Visual Inspection; Table 4-2 - Visual Inspection Procedure - Garmin GFC 500 Maintenance Manual

4.4 Visual Inspection

Perform a visual inspection in accordance with requirements in Table 4-2. Check for corrosion,
damage, or other defects of the GMC 507 and the GSA 28s. Replace any damaged parts as
required. Inspection may require the temporary removal of a unit or units to gain access to
connectors. Follow guidance in Section 6 for equipment removal and replacement. Refer to
the aircraft manufacturer service or maintenance manual for instructions on access panel
locations.
Item Description/Procedure
a)
GFC 500 Equipment
Visual Inspections
iii.
b)
a)
b)
c)
Servos, Servo
Control Cables, and d)
associated hardware
e)
f)
g)
GFC 500 Autopilot with ESP Part 23 AML STC Maintenance Manual
190-02291-01
Table 4-2 – Visual Inspection Procedure
Conduct a visual inspection of the GMC 507 and GSA 28 equipment installations in
accordance with 14 CFR Part 43, Appendix D. If the equipment does not pass the
visual inspection, complete the following procedure:
i. Correct improper installations and ensure that all install racks, brackets, and
fasteners are secure. Correct improper wire routing and ensure that the wire
harness is securely mounted. Replace install racks, brackets, wiring and
associated electrical bonding or shielding components with obvious defects
ii. Complete the equipment electrical bonding test as described in section 4.5 for any
components that are replaced.
Equipment shield terminations shall be free of corrosion and secure to the
backshell or aircraft ground.
Inspect all exposed wire harness for chafing, damage, proper routing of wire bundles
and security of attachment in accordance with AC 43.13-1B, Chapter 11, Section 8,
Paragraph 11-96.
Using a flashlight, inspect the GSA 28 servos, connectors, support structure, and
control cables to ensure that no corrosion, chafing, cracks, or other defects exist.
Have an assistant manually move the control surfaces from stop to stop and visually
observe the servo and control cabling/chain. Ensure there is no binding in the control
cabling or chain, that the capstan/sprocket rotates freely, and that there is no rough
turning or noise from the servo bearings.
Check the servo control cables in accordance with AC 43.13-1B, Chapter 7, Section
8, Paragraph 7-149 to ensure no fraying, corrosion, or other damage exists. If the
condition of any cable is questionable, replace it with a new one.
Check the tension on the servo control cables. Refer to the appropriate Install
Manual Addendum for the aircraft type for cable tension specifications:
Ensure that each cable is correctly attached to the existing flight control system as
shown in the appropriate Install Manual Addendum.
Visually inspect the condition of lock nuts, cable guard support plate, cable guard
posts, self-locking castle nuts, cotter pin, split lock washer, flat washer and the output
shaft to ensure no corrosion, cracks, or other defects exist.
For continuous travel servos only, visually inspect the condition of the idler pulley,
shaft, washer, and E-ring, to ensure no corrosion, chafing, cracks, or other defects
exist.
Initials
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