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(g) If there was corrosion, refer to (SWPM 20-60-03) to correct the problem.
(h) Apply the D5026NS or ZC-026 compound, G50171 to the connectors (SWPM 20-60-03).
(i) Connect the electrical connectors to the valve [3].
SUBTASK 27-81-52-860-003
(2) Use an bonding meter, COM-1550 to measure the resistance between the valve [3] and the
bracket.
(a) Make sure the maximum resistance between the valve [3] and the bracket is 0.0025 ohms.
SUBTASK 27-81-52-860-004
(3) Remove the safety tag and close this circuit breaker:
F/O Electrical System Panel, P6-2
Row Col Number Name
A 7 C00210 FLIGHT CONTROL FLAP SHUTOFF VALVES
SUBTASK 27-81-52-720-001
(4) If you replace the LE cruise depressurization valve, do this task: Leading Edge Cruise
Depressurization Test, TASK 27-81-00-730-801.
SUBTASK 27-81-52-720-002
(5) If you replace the LE UCM shutoff valve, do this task: Leading Edge Uncommanded Motion
Protection Test, TASK 27-81-00-700-804.
G. Put the plane back to its usual condition.
SUBTASK 27-81-52-940-001
(1) Install this access panel:
Number Name/Location
192BR ECS Ram Air Inlet Mixing Duct Panel - Forward
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LEADING EDGE FLAP AND SLAT HYDRAULIC FUSE - REMOVAL/INSTALLATION
1. General
A. This procedure has these tasks:
(1) A removal of the hydraulic fuses of the leading edge flap and slat.
(2) An installation of the hydraulic fuses of the leading edge flap and slat.
B. There are two hydraulic fuses (extend and retract) in the system B and one hydraulic fuse in the
standby system. The hydraulic fuses are all located in the airplane main landing gear wheel well.
C. This procedure is applicable for all three hydraulic fuses.
TASK 27-81-61-000-801
2. Leading Edge Flap and Slat Hydraulic Fuse 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. Location Zones
Zone Area
133 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Left
C. Leading Edge Flap and Slat Hydraulic Fuse Removal
SUBTASK 27-81-61-480-001
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 27-81-61-860-001
(2) To remove power from hydraulic systems B, do this task: Hydraulic System A or B Power
Removal, TASK 29-11-00-860-805.
SUBTASK 27-81-61-020-001
(3) Do this steps if you remove the fuse assembly [2] in system B:
(a) Loosen nuts [1] and [3] to disconnect the hydraulic tubes from the fuse assembly [2].
(b) Remove the fuse assembly [2].
SUBTASK 27-81-61-020-002
(4) Do these steps if you remove the fuse assembly [5] in the standby system:
(a) Loosen nuts [6] and [7] to disconnect the hydraulic tubes from the fuse assembly [5].
(b) Remove the fuse assembly [5] with the valve [4].
(c) Remove the fuse assembly [5] from the valve [4].
1) Remove and discard the O-ringpacking [8] installed between the fuse assembly [5] and
the valve [4].
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Leading Edge and Slat Hydraulic Fuse Installation
Figure 401 (Sheet 1 of 2)/27-81-61-990-801
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Leading Edge and Slat Hydraulic Fuse Installation
Figure 401 (Sheet 2 of 2)/27-81-61-990-801
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TASK 27-81-61-400-801
3. Leading Edge Flap and Slat Hydraulic Fuse Installation
(Figure 401)
A. References
Reference Title
12-12-00-610-801 Hydraulic Reservoir Servicing (P/B 301)
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737-600-700-800-900 飞机维护手册7 AIRCRAFT MAINTENANCE MANUA(91)
