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WARNING: DO THE STEPS BELOW IF THE AIRPLANE OPERATES AT AIRPORTS WHERE
DEICING FLUID THAT CONTAIN POTASSIUM FORMATE IS USED. ALSO DO THE
STEPS FOR ALL AIRPLANES THAT YOU FOUND CORROSION IN THE
ELECTRICAL CONNECTORS IN THE MAIN WHEEL WELL. THE ELECTRICAL
CONNECTOR IS PART OF A SYSTEM THAT IS NECESSARY FOR SAFE FLIGHT.
(a) If there was corrosion, refer to (SWPM 20-60-03) to correct the problem.
(b) Apply the D5026NS or ZC-026 compound, G50171 to the connector (SWPM 20-60-03).
SUBTASK 27-51-02-420-004
(6) Connect the electrical connector [5] to the bypass valve assembly [4].
SUBTASK 27-51-02-860-008
(7) 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 27-51-02-440-001
(8) Do this task: Trailing Edge Flap System Reactivation, TASK 27-51-00-440-801.
SUBTASK 27-51-02-720-005
(9) Do this task: Trailing Edge Flap Bypass Valve Functional Test, TASK 27-51-02-720-801.
SUBTASK 27-51-02-210-001
(10) Make sure there are no hydraulic leaks from the bypass valve assembly [4].
------------------------- END OF TASK ---------------------------
TASK 27-51-02-000-802
4. Trailing Edge Flap Bypass Valve and Bypass Valve Motor Removal
(Figure 401)
A. General
(1) This task includes the removal of the bypass valve and the bypass valve motor from the bypass
valve housing.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-02
Page 408
Jun 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
B. References
Reference Title
27-51-00-040-801 Trailing Edge Flap System Deactivation (P/B 201)
29-09-00-860-802 Hydraulic Reservoirs Depressurization (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. 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 27-51-02-480-002
WARNING: MAKE SURE THE DOWNLOCK PINS ARE INSTALLED ON ALL THE LANDING GEAR.
WITHOUT THE DOWNLOCK PINS, THE LANDING GEAR CAN RETRACT AND CAUSE
INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(1) If the downlock pins are not installed in the nose and main landing gear, do this task: Landing
Gear Downlock Pins Installation, TASK 32-00-01-480-801.
SUBTASK 27-51-02-040-002
(2) Do this task: Trailing Edge Flap System Deactivation, TASK 27-51-00-040-801.
SUBTASK 27-51-02-860-009
(3) Remove the pressure from the system B hydraulic reservoir. To remove the pressure, do this
task: Hydraulic Reservoirs Depressurization, TASK 29-11-01-860-802 or Hydraulic
Reservoirs Depressurization, TASK 29-09-00-860-802.
SUBTASK 27-51-02-860-010
(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
E. Trailing Edge Flap Bypass Valve and Bypass Valve Motor Removal
SUBTASK 27-51-02-020-005
(1) Disconnect the electrical connector [5] from the bypass valve motor [8].
SUBTASK 27-51-02-020-006
(2) Remove the flap bypass valve [10] and the bypass valve motor [8] as an assembly from the
bypass valve housing [15]:
(a) Remove the screws [18] that attach the bypass valve [10] to the bypass valve housing [15].
(b) Carefully lift the bypass valve [10] and the valve motor [8] out of the bypass valve housing
[15].
(c) Put a cover over the bypass valve housing [15].
------------------------- END OF TASK ---------------------------
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-02
Page 409
Jun 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
TASK 27-51-02-400-802
5. Trailing Edge Flap Bypass Valve and Bypass Valve Motor Installation
(Figure 401)
A. General
(1) This task includes the installation of the bypass valve and the bypass valve motor on the bypass
valve housing.
B. References
Reference Title
27-51-00-440-801 Trailing Edge Flap System Reactivation (P/B 201)
27-51-02-720-801 Trailing Edge Flap Bypass Valve Functional Test (P/B 501)
SWPM 20-60-03 Standard Wiring Practices Manual
C. Consumable Materials
Reference Description Specification
D00054 Fluid - Hydraulic Assembly Lubricant - MCS 352B
(Formally Monsanto MCS 352B)
D00070 Fluid - Hydraulic, Petroleum Base MIL-PRF-5606
(Replaces
MIL-H-5606)
D00559 Lubricant - White Lithium Multipurpose Grease,
　
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本文鏈接地址：737-600-700-800-900 AIRCRAFT MAINTENANCE MANUAL飛機維護手冊4(69)