INBOARD TRAILING EDGE FLAP - ADJUSTMENT/TEST
1. Inboard Trailing Edge Flap Adjustment
A. General
(1)
The inboard trailing edge flap assembly consists of foreflap, midflap, aftflap, hinged flap, aftflap drive boom and aftflap drive mechanism. Adjustment of the inboard trailing edge flap consists of adjusting the aftflap.
(2)
The inboard trailing edge flap may be adjusted while installed on the airplane or before installation. If adjustment is done before installation, the rigging pins must remain in the boom until the flap is installed and the boom is connected to wing structure.
B. Equipment and Materials
(1) Rigging Pins F-5 and F-6, 0.248 +0.000/-0.002 inch diameter, 3.7 +0.25-inches long (MS20392-3)
NOTE: Rigging pins are a part of Kit, F70207-61, or -84.
C. Adjust Inboard Trailing Edge Flap
(1)
If adjustment is being performed with flap installed, remove inboard flap track fairing (Ref 27-51-141, Inboard Flap Track Fairings).
(2)
Install rigging pins F-5 and F-6 through inboard side of boom (12, Fig. 501) trapping boom roller (11) between pins. If flap is installed on airplane, pressurize hydraulic system A (Ref 27-51-0 MP), retract flaps, and depressurize hydraulic system A before inserting rigging pins.
(3)
Remove access panels from lower surface of midflap.
587
Feb 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-12 Page 501
G12593G42445 A06651
Inboard Trailing Edge Flap Adjustment 500
27-51-12 Figure 501 (Sheet 1) Feb 15/69
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Inboard Trailing Edge Flap Adjustment
May 15/81 Figure 501 (Sheet 2) 27-51-12
Page 503
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Inboard Trailing Edge Flap Adjustment 589
27-51-12 Figure 501 (Sheet 3) Feb 20/92
Page 504
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(4)
Check position of bellcrank (2) and cam arm (6). With clutch (3) engaged, bellcrank and arm will form an angle of approximately 157 degrees. If clutch is not engaged, push bellcrank to position illustrated so that clutch engages.
NOTE: A load of 350 pounds at outboard end of bellcrank is required to disengage clutch. A relatively light force is required to re-engage clutch. If clutch is disengaged in normal operation, next operation will cause re-engagement.
(5)
Adjust boom cables (4 and 5), at adjusting screws (13 and 14), to position cam arm roller
(7)
0.42 +0.03 inch from forward end of slot as shown (Ref AMM 27-51-61 R/I).
(a)
If difficulty in obtaining 0.42-inch dimension is experienced, a rigging block of 2.25-inch plastic (or equivalent) shaped to curvature of cam slot and cut to required positioning dimension can be made.
(b)
Position rigging block in cam slot with cam roller against block, then tape block to cam drum.
(6)
Adjust boom cables to tension of 100 +10 pounds while maintaining dimension obtained in step (5) (Ref AMM 27-51-61 R/I).
NOTE: Cables should be adjusted to 100-pound tension at temperature of approximately 70°F. As temperature decreases, tension should be decreased and as temperature increases, tension should be increased. However, 10-pound tolerance should not be exceeded (AMM 27-51-01, Fig. 501).
(7)
Adjust cables (1 and 9) at turnbuckles so that difference between dimension X and dimension Y does not exceed 0.06 inch. Dimensions should be as near equal as possible.
(8)
Maintain dimensions X and Y and tighten cables (1 and 9) to tension of 200 +20 pounds.
NOTE: Cable tension should be 200 pounds at 70°F. Tension may be increased as temperature increases and decreased as temperature decreases. However, tension should not be decreased to less than 180 pounds nor increased to more than 220 pounds.
(9)
Adjust pushrods (8 and 10) to obtain 16.00 +0.12 inch dimension between midflap lower skin and aftflap trailing edge as shown in section A-A. Measure dimension at aft flap pushrod locations. When adjustment is obtained, tighten checknut to engage key and install lockwire.
(10)
Check seal at leading edge of aftflap. When fully retracted, aftflap leading edge shall be
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