(2)
If no longer required, remove electrical power from airplane.
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FLAPS 10-DEGREE SWITCH - REMOVAL/INSTALLATION
1. Remove Flaps 10-Degree Switch (S584)
A. Open FLAP SHUTOFF VALVES circuit breaker on panel P6.
B. Remove switch cover from flap control unit (Fig. 401).
C. Remove switch leads from connector.
D. Extract pin to release roller guide.
E. Remove retainer nut from switch and remove switch from control unit.
F. Replace nut, roller guide and pin on switch.
Install Flaps 10-Degree Switch (S584)
A. Remove pin, roller guide and one retainer nut from replacement switch.
B. Position switch in flap control unit and install retainer nut and roller guide. Install pin to secure roller guide.
C. Install switch leads in connector and connect to receptacle.
D. Replace switch cover and close FLAP SHUTOFF VALVES circuit breaker on panel P6.
E. Adjust and test switch (Ref Flaps 10-Degree Switch - Adjustment/Test).
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G43100
Flaps 10-Degree Switch Installation 521
27-88-21 Figure 401 Jan 20/82
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
FLAPS 10-DEGREE SWITCH - ADJUSTMENT/TEST
1. Flaps 10-Degree Switch Adjustment (S584)
A. Prepare for Adjustment
(1)
Provide hydraulic power to system A (Ref 27-81-0 MP).
(2)
Connect electrical power to airplane.
(3)
Check that FLAP SHUTOFF VALVES circuit breaker on panel P6 is closed.
B. Adjust Flaps 10-Degree Switch (S584)
WARNING: WING CONTROL SURFACES ARE FAST ACTING AND CAN CAUSE INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT. ENSURE PERSONNEL AND EQUIPMENT ARE CLEAR DURING OPERATION.
(1)
Retract trailing edge flaps hydraulically with flap control lever to normal retracted position (zero unit detent) and hold for 5 minutes.
(2)
Remove No. 4 jackscrew fairing and record dimension X (Fig. 501) between No. 4 ball screw nut and upstop.
(3)
Position alternate flaps arm switch to ARM.
NOTE: Actuation of alternate flaps arm switch to ARM energizes standby hydraulic pump motor.
CAUTION: FOR GROUND OPERATION, ALTERNATE FLAP DRIVE UNIT IS LIMITED TO 10 MINUTES OPERATION AND 25 MINUTES OFF.
(4)
Position flap control lever to 10-unit detent. Check that trailing edge and leading edge flaps do not respond.
NOTE: Flap control lever is moved to 10-unit detent as a standard procedure to minimize load on flap hydraulic motor when hydraulic system A is pressurized.
(5)
Actuate alternate flaps control switch to DOWN position. Hold switch in this position, extending trailing edge flaps as required until dimension X is 20.25 to 20.40 inches greater than that recorded in step (2) (Ref 27-51-0 A/T).
(6)
Actuate alternate flaps control switch to OFF.
(7)
Remove switch cover from flap control unit located in ceiling area of right wheel well (Fig. 502).
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G43105G43114
Flap Jackscrew 521
27-88-21 Figure 501 May 15/71
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
521 Flaps 10-Degree Switch
Jan 20/82 Figure 502 27-88-21
Page 503
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(8)
Adjust flaps 10-degree switch away from actuating cam until switch actuates.
NOTE: Care must be taken to pre-position switch so that actuation takes place with switch body being moved away from cam.
(9)
Lockwire switch retainer nuts.
(10)
Install switch cover on flap control unit.
(11)
Position alternate flap arm switch to OFF.
CAUTION: LEADING EDGE AND TRAILING EDGE WILL AUTOMATICALLY MOVE TO FLAP CONTROL LEVER POSITION. ENSURE PERSONNEL AND EQUIPMENT ARE CLEAR. 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 3(180)
