INSTALL AFT FUSELAGE CONNECTING LINKS
Install only steel connecting links
414C2520-3 and -4. See mandatory
safety-of-flight message CH-47-84-04.
Do not install connecting link unless it
is same length as link being replaced.
If length is not same, connecting
link can cause flight controls to be
Make sure bushings are in bellcranks
before installing bolts or damage will
result to bellcranks.
All bolts installed in flight control
system are self-retaining impedance
bolts. During installation of flight
controls make sure all bolts used are
Remove bolt (1), two washers (2 and 3), and nut
(4) from bellcrank (5).
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.
Position left side connecting link (6) in bellcrank
(5). Remove tag.
Install bolt (1), two washers (2 and 3), and nut
(4). Torque nut to 60 to 90 inch-pounds. Install
cotter pin (7).
Check bolt (1). Bolt shall not rotate with torque
less than 10 inch-pounds. Bolts shall have no
axial looseness. If bolt rotates or is loose, add
washer under nut and repeat step 3.