NOTE: The indicator dial should be tapped with the fingers to remove friction error.
(3)
At number four and five jackscrews check that angular clearance between jackscrew upstops is 170 to 190 degrees (1/2 turn +10 degrees) turn (Fig. 501).
CAUTION: MAXIMUM ALLOWABLE ANGULAR CLEARANCE IS 1/4 TO 5/6 TURN. A VALUE FOR (X1) OUTSIDE THIS RANGE MAY CAUSE DAMAGE DURING FLAP OPERATION. PREVIOUS LATERAL TRIM CORRECTIONS SHOULD BE RETAINED.
(4)
At number four jackscrew measure dimension X1. Record value.
(5)
Position flap control lever in FLAP DOWN (40-unit) detent.
500
May 15/80 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-221 Page 501
G25557
Flap Transmission Upstop Clearance 500
27-51-221 Figure 501 Aug 15/67
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(6)
Check that both flap position indicator pointers point into the 40-unit black area on indicator dial.
(7)
At number four jackscrew measure dimension X2. Using dimension X1 from step (5) perform the necessary subtraction to determine that X2 – X1 dimension is between 29.82 inches and 30.48 inches.
(8)
Position flap control lever in FLAP UP detent to retract flaps.
(9)
Check alternate trailing edge flap operation.
(a)
Position alternate flap switch to ARM (to energize standby hydraulic pump motor).
(b)
Position flap control lever in FLAP DOWN (40-unit) detent.
NOTE: Flap control lever is moved to FLAP DOWN to minimize load on flap hydraulic motor when hydraulic system A is pressurized.
(c)
Position alternate flap drive switch to DOWN and check that trailing edge flaps move in extend direction.
(d)
Position alternate flap drive switch to UP and check that flaps return to retracted position.
(e)
Position alternate flap drive switch to OFF, flap control lever in FLAP UP detent, and alternate flap arming switch to OFF.
NOTE: With hydraulic system A pressurized, leading edge devices will retract.
C. Restore Airplane to Normal Configuration
(1)
With flaps retracted, depressurize hydraulic system A (Ref 27-51-0).
(2)
Install inboard flap track fairings (Ref 27-51-141).
500
Nov 01/74 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-221 Page 503
FLAP POWER UNIT - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Flap Drive Adapter - F70300-1
B. Hydraulic Fluid -MIL-H-5606 (Ref 20-30-21)
C. Rigging Pin F-1 - 0.311 +0.000/-0.002 inch diameter 2.35 +0.06 inches long (MS20392-4)
NOTE: Rigging pin is a part of kit F70207-61 or -84.
D. Grease - MIL-G-23827 (Ref 20-30-21)
2. Prepare Flap Power Unit for Removal
A. Pressurize hydraulic system A (Ref 27-51-0 MP).
B. Position flap control lever to FLAP UP detent to retract flaps.
NOTE: If flap power unit is jammed, it will be necessary to disconnect torque tubes from both sides of power unit and manually rotate torque tubes to retract flaps.
C. Depressurize hydraulic system A and system A reservoir (Ref 27-51-0 MP).
D. Open TE ALT FLAP DRIVE MOTOR circuit breaker on circuit breaker panel P6.
E. Remove inboard flap track fairings (Ref 27-51-141 R/I).
3. Remove Flap Power Unit
A. Disconnect electrical connector from flap alternate drive unit (Fig. 401).
B. Remove lower pan on flap control unit (Fig. 402).
C. Install rigging pin F-1 in flap control unit.
587
Feb 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-222 Page 401
G25583G25846 G25577
Flap Power Unit Installation 535
27-51-222 Figure 401 (Sheet 1) Oct 20/87
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535 Flap Power Unit Installation
May 15/72 Figure 401 (Sheet 2) 27-51-222
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Flap Control Unit Adjustment 535
27-51-222 Figure 402 May 15/72
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D. Remove screws securing torque tube sleeves to power unit spline couplings and disconnect torque tubes (Fig. 401).
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