TM 55-1520-240-23-9
11-77
ASSEMBLE PILOT’S COCKPIT CONTROL ASSEMBLY
(Continued)
11-77
FLIGHT SAFETY PARTS
This is an installation critical flight
safety part. All aspects of its assembly
and installation must be ensured.
Ensure that both machined rod ends
attached to the link are secure.
Ensure that both rod end jam nuts are
installed and torqued.
Ensure that the rivet through the fixed
rod end bearing is secure.
Ensure adjustable rod end bearing
faces forward.
At installation of this component,
ensure proper attaching hardware
(impedance type bolt, nut, and
washers) is installed including
verification of bolt head orientation,
torque, and installation of cotter pins.
Loose attachments within flight control
primary linkage will degrade aircraft
control. Missing components will
cause loss of control.
ASSEMBLE LEFT OR RIGHT YAW CONNECTING
LINK
NOTE
Procedure is same to assemble left or
right link. Right link is shown here.
123.
If yaw connecting link (260) is a replacement,
loosen nut (261) of adjustable end. Turn bearing
(262) 90º to bearing (263). Torque nut to 100
inch-pounds.
124.
Position link (260) with fixed bearing (263)
through hole (264) in support (2) and in bellcrank
(134). Install bolt (265), two washers (266 and
267), and nut (268).
125.
Torque nut (268) 30 to 60 inch-pounds. Install
cotter pin (269).
126.
Check bolt (265). Bolt shall not rotate with torque
less than 10 inch-pounds. There shall be no
axial looseness. If bolt rotates or is loose, add
washer under nut and repeat step 125.
INSPECT
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