6. Restore Airplane to Normal Configuration
A. Remove hydraulic power from system A. Refer to 27-81-0.
B. Check hydraulic reservoirs and service if required. Refer to Chapter 12, Hydraulic Servicing.
C. Install lower pan on flap control unit.
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27-81-81 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
LEADING EDGE FLAP AND SLAT CONTROL VALVE - ADJUSTMENT/TEST
1. Leading Edge Flap and Slat Control Valve Adjustment
A. Equipment and Materials
(1) Rigging pin, F-1 - 0.311 +0.000/-0.002-inch diameter x 1.65 +0.06-inch length (MS20392-4)
NOTE: Rigging pin is part of kit F70207-61 or -84.
B. Prepare Leading Edge Flap and Slat Control Valve for Adjustment
(1)
Pressurize hydraulic system A (Ref 27-81-0 MP).
(2)
Ensure that flap control lever is in FLAP UP detent.
(3)
Wait 5 minutes then depressurize hydraulic systems (Ref 27-81-0 MP).
(4)
Remove lower pan from flap control unit.
(5)
Install rigging pin F-1 in flap control unit (Fig. 501, view 1).
C. Adjust Leading Edge Flap and Slat Control Valve
(1) Check that valve slide and indexing surface of control valve align within + 0.010 inch (Fig. 501, detail A). If not, adjust leading edge link as follows:
(a)
Break lockwire and loosen checknut.
(b)
Remove rod end bolt of cam follower arm.
(c)
Turn rod end in one-half turn increments to obtain adjustment.
(d)
Install rod end bolt and check that valve slide and indexing surface align within +
0.010 inch.
(e)
Install rod end bolt with washer and locknut.
(f)
Tighten checknut and install lockwire.
(g)
Ensure that thread engagement of rod end is within limits. (See view 1.)
(h)
Remove rigging pin F-1.
(i)
Install lower pan on flap control unit.
(j)
Test control valve per par. 2.
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Feb 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-81-81 Page 501
G43235G43238
Leading Edge Flap and Slat Control Valve Adjustment 500
27-81-81 Figure 501 (Sheet 1) Aug 15/67
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Leading Edge Flap and Slat Control Valve Adjustment
Aug 15/67 Figure 501 (Sheet 2) 27-81-81
Page 503
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
2. Leading Edge Flap and Slat Control Valve Test
A. Test Leading Edge Flap and Slat Control Valve
(1)
Pressurize hydraulic system A. Refer to 27-81-0.
(2)
Position flap control lever in FLAP UP detent.
(3)
Check that each flap and slat is in UP position and faired with wing structure.
(4)
Position flap control lever in 1-unit detent.
(5)
Check that all leading edge flaps and slats move to intermediate position.
(6)
Position flap control lever in 5-unit detent.
(7)
Leading edge flaps and slats shall not move.
(8)
Position flap control lever in 10-unit detent.
(9)
All slats shall extend fully.
(10)
Position flap control lever in 1-unit detent.
(11)
All slats shall retract to intermediate position.
(12)
Position flap control lever in FLAP UP detent.
(13)
All leading edge flaps and slats shall retract to UP position.
(14)
Depressurize hydraulic systems. Refer to 27-81-0.
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LEADING EDGE STANDBY DRIVE SHUTOFF VALVE - REMOVAL/INSTALLATION
1. General
A. The leading edge standby drive shutoff valve and standby rudder actuator shutoff valve are identical cartridge units. The leading edge standby drive shutoff valve is on the right portion of the modular package and the standby rudder actuator shutoff valve is on the left portion of the modular package. This procedure provides instructions for replacement of the leading edge standby drive shutoff valve. The complete cartridge unit, motor and valve, may be replaced or the motor only may be replaced without removing the valve body from the modular package. The motor drive and valve cam are indexed to aid in correct motor installation.
2. Removal/Installation Standby Drive Shutoff Valve
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