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than 1.00 inch (25.4 millimeters).
(i) Tighten the jam nut [14].
(j) Install the lockwire, G01048.
F. Put the Airplane Back to Its Usual Condition
SUBTASK 27-81-81-020-003
(1) Remove the rig pin [7] from the cam follower arm [6] and the valve cam [5].
SUBTASK 27-81-81-410-001
(2) Install the lower pan [3] on the flap control unit [1]:
(a) Put the lower pan [3] in its location on the flap control unit [1].
(b) Apply compound, C00913 to the shank and threads of the screws [4].
(c) Install the screws [4] that attach the lower pan [3] to the flap control unit [1].
SUBTASK 27-81-81-720-001
(3) Do this task: Leading Edge Flap and Slat Timing Test in Primary Mode,
TASK 27-81-00-700-802.
------------------------- END OF TASK ---------------------------
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Leading Edge Flap and Slat Control Valve Adjustment
Figure 501 (Sheet 1 of 3)/27-81-81-990-802
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Leading Edge Flap and Slat Control Valve Adjustment
Figure 501 (Sheet 2 of 3)/27-81-81-990-802
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Leading Edge Flap and Slat Control Valve Adjustment
Figure 501 (Sheet 3 of 3)/27-81-81-990-802
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LEADING EDGE STANDBY SHUTOFF VALVE - MAINTENANCE PRACTICES
1. General
A. This procedure has these tasks:
(1) A removal of the leading edge standby shutoff valve (valve and motor)
(2) An installation of the leading edge standby shutoff valve (valve and motor)
(3) A removal of the standby shutoff valve motor
(4) An installation of the edge standby shutoff valve motor
(5) A test of the leading edge standby shutoff valve.
B. The leading edge standby shutoff valve is referred to as the "valve", and the standby shutoff valve
motor is referred to as the "valve motor" in this procedure.
C. You can replace the valve motor with the valve installed in the standby flight controls hydraulic
module.
TASK 27-81-91-000-801
2. Leading Edge Standby Shutoff Valve Removal
(Figure 201)
A. General
(1) This task is the removal of the leading edge standby shutoff valve assembly, which contains the
motor and the valve.
B. References
Reference Title
29-09-00-860-802 Hydraulic Reservoirs Depressurization (P/B 201)
29-11-00-860-805 Hydraulic System A or B Power Removal (P/B 201)
29-11-01-860-802 Hydraulic Reservoirs Depressurization (P/B 201)
32-00-01-480-801 Landing Gear Downlock Pins Installation (P/B 201)
C. Tools/Equipment
Reference Description
STD-1154 Container - 5 Gallon (19 Liters)
D. Location Zones
Zone Area
133 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Left
211 Flight Compartment - Left
212 Flight Compartment - Right
E. Prepare for the Removal
SUBTASK 27-81-91-480-001
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.
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SUBTASK 27-81-91-860-001
(2) Make sure there is no power on hydraulic system B. To remove it, do this task: Hydraulic
System A or B Power Removal, TASK 29-11-00-860-805.
SUBTASK 27-81-91-860-002
(3) Do this task: Hydraulic Reservoirs Depressurization, TASK 29-11-01-860-802 or Hydraulic
Reservoirs Depressurization, TASK 29-09-00-860-802.
SUBTASK 27-81-91-860-003
(4) Open this circuit breaker and install safety tag:
F/O Electrical System Panel, P6-2
Row Col Number Name
A 7 C00210 FLIGHT CONTROL FLAP SHUTOFF VALVES
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737-600-700-800-900 飞机维护手册7 AIRCRAFT MAINTENANCE MANUA(97)
