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A00247 Sealant - Pressure And Environmental - Chromate
Type
BMS5-95
C00528 Compound - Corrosion Preventive, Petroleum Hot
Application (Soft Film)
MIL-C-11796,
Class III
C00913 Compound - Nondrying Resin Mix Corrosion
Inhibiting Material
BMS3-27
C. Expendables/Parts
AMM Item Description AIPC Reference AIPC Effectivity
6 Flap assembly 27-51-21-01-055 GUN ALL
27-51-21-01-060 GUN ALL
20 Pin 57-42-51-02-155 GUN 001-028, 101-121,
155-157, 201-999
D. Location Zones
Zone Area
567 Left Wing - Outboard Flap
667 Right Wing - Outboard Flap
E. Access Panels
Number Name/Location
571AB Lower Outboard Fixed Trailing Edge Access Panel at Deflector Rib
671AB Lower Outboard Fixed Trailing Edge Access Panel
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-21
Page 501
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
F. Prepare for the Adjustment
SUBTASK 27-51-21-860-003
(1) If the trailing edge flaps are not in the retracted position, do this task: Retract the Trailing Edge
Flaps, TASK 27-51-00-860-804.
SUBTASK 27-51-21-040-002
(2) Do this task: Trailing Edge Flap System Deactivation, TASK 27-51-00-040-801.
SUBTASK 27-51-21-010-003
(3) Remove the aft fairings from the flap supports:
(a) Do this task: Outboard Flap Outboard Support Aft Fairing Removal,
TASK 27-51-28-000-802.
(b) Do this task: Outboard Flap Inboard Support Aft Fairing Removal,
TASK 27-51-28-000-804.
SUBTASK 27-51-21-020-007
(4) Remove the outboard deflection control roller assembly [2] from the rib [1] (Figure 501):
(a) Remove or open the applicable access panels below the roller assembly [2]:
Number Name/Location
571AB Lower Outboard Fixed Trailing Edge Access Panel
at Deflector Rib
671AB Lower Outboard Fixed Trailing Edge Access Panel
(b) Remove the bolts [3] and washers [4] that attach the deflection control roller assembly [2]
to the rib [1].
(c) Remove the deflection control roller assembly [2] from the rib [1].
G. Outboard Trailing Edge Flap Adjustment
NOTE: There is no mismatch, or alignment dimension to fixed structure that the flap is adjusted to
meet. The flap shims can be changed from the nominal to meet lateral trim tolerances.
SUBTASK 27-51-21-220-006
(1) If you installed a different flap, then adjust the thickness of the shims [65] to the same thickness
as the original flap.
NOTE: The thickness of the shims [65] on the original flap may have been adjusted for lateral
trim per (TASK 27-09-71-820-801).
(a) If you do not know the original thickness of the shims [65], then change the thickness to the
nominal dimension.
NOTE: The nominal thickness of the shims [65] is 0.25 inch (6.35 mm).
SUBTASK 27-51-21-210-001
(2) On the inboard and outboard carriage [43], make sure three of the four main track rollers [44]
touch the flap track [45] (Figure 502).
NOTE: If you cannot get three of the four main track rollers [44] to touch, it is permitted for the
two forward rollers, or the two aft rollers to touch.
SUBTASK 27-51-21-820-002
(3) If it is necessary, then adjust the position of the main flap assembly [6] (Figure 503):
NOTE: To adjust the position of the main flap assembly [6], you will change the thickness of the
shims [65] at the aft link fitting [61] and aft link fitting [67] on the inboard and outboard
carriages.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-21
Page 502
Jun 10/2005
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(a) Do this task: Trailing Edge Flap System Reactivation, TASK 27-51-00-440-801.
(b) 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.
(c) Do this task: Trailing Edge Flap System Deactivation, TASK 27-51-00-040-801.
(d) At the outboard carriage [66], change the thickness of the shims [65]:
1) Remove the nuts [64], washers [63] and bolts [62] that attach the aft link fitting [61] to the
outboard carriage [66].
2) Add or remove shims [65] between the aft link fitting [61] and the outboard carriage [66]
to get the correct shim thickness.
3) Apply sealant, A00247 to the mating surfaces of the shims [65].
4) Put the shims [65] in their location between the aft link fitting [61] and the outboard
carriage [66].
NOTE: The nominal thickness of the shims [65] is 0.25 inch (6.35). The maximum
thickness of the shims [65] is 0.50 inch (12.7 mm). The minimum thickness of
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737-600-700-800-900 AIRCRAFT MAINTENANCE MANUAL飞机维护手册4(135)
