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(g) Before you connect the electrical connector [3], 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.
(h) If there was corrosion, refer to (SWPM 20-60-03) to correct the problem.
(i) Apply the D5026NS or ZC-026 compound, G50171 to the connector (SWPM 20-60-03).
(j) Connect the electrical connector [3] to the flap control valve assembly [6].
SUBTASK 27-51-65-080-001
(3) Remove the rig pin from the flap control unit [1]:
SUBTASK 27-51-65-860-004
(4) Remove the safety tag and close this circuit breaker:
F/O Electrical System Panel, P6-2
Row Col Number Name
A 6 C00566 FLIGHT CONTROL FLAP LOAD RELIEF
SUBTASK 27-51-65-860-005
(5) Use the primary system to extend and retract the trailing edge flaps. To extend and retract the
flaps, do this task: Trailing Edge Flap System Operation With Primary Control,
TASK 27-51-00-860-801.
SUBTASK 27-51-65-210-001
(6) Make sure there are no hydraulic leaks from the flap control valve assembly [6].
SUBTASK 27-51-65-820-001
(7) Do this task: Trailing Edge Flap Control Valve Adjustment, TASK 27-51-65-820-801.
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SUBTASK 27-51-65-410-001
(8) Install the lower pan [11] on the flap control unit [1]:
(a) Put the lower pan [11] in its location on the flap control unit [1].
(b) Apply compound, C00913 to the shank and threads of the screws [10].
(c) Install the washers [23] and screws [10] to attach the lower pan [11] to the flap control unit
[1].
F. Put the Airplane Back to Its Usual Condition
SUBTASK 27-51-65-610-001
(1) Service the system B hydraulic reservoir. To service the reservoir, do this task: Hydraulic
Reservoir Servicing, TASK 12-12-00-610-801.
------------------------- END OF TASK ---------------------------
TASK 27-51-65-000-802
4. Flap Load Limiter Solenoid Valve Removal
(Figure 401)
A. References
Reference Title
27-51-00-860-804 Retract the Trailing Edge Flaps (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)
B. Location Zones
Zone Area
134 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Right
C. Prepare for the Removal
SUBTASK 27-51-65-860-006
(1) If the trailing edge flaps are not in the retracted position, do this task: Retract the Trailing Edge
Flaps, TASK 27-51-00-860-804.
SUBTASK 27-51-65-860-007
(2) 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 27-51-65-480-005
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.
(3) 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.
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D. Flap Load Limiter Solenoid Valve Removal
SUBTASK 27-51-65-860-008
(1) Open this circuit breaker and install safety tag:
F/O Electrical System Panel, P6-2
Row Col Number Name
A 6 C00566 FLIGHT CONTROL FLAP LOAD RELIEF
SUBTASK 27-51-65-020-003
(2) Remove the solenoid valve assembly [21] from the flap control valve assembly [6]:
(a) Remove the screws [20] that attach the solenoid valve assembly [21] to the flap control
valve assembly [6].
(b) Remove the solenoid valve assembly [21] from the flap control valve assembly [6] with the
gasket [19] and packing [22].
------------------------- END OF TASK ---------------------------
TASK 27-51-65-400-802
5. Flap Load Limiter Solenoid Valve Installation
(Figure 401)
A. References
Reference Title
12-12-00-610-801 Hydraulic Reservoir Servicing (P/B 301)
27-51-00-740-803 Trailing Edge Flap Load Relief System BITE Test (P/B 501)
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737-600-700-800-900 飞机维护手册5 AIRCRAFT MAINTENANCE MANUA(114)
