INSTALL TUNNEL CONTROL ARMS (Continued)
INSTALL CONTROL ARMS AT STA 201.00, 241.00,
281.00, 321.00, AND 361.00
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 bearings are properly
installed and staked at each end of
the walking beam.
Ensure walking beam hub bearings
are serviceable, secure and properly
Ensure the locating pads on the
walking beam forging are installed
facing up at all locations.
Ensure the slip bushings are installed
when attaching the adjacent control
rods at each end of the walking beam
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.
Bellcrank must be positioned as
indicated, with side marked TOP
facing up; otherwise, serious damage
to components can occur.
Position control arm (15) on idler (16) with pads
(17) and the word TOP up.
Install bolt (18), two washers (19 and 20), and
nut (21). Torque nut 85 to 125 inch-pounds.
Install cotter pin (22).
Check bolt (18). Bolt shall not rotate with torque
less than 10 inch-pounds. Bolt shall have no
axial looseness. If bolt rotates or is loose, add
washer under nut and repeat step 13.