TM 55-1520-240-23-9
11-81
INSTALL PILOT’S COCKPIT CONTROL ASSEMBLY
(Continued)
11-81
INSTALL PITCH CONNECTING LINK
22.
Working through left access (26), position
bellcrank (40) to align bolt (41) and hole (42).
23.
Remove nut (43), two washers (44 and 45), and
bolt (41) from bellcrank (40).
FLIGHT SAFETY PARTS
This is an installation critical flight
safety part. All aspects of its assembly
and installation must be ensured.
Ensure that both rod end jam nuts are
installed and torqued.
Ensure that the rivet through the fixed
rod end bearing is secure.
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.
24.
Position pitch connecting link (46) in bellcrank
(40). Check that link is free of electrical wiring.
25.
Install bolt (41), two washers (45 and 44), and nut
(43) in bellcrank (40). Remove tag from link (46).
26.
Working through right access (7), position
bellcrank (47) to align bolt (48) and hole (49).
27.
Remove nut (50), two washers (51 and 52), and
bolt (48) from bellcrank (47).
28.
Position link (46) in bellcrank (47).
29.
Install bolt (48), two washers (52 and 51), and
nut (50) in bellcrank (47).
30.
Torque nuts (43 and 50) to 30 to 60 inch-pounds.
Install two cotter pins (53 and 54).
31.
Check bolts (41 and 48). Bolts 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 30.
11-423
