(4)
Remove four mounting screws (figure 401) attaching valve motor to valve. Remove valve motor from valve.
B. Install Flap Bypass Valve Motor
(1)
On replacement of valve motor, move manual override lever to position No. 2.
(2)
Position valve motor on valve and engage motor drive with valve cam.(See figure 401.)
(3)
Install the four mounting screws.
(4)
Install lockwire on mounting screws.
(5)
Install electrical connector on valve motor.
(6)
Test bypass valve. See Trailing Edge Flap Bypass Valve – Adjustment/Test.
500
Aug 15/67 27-51-181
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Page 405
TRAILING EDGE FLAP BYPASS VALVE - ADJUSTMENT/TEST
1. Test Flap Bypass Valve
A. Connect electrical power to airplane.
B. Pressurize hydraulic system A (Ref 27-51-0 MP).
C. Open TE ALT FLAP DRIVE MOTOR circuit breaker on circuit breaker panel P6.
D. Close FLAP VALVES circuit breaker to energize alternate flap drive system.
E. Position alternate flap master arming switch to ARM.
F. Position flap control lever to FLAP DOWN (40-unit) detent and check that flaps do not extend.
G. Position alternate flap master arming switch to OFF. Check that flaps extend.
H. Position flap control lever to FLAP UP detent to retract flaps.
I. Check bypass valve hydraulic fittings for leakage.
J. Depressurize hydraulic system A (Ref 27-51-0).
K. Close TE ALT FLAP DRIVE MOTOR circuit breaker on circuit breaker panel P6.
L. Determine whether there is any further need for electrical power on airplane. If not, disconnect electrical power.
500
Jun 20/92 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-181 Page 501
FLAP CONTROL QUADRANT - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Pressure Sealant - BMS 5-19, class A
B. Ball and Roller Bearing Grease - MIL-G-25760
2. Prepare Flap Control Quadrant for Removal
A. Gain access to flap control quadrant through passenger cabin floor or through aft cargo compartment.
(1) To gain access through passenger cabin floor:
(a) Remove necessary interior equipment, carpets and floor panel for access to flap control quadrant which is located outboard of seat tracks on right side o f airplane, 20 inches aft of main gear downlock viewer window. Refer to Chapter 25, Carpets, and Chapter 56, Main Gear Downlock Viewer Window.
NOTE: Floor panel is 60 inches long and begins 14 inches forward of flap control quadrant.
(2) To gain access through aft cargo compartment:
(a) Remove forward right ceiling panel in aft cargo compartment. Refer to Chapter 25, Cargo Compartment Ceiling Lining.
B. Provide system A hydraulic power. Refer to 27-51-0, Trailing Edge Flaps - Maintenance Practices.
C. Position flap control lever to FLAP UP detent to retract flaps.
D. Remove system A hydraulic power and depressurize hydraulic reservoirs. Refer to 27-51-0.
E. Remove flap control unit. Refer to 27-51-201, Flap Control Unit - Removal/Installation.
F. Open lower nose compartment access door. Refer to Chapter 12, Access Doors and Panels.
3. Remove Flap Control Quadrant
A. Remove turnbuckle locking clips and disconnect WFA and WFB turnbuckles. Tag cables and clamp to minimize slack.
500
Feb 15/73 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-191 Page 401
B. Disconnect cables from flap control quadrant. Tag cables and flap control quadrant. Clamp cables to minimize slack (Fig. 401).
C. If access is through aft cargo compartment:
(1)
Remove bolt securing quadrant segment to shaft and remove quadrant segment from airplane.
(2)
Slide shaft downward and remove from airplane.
D. Remove eight screws and three bolts to disconnect quadrant support.
E. Lift quadrant support away from pressure sealant on mounting surface and remove from airplane.
4. Prepare Flap Control Quadrant for Installation
A. Use a wood or phenolic scraper to remove pressure sealant from wheel well ceiling in area of flap control quadrant.
B. Apply a brush coat of pressure sealant in and around the upper surface of the 15 holes in wheel well ceiling.
C. If access is through aft cargo compartment, remove bolt which secures quadrant segment to shaft and remove shaft from quadrant support.
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(55)
