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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 27-59-01-420-008
(4) Connect the electrical connector [93] to the flap skew sensor [100].
SUBTASK 27-59-01-860-018
(5) Remove the safety tags and close these circuit breakers:
F/O Electrical System Panel, P6-2
Row Col Number Name
A 11 C01443 FC TE FLAP POS/SKEW SNSR & IND RIGHT
A 12 C00213 FC TE FLAP POS/SKEW SNSR & IND LEFT
SUBTASK 27-59-01-440-004
(6) Do this task: Trailing Edge Flap System Reactivation, TASK 27-51-00-440-801.
SUBTASK 27-59-01-860-019
(7) Retract the trailing edge flaps to the UP position. To retract the flaps, do this task: Retract the
Trailing Edge Flaps, TASK 27-51-00-860-804.
SUBTASK 27-59-01-730-004
(8) Do this task: Flap Skew Detection System Functional Test, TASK 27-59-00-730-801.
------------------------- END OF TASK ---------------------------
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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Feb 10/2006
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
FLAP SKEW MECHANISM - MAINTENANCE PRACTICES
1. General
A. This procedure has these tasks:
(1) A removal of the outboard flap skew mechanism for the outboard flap
(2) An installation of the outboard flap skew mechanism for the outboard flap
(3) A removal of the inboard flap skew mechanism for the outboard flap
(4) An installation of the inboard flap skew mechanism for the outboard flap
(5) A removal of the outboard flap skew mechanism for the inboard flap
(6) An installation of the outboard flap skew mechanism for the inboard flap
(7) A removal of the inboard flap skew mechanism for the inboard flap
(8) An installation of the inboard flap skew mechanism for the inboard flap.
B. There are eight flap skew mechanisms and sensors for the trailing edge flaps. One at each of the flap
supports.
C. The flap skew mechanisms include a sensor input assembly and a control rod.
TASK 27-59-02-000-801
2. Outboard Flap Outboard Skew Mechanism Removal
(Figure 201)
A. General
(1) This task is applicable to the flap skew mechanisms installed on flap supports No. 1 and 8.
(2) You can remove the flap skew mechanism with the flap skew sensor [13] either removed or
installed. This task shows the removal with the flap skew sensor [13] installed.
B. References
Reference Title
27-51-00-040-801 Trailing Edge Flap System Deactivation (P/B 201)
27-51-00-860-803 Extend the Trailing Edge Flaps (P/B 201)
C. Location Zones
Zone Area
544 Left Wing - Fairing Flap Support No. 1
644 Right Wing - Fairing Flap Support No. 8
D. Procedure
SUBTASK 27-59-02-860-001
(1) Extend the trailing edge flaps to the 40-unit position. To extend them, do this task: Extend the
Trailing Edge Flaps, TASK 27-51-00-860-803.
SUBTASK 27-59-02-040-001
(2) Do this task: Trailing Edge Flap System Deactivation, TASK 27-51-00-040-801.
SUBTASK 27-59-02-860-002
(3) Open these circuit breakers and install safety tags:
F/O Electrical System Panel, P6-2
Row Col Number Name
A 11 C01443 FC TE FLAP POS/SKEW SNSR & IND RIGHT
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Row Col Number Name
A 12 C00213 FC TE FLAP POS/SKEW SNSR & IND LEFT
SUBTASK 27-59-02-020-001
(4) Disconnect the electrical connector [14] from the flap skew sensor [13].
SUBTASK 27-59-02-020-002
(5) Remove the nuts [20], washers [19], bushings [18], washers [17] and bolts [16] that attach the
control rod [21] to the crank arm [15] and to the carriage [22].
SUBTASK 27-59-02-020-003
(6) Remove the sensor input assembly [2]:
(a) Remove the nut [7], washer [6], washer [5], washer [4] and bolt [3] that attach the sensor
input assembly [2] and the jumper wire [8] to the flap track [1].
(b) Remove the nuts [12], washers [11], washers [10] and bolts [9] that attach the sensor input
assembly [2] to the flap track [1].
(c) Remove the sensor input assembly [2] from the flap track [1].
------------------------- END OF TASK ---------------------------
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AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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737-600-700-800-900 飞机维护手册5 AIRCRAFT MAINTENANCE MANUA(135)
