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(b) Put the slat actuator door [8] in its position on the slat actuator [9].
(c) Install the bolts [1], washers [2] and nuts [3] that attach the slat actuator door [8] and the
bracket to the slat actuator [9].
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(d) Install the bolts [4], washers [5], washers [6] and nuts [7] that attach the slat actuator door
[8] to the slat actuator [9].
F. Put the Airplane Back to Its Usual Condition
SUBTASK 27-81-41-080-001
(1) To remove the lockout set, SPL-1734 from the adjacent leading edge slats, do this task: Leading
Edge Flap and Slat Locks Removal, TASK 27-81-00-080-801.
SUBTASK 27-81-41-860-003
(2) Move the flap control lever to the UP detent position to retract the slats.
SUBTASK 27-81-41-860-004
(3) To remove power from hydraulic system B, do this task: Hydraulic System A or B Power
Removal, TASK 29-11-00-860-805.
------------------------- END OF TASK ---------------------------
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Leading Edge Slat Actuator Lock Indicator Visual Inspection
Figure 601 (Sheet 1 of 2)/27-81-41-990-801
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Leading Edge Slat Actuator Lock Indicator Visual Inspection
Figure 601 (Sheet 2 of 2)/27-81-41-990-801
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LEADING EDGE UNCOMMANDED MOTION (UCM) VALVE AND LEADING EDGE CRUISE DEPRESSURIZATION
VALVE - REMOVAL/INSTALLATION
1. General
A. This procedure has these tasks:
(1) A removal of the leading edge flap and slat uncommanded motion (UCM) or cruise
depressurization valve
(2) An installation of the leading edge flap and slat uncommanded motion (UCM) or cruise
depressurization valve
B. There are two valves installed on the airplane. The LE cruise depressurization valve and the LE UCM
shutoff valve. This procedure is applicable for the two valves.
C. The leading edge flap and slat uncommanded motion (UCM) or cruise depressurization valve is
referred as the valve [3] in this procedure.
D. The LE cruise depressurization valve will be operated each flight to depressurize the leading edge
extend at cruise. The LE UCM shutoff valve will be operated only when there is uncommanded
motion of the leading edge.
TASK 27-81-52-000-801
2. LE Uncommanded Motion (UCM) or LE Cruise Depressurization Valve Removal
(Figure 401)
A. References
Reference Title
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-1054 Container - Fuel Resistant, 5 Gallon (19 Liters)
C. Location Zones
Zone Area
132 Center Section Wing Box, Body Station 540.00 to Body Station 663.75
- Right
133 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Left
134 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Right
D. Access Panels
Number Name/Location
192BR ECS Ram Air Inlet Mixing Duct Panel - Forward
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E. Prepare for the Removal
SUBTASK 27-81-52-480-001
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 27-81-52-860-001
(2) 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
SUBTASK 27-81-52-860-002
(3) If there is hydraulic power on hydraulic system B, do this task: Hydraulic System A or B Power
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737-600-700-800-900 飞机维护手册7 AIRCRAFT MAINTENANCE MANUA(89)
