TM 55-1520-240-23-9
11-81
INSTALL PILOT’S COCKPIT CONTROL ASSEMBLY
(Continued)
11-81
INSTALL ROLL CONNECTING LINK
32.
Position bellcrank (55) to align bolt (56) and hole
(57).
33.
Working through right access (7), remove nut
(58), and washer (59) from bolt (56).
34.
Have helper in cockpit remove bolt (56) and
washer (60).
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.
35.
Slide roll connecting link (61) from left, through
hole (62) and position in bellcrank (55).
36.
Check that link (61) is free of electrical wiring.
37.
Have helper install washer (60) and bolt (56) in
bellcrank (55) and hold bolt.
38.
Install washer (59), and nut (58) on bolt (56).
Remove tag from link (61).
39.
Torque nut (58) to 30 to 60 inch-pounds. Install
cotter pin (63).
40.
Working from cockpit, remove nut (64), two
washers (65 and 66), and bolt (67) from bellcrank
(68).
41.
Position link (61) in bellcrank (68).
42.
Install bolt (67), two washers (66 and 65), and
nut (64) in bellcrank (68).
43.
Torque nut (64) to 30 to 60 inch-pounds. Install
cotter pin (69).
44.
Check bolts (56 and 67). 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
39 or 43.
11-424
