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(a) Remove the screws [9] that attach the bypass valve motor [8] to the bypass valve [10].
(b) Carefully lift the bypass valve motor [8] off bypass valve [10].
------------------------- END OF TASK ---------------------------
TASK 27-51-02-400-803
7. Trailing Edge Flap Bypass Valve Motor Installation
(Figure 401)
A. General
(1) This task includes the installation of the bypass valve motor on the bypass valve.
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
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EFFECTIVITY
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C. Consumable Materials
Reference Description Specification
G50171 Compound - Corrosion Inhibiting Compound,
Interior Application - D5026NS or ZC-026
D. Location Zones
Zone Area
134 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Right
E. Trailing Edge Flap Bypass Valve Motor Installation
SUBTASK 27-51-02-860-014
(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 27-51-02-420-007
(2) Install the bypass valve motor [8] on the flap bypass valve [10]:
(a) Carefully put the bypass valve motor [8] in its location on the flap bypass valve [10].
(b) Install the screws [9] to attach the bypass valve motor [8] to the flap bypass valve [10].
(c) Tighten the screws [9] to 12-15 pound-inches (1.4-1.7 newton-meters).
(d) Install lockwire on the screws [9].
SUBTASK 27-51-02-210-005
(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 27-51-02-420-008
(4) Connect the electrical connector [5] to the bypass valve motor [8].
SUBTASK 27-51-02-860-015
(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 27-51-02-440-003
(6) Do this task: Trailing Edge Flap System Reactivation, TASK 27-51-00-440-801.
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SUBTASK 27-51-02-720-007
(7) Do this task: Trailing Edge Flap Bypass Valve Functional Test, TASK 27-51-02-720-801.
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TRAILING EDGE FLAP BYPASS VALVE - ADJUSTMENT/TEST
1. General
A. This procedure has a functional test of the trailing edge flap bypass valve.
TASK 27-51-02-720-801
2. Trailing Edge Flap Bypass Valve Functional Test
(Figure 501)
A. References
Reference Title
24-22-00-860-811 Supply Electrical Power (P/B 201)
27-51-00-740-802 Trailing Edge Flap Asymmetry Skew System BITE Test (P/B 501)
27-51-00-860-804 Retract the Trailing Edge Flaps (P/B 201)
29-11-00-860-801 Hydraulic System A or B Pressurization (P/B 201)
29-11-00-860-805 Hydraulic System A or B Power Removal (P/B 201)
B. Location Zones
Zone Area
117 Electrical and Electronics Compartment - Left
118 Electrical and Electronics Compartment - Right
211 Flight Compartment - Left
212 Flight Compartment - Right
C. Prepare for the Test
SUBTASK 27-51-02-860-001
(1) Do this task: Supply Electrical Power, TASK 24-22-00-860-811.
SUBTASK 27-51-02-860-002
WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE FLIGHT CONTROL SURFACES, THE
THRUST REVERSERS, AND THE LANDING GEAR. THESE COMPONENTS CAN MOVE
SUDDENLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURIES TO
PERSONS AND DAMAGE TO EQUIPMENT.
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737-600-700-800-900 AIRCRAFT MAINTENANCE MANUAL飞机维护手册4(71)
