LEADING EDGE FLAP FLOW LIMITING VALVE - ADJUSTMENT/TEST
1. Test Flap Flow Limiting Valve
A.  Connect electrical power to airplane.
B.  Close FLAP VALVES circuit breaker on P6 panel.
C.  Open TE ALT FLAP DRIVE MOTOR circuit breaker on P6 panel.
D.  Pressurize hydraulic system A. Refer to 27-81-0, Leading Edge Flaps and Slats - Maintenance Practices.
E.  Position flap control lever to FLAPS UP detent.
F.  Position alternate flap master arming switch to ARM.
G.  Position alternate flap drive control switch to DOWN.
H.  Check that leading edge flaps and slats fully extend within 15 +/- 4 seconds.
I.  Position alternate flap drive control switch and alternate flap arming switch to OFF.
J.  Check that leading edge flaps and slats fully retract.
NOTE: Retraction is due to hydraulic system A being pressurized.
K.  Repeat steps F thru I to bleed standby hydraulic system by actuating leading edge devices.
L.  Check flap flow limiting valve hydraulic fittings for leakage.
M.  Close TE ALT FLAP DRIVE MOTOR circuit breaker.
N.  Depressurize hydraulic system A. Refer to 27-81-0.
O.  Lockwire alternate flap master arming switch.
P.  Determine whether there is any further need for electrical power. If not, disconnect power.
Q.  Check hydraulic reservoirs and service if required. Refer to Chapter 12, Hydraulic Servicing.
May 01/98 27-81-71 Page 501 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

LEADING EDGE FLAP AND SLAT CONTROL VALVE - REMOVAL/INSTALLATION
1. General
A.  The leading edge flap and slat control valve and the trailing edge flap control valve are similar units. The leading edge flap and slat control valve is mounted on the flap control unit forward of the trailing edge flap control valve. This procedure provides instructions for replacement of the leading edge flap and slat control valve.
2.  Equipment and Materials
A.  Hydraulic Fluid, Fire Resistant - BMS 3-11 (Ref 20-30-21)
B.  Skydrol Assembly Lube - MCS 352 (Ref 20-30-21)
C.  Rigging Pin, F-1 - 0.311 +0.000/-0.002-inch diameter x 2.35 +0.06-inch length (MS20392-4)
NOTE: Rigging pin is part of kit F70207-61 or -84.
3.  Prepare Leading Edge Flap and Slat Control Valve for Removal
A.  Pressurize hydraulic system A (Ref 27-81-0 MP)
B.  Position flap control lever to FLAP UP detent.
C.  Depressurize hydraulic systems (Ref 27-81-0 MP).
D.  Remove lower pan from flap control unit.
E.  Install rigging pin F-1 through follower arm and valve cam (Fig. 401).
4.  Remove Leading Edge Flap and Slat Control Valve
A.  Disconnect control valve rod end from link assembly (Fig. 401).
B.  Disconnect hydraulic lines from control valve.
CAUTION: BE PREPARED TO CATCH HYDRAULIC FLUID.
C.  Install caps on all ports and plugs in hydraulic lines.
D.  Remove four mounting volts attaching control valve to control unit.
E.  Carefully remove control valve from control unit.
587 
Feb 20/88  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-81-81 Page 401 

G43010G43188
Leading Edge Flap and Slat Control Valve Installation  500 
27-81-81  Figure 401 (Sheet 1)  Aug 15/67 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

506  Leading Edge Flap and Slat Control Valve Installation 
Aug 15/68  Figure 401 (Sheet 2)  27-81-81 
Page 403 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

5.  Install Leading Edge Flap and Slat Control Valve (See figure 401.)
A.  Install union and O-ring in each port of valve. Lightly lubricate O-ring with hydraulic fluid or assembly lube prior to installation.
B.  Carefully insert control valve into control unit.
C.  Install four mounting bolts. Tighten bolts and lockwire.
D.  Remove caps from ports and plugs from hydraulic lines.
E.  Connect hydraulic lines to control valve.
F.  Connect control valve rod end to link assembly.
G.  Remove rigging pin F-1.
H.  Pressurize hydraulic system A. Refer to 27-81-0.
I.  Position flap control lever to fully extend flaps and slats.
J.  Position flap control lever to FLAP UP detent to retract flaps and slats.
K.  Examine hydraulic lines at control valve for leakage.
L.  Adjust and test control valve. Refer to Leading Edge Flap and Slat Control Valve -Adjustment/Test.
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(169)