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Extend the Trailing Edge Flaps, TASK 27-51-00-860-803.
3) Do this task: Trailing Edge Flap System Deactivation, TASK 27-51-00-040-801.
4) Adjust the length of the aft flap drive rod [101]:
NOTE: For each 90 degree turn of the aft flap drive rod [101], the trailing edge of the
aft flap will move 0.04 inches (1.02 millimeters).
a) Loosen the nuts [102] on the aft flap drive rod [101].
b) Adjust the length of the aft flap drive rod [101].
c) Tighten the nuts [102].
d) Install lockwire on the nuts [102].
5) Do this task: Trailing Edge Flap System Reactivation, TASK 27-51-00-440-801.
6) Retract the flaps to the retracted position, do this task: Retract the Trailing Edge Flaps,
TASK 27-51-00-860-804.
7) Do this task: Trailing Edge Flap System Deactivation, TASK 27-51-00-040-801.
8) Make sure the distance from the trailing edge of the aft flap [99] to the trailing edge of
the upper cove panel [100] on the inboard flap [71] is in the limit.
SUBTASK 27-09-71-940-003
(13) Put the airplane back to its usual condition:
(a) Do this task: Trailing Edge Flap System Reactivation, TASK 27-51-00-440-801.
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(b) Retract the flaps to the retracted position, do this task: Retract the Trailing Edge Flaps,
TASK 27-51-00-860-804.
K. Inboard Flap Bullnose Seal Position Adjustment
NOTE: Use these steps if the change in the aileron trim necessary to keep level flight with the flaps
extended to 40-units condition is not in the limit. The compression of the bullnose seals
should be symmetric for flaps 40 lateral trim. Asymmetric compression of the bullnose
seals on the inboard flap can cause the aftflap bellcrank adjustment on the outboard flap to
be not effective.
NOTE: The bullnose seals are not installed on adjustable retainers, therefore it is necessary to
create shims to fit under the seals.
SUBTASK 27-09-71-970-018
(1) Find the appropriate thickness and location of the shims (Figure 508):
(a) Extend the trailing edge flaps to the 40-unit position. To extend them, do this task: Extend
the Trailing Edge Flaps, TASK 27-51-00-860-803.
(b) Do this task: Trailing Edge Flap System Deactivation, TASK 27-51-00-040-801.
(c) On the left and right wings, measure and record the distance between the main flap
structure, and the wing to body fairing.
NOTE: Measure the distance at the edge of the structure near the lower part of the
bullnose seal.
(d) The difference between the two measurements is the approximate thickness of shim that is
required.
NOTE: Do not install shims thicker than 0.25 inch.
(e) Flight test condition; Right Trim at the 40-unit flap condition:
NOTE: Right aileron trim indicates a left wing heavy condition.
1) Install the shim under the bullnose seal on the left main flap.
(f) Flight test condition; Left Trim at the 40-unit flap condition:
NOTE: Left aileron trim indicates a right wing heavy condition.
1) Install the shim under the bullnose seal on the right main flap.
(g) The effect of the shim on the lateral trim with the flaps in the 40-unit position will be
approximately 0.4 units of trim for each 0.1 inch of shim added.
NOTE: For example, a 0.2 inch shim on the left bullnose seal will reduce the right lateral
trim requirement by 0.8 units.
SUBTASK 27-09-71-860-015
(2) Retract the trailing edge flaps to the 15-unit position. To retract them, do this task: Retract the
Trailing Edge Flaps, TASK 27-51-00-860-804.
SUBTASK 27-09-71-040-006
(3) Do this task: Trailing Edge Flap System Deactivation, TASK 27-51-00-040-801.
SUBTASK 27-09-71-480-005
WARNING: MAKE SURE THE DOWNLOCK PINS ARE INSTALLED ON ALL THE LANDING GEAR.
WITHOUT THE DOWNLOCK PINS, THE LANDING GEAR CAN RETRACT AND CAUSE
INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(4) If the downlock pins are not installed in the nose and main landing gear, do this task: Landing
Gear Downlock Pins Installation, TASK 32-00-01-480-801.
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SUBTASK 27-09-71-020-003
(5) Remove the bullnose seal [107] (Figure 507):
(a) Move the torque tube door [94] up and inboard to get access to the bullnose seal [107].
(b) Remove the bolts [108] and washers [109] that attach the bullnose seal [107] to the inboard
flap [71].
(c) Remove the bullnose seal [107] from the inboard flap [71].
　
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