Airplane Flight Manual Supplement

G500 PFD/MFD System 190-01102-00 Rev. 5
Instructions for Continued Airworthiness Page 9 of 13
If any work has been done on the aircraft that could affect the system wiring, antenna cable, or any
interconnected equipment, verify the G500 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 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 5.5.11.3
of the G500 AML STC Installation Manual must be performed whenever the GAD 43e and/or the analog
navigation receiver is replaced.
2.8 Diagrams
Aircraft specific LRU locations and wire routing diagram are contained in Appendix A of this document.
Refer to the G500 AML STC Series Installation Manual (listed under reference documentation in Section
2.1 of this document) for drawings applicable to this installation. Point to point wiring diagrams are in
Appendix F of the G500 AML STC Installation Manual. Refer to the G500 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 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 AML STC Installation Manual.
 Aircraft with a GMU mounted in the wingtip of metallic aircraft with non-metallic wingtip covers
must inspect the magnetometer installation in accordance with section 8.4.1 of the G500 AML
STC Installation Manual.
 Aircraft with an ARINC 708 weather radar interfaced to the GDU 620 must inspect the overbraid
to the weather radar in accordance with section 8.4.2 of the G500 AML STC Installation Manual.
If the Mid-Continent Standby Attitude Indicator (if installed) has not been operated for more than 3
months, charge each battery pack using one of the methods described in Section 2.4.
2.10 Application of Protective Treatments
None, N/A.
2.11 Data Relative to Structural Fasteners
Data relative to structural fasteners, such as type, torque, and installation requirements can be found in
Section 3 of the G500 AML STC Installation Manual.
2.12 Special Tools
For electrical bonding testing, a milli-ohm meter is required.
No special tools are required for system checkout. See G500 AML STC Installation Manual listed in
reference documentation in Section 2.1 of this document.