Garmin G500, Instructions Manual

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G500/G600 PFD/MFD System 190-00601-00 Rev. M
Instructions for Continued Airworthiness Page 8 of 13
2.7 Removal and Replacement Information
If any G500/G600 LRUs are removed and reinstalled, verify that the LRU unit power-up self-test
sequence is successfully completed and no failure messages are annunciated on the GDU 620 display.
See the unit replacement procedure in section 3.5 of the G500/G600 AML STC Installation Manual.
Perform any additional procedures that are required for each LRU, as specified in the following
subsections. Any component installed under this STC must be replaced by a component of the same
model and part number or defined equivalent component.
If any work has been done on the aircraft that could affect the system wiring, antenna cable, or any
interconnected equipment, verify the G500/G600 system unit power-up self-test sequence is
successfully completed and no failure messages are annunciated on the GDU 620 display.
Refer to the G500/G600 AML STC Installation Manual (listed under reference documentation in Section
2.1 of this document) for particular LRU removal/installation procedures and special handling
precautions.
2.7.1 GAD 43e Adapter Replacement
If the GAD 43e is used with an analog navigation receiver, the GAD 43e calibration specified in section
5.5.14.3 of the G500/G600 AML STC Installation Manual must be performed whenever the GAD 43e
and/or the analog navigation receiver is replaced.
2.7.2 TBM 700(850) RVSM Return to Service (G600 Only)
If the ADC was removed or replaced, check the air data systems as specified in the Socata Maintenance
Manual section 34-11-00 except check the G600 altitude display in accordance with G500/G600 AML
STC Installation Manual section P.3.2.1.
If the co-
pilot’s RVSM altimeter is removed or replaced, verify ADC 1/ADC 2 switch is operating normally
as specified in the G500/G600 AML STC Installation Manual section P.3.1
. Refer to the manufacturer’s
instructions for additional calibration and return service instructions. Check the air data systems as
specified in the Socata Maintenance Manual section 34-11-00 except check the co-
pilot’s altitude display
as specified in the G600 Installation Manual section P.3.2.1.
If work was performed in the RVSM critical areas, including rear cargo door (if installed), static ports, and
fixation rivets, it must be checked as specified in Socata Maintenance Manual section 53-00-00.
2.8 Diagrams
Aircraft specific LRU locations and wire routing diagram are recorded during installation using the forms
in Appendix A of this document. Refer to the G500/G600 AML STC Installation Manual (listed under
reference documentation in Section 2.1 of this document) for drawings applicable to this installation and
for instructions to complete the forms in Appendix A. Point to point wiring diagrams are in Appendix F of
the G500/G600 AML STC Installation Manual. Refer to the G500/G600 Post-Installation Checkout Log
retained in the aircraft permanent records for a list of the interfaced equipment and port configurations.
2.9 Special Inspection Requirements
After a suspected lightning strike, the following actions must be performed:

Inspect the GTP 59 OAT for signs of lightning damage. Check the self-sealing washer
(P/N 212-00026-00) used on the probe tip outside of the aircraft for any evidence of melting or
lack of seal. Replace washer if damaged. If there is evidence of lightning strike to the OAT or
any lightning damage, replace the GTP 59 OAT.

Non-metallic aircraft must have all Transient Voltage Suppressors replaced in accordance with
section 8.3.1 of the G500/G600 AML STC Installation Manual.

Tube and fabric aircraft must replace the OAT bond strap (if installed) in accordance with section
8.3.3 of the G500/G600 AML STC Installation Manual.