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Trailing Edge Flap Bypass Valve
Figure 202 (Sheet 1 of 2)/27-51-00-990-802
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EFFECTIVITY
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Trailing Edge Flap Bypass Valve
Figure 202 (Sheet 2 of 2)/27-51-00-990-802
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TASK 27-51-00-440-801
3. Trailing Edge Flap System Reactivation
A. General
(1) Use this procedure to reactivate the trailing edge flap system.
B. References
Reference Title
32-00-01-480-801 Landing Gear Downlock Pins Installation (P/B 201)
SWPM 20-60-03 Standard Wiring Practices Manual
C. Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference Description
SPL-1676 Assembly - Lock, Flight Controls
(Part #: F80049-17, Supplier: 81205, A/P Effectivity: 737-100, -200,
-200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900,
-900ER, -BBJ)
D. Consumable Materials
Reference Description Specification
G50171 Compound - Corrosion Inhibiting Compound,
Interior Application - D5026NS or ZC-026
E. Location Zones
Zone Area
134 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Right
211 Flight Compartment - Left
212 Flight Compartment - Right
F. Procedure
SUBTASK 27-51-00-480-006
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 27-51-00-440-001
(2) Reactivate the trailing edge flap bypass valve (Figure 202):
(a) Remove the lock, SPL-1676 from the bypass valve.
(b) Move the manual override lever on the bypass valve to POSITION 1.
(c) Before you connect the electrical connector, examine the connector for corrosion.
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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.
(d) If there was corrosion, refer to (SWPM 20-60-03) to correct the problem.
(e) Apply the D5026NS or ZC-026 compound, G50171 to the connector (SWPM 20-60-03).
(f) Connect the electrical connector to the bypass valve.
SUBTASK 27-51-00-860-002
(3) Remove the safety locks and close these circuit breakers:
F/O Electrical System Panel, P6-2
Row Col Number Name
A 7 C00210 FLIGHT CONTROL FLAP SHUTOFF VALVES
D 13 C00841 FLIGHT CONTROL ALTN T.E. FLAP DRIVE
SUBTASK 27-51-00-080-001
(4) Remove the DO-NOT-OPERATE tags from the flap control lever and the ALTERNATE FLAPS
switches (Figure 201).
------------------------- END OF TASK ---------------------------
TASK 27-51-00-860-801
4. Trailing Edge Flap System Operation With Primary Control
(Figure 201)
A. General
(1) The primary control system uses the hydraulic system B to move the flaps.
B. References
Reference Title
24-22-00-860-811 Supply Electrical Power (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)
C. Location Zones
Zone Area
211 Flight Compartment - Left
212 Flight Compartment - Right
D. Procedure
SUBTASK 27-51-00-860-003
(1) Do this task: Supply Electrical Power, TASK 24-22-00-860-811.
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AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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737-600-700-800-900 AIRCRAFT MAINTENANCE MANUAL飞机维护手册4(33)
