TM 55-1520-240-23-9
11-245
INSTALL AFT FUSELAGE CONNECTING LINKS
(Continued)
11-245
5.
Remove bolt (8), two washers (9 and 10), and
nut (11) from bellcrank (12).
6.
Position right side connecting link (13) in
bellcrank (12). Remove tag.
7.
Install bolt (8), two washers (9 and 10), and nut
(11). Torque nut to 60 to 90 inch-pounds. Install
cotter pin (14).
8.
Check bolt (8). 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 7.
NOTE
Procedure is same for forward end of
left and right connecting link. Right
side connecting link at sta. 444.5 is
shown here.
9.
Remove bolt (15), two washers (16 and 17), and
nut (18) from bellcrank (19).
FLIGHT SAFETY PARTS
This is an installation critical flight
safety part. All aspects of its assembly
and installation must be ensured.
Ensure that both rod end jam nuts are
installed and torqued.
Ensure that the rivet through the fixed
rod end bearing is secure.
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.
10.
Position connecting link (13) in bellcrank (19).
11.
Install bolt (15), two washers (16 and 17), and
nut (18). Torque nut to 60 to 90 inch-pounds.
Install cotter pin (20).
12.
Check bolt (15). 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 11.
NOTE
If connecting links are changed in
length, perform neutral rig check
(Task 11-33).
INSPECT
11-955
