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(h) Install the bolts [9], washers [10] and nuts [11] at the forward end of the carriage
assembly [2].
NOTE: Install the bolts [9] with the heads down.
(i) Install the bolts [12], bolts [16], washers [13], washers [14] and nuts [15] to attach the aft end
of the carriage assembly [2] to the main flap [1].
SUBTASK 27-51-13-410-001
(2) Install the upper skin panel [3] on the main flap [1]:
(a) Apply sealant, A00247 to the mating surface of the upper skin panel [3] and the main flap
[1].
(b) Put the upper skin panel [3] in its position.
(c) Install the bolts [4]:
1) Apply compound, C00528 to the forward and aft rows of holes in the upper skin panel
[3].
2) Install the bolts [4] in the forward and aft rows of holes.
3) Apply sealant, A00247 to the bolts [4] that go in the ribs and stiffeners in the main flap
[1].
4) Install the bolts [4] in the ribs and stiffeners.
G. Put the Airplane Back to Its Usual Condition
SUBTASK 27-51-13-420-002
(1) Do this task: Inboard Trailing Edge Flap Installation, TASK 27-51-11-400-801.
SUBTASK 27-51-13-440-001
(2) Do this task: Trailing Edge Flap System Reactivation, TASK 27-51-00-440-801.
------------------------- END OF TASK ---------------------------
TASK 27-51-13-000-802
4. Inboard Flap Inboard Carriage Removal
(Figure 402)
A. General
(1) This task is applicable to the flap carriages at flap supports No. 4 and 5.
B. References
Reference Title
27-51-00-040-801 Trailing Edge Flap System Deactivation (P/B 201)
27-51-11-000-801 Inboard Trailing Edge Flap Removal (P/B 401)
C. Location Zones
Zone Area
541 Left Wing - Fairing Flap Support No. 4
553 Left Wing - Inboard Flap
641 Right Wing - Fairing Flap Support No. 5
653 Right Wing - Inboard Flap
D. Prepare for the Removal
SUBTASK 27-51-13-040-002
(1) Do this task: Trailing Edge Flap System Deactivation, TASK 27-51-00-040-801.
737-600/700/800/900
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EFFECTIVITY
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SUBTASK 27-51-13-020-003
(2) Do this task: Inboard Trailing Edge Flap Removal, TASK 27-51-11-000-801.
E. Inboard Flap Inboard Carriage Removal
SUBTASK 27-51-13-010-002
(1) Remove the upper skin panel [31] from the main flap [1]:
(a) Remove the bolts [32] that attach the upper skin panel [31] to the main flap [1].
(b) Remove the upper skin panel [31].
SUBTASK 27-51-13-020-004
(2) Remove the secondary torque tube [40] from the main flap [1]:
(a) Remove the retainer [39] from the secondary torque tube [40]:
1) Remove the bolt [41], washer [42], nut [44] and filler [43] that attach the secondary
torque tube [40] to the main flap [1].
2) Remove the retainer [39] from the secondary torque tube [40].
(b) Remove the nuts [49], washers [48], washers [51], filler [53] and bolts [50] that attach the
inboard end of the carriage assembly [34] and the secondary torque tube [40] to the
primary torque tube [38].
(c) Remove the secondary torque tube [40].
SUBTASK 27-51-13-020-005
(3) Remove the carriage assembly [34] from the main flap [1]:
(a) Remove the nuts [46], washers [45], bolts [47], bolt [54] and spacers [52] that attach the
carriage assembly [34], attach plate [37] and rub block [33] to the primary torque tube [38].
(b) Slide the carriage assembly [34] inboard, off of the primary torque tube [38].
------------------------- END OF TASK ---------------------------
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EFFECTIVITY
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Inboard Flap Inboard Carriage Installation
Figure 402 (Sheet 1 of 3)/27-51-13-990-802
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EFFECTIVITY
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Inboard Flap Inboard Carriage Installation
Figure 402 (Sheet 2 of 3)/27-51-13-990-802
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EFFECTIVITY
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Inboard Flap Inboard Carriage Installation
Figure 402 (Sheet 3 of 3)/27-51-13-990-802
737-600/700/800/900
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737-600-700-800-900 AIRCRAFT MAINTENANCE MANUAL飞机维护手册4(105)
