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.
1. INTRODUCTION................................................................................................................... 3 1.1 Purpose................................................................................................................. 3 1.2 Scope .................................................................................................................... 3 1.3 Document Control ...............................................................................................
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 SR02295LA. 1.
2. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 2.1 Introduction Content, Scope, Purpose and Arrangement: This document identifies the Instructions for Continued Airworthiness for the modification of the rotorcraft by installation of the Garmin G500H PFD/MFD System. Applicability: Applies to Bell models 407 rotorcraft altered by installation of the Garmin G500H PFD/MFD System. Definition of Abbreviations: See Section 1.
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: 2.2 This document, or the information contained within, will be included in the rotorcraft’s permanent records.
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: ALT ICS 5 3 3 1 XPNDR ENCDG SPKR PHONE VHF 2 VHF 1 NAV-COMM ICS 5 5 5 20 ADF GPS COMM NAV COMM FLOATS CARGO 5 5 1 35 2 HOOK ELT AIR COND HEATER AUX PFD AHRS ADC 15 5 5 5 FIRE 3 RECP DETECT LIGHTS LDG PEDAL 25 2 5 5 5 5 PWR CONT INSTR CKPT CAUT STOP HYD INSTR 5 3 SYSTEM O
The installed G500H equipment can be accessed as described below: 1 2 6 5 4 3 1. 2. 3. 4. 5. 6. GDU 620: FS38.0, WL 46.0 Access or remove by removing the six screws in the bezel of the GDU 620. 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. 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. GRS 77H: FS174.
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 Perform an electrical bonding test for each listed LRU: GDU 620, GRS 77H, GDC 74H, GMU 44, GTP 59 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.
Problem Vertical GPS deviation is not displayed on the GDU 620. Unable to control the GPS course when in OBS mode. 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) Cause For 400W/500W Series units, the ARINC 429 vertical deviation labels are not being transmitted. The GPS navigator is not correctly configures as LNAV1/2 or SYS1/2. ARINC 429 bus hi and low are swapped.
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 AHRS1 GPS – AHRS 1 using backup GPS source. AHRS1 GPS - AHRS is not receiving any GPS information AHRS1 GPS – AHRS 1 operating in exclusively in noGPS mode. Cause AHRS is using the backup GPS information AHRS is not receiving any GPS information. AHRS is not receiving any GPS information.
Alert Text FAN 2 FAIL Cause Fan 2 has reported 0 RPM when it was powered with a PWM duty cycle higher than or equal to 10% Solution 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.
Alert Text GPS2 FPL USED Cause The GPS1 has failed and GPS2 is configured and operating. 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. SERVICE Specific LRU should be serviced, where denotes specific LRU. Return indicated LRU to Garmin for service.
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 2.7.1.1 1. 2. 3. 4. 2.7.1.2 GDU™ 620 Unit Removal Remove the six mounting screws from the bezel of the GDU 620.
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 2.7.2.1 GRS 77H Unit Removal 1. Disconnect the GRS 77H connector. 2. Loosen the four Phillips thumbscrews with a screwdriver. 3.
Table 2-3. GRS 77H Calibration Criteria Calibrations Required Condition GRS 77H Pitch/Roll Offset 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. GRS 77H AHRS was removed and/or replaced. The mounting tray WAS removed and/or mounting tray bolts WERE loosened. GRS 77H AHRS Configuration Module was replaced. 2.7.3 2.7.3.
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.
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.
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.
