TM 55-1520-240-23-9
11-130
INSTALL YAW VISCOUS DAMPER CONNECTING LINK
(Continued)
11-130
Bushings must be in links before
installing bolts; otherwise, damage to
components will result.
NOTE
Impedance bolts are installed in flight
control connections. These bolts are
self-retaining and require a special
nut and torque (Task 1-13).
1.
Remove nut (1), two washers (2 and 3), and bolt
(4) from magnetic brake arm (5), and spring
assembly (6).
FLIGHT SAFETY PARTS
This is an installation critical flight
safety part. All aspects of its assembly
and installation must be ensured.
Ensure bearing is properly staked.
Ensure flanged and straight slip
bushings are installed at clevis end
of link 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
secondary linkage will degrade
aircraft control. Missing components
will cause loss of control.
2.
Position yaw viscous damper connecting link (7)
yoke end (8), between spring (6) and inboard
lug (9) of arm (5). Install bolt (4), two washers
(3 and 2), and nut (1).
3.
Torque nut (1) to 30 to 45 inch-pounds. Install
cotter pin (10).
4.
Remove nut (11), two washers (12 and 13), and
bolt (14) from damper arm (15).
5.
Position link (7) on arm (15). Move arm to align.
Install bolt (14), two washers (13 and 14) and nut
(11). Remove tag from link.
6.
Torque nut (11) to 15 to 25 inch-pounds. Install
cotter pin (16).
7.
Check two bolts (4 and 14). 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 (2 or 12) under nut (1 or 11)
and repeat step 3 or 6.
INSPECT
FOLLOW-ON MAINTENANCE:
Perform yaw control operational check (TM
55-1520-240-T).
Install closet backup panel (Task 2-2).
Install closet acoustic blanket (Task 2-108).
END OF TASK
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