Garmin G600 사용 설명서 - 페이지 10
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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.
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/G600
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/G600 AML STC Installation
Manual.
Aircraft with optional GDU 620 dual power bus diodes (see Installation Manual Figure F-2) must
perform a functional check of the diode isolation as follows:
o
Power on Avionics #1 Bus and Avionics #2 Bus. Verify that all avionics are powered on.
o
Power off Avionics #1 Bus only. Verify that both GDU 620 units remain powered on.
Verify that Avionics #1 Bus is unpowered.
o
Power on Avionics #1 Bus and Power off Avionics #2 Bus only. Verify that both
GDU 620 units remain powered on. Verify that Avionics #2 Bus is unpowered.
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/G600 AML STC Installation Manual.
2.12 Special Tools
For electrical bonding testing, a milliohm meter is required.
No special tools are required for system checkout. See G500/G600 AML STC Installation Manual listed
in reference documentation in Section 2.1 of this document.
G500/G600 PFD/MFD System
Instructions for Continued Airworthiness
190-00601-00 Rev. L
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