TM 55-1520-240-23-9
11-77
ASSEMBLE PILOT’S COCKPIT CONTROL ASSEMBLY
(Continued)
11-77
ASSEMBLE YAW BELLCRANK
75.
Press bearing (dissimilar metals) (133) in
bellcrank (134) until it bottoms. Use arbor press.
76.
Install spacer (dissimilar metals) (135) in
bellcrank (134). Press bearing (dissimilar metals)
(136) in bellcrank until it bottoms. Use arbor
press.
77.
Install three bushings (dissimilar metals) (137,
138, and 139), flange inward, in upper lugs of
bellcrank (134).
78.
Install three bushings (dissimilar metals) (140,
141, and 142) in lower lugs of bellcrank (134).
INSPECT
INSTALL YAW BELLCRANK
79.
Install bushing (dissimilar metals) (143), flange
inward, in hole (144) of support (2).
80.
Install bushing (dissimilar metals) (145) opposite
hole (144) in support (2).
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
control box 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.
81.
Install bellcrank (134) in support (2) with arm
(146) up and forward. Remove tag.
82.
Install bolt (147), two washers (148 and 149) and
nut (150) in support (2) and bellcrank (134).
83.
Torque nut (150) to 60 to 90 inch-pounds.
Install cotter pin (151).
84.
Check bolt (147) not 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 83.
INSPECT
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