INSTALL THRUST OR PITCH VISCOUS DAMPER CONNECTING LINK
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.
Procedure is same to install thrust or
pitch viscous damper connecting link.
Thrust connecting link is shown here.
Attaching bolts, washers, and nuts will
be temporarily installed after removing
Position thrust damper connecting link (1) on
damper arm (2), with clevis end (3) to arm. Install
bolt (4), two washers (5 and 6), and nut (7).
Torque nut (7) to 15 to 25 inch-pounds. Install
cotter pin (8).
Position link (1) in bellcrank (9), move arm (2) to
align. Install bolt (10), two washers (11 and 12)
and nut (13). Remove tag from link.
Torque nut (13) to 30 to 45 inch-pounds. Install
cotter pin (14).
Check two bolts (4 and 10). 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 under nut and repeat steps 2