INSTALL PITCH OR ROLL VISCOUS DAMPERS
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
Ensure that the correct damper
is installed in the pitch or roll
axis. Incorrect axis orientation will
adversely affect force feel damping
characteristics of the flight control
Ensure the proper damper arm
assembly is installed. Arm assembly
has shear rivets sized to specific load
requirements in the event of a damper
Ensure all hardware mounting the
damper assembly to the pallet
assembly is secure and that there is
no evidence of loose pallet inserts.
Loose attachments within flight control
secondary linkage will degrade
aircraft control, missing components
may cause loss of control.
Bushings must be in link before
installing bolt; otherwise, damage to
component will result.
Impedance bolts are installed in flight
control connections. These bolts are
self-retaining and require a special
nut and torque (Task 1-13).
Position damper (5) on pallet (9), arm (1) inboard.
Install two bolts (10) and washers (11) in damper.
Torque bolts (10) to 23 inch-pounds.
Remove nut (12), two washers (13 and 14), and
bolt (15) from link (16).
Position arm (1) in link (16). Install bolt (15), two
washers (14 and 13) and nut (12) in link and arm.
Torque nut (12) to 15 to 25 inch-pounds. Install
cotter pin (17).
Check bolt (15). 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 (13) under nut (12) and repeat step 10.
Perform pitch or roll control operational check (TM
Install closet backup panel (Task 2-2).
Install closet acoustic blanket (Task 2-108).
END OF TASK