Garmin STC for Bell 206/407 Instruction Manual
Contents
1. the unit may be removed and replaced See the troubleshooting section contained in the G500H STC Installation Manual listed under reference documentation in paragraph 2 1 of this document 2 15 ICA Revision and Distribution To revise this ICA a letter must be submitted to the ACO along with the revised ICA The ACO will obtain AEG acceptance and approve any revision to the Airworthiness Limitations in Section 3 After FAA acceptance approval Garmin will release the revised ICA for customer use and provide any required notification of the revision The latest revision of this document will be available through any Garmin dealer or from Garmin customer assistance A Garmin Service Bulletin describing ICA revision will be sent to dealers if revision is determined to be significant 2 16 Assistance FAA Flight Standards Inspectors or the certificate holder s PMI have the required resources to respond to questions regarding this ICA In addition the customer may refer questions regarding this equipment and its installation to the manufacturer Garmin Garmin customer assistance may be contacted during normal business hours via telephone 913 397 8200 or email from the Garmin web site at www garmin com 2 17 Implementation and Record Keeping Modification of an rotorcraft by this Supplemental Type Certificate obligates the rotorcraft operator to include the maintenance information provided by this document in the operator s rotorcraft maint2. Applies to Bell models 407 rotorcraft altered by installation of the Garmin G500H PFD MFD System See Section 1 5 None None Garmin 190 01150 06 Rev 3 G500H Rotorcraft STC Installation Manual or later FAA Approved Revisions Garmin 190 01150 44 Rev 3 GENERAL ARRANGEMENT G500H SYSTEM BELL 407 ROTORCRAFT or later FAA Approved Revisions Garmin 190 01150 45 Rev 3 INSTALLATION G500H SYSTEM BELL 407 ROTORCRAFT or later FAA Approved Revisions Garmin 005 W0222 00 Rev 3 G500H MAIN WIRE HARNESS ASSEMBLY or later FAA Approved Revisions Garmin 005 W0222 01 Rev 1 G500H NAV 1 HARNESS ASSEMBLY or later FAA Approved Revisions Garmin 005 W0222 02 Rev 1 G500H GPS 2 HARNESS ASSEMBLY or later FAA Approved Revisions Garmin 005 W0222 03 Rev 1 G500H NAV 2 HARNESS ASSEMBLY or later FAA Approved Revisions Garmin 005 W0222 04 Rev 1 G500H WX DATALINK HARNESS ASSEMBLY or later FAA Approved Revisions Garmin 005 W0222 05 Rev 1 G500H IRIDIUM DATALINK HARNESS ASSEMBLY 190 01150 21 Rev 2 Page 4 of 19 Retention 2 2 Description of Alteration or later FAA Approved Revisions Garmin 005 W0222 06 Rev 1 G500H VIDEO HARNESS ASSEMBLY or later FAA Approved Revisions Garmin 005 W0222 07 Rev 2 G500H SERIAL ALTITUDE HARNESS ASSEMBLY or later FAA Approved Revisions Garmin 005 W0222 08 Rev 1 G500H TRAFFIC HARNESS ASSEMBLY or later FAA Approved Revisions T
3. SpeClal Ee ee dE EE EE e 18 2 13 Additional Insiruchons nnmn 19 2A4 Overhaul m1 BAAT EE ATE EATE I EAE 19 2 15 ICA Revision and Distribution ccccccceecceesseeecessneeeeeeesaeeeeecsaeeesseaeeeeeenaeeeeeseaas 19 PAn A TE i I ue 19 2 17 Implementation and Record Keeping sssssssssssssrssssrnsssirrssirnssinnsnnrnnnssrnnnnntnnns 19 3 AIRWORTHINESS LIMITATIONS B ed eoe Eee EREEREER TA 19 G500H Flight Display System 190 01150 21 Rev 2 Instructions for Continued Airworthiness Bell 407 Page 2 of 19 1 INTRODUCTION 1 1 Purpose This document is designed for use by the installing agency of the Garmin G500H PFD MFD System as Instructions for Continued Airworthiness in response to Title 14 CFR Part 27 1529 Part 27 Appendix A This ICA includes information required by the operator to adequately maintain the Garmin G500H system installed under STC SRO2295LA 1 2 Scope This document identifies the Instruction for Continued Airworthiness for the modification of the rotorcraft for installation of the Garmin G500H PFD MFD System installed under STC SRO2295LA 1 3 Document Control This document shall be released archived and controlled in accordance with the Garmin document control system When this document is revised refer to Section 2 15 for information on how to gain FAA acceptance or approval and how to notify customers of changes 1 4 Permission to Use Certain Documents Permission is granted to any corporation or person ap
4. wires backshells or connectors on units and their wire harnesses to ensure installation integrity 1 Gain access to LRU see General Arrangement Drawing for LRU locations 2 Inspect each unit for security of attachment 3 Inspect all knobs and buttons for legibility 4 Inspect condition of wiring routing and attachment clamping 5 Inspect integrity of shield terminations 6 Inspect for signs of corrosion on equipment and their rack installations G500H Flight Display System Instructions for Continued Airworthiness Bell 407 Page 8 of 19 190 01150 21 Rev 2 Item Interval Description Procedure Perform an electrical bonding test for each listed LRU 1 Gain access to the LRU see General Arrangement Drawing for LRU location 2 Disconnect all harness connectors from the LRU 3 Measure the resistance between the LRU and a nearby TARA exposed portion of aircraft metallic structure GDU 620 GRS 77H ten 10 a For the GDU 620 verify the resistance is less than GDC 74H GMU 44 GTP or equal to 40 milliohms 59 ee is b For the remaining LRUs verify the resistance is first less than or equal to 20 milliohms 4 Reconnect all disconnected harness connectors and ensure they are secure Repeat for each listed LRU 2 6 Troubleshooting Information If error indications are displayed on the GDU 620 display unit consult the Troubleshooting section contained below 2 6 1 G500H Troubleshooting
5. A A Z A ADF FLOATS CARGO D STOP GENERATOR SYSTEM OAT V AMPS RESET FIELD ENGINE CONTROLS ANTI d fA SS SS SYN SEP I START IGNTR FADEC ENGINE INSTR MGT mo NG NP NR TEMP PRESS FUEL XMSN INSTR INSTR OIL VALVE QTY PRESS TEMP PRESS BOOST XFR FLIGHT INSTR OEF o OEF o or pan LEFT RIGHT DG AT TURN G g BRT CABINLT OFF k no F NY NV F NY DIM PASS AVIONICS CAUT LT MASTER OFF G500H Flight Display System Instructions for Continued Airworthiness Bell 407 190 01150 21 Rev 2 Page 6 of 19 The installed G500H equipment can be accessed as described below CA L E 8 a 2 Ris G 3 1 GDU 620 FS38 0 WL 46 0 Access or remove by removing the six screws in the bezel of the GDU 620 2 GDC 74H FS27 7 WL 40 1 Access or remove by lowering instrument console at its hinge point and removing the top instrument console cowling 3 GRS 77H FS57 0 WL22 0 Secondary location Access or remove by removing the cushion from the co pilots seat and the panel on top of the seat pedestal 4 GRS 77H FS174 5 WL59 4 Primary location Access or remove by opening the baggage compartment and removing the access panel located on the ceiling of the baggage compartment 5 GMU 44 FS243 0 WL70 1 Secondary location Access or remove by removing the bolts from the access panel on the pilots side of the aircraft at the juncture of the tail boom and fuselage 6 GMU 44 FS316 5 WL74 3 Primary location Access or remo
6. Continued Airworthiness Bell 407 190 01150 21 Rev 2 Page 16 of 19 Return to Service After removing and reinstalling the GMU 44 the following return to service checks should be performed 1 Power up the G500H system with the GDU 620 in normal mode 2 Verify that the GDU displays valid heading within approximately one minute Note that heading can remain invalid if the magnetometer is near a large metal structure such as a hangar wall or if the magnetometer is close to a large ground power cart 3 Verify that no unexpected alerts are present If alerts are present troubleshoot using Section 2 6 of this ICA 2 7 4 GDC 74H Unit 2 7 4 1 Removal 1 Disconnect the pitot static plumbing from the rear of the unit Disconnect the single connector 2 Remove the two 2 screws on the mounting plate near the pitot static ports Loosen the other two 2 screws 3 Carefully remove the unit from its mounting location 2 7 4 2 Installation 1 Place the unit in the mounting tray 2 Position the unit and fasten using the four 4 screws 3 Connect the pitot static plumbing 4 Inspect the connector and pins for damage Repair any damage 5 Connect the connector to the unit ensuring that each jackscrew is secured Original GDC 74H is Reinstalled If the original GDC 74H is re installed then no software loading is required This does not include units that were returned for repair as their software and configuration files are d
7. G500H Flight Display System Instructions for Continued Airworthiness Bell 407 Reg No S N STC SR02295LA Dwg Number 190 01150 21 Rev 2 Garmin International Inc 1200 E 151st Street Olathe Kansas 66062 USA Record of Revision Rev Date Description of Change 04 05 10 Initial Release 12 8 10 Added VSI Placard See 1 ANTRODUGTION EE 3 AS PUROS EE 3 1 22 COPS Reser a Ee 3 1 3 DOCUMENT Control 3 1 4 Permission to Use Certain Documents 3 ES Ree e EE 3 2 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS nsninsannnnnennnnnennnnnnennnnsrnnnnnrnnnsren nne 4 SC JottrogltOeteft gang eean ata a e cee eae A 2 2 Description of Alieratton nenn 5 2 3 Control Operating Information cecceeceeeceeeeeeeeeeeceeeeecaeeeseaeseeeeeseeeesaeeseeeeeaes 8 2 4 Servicing Information 8 2 5 Periodic Maintenance Instructons nenne 8 2 6 Troubleshooting Information cccccccceeceeceeeeeeseeeeeeeeseaeeeeaaeseeeeeseeesssaeeseeeteaes 9 2 7 Removal and Installation Information 0 c ccccccccsscecessseeeeeesneeeeseseeeeesseeseeeaaes 13 2 8 DiaQrams s 200 chet ten E th heen ete 18 2 9 Special Inspection Requirements ssseesseesssesssetssetesesstntstntsennstnnstnnnsnnsrnssnn nenn 18 2 10 Application of Protective Treatment cccccceeseeceeeeeceteeeeneeeeeeeeeeeeeseaeeseeeeeaas 18 2 11 Data Relative to Structural Fasteners cccccccccssseceeessseeecesseeeeseseeeeeesneeeeseaas 18 21 2e
8. S power and check the wiring AHRS1 GPS AHRS 1 AHRS is not receiving any GPS operating in exclusively in no Jinformation GPS mode Ensure that at least one GPS has acquired a valid position If GDU 620 does not have a valid position verify wiring between GDU and GPS receiver and configuration of GDU 620 and GPS receiver If GDU has a valid GPS position verify wiring between GDU and GRS Also verify time mark wiring AHRS1 GPS AHRS 1 not AHRS is not receiving GPS Verify GPS2 power and check the wiring receiving backup GPS information from GPS2 information AHRS1 SRVC AHRS magnetic field model should Update GRS 77H IGRF model current be updated Appears on ground model is with aviation database only AHRS1 TAS AHRS is not receiving true airspeed GDC not powered up Close ADC C B KARG GDC not receiving input from GTP 59 OAT probe Verify wiring is correct ARINC 429 connection from GDC 74H to GRS 77H is not working Verify wiring is correct CAL LOST Registry reports that it has lost Contact Garmin Technical Support calibration data CNFG MODULE The configuration module is Verify wiring to configuration module lee Replace configuration module DATA LOST Pilot stored data was lost Recheck data and settings FAN 1 FAIL Fan 1 has reported 0 RPM when it Inspect the GDU fan for an obstruction was powered with a PWM duty cycle higher than or equal to 10 Contact Garmin Tec
9. Table 2 1 GDU 620 Troubleshooting Guide Problem Cause Solution ____ OE Unit does not power up Improper wiring circuit breaker Ensure power is properly wired to the blank screen open GDU 620 and the circuit breaker is closed Unit intensity turned down Ensure that unit is not in manual intensity control mode with the intensity turned down All expected configuration An Installer Unlock Card is not Insert the Installer Unlock Card pages are not displayed inserted into the GDU 620 P N 010 00769 60 into the bottom slot of the GDU 620 and cycle power Ensure that the GDC 74H RS 232 connection to the GDU is properly wired and ensure that the GDC 74H circuit breaker is closed Insert the loader card in the top slot and cycle power to the GDU The GDC OAT probe type The RS 232 connection to the shows up as UNKNOWN GDC 74H is not working When loading software the The software loader card is LRU software is not being installed in the bottom slot of the displayed on the GDU 620 SOFTWARE UPLOAD page The software loader card contains no information Configuration errors are The configuration module has not displayed on power up been updated before the GDU enters normal mode Repeat the process for making the software loader card Update the configuration module G500H Flight Display System 190 01150 21 Rev 2 Instruction
10. ble 2 3 to determine whether re calibration is required GRS 77H Configuration Module is Replaced If the GRS 77H Configuration Module is replaced the GRS 77H must be re calibrated Reference Table 2 3 2 7 2 3 Return to Service After removing and reinstalling the GRS 77H the following return to service checks should be performed 1 Power up the G500H system with the GDU 620 in normal mode 2 Verify that the GDU displays valid heading and attitude within approximately one minute Note that heading can remain invalid if the magnetometer is near a large metal structure such as a hangar wall or if the magnetometer is close to a large ground power cart 3 Verify that no unexpected alerts are present If alerts are present troubleshoot using Section 2 6 of this ICA G500H Flight Display System 190 01150 21 Rev 2 Instructions for Continued Airworthiness Bell 407 Page 15 of 19 Table 2 3 GRS 77H Calibration Criteria Condition GRS 77H AHRS was removed and or replaced The mounting tray was NOT removed and the mounting tray bolts were NOT loosened Calibrations Required GRS 77H Pitch Roll Offset See Section 5 of the G500H STC Installation Manual GRS GMU Magnetic Calibration See Section 5 of the G500H STC Installation Manual None Required Engine Run up Vibration Test See Section 5 of the G500H STC Installation Manual GRS 77H AHRS was removed and or replaced The mounting tray WAS rem
11. eleted during the repair testing process New Repaired or Exchange GDC 74H is Installed If a new repaired or exchange GDC 74H unit is installed then software must be loaded to the unit Refer to Section 5 4 4 of the G500H STC Installation Manual for more information GDC 74H Configuration Module is Replaced If the GDC 74H Configuration Module is replaced the GDC 74H must be configured Refer to Section 5 5 8 of the G500H STC Installation Manual 2 7 4 3 Return to Service After removing and reinstalling the GDC 74H the following return to service checks must be performed 1 Power up the G500H system with the GDU 620 in normal mode 2 Verify that the GDU displays valid air data within approximately one minute 3 Verify that no unexpected alerts are present If alerts are present troubleshoot using Section 2 6 of this ICA 4 Perform a leak check of the pitot static system and observe the airspeed altitude and vertical speed for proper operation G500H Flight Display System 190 01150 21 Rev 2 Instructions for Continued Airworthiness Bell 407 Page 17 of 19 2 8 Diagrams Rotorcraft specific LRU locations and wire routing diagrams are contained in the Garmin Reference Publications listed in Section 2 1 of this document Point to point wiring diagrams are in Appendix D of the G500H STC Installation Manual Refer to the G500H Post Installation Checkout Log retained in the rotorcraft permanent records for a list of the in
12. enance manual and or the operator s rotorcraft scheduled maintenance program 3 AIRWORTHINESS LIMITATIONS There are no additional Airworthiness Limitations as defined in 14 CFR 27 Appendix A A27 4 that result from this modification The Airworthiness Limitations section is FAA approved and specifies maintenance required under 43 16 and 91 403 of the Federal Aviation Regulations unless an alternative program has been FAA approved G500H Flight Display System 190 01150 21 Rev 2 Instructions for Continued Airworthiness Bell 407 Page 19 of 19
13. his document or the information contained within will be included in the rotorcraft s permanent records This STC upgrades existing avionics for the Bell 407 rotorcraft as summarized below The Garmin G500H Flight Display System consists of an instrument panel mounted GDU 620 display and remote mounted LRUs which provide data to the display The GDU 620 provides controls for the G500H system and a PFD and MFD in the pilot s primary field of view The remote mounted LRUs include one GRS 77H AHRS one GMU 44 Magnetometer one GDC 74H ADC and one GTP 59 OAT probe Rotorcraft modified under this G500H STC are restricted to VFR only including rotorcraft that may not have previously been restricted to VFR To clarify this operation limitation a placard with the text APPROVED FOR DAY NIGHT VFR is required to be in the pilot s view A placard with the text MAX RATE OF CLIMB 2000 FPM shall be installed adjacent to the primary flight display All installed G500H equipment is connected to a power bus that receives power as soon as the battery master switch is turned on G500H Flight Display System Instructions for Continued Airworthiness Bell 407 190 01150 21 Rev 2 Page 5 of 19 Separate circuit breakers have been installed in the overhead circuit breaker panel for each for the GDU 620 PFD GRS 77H GMU 44 AHRS and GDC 74H ADC as circled below D Es Bae EATA BAER E A
14. hnical Support G500H Flight Display System Instructions for Continued Airworthiness Bell 407 190 01150 21 Rev 2 Page 11 of 19 Alert Text FAN 2 FAIL SA 2 has reported 0 RPM when it was powered with a PWM duty cycle higher than or equal to 10 Inspect the GDU fan for an obstruction Contact Garmin Technical Support With the GDU 620 in configuration mode go to the GDL 69 page in the GDL page group Verify that the SET and ACTIVE configuration settings are the same If not use the SET gt ACTV soft key to copy the configuration settings from the GDU 620 into the GDL 69 GDL69 CONFIG The GDL 69 configuration information stored in the GDL 69 and the GDU 620 configuration module do not match The GDL 69 configuration was updated using another LRU e g the GMX 200 or 400W 500W Update the GDL 69 configuration using the GDU 620 Cycle power to the GDU This error automatically clears on the second power up with a different configuration module GDU CONFIG This error appears whenever the d GDU is replaced with a GDU that i was configured for a different i i i i installation Error in the configuration of the GDU 620 GDU 1 2 COOLING Specific GDU has poor cooling and power usage is being reduced Ensure fans on indicated GDU are functioning Ensure fans on indicated GDU are not obstructed GDU 1 2 DB ERR Error in specific database where GDU 1 2 DB denotes specific database Verify
15. iated on the GDU 620 display G500H Flight Display System Instructions for Continued Airworthiness Bell 407 190 01150 21 Rev 2 Page 13 of 19 If any work has been done on the rotorcraft that could affect the system wiring or any interconnected equipment verify the G500H system unit power up self test sequence is successfully completed and no failure messages are annunciated on the GDU 620 display Whenever removing or installing units remove power from the LRU by removing aircraft power or opening the LRU circuit breaker 2 7 1 GDU 620 Unit 2 7 1 1 Removal 1 Remove the six mounting screws from the bezel of the GDU 620 2 Pull the GDU 620 far enough out from the instrument panel to access the three rear connectors 3 Disconnect the rear connectors 4 Remove the GDU 620 2 7 1 2 Installation 1 Visually inspect the connectors to ensure that there are no bent or damaged pins Repair any damage 2 Connect the rear connectors ensuring that each slidelock is secured on both sides 3 Set the GDU 620 into place 4 Install the six mounting screws into the bezel of the GDU 620 NOTE The installation configuration settings are stored in the configuration module and will be A retained when the GDU 620 is replaced with a new unit User settings such as map orientation preferences are stored internally and will be lost when the GDU 620 is replaced with a new unit Original GDU 620 is Reinstalled If the original GDU 620 i
16. nce documentation in paragraph 2 1 of this document for system operation and self test information 2 4 Servicing Information None In the event of system failure troubleshoot the G500H system in accordance with Section 2 6 2 5 Periodic Maintenance Instructions Maintenance of the components installed by this STC is on condition except as noted in the following table Hem Interval Description Procedure GRS 77H AHRS 5 years The GRS 77 utilizes an Earth magnetic field model which is updated once every five years as part of the Aviation Database maintained by the owner operator If the magnetic model is not current the unit will issue an alert upon startup indicating the model has expired The model can be updated by inserting an aviation database card with an updated IGRF model and powering on the system A prompt will direct the user to press ENT to update the model GDC 74H ADC On condition Per Part 43 Appendix E paragraph b 2 the GDC 74H must be checked using a test procedure equivalent to Part 43 Appendix E paragraph b 1 with the following exception The tests of sub paragraphs iv Friction and vi Barometric Scale Error are not applicable because the digital outputs of the GDC 74H are not susceptible to these types of errors GDU 620 GRS 77H GDC 74H GMU 44 GTP 59 12 Calendar Months Conduct a visual inspection look for signs of wear deterioration or damage to
17. oved and or mounting tray bolts WERE loosened GRS 77H AHRS Configuration Module was replaced 2 7 3 GMU 44 Unit 2 7 3 1 Removal 1 Gain access to the GMU 44 magnetometer 2 Unscrew the three screws that hold the GMU 44 to its mounting rack 3 Carefully lift the GMU 44 from the rack 4 Disconnect the wiring harness 2 7 3 2 Installation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Connect the wiring harness to the GMU 44 3 Lower the GMU 44 into the rack and secure the plate with the three Phillips screws Original GMU 44 is Reinstalled If the original GMU 44 was reinstalled then software loading is not required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Recalibration is required only if the mount for the magnetometer was changed If the magnetometer mount was changed refer to Section 5 6 2 of the G500H STC Installation Manual for the GRS 77H GMU 44 Magnetic Calibration New Repaired or Exchange GMU 44 is Installed If a new repaired or exchange GMU 44 unit is installed then software must be loaded and the GRS 77H GMU 44 Magnetic Calibration must be performed Refer to Section 5 of the G500H STC Installation Manual for instructions on software loading 5 4 3 and Magnetic Calibration 5 6 2 G500H Flight Display System Instructions for
18. plying for approval of a Garmin G500H system to use and reference appropriate STC documents to accomplish the Instructions for Continued Airworthiness and show compliance with STC engineering data This permission does not construe suitability of the documents It is the responsibility of the applicant to determine the suitability of the documents for the ICA 1 5 Definitions The following terminology is used within this document 1 ACO Aircraft Certification Office Wel Sc Primary Flight Display PMI Principle Maintenance Inspector E Supplemental Type Certificate 2 ADC Air Data Computer 3 AEG Aircraft Evaluation Group 4 AHRS Attitude Heading Reference System 5 CFR Code of Federal Regulations 6 FAA Federal Aviation Administration 7 ICA Instructions for Continued Airworthiness 8 MFD Multi Function Display 10 11 G500H Flight Display System 190 01150 21 Rev 2 Instructions for Continued Airworthiness Bell 407 Page 3 of 19 2 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 2 1 Introduction Content Scope Purpose and Arrangement Applicability Definition of Abbreviations Precautions Units of measurement Referenced publications Additional Maintenance Data G500H Flight Display System Instructions for Continued Airworthiness Bell 407 This document identifies the Instructions for Continued Airworthiness for the modification of the rotorcraft by installation of the Garmin G500H PFD MFD System
19. rn to service check should be performed 1 Power up the GDU 620 and all interfaced systems in normal mode 2 Verify that there are no red Xs and that no alerts are present If red Xs or alerts are present troubleshoot using Section 2 6 of this ICA 2 7 2 GRS 77H Unit 2 7 2 1 Removal 1 Disconnect the GRS 77H connector 2 Loosen the four Phillips thumbscrews with a screwdriver 3 Gently lift the GRS 77H from the mounting plate if the supports for the mounting plate are removed the GRS 77H must be recalibrated 2 7 2 2 Installation 1 Place the GRS 77H on the mounting plate ensuring the orientation is correct 2 Fasten the unit to the plate using the Phillips thumbscrews Recommended torque is 22 25 inch pounds 3 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 4 Connect the connector to the GRS 77H ensuring that each slidelock is secured on both sides Original GRS 77H is Reinstalled If the original GRS 77H is reinstalled then no software loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Reference Table 2 3 to determine whether recalibration is required New Repaired or Exchange GRS 77H is Installed If a new repaired or exchange GRS 77H unit is installed then software must be loaded per Section 5 4 2 of the G500H STC Installation Manual Reference Ta
20. rsion Update the LRU software to match the number in the manifest does not manifest match the values being reported by Update the manifest to match the LRU MANIFEST NAV1 FAIL No navigation receiver 1 data NAV2 FAIL No navigation receiver 2 data SIMULATOR The simulator mode is active Ensure P6202 36 is not grounded SVT DISABLED Out of available terrain region SVT DISABLED Terrain DB resolution too low SW MISMATCH Location is beyond region covered by terrain database A 30 arc second terrain database is Update the Supplemental Data card with being used the 9 arc second terrain database GDU software version strings do not Verify the correct SW is loaded match The traffic information system has failed TRAFFIC FAIL The GDU 620 is not receiving traffic information from the traffic sensor Verify wiring between GDU 620 and traffic sensor The GDU 620 is receiving information from the traffic sensor but the information is indicating that the traffic sensor has failed Troubleshoot traffic system TRK LOST GPS1 TRK lost HSI defaulted to GPS2 TRK Heading Lost Traffic is now based See HDG errors on track TRK TRAFFIC 2 7 Removal and Installation Information If any G500H LRUs are removed and reinstalled or a new unit is installed verify that the LRU unit power up self test sequence is successfully completed and no failure messages are annunc
21. s for Continued Airworthiness Bell 407 Page 9 of 19 Problem Cause Solution ______ O Vertical GPS deviation is not For 400W 500W Series units the Enable Labels on the 400W 500W Series displayed on the GDU 620 ARINC 429 vertical deviation unit ARINC 429 configuration page labels are not being transmitted Unable to control the GPS The GPS navigator is not correctly Configure the ARINC 429 inputs outputs course when in OBS mode __ configures as LNAV1 2 or for LNAV1 SYS1 or LNAV2 SYS2 SYS1 2 based upon whether the navigator is GPS1 or GPS2 Data is not being received ARINC 429 bus hi and low are Verify wiring from an ARINC 429 device Swapped valid data is being received on the 429 input port as Wrong device is connected to port Use correct ports refer to interconnect shown on the GDU 620 on GDU 620 PORT MONITORING page Data is not being received On the transmitting LRU the Set the ARINC 429 transmitter speed to from an ARINC 429 device ARINC 429 transmitter speedis correct speed no data is being received on EE the 429 input port as shown __ Wiring is not correct Check for continuity shorts and correct as on the GDU 620 PORT required MONITORING page Attitude and heading on Attitude and heading errors resets This is expected behavior and no GDU 620 red X GRS 77H _ are possible if the air data tests troubleshooting is required if this occurs resets during air data ground are cond
22. s reinstalled then no software loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair process No configuration is required New Repaired or Exchange GDU 620 is Installed If a new repaired or exchange GDU 620 unit is installed then software must be loaded No configuration is required NOTE Upon first power up after installing a new GDU 620 it is normal to see a series of B LOADING messages appear on the screen These messages indicate that the GDU 620 is updating its configuration settings from the configuration module Refer to Section 5 of the G500H STC Installation Manual for the GDU 620 Software Loading procedure 5 4 1 followed by the Manifest Configuration 5 5 5 and the Configuration Module Update 5 5 12 GDU 620 Configuration Module is Replaced If the GDU 620 Configuration Module is replaced the GDU 620 will update the configuration module from its internally stored settings when the UPDT CFG soft key is pressed If the GDU 620 is replaced at the same time as the Configuration Module then the System Setup will need to be performed per Section 5 5 of the G500H STC Installation Manual G500H Flight Display System 190 01150 21 Rev 2 Instructions for Continued Airworthiness Bell 407 Page 14 of 19 2 7 1 3 Return to Service After removing and reinstalling the GDU 620 per the instructions above a simple retu
23. terfaced equipment and port configurations 2 9 Special Inspection Requirements 2 9 1 Post Lightning Strike Inspection In the event of a suspected or actual lightning strike to the aircraft the GTP 59 OAT Probe and its associated installation shall be inspected The probe and the surrounding installation shall be inspected to ensure that there is no structural damage around the areas where lightning may have attached If there is visible sign of damage to the probe then it must be replaced Verify that OAT is displayed on the GDU 620 PFD normally 2 10 Application of Protective Treatments None N A 2 11 Data Relative to Structural Fasteners Refer to the following table for data on the location type and torque values for structural fasteners i FASTENER TYPE AND TORQUE Location 6 32 Screw 8 32 Screw 10 32 Screw NUT 5 16 HEX SKIRT see General Arrangement Drawing 12 15 inch pounds 12 15 inch pounds 22 25 inch pounds 100 20 inch pounds Instrument Panel Instruments C em ewe Cr 2 12 Special Tools For electrical bonding testing a millionm meter is required G500H Flight Display System 190 01150 21 Rev 2 Instructions for Continued Airworthiness Bell 407 Page 18 of 19 2 13 Additional Instructions None 2 14 Overhaul Period The system does not require overhaul at a specific time period Power on self test and continuous BIT will monitor the health of the G500H system If any LRU indicates an internal failure
24. the correct card is installed reload the DB on the card GDU 1 2 VOLTAGE GDU supply voltage is below 12 VDC Increase the voltage above 12VDC GEO LIMITS Location is too far north south for GRS 77H magnetic compass GPS 1 2 FAIL No GPS1 or GPS2 data is available Ensure GPS 1 2 is turned on Verify RS 232 wiring from the GPS to the GDU 620 GPS 1 2 PPS Failure This alert will be set if the PPS signal has not been received in more than 5 sec If the unit is configured for dual GPSs then the side will be specified in the error G500H Flight Display System Instructions for Continued Airworthiness Bell 407 Ensure GPS 1 2 is turned on Verify 1PPS wiring from the GPS to the GDU 620 190 01150 21 Rev 2 Page 12 of 19 Alert Text Pp Cause Solution GPS2 FPL USED The GPS1 has failed and GPS2 is configured and operating AHRS magnetometer fault has occurred Heading from the GRS77 GMU 44 is not valid HDG FAULT GRS 77H not receiving information from GMU 44 Verify wiring to GMU 44 Caused by a local magnetic anomaly No action required Return indicated LRU to Garmin for service HDG LOST lt LRU gt SERVICE Specific LRU should be serviced where lt LRU gt denotes specific LRU GDU has received product data for Ensure the manifest is properly an LRU that should have a manifest configured entry but is not in the manifest The LRU software P N and ve
25. ucted indoors without a__ To reduce the chances of inducing testing good GPS signal With marginal attitude and heading errors resets while or no GPS signals present conducting the air data tests ensure that sudden changes in airspeed the G500H is receiving good GPS signals caused by using a pressure tester may result in attitude and heading errors and possibly cause the GRS 77H to reset This occurs because the artificial changes in airspeed cause disagreement with the other sensor measurements internal to the GRS 77H This sensor disagreement will not occur in the normal conditions of flight Heading red X during air Invalidation of heading is possible This is expected behavior and no data ground testing if the air data tests are conducted troubleshooting is required if this occurs indoors due to typical magnetic anomalies even with a good GPS signal G500H Flight Display System 190 01150 21 Rev 2 Instructions for Continued Airworthiness Bell 407 Page 10 of 19 2 6 2 G500H Alerts The G500H will display a number of alerts on the GDU 620 MFD These are listed in the following table Table 2 2 GDU 620 Alert Troubleshooting Guide Alert Text p Cause Solution _ _ AHRS1 GPS AHRS 1 using AHRS is using the backup GPS backup GPS source information Verify GPS1 power and check the wiring AHRS1 GPS AHRS is not AHRS is not receiving any GPS receiving any GPS information information Verify GP
26. ve by removing the bolts from the access panel on either side of the aircraft at the juncture of the horizontal stabilizer and tail boom 2 2 1 Weight and Balance Information Weight and Balance Bell 407 Moment am NM Location tem Part Number Weight LB 1 011 01264 50 S 2 joii 00882 11 A ee 3 1011 00868 20 GRS 77H GRS 77H Unit Only OO O O Only GRS 77H Installed with rack and connector 011 00870 10 GMU 44 EMAU Oot __ Only GMU 44 GMU 44 Installed with rack and connector with rack and connector GMU 44 Unit Only GMU 44 GMU 44 Installed with rack and connector GMU 44 Installed with rack and connector rack and connector 1 A rotorcraft weight and balance is required after installation of the G500H system Refer to STC installation manual P N 190 01150 06 for additional information including overall size and center of gravity location of all LRUs 2 The longitudinal arm is measured in terms of the fuselage station FS number 3 The lateral arm is measured in terms of the butt line BL The centerline of the helicopter is BLO 00 The moment arms to the left side looking forward are negative and the moment arms to the right side are positive G500H Flight Display System 190 01150 21 Rev 2 Instructions for Continued Airworthiness Bell 407 Page 7 of 19 2 3 Control Operating Information See the G500H Pilote Guide or the G500H STC Installation Manual listed under the refere
Download Pdf Manuals
Related Search