TM 55-1520-240-23-9
11-77
ASSEMBLE PILOT’S COCKPIT CONTROL ASSEMBLY
(Continued)
11-77
ASSEMBLE PITCH TRANSFER BELLCRANK
7.
Press bearing (dissimilar metals) (18) in pitch
bellcrank (19) until it bottoms. Use arbor press.
8.
Install spacer (dissimilar metals) (20) in bellcrank
(19).
9.
Press bearing (dissimilar metals) (21) in bellcrank
(19) until it bottoms. Use arbor press.
10.
Install two bushings (dissimilar metals) (22 and
23) flange inward, in upper lugs of arms (24 and
25).
11.
Install two bushings (dissimilar metals) (26 and
27) in lower lugs of arms (24 and 25).
INSPECT
INSTALL PITCH TRANSFER BELLCRANK
12.
Install bushing (dissimilar metals) (28) in support
(29), upper arm, flange inward.
13.
Install bushing (dissimilar metals) (30) in support
(29) lower arm.
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.
14.
Position bellcrank (19) in support (29), long arm
(25) up. Install bolt (31), two washers (32 and
33), and nut (34) in support.
15.
Torque nut (34) to 60 to 90 inch-pounds. Install
cotter pin (35).
16.
Check bolt (31). 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 15.
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