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forward attach assembly [50].
(c) Install the pin [59] in the nut [58].
(d) Install the bolt [52], washer [55] and nut [56] that attach the flap track assemblies [41] to the
forward attach assembly [50].
(e) Install the pin [57] in the nut [56].
SUBTASK 27-51-15-020-013
(4) Connect the link assembly [45] to the structure:
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(a) Put the link assembly [45] in its position on the structure.
(b) Install the bolt [49], washer [47] and nut [48] to attach the link assembly [45] to the structure.
(c) Tighten the nut [48] to 290-510 pound-inches (32.8-57.6 newton-meters).
(d) Install lockwire between the nut [48] and the washer [47].
(e) Install the bolt [46], washer [42] and nut [43] in the bolt [49].
(f) Tighten the nut [43] to 30-60 pound-inches (3.4-6.7 newton-meters).
(g) Install the pin [44] in the nut [43].
SUBTASK 27-51-15-480-007
(5) If it is necessary, remove the adapter, SPL-1733 from the flap track assemblies [41].
SUBTASK 27-51-15-420-009
(6) Do this task: Inboard Flap Inboard Transmission Installation, TASK 27-51-31-400-802.
SUBTASK 27-51-15-420-010
(7) Do this task: Inboard Flap Inboard Skew Mechanism Installation, TASK 27-59-02-400-804.
SUBTASK 27-51-15-420-011
(8) Do this task: Inboard Trailing Edge Flap Installation, TASK 27-51-11-400-801.
SUBTASK 27-51-15-820-003
(9) Do this task: Inboard Trailing Edge Flap Adjustment, TASK 27-51-11-820-801.
SUBTASK 27-51-15-820-004
(10) Do this task: Flap Skew Detection System Adjustment, TASK 27-59-00-820-801.
SUBTASK 27-51-15-640-002
(11) Do this task: Inboard Flap Inboard Flap Track Lubrication, TASK 12-22-51-640-813.
G. Put the Airplane Back to Its Usual Condition
SUBTASK 27-51-15-440-002
(1) Do this task: Trailing Edge Flap System Reactivation, TASK 27-51-00-440-801.
SUBTASK 27-51-15-860-004
(2) 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.
------------------------- END OF TASK ---------------------------
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INBOARD FLAP TRACKS - INSPECTION/CHECK
1. General
A. This procedure contains the task to do an inspection of the flap tracks for the inboard trailing edge
flaps.
TASK 27-51-15-200-801
2. Inboard Flap Outboard Track Inspection
(Figure 601)
A. General
(1) This task gives wear limits for the outboard track on the inboard flap.
(2) this task is applicable to the flap tracks at flap supports No. 3 and 6.
B. References
Reference Title
27-51-15-000-801 Inboard Flap Outboard Track Removal (P/B 401)
27-51-15-400-801 Inboard Flap Outboard Track Installation (P/B 401)
C. Tools/Equipment
Reference Description
STD-1096 Micrometer - Depth, 0-1 Inch, Readable to 1/1000 Inch
STD-1097 Caliper - Vernier, 0-6 Inch, Readable to 1/1000 Inch
D. Location Zones
Zone Area
542 Left Wing - Fairing Flap Support No. 3
642 Right Wing - Fairing Flap Support No. 6
E. Procedure
SUBTASK 27-51-15-020-014
(1) Do this task: Inboard Flap Outboard Track Removal, TASK 27-51-15-000-801.
SUBTASK 27-51-15-020-015
(2) Use these tools to do a check for wear on the part of the inboard flap outboard track:
(a) micrometer (0-1 Inch, readable to 1/1000 Inch), STD-1096
(b) readable to 1/1000 inch vernier 0 - 6 inch caliper, STD-1097.
SUBTASK 27-51-15-020-016
(3) Examine the parts of the inboard flap outboard track (Table 601):
(a) Remove the parts that you will measure.
(b) Measure the parts with a micrometer (0-1 Inch, readable to 1/1000 Inch), STD-1096 or a
readable to 1/1000 inch vernier 0 - 6 inch caliper, STD-1097.
(c) Compare the dimensions you measured with the permitted wear dimensions.
(d) If the parts are not in tolerance, replace or repair the parts.
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Table 601/27-51-15-993-805
NAME OF THE PARTS
THAT ARE IN CONTACT
DIM.
DIAMETER DESIGN LIMITS WEAR LIMITS
MINIMUM
inches/mm
MAXIMUM
inches/mm
PERMITTED
MAXIMUM I.D./
MINIMUM O.D. OF
WORN PART
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737-600-700-800-900 AIRCRAFT MAINTENANCE MANUAL飞机维护手册4(119)
