TM 55-1520-240-23-9
11-77
ASSEMBLE PILOT’S COCKPIT CONTROL ASSEMBLY
(Continued)
11-77
ASSEMBLE THRUST INPUT BELLCRANK
44.
Press bearing (dissimilar metals) (84) in bellcrank
(85) until it bottoms. Use arbor press.
45.
Install spacer (dissimilar metals) (86) in bellcrank
(85).
46.
Press bearing (dissimilar metals) (87) in bellcrank
(85) until it bottoms. Use arbor press.
47.
Install two bushings (dissimilar metals) (88 and
89) flanges inward, in right lugs of arms (90 and
91).
48.
Install two bushings (dissimilar metals) (92 and
93) in left lugs of arms (90 and 91).
INSPECT
INSTALL THRUST INPUT BELLCRANK
49.
Install bushing (dissimilar metals) (94), flange
inward, in inboard lug of fitting (95).
50.
Install bushing (dissimilar metals) (96) in
outboard lug of fitting (95).
FLIGHT SAFETY PARTS
This is an installation critical flight
safety part. All aspects of its assembly
and installation must be ensured at
each joint connection and mounting to
the airframe.
Ensure that all bushings are properly
installed (including orientation) in
the output and input clevises of the
bellcrank assembly.
Ensure bellcrank hub bearings are
serviceable and properly installed.
Ensure associated bushings are
properly installed in the adjacent
support assembly.
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.
51.
Position bellcrank (85) in fitting (95) long arm
forward, short arm down.
52.
Install bolt (97), two washers (98 and 99), and
nut (100).
53.
Torque nut (100) to 60 to 90 inch-pounds.
Install cotter pin (101).
54.
Check bolt (97). 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 53.
11-366
