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NLGI #1 - Lubriplate 630AA
G50171 Compound - Corrosion Inhibiting Compound,
Interior Application - D5026NS or ZC-026
D. Expendables/Parts
AMM Item Description AIPC Reference AIPC Effectivity
10 Valve 27-51-02-01-030 GUN ALL
E. Location Zones
Zone Area
134 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Right
F. Trailing Edge Flap Bypass Valve and Bypass Valve Motor Installation
SUBTASK 27-51-02-860-011
(1) Make sure that this circuit breaker is open:
F/O Electrical System Panel, P6-2
Row Col Number Name
A 7 C00210 FLIGHT CONTROL FLAP SHUTOFF VALVES
SUBTASK 27-51-02-420-005
(2) Install the flap bypass valve [10] and the bypass valve motor [8] on the valve housing [15]:
(a) Apply MCS 352B fluid, D00054 or fluid, D00070 to the packings [17] and packing [12].
(b) If they are not installed, install the packing [12], packings [17], backup ring [11] and backup
rings [16] on the bypass valve [10].
(c) Remove the cover from the bypass valve housing [15].
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-02
Page 410
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(d) Carefully put the bypass valve [10] in its location on the bypass valve housing [15].
(e) Apply a thin layer of Lubriplate 630AA lubricant, D00559 to the threads of the screws [18].
(f) Install the screws [18] to attach the bypass valve [10] to the bypass valve housing [15].
(g) Tighten the screws [18] to 9-11 pound-inches (1.0-1.2 newton-meters).
(h) Install lockwire on the screws [18].
SUBTASK 27-51-02-210-004
(3) Before you connect the electrical connector [5], examine the connector for corrosion.
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 27-51-02-420-006
(4) Connect the electrical connector [5] to the bypass valve motor [8].
SUBTASK 27-51-02-860-012
(5) 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 27-51-02-440-002
(6) Do this task: Trailing Edge Flap System Reactivation, TASK 27-51-00-440-801.
SUBTASK 27-51-02-720-006
(7) Do this task: Trailing Edge Flap Bypass Valve Functional Test, TASK 27-51-02-720-801.
SUBTASK 27-51-02-210-002
(8) Make sure there are no hydraulic leaks from the bypass valve assembly [4].
------------------------- END OF TASK ---------------------------
TASK 27-51-02-000-803
6. Trailing Edge Flap Bypass Valve Motor Removal
(Figure 401)
A. General
(1) This task includes the removal of the bypass valve motor from the bypass valve.
B. References
Reference Title
27-51-00-040-801 Trailing Edge Flap System Deactivation (P/B 201)
32-00-01-480-801 Landing Gear Downlock Pins Installation (P/B 201)
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-02
Page 411
Jun 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
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 27-51-02-480-003
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 27-51-02-040-003
(2) Do this task: Trailing Edge Flap System Deactivation, TASK 27-51-00-040-801.
SUBTASK 27-51-02-860-013
(3) 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 Motor Removal
SUBTASK 27-51-02-020-007
(1) Disconnect the electrical connector [5] from the bypass valve motor [5].
SUBTASK 27-51-02-980-001
(2) Move the manual override lever [3] to POSITION 2.
SUBTASK 27-51-02-020-008
(3) Remove the bypass valve motor [8] from the bypass valve [10]:
　
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