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4) Put the shims [5] in their location between the aft link fitting [1] and the outboard
carriage [6].
NOTE: The maximum total thickness of the shims [5] is 0.50 inch (12.7 mm). The
minimum total thickness of the shims [5] is 0.00 inch.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-09-71
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BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
5) Apply compound, C00913 to the shank and threads of the bolts [2].
NOTE: Make sure the bolts [2] are the correct length for installation with the new shim
thickness.
6) Install the bolts [2], washers [3] and nuts [4] that attach the aft link fitting [1] to the
outboard carriage [6].
(b) At the inboard carriage [11], change the thickness of the shims [5]:
1) Remove the nuts [10], washers [9] and bolts [8] that attach the aft link fitting [7] to the
inboard carriage [11].
2) Add or remove shims [5] between the aft link fitting [7] and the inboard carriage [11] to
get the correct shim thickness.
3) Apply sealant, A00247 to the mating surfaces of the shims [5].
4) Put the shims [5] in their location between the aft link fitting [7] and the inboard carriage
[11].
NOTE: The maximum thickness of the shims [5] is 0.50 inch (12.7 mm). The minimum
thickness of the shims [5] is 0.00 inch.
5) Apply compound, C00913 to the shank and threads of the bolts [8].
6) Install the bolts [8], washers [9] and nuts [10] that attach the aft link fitting [7] to the
inboard carriage [11].
SUBTASK 27-09-71-940-001
(5) Put the airplane back to its usual condition:
(a) Do this task: Trailing Edge Flap System Reactivation, TASK 27-51-00-440-801.
(b) Retract the trailing edge flaps to the retracted position. To retract the flaps, do this task:
Retract the Trailing Edge Flaps, TASK 27-51-00-860-804.
(c) Do a check of the fair and alignment of the aft flap [51] with the main flap. To check the fair
and alignment, do this task: Outboard Aft Flap Installation, TASK 27-51-22-400-801.
NOTE: Use a tolerance for the mismatch between the main flap and the aft flap of 0.00
±0.030 inches (1.524 mm). This tolerance is smaller than the normal adjustment
tolerance. This increases the effect of the lateral trim adjustment.
(d) Do a check of the clearances between the aft fairings, and the flap:
1) To check the outboard fairing on the outboard flap, do this task: Outboard Flap
Outboard Support Fairing Adjustment, TASK 27-51-28-820-801.
2) To check the inboard fairing on the outboard flap, do this task: Outboard Flap Inboard
Support Fairing Adjustment, TASK 27-51-28-820-802.
(e) Do a check of the clearances between the spoilers and the flap. To check the clearances,
do this task: Flight Spoiler Adjustment, TASK 27-61-00-820-803.
I. Lateral Trim Correction for the Flaps Extended Conditions
NOTE: Use these steps if the aileron trim necessary to keep level flight is not in the limits with the
flaps extended. This change will primarily effect the trim at the flaps 40 position, with less
effect at the other flap positions. This change will not have an affect on the lateral trim with
the flaps retracted. This procedure uses the adjustment fitting to change the length of the
bellcranks on the carriages for the outboard flap.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-09-71
Page 508
Jun 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
SUBTASK 27-09-71-970-003
(1) Use the graphs to find the total length change of the bellcrank [34] necessary to correct the
lateral trim error with the flaps extended (Figure 503).
NOTE: You will use the nuts [32] on the adjustment fitting [31] at the end of the bellcrank [34] to
change the length of the bellcrank [34].
SUBTASK 27-09-71-970-004
(2) Find the dimension and direction to adjust the nuts [32] for the adjustment fittings [31] on the
bellcranks [34]:
NOTE: The number of turns of the nuts [32] for the adjustment fittings [31] on one wing should
be the same, but in the opposite direction of the nuts [32] on the other wing.
(a) Flight test condition; Right Trim:
NOTE: Right aileron trim indicates a left wing heavy condition.
1) Decrease the length of the bellcranks on the right wing by the 1/2 the dimension shown
in the graph.
2) Increase the length of the bellcranks on the left wing by the 1/2 the dimension shown in
the graph.
(b) Flight test condition; Left Trim:
NOTE: Left aileron trim indicates a right wing heavy condition.
1) Decrease the length of the bellcranks on the left wing by the 1/2 the dimension shown in
　
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