cracks or other defects exist For pitch and pitch trim GSM 86 servo gearboxes check that the retaining bolt for the slip clutch cartridge is not damaged or loose For the GSM 9100 yaw servo mount verify the two capstan retaining screws six drive shaft seal screws and hole plug are tightly secured If any of these items are missing or loose remove the GSM 9100 yaw servo gear box and send to a properly rated FAA Approved Repair Station qualified for servicing of this unit Visually inspect the hydrophobic vent and remove any obstructions if present Have an assistant manually move the control surfaces and elevator trim wheel from GFC 700 Equipment stop to stop and visually observe the corresponding servo and control cabling Ensure there is no binding in the control cabling and that the capstan rotates freely Ch
374. t the CABLE LOSS INCLUDING INLINE ATTENUATORS IS USED NOMINAL dB field 4 Use the small FMS knob to select a value of 6 20 then press the ENT key on PFD1 SET SELECT GDL ANTENNA Manual ANTENNA GAIN LOWER dB 25 00 CABLE LOSS INCLUDING INLINE ATTENUATORS IF USED NOMINAL dB 6 20 GDL CONFIGURABLE ATTENUATION dB 5 0 Figure 3 24 GDL 69 Cable Loss 5 Verify GDL 69 is configured then press the ENT key on PFD1 to acknowledge CONFIGURATION SET SELECT GDL ANTENNA Manual ANTENNA GAIN LOWER dB 25 00 CABLE LOSS INCLUDING INLINE ATTENUATORS IF USED NOMINAL dB 6 20 GDL CONFIGURABLE ATTENUATION dB 5 0 ETHERNET PORT 2 ETHERNET PORT 3 ETHERNET PORT 4 GDL 69 CONFIGURED DATA RADIO ID ACTIVE K SIGNAL Figure 3 25 GDL 69 Cable Loss Configured Page 3 64 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 47 BLR Winglet Option model 300 only Follow this procedure only if BLR Aerospace STC SA01615SE for 300 300LW series winglets is installed on the aircraft This option changes the airspeed indicator marking for air minimum control speed Vmca to 95 KIAS 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 Options
375. tain 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 MFD by resetting the PFD1 PRI PFD1 SEC PFD2 and MED circuit breakers 11 The standby navigation databases in PFD1 PFD2 and MFD 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 the MFD1 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 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 Page 3 68 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 50 Configuration of Navigation Map for Traffic System 1 With the MFD in normal mode use the GCU 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 fl
376. tallation 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 click 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 Page 3 44 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 29 Non Garmin TCAS Il Traffic System Option Configuration Follow this procedure to enable a non Garmin TCAS II traffic system function for the G1000 system if required Do not accomplish the GTX33 33D configuration procedure per Section 3 13 NOTE The G1000 can onl
377. 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 Set the WX 500 to STRIKE mode 100 NM range or next highest available range 11 Select the Continuous Out mode displayed on the WX PA menu and press MENU ENTER 12 Select the bottom mount antenna configuration on the WX PA keyboard CAT key 13 Select a cardinal bearing and a range of 120 NM 14 Use the F1 and F2 keys to adjust range and F3 and F4 keys to adjust heading NOTE The WX 500 will plot data at one half the range selected on the WX PA G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 33 190 00716 01 Revision 4 15 16 17 18 19 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 t
378. tate 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 selection 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 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 3 2 GCU 477 MFD Controller The MFD controls are located on the GCU 477 as show in Figure 3 4 Range pan Flight FMS Ctrl knob planning keys knob RANGE VIEN PUSH W PAN OFLT_ PUSH CRSR Comm Nav MAP Tranponder keys Alpha entry keys SOFTKEY SELECT d sp a Numeric Entry keys Figure 3 4 MFD Controls GCU 477 shown 3 3 GMC 710 AFCS Controls 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 modelkey Navigation mode key Altitude hold key s 5 S Flight level change Approach Flight director mode key Vertical sp
379. tatic System at 30 000 ft 300 kts pass if lt 300 ft in 1 min Pilot Feet Min Copilot Feet Min Leak Check Pitot System at 200 kts pass if lt 1 KIAS in 1 min Pilot KIAS Min Copilot KITAS Min Page 7 16 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 field on PFD1 and PFD2 are within the tolerances specified in Table 7 6 Table 7 6 Vertical Speed Table Vertical Speed feet minute Allowed tolerance feet minute 50 100 7 6 3 OAT Probe Check 1 Ensure on side sensors for PFD1 and PFD2 2 Ensure the outside air temperature OAT probes and a calibrated thermometer stabilize at ambient temperature 3 Verify that the OAT measurement shown on PED 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 300 B300 Series King Air Page 7 17 190 00716 01 Revision 4 7 7 GRS 77 or GRS 7800 AHRS GMU 44 Magnetometer Original GRS is Reinstalled If the original GRS is reinstalled the
380. tch 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 300 B300 Series King Air Page 3 23 190 00716 01 Revision 4 3 10 Non Garmin TAS TCAS Traffic System Option Configuration Follow this procedure to enable a non Garmin TAS TCAS I traffic system function for the G1000 system if required NOTE The G1000 can only be configured for TIS or TAS TCAS I but not both Performing this procedure will automatically disable the TIS function Coordinate this configuration with section 7 13 Non Garmin Traffic System TAS TCAS D Functional Check 1 With the loader card in the top slot of PFD1 and PFD1 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 Airframe Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight King Air Traffic System Option Press ENT key on PFD1 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 in the Configuration column for each item loaded e Upload
381. tch 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 near the wing front spar The pitch and pitch trim servos are located in the tail Power to the servos is received from No 2 Triple Fed Bus All servos mount to Garmin GSM 86 Servo Gearboxes The GSM 86 is responsible for transferring the output torque of the GSA 80 servo actuators to the mechanical flight control surface linkage Figure 2 19 GSA 80 GSM 86 Page 2 12 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 2 1 21 GSA 9000 Servo and GSM 9100 Servo Gearbox The Garmin GFC 700 AFCS uses a GSA 9000 servo to control aircraft yaw damper turn coordination and rudder boost The GSA 9000 contains a motor control and monitor circuit board as well as a solenoid and a brushless DC motor The GSA 9000 servo receives serial RS 485 data packets from the GIA 63Ws The GSA 9000 yaw servo is located in the tail Power to the servo is received from No 2 Triple Fed Bus The servo mounts to a Garmin GSM 9100 Servo Gearbox The GSM 9100 is responsible for transferring the output torque of the GSA 9000 servo actuator to the mechanical flight control surface linkage Figure 2 20 GSA 9000 GSM 9100
382. te the AHRS magnetometer interference test procedure by performing the following steps 2 On PED enter Configuration Mode and go to GRS GMU Calibration page as shown in Figure 5 7 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 71 190 00716 01 Revision 4 3 This page is protected and requires a keystroke password to perform this test Press the following softkeys in sequence as counted from left to right on lower bezel of MFD softkey 9 softkey 10 softkey 11 softkey 12 4 Select MAG INTERFERENCE TEST and press the PFD1 ENT key 5 Follow the checklist items displayed on the PFD1 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 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 Aion 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
383. ter several seconds 9 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 300 B300 Series King Air Page 7 31 190 00716 01 Revision 4 7 14 Non Garmin Traffic System TCAS Il Functional Check 1 Select the TRAFFIC MAP page on the MFD 2 Verify that the REL ABS TFC STBY TA ONLY TA RA TEST and ALT RNG softkeys are available on the bottom of the MFD NOTE If the correct softkeys are not displayed the G1000 has not been properly configured for the traffic system Reference section 3 29 TCAS II Traffic System Option Configuration to enable the traffic system 3 Verify that FAIL is not displayed in the upper left corner of the traffic map 4 Verify that NO DATA is not displayed in the center of the traffic map over the aircraft symbol 5 Press the TFC STBY softkey and verify that STANDBY is displayed in the upper left corner of the traffic map 6 Press the TA ONLY softkey and verify that TA ONLY is displayed in the upper left corner of the traffic map 7 Press the TEST softkey and verify that the traffic system enters a self test Upon successful completion of the test verify that TCAS SYSTEM TEST OK is heard over the cockpit speaker 8 Open the TRFC circuit breaker on the copilot circu
384. terclockwise 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 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 7 Connect the two coaxial cable connectors 6 Configure the GRA 5500 according to Section 3 26 and test per Section 7 22 Page 6 24 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 Ca
385. ternational Inc 1200 E 151 Street Olathe KS 66062 USA Telephone 913 397 8200 Wwww garmin com Garmin Europe Ltd Liberty House Bulls Copse Road Hounsdown Business Park Southampton SO40 9RB UK Phone 44 0 23 8052 4000 Fax 44 0 23 8052 4004 RECORD OF REVISIONS Revision Revision Date Description 5 11 12 Initial release 10 24 12 Add sw v0985 06 Add section 3 36 BLR winglet Update Section 4 1 and 4 11 6 4 13 Update for GMU 44 installation in horizontal stab 103013 2 21 14 Update for GRS 7800 GTX 3000 GTS Processor 111858 DOCUMENT PAGINATION Section Pagination Table of Contents i viii Section 1 1 1 1 6 Section 2 2 1 2 24 Section 3 3 1 3 70 Section 4 4 1 4 36 Section 5 5 1 5 92 Section 6 6 1 6 24 Section 7 7 1 7 60 Section 8 8 1 8 16 Page A G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 i
386. testing process Continue to GDC 7400 Test Section 7 6 1 Original GDC 7400 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 7400 Test Section 7 6 1 New Repaired or Exchange GDC 7400 is Installed If a new repaired or exchange GDC 7400 is installed the correct software and configuration files must be loaded to the unit See Section 3 9 and then continue to GDC 7400 Test Section 7 6 1 New GDC 7400 Configuration Module is Installed The correct configuration files must be loaded if the GDC 7400 configuration module has been replaced See Section 3 9 and then continue to GDC 7400 Test Section 7 6 1 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 13 190 00716 01 Revision 4 7 6 1 Air Data Test 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 7400 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 e Do not perform paragraph b 1 iv Friction e 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 test
387. the connectors to ensure there are no bent or damaged pins Repair any damage 2 Gently insert the GIA 63W into its rack The handle should engage the dogleg track 3 Press down on the GIA 63W handle to lock the unit into the rack 4 Lock the handle to the GIA 63W body using the Philips screw 5 Configure and test the GIA 63W s according to Section 7 3 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 damaged 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 300 B300 Series King Air Page 6 3 190 00716 01 Revision 4 6 5 GTX 33 or GTX 3000 Transponder GTX 33 Removal 1 Gain access to the avionics shelf in the tail area 2 Unlock the GTX 33 handle by loosening the Phillips screw on the handle 3 Pull the handle upward to unlock the GTX 33 Gently
388. 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 28 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 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 1 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 lt RUD annunciator is displayed on both PFD 1 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 1 and PFD 2 34 Disengage autopilot 35 The Trim Annunciator Check is complete G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 4 29 190 00716 01 Revision 4 4 13 G1000 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
389. the procedure e Attitude and Heading from AHRS e Airspeed Altitude Vertical Speed and OAT from Air Data Computer e GPS Course Deviation Indicator For a GIA1 GPS Failure an amber BOTH ON GPS2 is displayed on PFD 1 and PFD 2 For a GIA2 GPS Failure an amber IBOTH ON GPS1 is displayed on PFD 1 and PFD 2 For a dual GPS failure condition the following shall occur GPS CDI flags LOI on both PFDs Attitude and Heading remain valid from both AHRS on both PFDs Airspeed Altitude Vertical Soeed and OAT remain valid from both Air Data Computers on both PFDs LOI appears on MFD Map TAWS N A 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 10 seconds of stable GPS position reacauisition 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 Page 8 2 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 8 1 2 GIA Failure Test Step Desired Beeuht _ O O Z O Z O O O O O U U O GIA 1 Failure Condition For a GIA 1 failure condition the following shall 1 Ensure GPS satellites are acquired occur NAV 1 and COMM1 tuning fields on PFD1 and PFD2 are invalid red X L R engine data remains v
390. the procedure below using PFD to calibrate GRS 1 and PFD 2 to calibrate GRS 2 4 Restart the PFD 1 in configuration mode 5 Go to the GRS Page Group on the PFD Select the GRS GMU Calibration page and enter the following softkey password e 9 e 10 e l e 12 far right softkey 7 Use the FMS small knob to highlight GRS 1 for calibration and press ENT key The SELECT PROCEDURE field is not blinking 8 Using the FMS small knob select MAGNETOMETER Press the ENT button Use the cursor to highlight the BEFORE CALIBRATION window 10 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 11 The PFD display advises the operator when to turn the aircraft when to stop and when to turn again 12 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 Page 7 22 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 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 outsi
391. the summary box 6 Press ENT key on PFD to acknowledge upload complete De activate the cursor 8 Power down the system and remove the SAR Enable card from PFD G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 59 190 00716 01 Revision 4 3 43 Optional Garmin TCAS I 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 physical card may say unlock If uncertain the technician should verify the card part number prior to use Coordinate the GTS Processor TCAS I configuration with Section 7 27 GTS Traffic System Functional Check 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 I Enablement Press ENT key on MFD Press LOAD softkey 5 Monitor load progress Verify software load completes without errors as indicated by the follow
392. tion 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 300 B300 Series King Air Page 3 7 190 00716 01 Revision 4 Data can be manually copied from one column to the other and consequently from PFD memory to the LRU memory and vice versa by using the following two softkeys when available e SET gt ACTV 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 ACTV gt SET read Active to Set softkey Causes the LRUs current settings to be copied to the 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 Master Configuration Module LRUMemory Master Configuration Module LRUMemory OUTPUT ACTIVE
393. tion 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 be 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
394. tions 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 Reinstallation 1 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 Reinstall cabin interior ceiling panel 5 Proceed to Section 7 3 1 GPS Signal Acquisition for testing 6 19 Diversity Transponder Antenna Removal 1 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 1 Install antenna using retained hardware 2 Connect the antenna coaxial cable 3 Fillet seal around antenna Refer to the Antenna Install drawing listed in Table 1 2 4 Reinstall cabin interior ceiling panel 5 Test the GTX 33D or GTX 3000 according to Section 7 5 2 Page 6 14 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 6 20 Iridium Antenna Removal 1 Gain access to the antenna coaxial cable connector by removing the aft
395. to create a 300 B300 loader card the individual facility completing these procedures must be an authorized King Air 300 B300 service center to gain access to the necessary data via the Garmin website 1 Go to 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 e g username mail com Password By signing in you agree to the Garmin Confidentiality Agreement Sign In 2 Click the I Agree button on the confidentiality agreement page 3 Select Technical Tools then select Software Downloads 4 Inthe Keyword s filter enter 0985 and click on the Go button 5 A screen similar to the one shown below will appear The numbers shown are for example only Download symbol Name Type Doc Publish ID Date w G1000 King Air 200 300 Version Software Jun 17 2011 a Ee 0985 04 Summary Support Content Name Type Size kb G1000 King Air 200 300 Version 0985 04 006 B0985 04 EF B0920 pdf pdf 123 6 Click on the download symbol for the appropriate software version part number based upon the information provided in Garmin GA Drawing 005 00629 02 and save the file to the local hard drive G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 13 190 00716 01 Revision 4 7 Double click the exe file that was downloaded The following window will pop up on the screen Ensure
396. tor is fully seated and locked If the 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 v 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 Ensure the PFD connector is fully seated and locked If the 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 v Ifthe 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 MFD
397. tructions 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 the XFR button 2 Simulate a VOR signal on a radial equivalent to the aircraft heading Tune the NAV 1 and NAV 2 receivers to the simulation frequency 3 Set the HSI on PFD1 to VOR by pressing the CDI soft key until VOR1 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 VOR1 and VOR2 course pointers to aircraft heading CDI Synchronization must be set to OFF on the AUX SYSTEM SETUP page on the MFD 4 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 5 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 6 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 8 Simulate a Localizer Glideslope signal Tune this signal on NAV 1 and NAV 2 receiver Set the PFD1
398. ts and replace Note The GDC 7400 software for the 300 B300 contains error correction at 19 000 feet and above The standby altimeter does not contain any correction Failure Message Cause Solutions MANIFEST GDC1 software mismatch Communication halted MANIFEST GDC2 software mismatch Communication halted The system has detected an e Load correct software version incorrect software version loaded See Section 3 9 for the Software in the specified GDC 7400 Load Procedure Page 5 74 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 17 GWX 68 GWX 70 Troubleshooting 5 17 1 GWX 68 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 Failure Message GWX CONFIG GWX configuration error Configuration service required The G1000 has detected a GWX 68 or GWX 70 configuration mismatch Solutions Load GWX configuration files e Replace GWX e f 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 featur
399. ttery operation 2 1 25 Standby Airspeed Indicator A Standby Airspeed indicator Aerosonic part number 25030 0184 or Mid Continent Instruments part number MD25 300 is installed between PFD 1 and the MFD The standby airspeed indicator does not require electrical power for normal operation except for internal instrument lighting which is powered from No 3 Triple Fed Bus and the emergency standby battery This unit is connected to the right side pitot static system 2 1 26 Standby Altimeter A standby altimeter Aerosonic part number 16650 1172 or Thommen part number 3A43 22 35F 28 1 FU is installed between PFD 1 and the MFD This unit incorporates a vibrator to ensure accurate display altitude information The vibrator is powered by No 3 Triple Fed Bus and the emergency standby battery Internal lighting of this unit is powered from Left Gen Bus and the emergency standby battery This unit is connected to the right side static system 2 1 27 Standby Attitude Indicator The Mid Continent Model 4200 11 Electric Attitude Indicator is used as the standby attitude indicator It is powered by No 3 Triple Fed Bus and the emergency standby battery Gyro power and internal lighting of this unit is powered from Left Gen Bus and the emergency standby battery 2 1 28 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 fol
400. tude Display Page 7 50 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 12 13 14 15 16 17 18 19 20 21 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 Rotate the inner FMS knob to change the status to DISABLED Verify that on the MFD SETUP 2 page Stability amp Protection window that the status is DISABLED STABILITY amp PROTECTION STATUS Verify on PFD 1 and PFD 2 the ESP Roll Indices are not displayed at 45 on the roll indicator on the Attitude Display Verify on PFD 1 and PFD 2 that there is an ESP OFF alert message ESP OFF E e E E AA Remove the cover from both GPS1 and GPS2 antennas Remove power to the aircraft and avionics systems by placing the aircraft AVIONICS MASTER PWR and EXP PWR switches to OFF Wait 1 minute before re applying aircraft power Apply power to the aircraft and avionics systems by setting the BAT EXT PWR and AVIONICS MASTER PWR switches to ON During power up and GPS satellite acquisition verify on PFD1 and PFD2 the ESP Roll Indices are displayed at 45 on the roll indicator on the Attitude Display G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 51 190 00716 01 Revision 4 22 Once AFCS PFT is complete and GPS has acquired satellites
401. turn air data test set to GROUND 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 7 37 190 00716 01 Revision 4 7 17 FliteCharts Functional Check Reference Section 3 35 FliteCharts Configuration for configuring FliteCharts NOTE This test is not required if ChartView is enabled 1 With the G1000 in Normal Mode use the GCU FMS knob to select AUX System Status page then select MFD1 DB softkey Use the small FMS knob to scroll to CHART 3 Verify FliteCharts is displayed in blue text adjacent to CHART 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 e CHRT OPT e CHRT e INFO 1 e DP e STAR e APR e WX e NOTAM e GOBACK 7 Press the CHRT OPT softkey and verify the following softkeys are displayed some softkeys may be grayed out e ALL e HEADER e PLAN e PROFILE e MINIMUMS e FIT WDTH e FULL SCN e BACK If no other service is to be performed continue to the return to service checks in Sectio
402. tus is OK using the System Status page on the MFD If it is not correct condition before proceeding reference GDC troubleshooting sections Load PFD1 and GDC 7400 1 configuration files Swap PED and PFD2 to confirm if the problem is in the original PFD1 o Replace original PFD1 if box turns green after swapping displays Check the PFD1 GDC 7400 1 interconnect wiring for faults Replace GDC 7400 1 if problem remains PFD1 GDC 7400 1 data path functionality is unknown Reload PFD1 configuration file G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 7 190 00716 01 Revision 4 PFD 2 RS 232 Channel GMC 710 Indicator Status PFD2 GMC 710 data path is functioning correctly PFD2 GMC 710 data path is not functioning correctly e Verify GMC 710 is powered on o IfGMC 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 GMC 710 Load PFD2 and GMC 710 configuration files Swap PFD2 and PED 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 PFD2 GMC 710 data path functionality is unknown Reload PFD2 configuration file
403. ty of the individual shields and their attachment Signal Conditioners Qty 2 Inspect the signal conditioner unit mount and connectors for corrosion or other defects Standby Attitude Indicator Inspect the standby attitude indicator unit including face of unit and connector for corrosion or other defects Check the integrity of the harness connector assembly in 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 Standby Airspeed Indicator Inspect the standby airspeed indicator unit including face of unit and connector for corrosion or other defects Visually inspect the plumbing and harness connector assembly and ensure it is secure and in good condition Standby Altimeter Inspect the standby altimeter indicator unit including face of the unit and connector for corrosion or other defects Visually inspect the plumbing and harness connector assembly and ensure it is secure and in good condition Circuit Breaker Panels 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 Breaker Panel Modification drawing listed in Table 1 2 and the Cabin Wire Harness Routing drawing listed in Table 1 2 Pay particular attention
404. uality 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 PRODUCT LRU VERS CARD VERS CARD PART NUM SOFTHARE CONFIGURATION N A MANIFEST N A AIRFRAME N A AIRFRAME PROP N A AIRFRAME ENGINE N A N A N A N A N A 6 3
405. ue to the PFD MFD Test procedure New Repair or Exchange Display s Installed If a new repaired or exchange GDU 1040A or GDU 1500 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 36 and 3 37 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 300 B300 Series King Air Page 7 1 190 00716 01 Revision 4 7 1 1 PFD MFD Test 1 2 3 Allow displays to initialize for 1 minute Check that all COM NAV display fields are valid in the top corners of both PFDs Check that attitude heading altitude airspeed vertical speed and OAT fields are valid within 2 minutes of power up on both PFDs Press the SENSOR softkey on each PFD and switch between ADC1 and ADC2 Verify that data from both GDC 7400s is valid on both displays Press the SENSOR softkey on each PFD and switch between AHRS1 and AHRS2 Verify that data from both GRS 77s is valid on both displays Check that the engine instrument fields are valid on the MFD 7 Push the red DISPLAY BACKUP button on the pilot side GMA 1347D Verify that the pilot side PFD and MFD displays enter reversion mode MFD should have valid altitude airspeed vertical speed COMM1 COMM2 NAV1 NAV2 and en
406. ument 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 Standby Battery Switch Annunciator legends illuminate and reflect STANDBY BATTERY in white ARM in green and ON in amber e For the Prop Synch Switch Annunciator legends illuminates and reflect 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 Emergency Frequency Switch Annunciator Removal 1 Remove the switch plate from the pedestal using a screw driver to loosen the quarter turn fasteners 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 switch plate 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 switch plate Reinstallation 1 Reinstallation of the Emergency Frequency switch annunciator is the reverse of the removal Reference the Pedestal Re Configuration drawing listed in Table 1 2 for more details 2 Press and hold the cockpit annunciator Press To Test swit
407. uments located between the Pilot s PFD PFD 1 and the MFD GMA 1347D Audio Panels are located outboard of each PFD Additionally a GMC 710 AFCS Controller is located in the upper instrument panel above the MED and a GCU 477 is installed in the pedestal The GCU 477 provides the control interface for the MFD The GDU 1500 communicates with the GDU 1040A units GDL 69A datalink GWX68 or GWX70 weather radar optional GSD41 data concentrator optional GDL59 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 PFD 1 receives primary electrical power from No 1 Triple Fed Bus and secondary electrical power from Center Bus PFD 2 receives electrical power from No 3 Triple Fed Bus Electrical power to the MFD is provided by No 2 Triple Fed Bus The displays will power up immediately with external or aircraft power or battery operation All displays are installed in the King Air panel using 4 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 300 B300 Series King Air Revision 4 190 00716 01 2 1 3 GMA 1347D Audio Panel 2 The G
408. unication Halted The system has detected an incorrect software version loaded in MFD Solution e Load correct software version See Section 3 9 for GDU 1040 Software Loading procedure CNFG MODULE PFD 1 configuration module is inoperative The PFD master configuration module has failed Check master configuration module connector and wiring for damage inside the GDU connector backshell v Replace master configuration module wiring and pins If problem persists replace master configuration module 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 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 5 47 Revision 4 Failure Message Solution Reload the display configuration files from SD Loader Card Reload system configuration files MFD1 CONFIG MED by pressing the UPDT CFG configuration error Config service SE SCH S 9 Upload Page in the PFD1 System Page Group to load configuration files into the configuration module v If message persists check PFD1 config module wiring for faults and replace
409. unit for repair The system has detected a failure in G S1 receiver Solution Replace GIA1 G S2 SERVICE G S2 needs service Return unit for repair The system has detected a failure in G S2 receiver Replace GIA2 G S1 FAIL G S1 is inoperative The system has detected a failure in G S1 receiver Switch GIA1 and GIA2 to verify location of problem v v If problem follows the unit replace GIA 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 GIA1 and GIA2 to verify location of problem vi v If problem follows the unit replace GIA 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 a monitoring state in the cabin Failure Message MANIFEST GPS1 software mismatch Communication halted The system has detected an incorrect software version loaded in GIA1 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 GPS1 needs service Return unit for repair The system has detected a failure in
410. upply configuration and D calibration boxes should be green If they are GIA 63W 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 v If any voltages are dashed out replace the GEA Ensure the GEA is online green checkmark on the AUX SYSTEM STATUS page v If GEA is not online verify unit is receiving power at the rack connector v Check the GIA GEA interconnects for faults v Reload configuration files to both GIA s and the GEA If problem persists replace the GEA 71 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 5 23 190 00716 01 Revision 4 5 2 3 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 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 Super King Air 300 or B300 Maintenance Manual listed in Table 1 2 as needed Invalid Field Sensor Possible Solutions for applicable engine system Check thermocoupl
411. uration Upload Page on PFD 1 3 Press the 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 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 1 The entire G1000 system must be re configured Insert the correct G1000 software loader card into PFD 1 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 300 B300 Series King Air Revision 4 190 00716 01 6 17 GEA 71 Backshell Thermocouple Removal amp Replacement The GEA 71 has a K Type thermocouple Item 1 shown below installed in its backshell in addition to the configuration module The thermocouple is used in conjunction with the configuration module te
412. urned 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 f hardware to the airframe shelf or the aircraft will need to be re leveled Attitude appears unstable 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 68 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 15 2 GRS Alerts Failure Message MANIFEST GRS1 software mismatch Communication halted MANIFEST GRS2 software mismatch Communication halted 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 AHRS2 SERVICE AHRS2 magnetic field model needs update The AHRS magnetic field model should be updated for the specified unit Appears on ground only Load updated AHRS mag
413. val 2 Identify the PFD1 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 GDU Cooling Fans Operational Check is complete G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 4 31 190 00716 01 Revision 4 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 5 With the PS 835 battery installed in the aircraft and no aircraft power applied press TEST SWITCH Figure 4 5 Item 4 into TEST position for 5 seconds The PS 835 indicates that it is adequately charged when the VOLTAGE LEVEL 24Vdc LED Figure 4 5 Item 2 illuminates momentarily AND the 20Vdc LED Figure 4 5 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 14 Standby Battery Required Equipment DESCRIPTION VENDOR SPECIFICATION Power Supply 0 30 VDC 20A capacity DVM Fluke Model 8050A Load Resistor 7Q 1 250 watt Stopwatch C
414. vertical speed and climbing or descending through the threat s flight path Increase Descent Increase Descent 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 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 safe 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 II 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 sp
415. volts if installed e GSD 41 top milli volts if installed e GRA 5500 milli volts if installed Page 4 18 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 TIP If 1 amp reference current cannot be maintained note the difference between the attainable current and 1 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 4 6 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 Service Bulletin 0533 addresses the most recent update to the 2005 database Service Bulletins may be obtained from www garmin com at the De
416. wer 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 and PFD is in configuration mode On PFD1 select the System Upload page using the PFD1 small FMS knob 2 Activate the cursor and use the PFD1 small FMS knob to highlight the GROUP field Scroll small FMS knob to select the appropriate airframe King Air 300 Series PT6A 60A or King Air B300 Series PT6A 60A Press the PFD1 ENT key to select the configuration Figure 3 17 Airframe Options 3 Once an airframe type is selected the cursor moves to the ITEM window Rotate the 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 PFD1 ITEM Hartzell 300 8300 4 Bladel f Figure 3 18 Propeller Options 4 Once the propeller type is selected the cursor moves to the PRODUCT window Select the software and or configuration which is to be loaded for each G1000 LRU G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 21 190 00716 01 Revision 4 NOTE The PRODUCT window displays information regarding each G1000 LRU The LRU column depicts the reported software version of the LRU whereas the CARD VERS column shows the LRU software version stored on the Loader Card If an ineq
417. window will pop up onto the screen to indicate file progress Transferring Data Copying E aud rgn IN NN NN NN NN WEE Copy of files to selected drive G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 15 190 00716 01 Revision 4 10 Once successfully completed the following message window will pop up Click Finish to finalize SD card gt G1000 Software Update The update was successfully transferred to your card To complete the software update insert this card into your G1000 system 3 8 3 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 e 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 9 2 3 8 4 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
418. wn 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 ESP Support no AOA Press ENT key on PFD1 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 PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 49 190 00716 01 Revision 4 3 33 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 15 prior to loading the POTS handset configuration Power up the PFD1 in configuration mode On the PFD1 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 re NEE Ka Page 3 50 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revis
419. xt IAS MISCOMP is displayed on PFD 1 and PFD2 11 Use the pitot static test set to simulate an airspeed of 95 kts for ADC1 and 85 kts for ADC2 Verify the autopilot does not disconnect and amber comparator window text IAS MISCOMP is displayed on PFD 1 and PFD2 12 Reduce ADC1 and ADC2 airspeeds to 0 kts 13 Slowly rotate AHRS1 along the lateral pitch axis to a pitch attitude of greater than 5 degrees verify the following D AHRS2 pitch attitude does not change An amber PIT MISCOMP is annunciated on PFD1 and PFD2 Autopilot disconnects at approximately 5 deg AHRS1 AHRS2 miscompare e The autopilot disconnect audio alert two hi low tones sounds A red flashing AP annunciator on PFD1 and PFD2 Flight director command bars remain in view with autopilot in HDG and ALT mode 14 Replace AHRS1 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 AHRS1 along the longitudinal roll axis to a roll attitude of greater than 5 degrees verify the following e AHRS72 roll attitude does not change e An amber ROL MISCOMP is annunciated on PED and PFD2 e Autopilot disconnects at approximately 5 deg AHRS1 AHRS2 miscompare e The autopilot disconnect audio alert two hi low tones sounds e A red flashing AP annunciator on PED and PFD2 Page 4 30 G1000 GFC 700 System Maintenance Manua
420. y at the bottom of the screen Select OK in the Clear GIA nonvolatile memory pop up window Next reload 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 v If clearing nonvolatile memory is unsuccessful and the GPS still can not acquire a position replace the GIA v If problem does not follow unit check GPS antenna and cabling Page 5 56 G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Revision 4 190 00716 01 5 11 5 11 1 COM Alerts Failure Message COM1 SERVICE COM1 needs service Return unit for repair GIA Alert Messages The system has determined COM1 needs service Solutions e Replace GIA1 according to instructions in Section 6 COM2 SERVICE COM2 needs service Return unit for repair The system has determined COM2 needs service Replace GIA2 according to instructions in Section 6 COM1 PTT COM1 push to talk key is stuck The COM1 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 tal
421. y be configured for FliteCharts or ChartView but not both Performing this procedure will automatically disable the ChartView function Coordinate this configuration with Section 7 17 FliteCharts Functional Check Optional ChartView Enable Follow this procedure to activate the ChartView option A ChartView Enable Card as specified in 005 00629 02 General Arrangement Drawing King Air 300 B300 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 18 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 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 King Air Enable ChartView Press ENT key on PFD1 4 Verify King Air 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
422. y be configured for TIS or TCAS U but not both Performing this procedure will automatically disable the TIS function Coordinate this configuration with Section 7 14 Non Garmin Traffic System TCAS II Functional Check 1 With the loader card in the top slot of PED and PFD1 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 Airframe Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight King Air TCAS U System Option Press ENT key on PFD1 4 Verify the King Air TCAS II 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 in the Configuration column for each item loaded e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air Page 3 45 190 00716 01 Revision 4 3 30 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 once the following steps are complete 1 With the loader card in the top sl
423. y power standby compass checked during existing maintenance 220 hours max or 6 Calendar Months whichever occurs first 220 hours max Removal amp Replacement Denotes Airworthiness Limitation Maintenance Requirement See Section 4 1 On Condition G1000 GFC 700 System Maintenance Manual 300 B300 Series King Air 190 00716 01 Page 4 9 Revision 4 4 3 1 Discontinued Maintenance Table 4 2 shows a list of inspections and tests that are listed in the Super King Air 300 or B300 Maintenance Manual but may be no 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 ltem _ __ Description Procedure Manual interval AG Inverter Operational Check Phase Inspections Phases 1 2 3 amp 4 if removed IMPORTANT For installed equipment not listed in this maintenance manual use the inspection procedures set forth in Chapter 05 of the Super King Air 300 or B300 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 Super King Air 300 or B300 Maintenance Manual or other appropriate maintenance manual in cases where the requirements conflict P
424. ystem Ammunciattons 5 5 Figure 5 5 AFCS Ammunciation Field c cc ccccssecscsssceceessssessssscseseenteeatecsecesosnesdsecsenacnecenesasessesscenadenanss 5 29 Figure 5 6 GEC Status Page seenen eneen AER 5 32 Figure 5 7 Magnetometer Interference Test 5 71 Figure 5 8 GIA 63W Backplate Connectors 5 80 Figure 5 9 GEA 71 Backplate Connectors 0 cceccescceseeseesecceeseeseceaecaeeseceaecaeeeceaecaaeeaeeeeenaeeaeeeeeaeeaeees 5 81 Figure 5 10 GMA 1347D Backplate Connectors 5 81 Figure 5 11 GTX 33 33D Backplate Connectors 5 81 Figure 5 12 GTX 3000 Connector inienn e e i aiaa eaaa a aias ieai a aani 5 82 Figure 5 13 GDU 1040A 1500 Mating Connector P10401 or P15001 cece ecceecceesteenteeeteenteenseeees 5 82 Figure 5 14 GRS 77 Mating Connector Dm 5 82 Figure 5 15 GRS 7800 Mating Connector P78001 ceccescceseceseceseceeeeeseeeseeesaecsaecaecnseenseeseesereseeeeses 5 82 Figure 5 16 GDC 7400 Mating Connector P74001 eccecccesccessceseceeseeeeeeeseeeseeeseeeseecsaeeseenseseeeenneeses 5 83 Figure 5 17 GDL 69A Mating Connector Do AaI 5 83 Figure 5 18 GCU 477 Mating Connector P4751 cceccccccsscceseceseceeecseeceeeeeeseeeseeeseecaeeesaecaeceaeeneeeneeeags 5 83 Figure 5 19 GMC 710 Mating Connector P7101 cccccesccesecessceeeceeeceeeeeeeeeeseeeseeeseecsaecsaeceaeenseesnenags 5 83 Figure 5 20 GWX 68 Mating Connector Dol 5 83 Figure 5 21 GWX 70 Backshell Connector BI I 5 84 Figure 5 22 GTS 820 850 Matin
425. ystems checks for the following left and right engine indications Reference Hawker Beechcraft King Air 300 300LW or B300 B300C Maintenance Manual Chapter 77 00 00 Engine Indicating Maintenance Practices e ITT e N 1 e N2 e Torque 7 4 3 GEA 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 10Vdc 0 1k Hz The following steps are required to be completed on both engines as necessary l zk Si E RNS Remove the engine cowling Ref Hawker Beechcraft King Air 300 300LW or B300 B300C Maintenance Manual Chapter 71 10 00 to gain access to the engine MT5 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 BAT EXT PWR and AVIONICS MASTER PWR switches to ON Inject a 25 mV P P signal with the signal generator and simulate the frequencies specified in the

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