Garmin STC for Bell 206/407 Instruction Manual

Referenced publications: 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 Additional Maintenance Data: 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” G500H Flight Display System 190-01150-21 Rev. 2 Instructions for Continued Airworthiness Bell 407 Page 5 of 19 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 Retention: This document, or the information contained within, will be included in the rotorcraft’s permanent records. 2.2 Description of Alteration 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 190-01150-21 Rev. 2 Instructions for Continued Airworthiness Bell 407 Page 6 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: 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 1 1 20 2 35 15 2 25 10 ENCDG ALT XPNDR SPKR ICS PHONE ICS ADF GPS COMM VHF 2 NAV VHF 1 COMM NAV-COMM AIR COND FLOATS CARGO ELT HOOK HEATER RECP AUX DETECT FIRE LDG LIGHTS STOP PEDAL PWR CONT INSTR CKPT CAUT SYSTEM HYD OAT/V AMPS RESET FIELD GENERATOR INSTR SEP PART ICE ANTI START IGNTR FADEC ENGINE CONTROLS OIL ENGINE INSTR MGT TRQ NG NP NR PRESS TEMP FUEL INSTR OIL XMSN INSTR VALVE QTY PRESS TEMP PRESS LEFT OFF RIGHT OFF DG OFF ATT OFF TURN OFF FLIGHT INSTR BOOST/XFR POS LT OFF DEFOG OFF PITOT OFF PART OFF ANTI OFF OFF OFF OFF OFF HEATER ENG ANTI AVIONICS MASTER ICE SEP COLL LT RESET GEN BATT DIM BRT CAUT LT PASS CABIN LT AIR COND HEATER HIGH LOW BLO FWD AFT AIR COND BRT OFF INSTR LT HYD OFF SYS O F F O F F O F F + 5 5 5 PFD AHRS ADC G500H Flight Display System 190-01150-21 Rev. 2 Instructions for Continued Airworthiness Bell 407 Page 7 of 19 The installed G500H equipment can be accessed as described below: 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 remove 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 arm (IN) Location Item Part Number Weight (LB) Longitudinal Lateral Primary Secondary 1 011‐01264‐50 GDU 620 (Unit Only) 6.38 38.0 6.0 GDU 620 (Installed with rack and connector) 7.04 2 011‐00882‐11 GDC 74H (Unit Only) 1.70 27.7 4.0 GDC 74H (Installed with connector) 1.92 3 011‐00868‐20 GRS 77H (Unit Only) 2.80 GRS 77H (Installed with rack and connector) 3.46 4 011‐00870‐10 GMU 44 (Unit Only) 0.35 316.5 0.0 † GMU 44 (Installed with rack and connector) 0.50 316.5 0.0 † GMU 44 (Unit Only) 0.35 243.0 † GMU 44 (Installed with rack and connector) 0.50 243.0 † [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 BL0.00. The moment arms to the left side (looking forward) are negative (-) and the moment arms to the right side are positive (+). 6 5 4 1 2 3 G500H Flight Display System 190-01150-21 Rev. 2 Instructions for Continued Airworthiness Bell 407 Page 8 of 19 2.3 Control, Operating Information See the G500H Pilot’s Guide or the G500H STC Installation Manual, listed under the reference 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. Item 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 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 190-01150-21 Rev. 2 Instructions for Continued Airworthiness Bell 407 Page 9 of 19 Item Interval Description/Procedure GDU 620, GRS 77H, GDC 74H, GMU 44, GTP 59 Every 2000 flight hours or ten (10) years, whichever is first 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 exposed portion of aircraft metallic structure a. For the GDU 620, verify the resistance is less than or equal to 40 milliohms b. For the remaining LRUs, verify the resistance is 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 Table 2-1. GDU 620 Troubleshooting Guide Problem Cause Solution Unit does not power up – blank screen. Improper wiring; circuit breaker open. Ensure power is properly wired to the 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 pages are not displayed. An Installer Unlock Card is not inserted into the GDU 620. Insert the Installer Unlock Card P/N 010-00769-60 into the bottom slot of the GDU 620 and cycle power. The GDC OAT probe type shows up as UNKNOWN The RS-232 connection to the GDC 74H is not working. Ensure that the GDC 74H RS-232 connection to the GDU is properly wired, and ensure that the GDC 74H circuit breaker is closed. When loading software, the LRU software is not being displayed on the SOFTWARE UPLOAD page. The software loader card is installed in the bottom slot of the GDU 620. Insert the loader card in the top slot and cycle power to the GDU. The software loader card contains no information. Repeat the process for making the software loader card. Configuration errors are displayed on power-up, before the GDU enters normal mode. The configuration module has not been updated. Update the configuration module. G500H Flight Display System 190-01150-21 Rev. 2 Instructions for Continued Airworthiness Bell 407 Page 10 of 19 Problem Cause Solution Vertical GPS deviation is not displayed on the GDU 620. For 400W/500W Series units, the ARINC 429 vertical deviation labels are not being transmitted. Enable Labels on the 400W/500W Series unit ARINC 429 configuration page. Unable to control the GPS course when in OBS mode. The GPS navigator is not correctly configures as LNAV1/2 or SYS1/2. Configure the ARINC 429 inputs/outputs for LNAV1 (SYS1) or LNAV2 (SYS2) based upon whether the navigator is GPS1 or GPS2. Data is not being received from an ARINC 429 device. (valid data is being received on the 429 input port as shown on the GDU 620 PORT MONITORING page) ARINC 429 bus hi and low are swapped. Verify wiring. Wrong device is connected to port on GDU 620. Use correct ports (refer to interconnect details). Data is not being received from an ARINC 429 device. (no data is being received on the 429 input port as shown on the GDU 620 PORT MONITORING page) On the transmitting LRU, the ARINC 429 transmitter speed is not set correctly. Set the ARINC 429 transmitter speed to correct speed. Wiring is not correct. Check for continuity/shorts and correct as required. Attitude and heading on GDU 620 red ‘X’ / GRS 77H resets during air data ground testing. Attitude and heading errors/resets are possible if the air data tests are conducted indoors without a good GPS signal. With marginal or no GPS signals present, sudden changes in airspeed 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. This is expected behavior and no troubleshooting is required if this occurs. To reduce the chances of inducing attitude and heading errors/resets while conducting the air data tests, ensure that the G500H is receiving good GPS signals. Heading red ‘X’ during air data ground testing Invalidation of heading is possible if the air data tests are conducted indoors, due to typical magnetic anomalies, even with a good GPS signal. This is expected behavior and no troubleshooting is required if this occurs. G500H Flight Display System 190-01150-21 Rev. 2 Instructions for Continued Airworthiness Bell 407 Page 11 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 Cause Solution AHRS1 GPS – AHRS 1 using backup GPS source. AHRS is using the backup GPS information Verify GPS1 power and check the wiring AHRS1 GPS - AHRS is not receiving any GPS information AHRS is not receiving any GPS information. Verify GPS power and check the wiring AHRS1 GPS – AHRS 1 operating in exclusively in no- GPS mode. AHRS is not receiving any GPS information. 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 receiving backup GPS information. AHRS is not receiving GPS information from GPS2. Verify GPS2 power and check the wiring AHRS1 SRVC AHRS magnetic field model should be updated. Appears on ground only. Update GRS 77H IGRF model (current model is with aviation database). AHRS1 TAS AHRS is not receiving true airspeed from ADC. GDC not powered up. Close ADC C/B. 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 calibration data. Contact Garmin Technical Support. CNFG MODULE The configuration module is inoperative. Verify wiring to configuration module 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 was powered with a PWM duty cycle higher than or equal to 10% Inspect the GDU fan for an obstruction. Contact Garmin Technical Support. G500H Flight Display System 190-01150-21 Rev. 2 Instructions for Continued Airworthiness Bell 407 Page 12 of 19 Alert Text Cause Solution FAN 2 FAIL Fan 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. GDL69 CONFIG The GDL 69 configuration information stored in the GDL 69 and the GDU 620 configuration module do not match. 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>ACTV soft key to copy the configuration settings from the GDU 620 into the GDL 69. 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. GDU CONFIG This error appears whenever the GDU is replaced with a GDU that was configured for a different installation. Cycle power to the GDU. This error automatically clears on the second power up with a different configuration module. 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 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. Ensure GPS (1/2) is turned on Verify 1PPS wiring from the GPS to the GDU 620. G500H Flight Display System 190-01150-21 Rev. 2 Instructions for Continued Airworthiness Bell 407 Page 13 of 19 Alert Text Cause Solution GPS2 FPL USED The GPS1 has failed and GPS2 is configured and operating. HDG FAULT AHRS magnetometer fault has occurred. GRS 77H not receiving information from GMU 44. Verify wiring to GMU 44. HDG LOST Heading from the GRS77/ GMU 44 is not valid. Caused by a local magnetic anomaly. No action required. <LRU> SERVICE Specific LRU should be serviced, where <LRU> denotes specific LRU. Return indicated LRU to Garmin for service. MANIFEST GDU has received product data for an LRU that should have a manifest entry, but is not in the manifest. Ensure the manifest is properly configured. The LRU software P/N and version number in the manifest does not match the values being reported by that LRU. Update the LRU software to match the manifest Update the manifest to match the LRU software 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. Location is beyond region covered by terrain database. SVT DISABLED - Terrain DB resolution too low. A 30 arc-second terrain database is being used. Update the Supplemental Data card with the 9 arc-second terrain database. SW MISMATCH GDU software version strings do not match. Verify the correct SW is loaded TRAFFIC FAIL The traffic information system has failed. 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. TRK TRAFFIC Heading Lost. Traffic is now based on track. See HDG errors. 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 annunciated on the GDU 620 display. G500H Flight Display System 190-01150-21 Rev. 2 Instructions for Continued Airworthiness Bell 407 Page 14 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 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 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 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 “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 15 of 19 2.7.1.3 Return to Service After removing and reinstalling the GDU 620 per the instructions above, a simple return-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 Table 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 16 of 19 Table 2-3. GRS 77H Calibration Criteria Condition 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 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 NOT removed and the mounting tray bolts were NOT loosened. None Required. GRS 77H AHRS was removed and/or replaced. The mounting tray WAS removed and/or mounting tray bolts WERE loosened. X X X GRS 77H AHRS Configuration Module was replaced. X X X 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 190-01150-21 Rev. 2 Instructions for Continued Airworthiness Bell 407 Page 17 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 deleted 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 18 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 interfaced 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. Location (see General Arrangement Drawing) FASTENER TYPE AND TORQUE 6‐32 Screw 12‐15 inch‐pounds 8‐32 Screw 12‐15 inch‐pounds 10‐32 Screw 22‐25 inch‐pounds NUT, 5/16", HEX, SKIRT 100±20 inch‐pounds Instrument Panel, Instruments X X GDU 620 X GRS 77H X X GDC 74H X X GMU 44 X X GTP 59 X 2.12 Special Tools For electrical bonding testing, a milliohm meter is required. G500H Flight Display System 190-01150-21 Rev. 2 Instructions for Continued Airworthiness Bell 407 Page 19 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, 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 maintenance 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.