ASSEMBLE PILOTS COCKPIT CONTROL ASSEMBLY
ASSEMBLE ROLL INPUT BELLCRANK
Position nut (102) in retainer (103), flat side to
Install nut (102) and retainer (103) in hole (104)
of bellcrank (105), nut forward.
Install bushing (dissimilar metals) (106) in
forward end of bellcrank (105).
Install two bushings (dissimilar metals) (107 and
108) in aft end of bellcrank (105).
Install bushing (dissimilar metals) (109) flange
inward, in right side of bellcrank (105).
Install bushing (dissimilar metals) (110) in left
side of bellcrank (105).
Install bushing (dissimilar metals) (111) flange
inward, in aft lug of arm (112).
Install bushing (dissimilar metals) (113) in
forward lug of arm (112).
INSTALL ROLL INPUT BELLCRANK
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 all bushings are properly
installed (including orientation) at the
following locations: at the output clevis
of the bellcrank, at both the forward
and aft ends along the roll pivot axis,
and on both sides at the pivot axis of
the mating socket assembly.
Ensure proper barrel nut and retainer
are installed in cavity at forward end
of the bellcrank.
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.
Working through access (3), position bellcrank
(105) in support (2), arm (112) down and forward.
Install washer (114) and bolt (115) through aft
end of bellcrank (105) and bearing (5).
Install washer (116) and nut (117) on bolt (115).
Do not tighten nut at this time.
Working through access (118), slide bolt (119)
through bearing (1) and install in bellcrank (105).
Torque bolt to 75 inch-pounds.
Torque nut (117) to 60 to 90 inch-pounds.
Install cotter pin (120).