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Garmin GTN 650 Manual

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GTN 6XX/7XX AML STC Installation Manual 190-01007-A3
Page 5-2 Rev. 4
5.2 Mounting, Wiring, and Power Checks
Verify that all cables are properly secured and shields are connected to the shield block of the connectors.
Check the movement of the flight and engine controls to verify there is no interference between the
cabling and control systems. Ensure that all wiring is installed in accordance with Section 2.4.11.
Prior to powering up the GTN, the wiring harness must be checked for proper connections to the aircraft
systems and other avionics equipment. Point to point continuity must be checked on all wiring to expose
any faults such as shorting to ground. Any faults or discrepancies must be corrected before proceeding. If
any TVSs are installed as part of the installation, proper TVS installation should be verified prior to
application of power. Refer to Section 3.6.5.1 for guidance on checking each TVS assembly. Also, check
the lighting bus wiring to ensure it is wired correctly before applying power to the GTN.
CAUTION
Incorrect lighting bus wiring could cause damage to the GTN.
After accomplishing a continuity check, perform power and ground checks to verify proper power
distribution to the GTN, including the lighting bus and any high level inputs to the GTN. Any faults or
discrepancies should be corrected at this time. Remove power from the aircraft upon completion of the
harness checkout.
The GTN can be installed after completion of the continuity and power checks. The GTN should be
installed into the rack and secured appropriately, as described in Section 3.4.2. The GTN backplate must
be connected to the wiring harness and antenna coaxial cables.
5.3 Connector Engagement Check
Prior to configuration and checkout of the GTN, the connector engagement should be checked as
described below:
1. Ensure that the GTN GPS/NAV and COM circuit breakers are pulled.
2. Slide the GTN straight into the rack until it stops about 1 inch short of the fully seated position.
3. Insert a 3/32-inch hex drive into the unit retention mechanism access hole at the bottom of the
unit face and rotate the tool clockwise while pressing the bezel until the unit is firmly seated in
the rack.
4. With the GTN seated, reapply power by closing the circuit breakers and turning on the avionics
master switch (if installed).
5. Again, insert the hex drive into the unit retention mechanism access hole. Rotate the tool
counter-clockwise to back out the retention mechanism. Ensure that three (3) complete
revolutions of the Allen screw can be performed without red ‘X’ indication or loss of power to
the GTN.
NOTE
If power is lost or the red ‘X’ condition occurs with fewer than three (3) turns, ensure
there are no obstructions to the unit fully seating in the rack. Also, the mounting rack may
need to be moved aft (toward the pilot) such that the instrument panel does not obstruct
the unit from properly engaging in the rack.
6. Re-seat the GTN per step 3.
… 140 …


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