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SUBTASK 27-81-71-610-001
(2) If it is necessary to service the hydraulic reservoirs, do this task: Hydraulic Reservoir
Servicing, TASK 12-12-00-610-801.
SUBTASK 27-81-71-710-001
(3) Do a test of the flap flow limiting valve [1]:
(a) Do this task: Supply Electrical Power, TASK 24-22-00-860-811.
(b) Open this circuit breaker and install safety tag:
F/O Electrical System Panel, P6-2
Row Col Number Name
D 13 C00841 FLIGHT CONTROL ALTN T.E. FLAP DRIVE
(c) To pressurize hydraulic system B, do this task: Hydraulic System A or B Pressurization,
TASK 29-11-00-860-801.
(d) If it is necessary, move the flap control lever to the FLAP UP detent position to retract the
leading edge flaps and slats.
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE LEADING
EDGE FLAPS AND SLATS. THE LEADING EDGE FLAPS AND SLATS WILL
EXTEND. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-81-71
Page 404
Oct 10/2003
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(WARNING PRECEDES)
CAUTION: MAKE SURE THE INBOARD FAN DUCT COWL AND THE INBOARD AND
OUTBOARD THRUST REVERSERS ARE CLOSED OR REMOVED BEFORE YOU
EXTEND THE LEADING EDGE FLAPS AND SLATS. THERE IS NOT SUFFICIENT
CLEARANCE FOR THE FLAPS AND SLATS TO EXTEND IF THE COWL AND THE
THRUST REVERSERS ARE IN THE OPEN POSITION. THIS CAN CAUSE DAMAGE
TO EQUIPMENT.
(e) Put the alternate flap arm switch in the ARM position.
(f) Put the alternate flap control switch in the DOWN position.
1) Make sure the leading edge flaps and slats fully extend.
(g) Put the alternate flap control switch in the OFF position.
(h) Put the alternate flap arm switch in the OFF position.
1) Make sure the leading edge flaps and slats fully retract.
(i) Examine the hydraulic fittings of the flow limiting valve [1] for leakage.
D. Put the Airplane Back to Its Usual Condition
SUBTASK 27-81-71-860-002
(1) Remove the safety tag and close this circuit breaker:
F/O Electrical System Panel, P6-2
Row Col Number Name
D 13 C00841 FLIGHT CONTROL ALTN T.E. FLAP DRIVE
SUBTASK 27-81-71-860-003
(2) To remove pressure from hydraulic system B, do this task: Hydraulic System A or B Power
Removal, TASK 29-11-00-860-805.
SUBTASK 27-81-71-610-002
(3) If it is necessary to service the hydraulic reservoirs, do this task: Hydraulic Reservoir
Servicing, TASK 12-12-00-610-801.
------------------------- END OF TASK ---------------------------
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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LEADING EDGE FLAP AND SLAT CONTROL VALVE - REMOVAL/INSTALLATION
1. General
A. This procedure has these tasks:
(1) A removal of the leading edge flap and slat control valve.
(2) An installation of the leading edge flap and slat control valve.
B. The leading edge flap and slat control valve is attached to the flap control unit forward of the trailing
edge flap control valve.
C. The leading edge flap and slat control valve is referred to as the "control valve" in this procedure.
TASK 27-81-81-000-801
2. Leading Edge Flap and Slat Control Valve Removal
(Figure 401)
A. References
Reference Title
27-81-00-860-804 Leading Edge Flaps and Slats Retraction (P/B 201)
29-11-00-860-805 Hydraulic System A or B Power Removal (P/B 201)
32-00-01-480-801 Landing Gear Downlock Pins Installation (P/B 201)
B. Tools/Equipment
Reference Description
STD-1154 Container - 5 Gallon (19 Liters)
C. Location Zones
Zone Area
134 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Right
D. Prepare for the Removal
SUBTASK 27-81-81-480-001
WARNING: MAKE SURE THE DOWNLOCK PINS ARE INSTALLED ON ALL THE LANDING GEARS.
WITHOUT THE DOWNLOCK PINS, THE LANDING GEARS COULD RETRACT AND
CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(1) If the downlock pins are not installed on all the landing gears, do this task: Landing Gear
Downlock Pins Installation, TASK 32-00-01-480-801.
SUBTASK 27-81-81-860-001
(2) If the leading edge flaps and slats are not in the retracted position, do this task: Leading Edge
Flaps and Slats Retraction, TASK 27-81-00-860-804.
SUBTASK 27-81-81-860-002
(3) To remove power from hydraulic system B, do this task: Hydraulic System A or B Power
Removal, TASK 29-11-00-860-805.
E. Leading Edge Flap and Slat Control Valve Removal
SUBTASK 27-81-81-020-001
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737-600-700-800-900 飞机维护手册7 AIRCRAFT MAINTENANCE MANUA(94)
