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(a) Apply a layer of compound, C00913 to the mating surface of the sensor input assembly [122]
and the flap track [136].
(b) Apply compound, C00913 to the shank and threads of the bolts [124].
(c) Put the sensor input assembly [122] in its location on the flap track [136].
(d) Install the bolts [124], washers [125], washers [126] and nuts [127] that attach the sensor
input assembly [122] to the flap track [136].
SUBTASK 27-59-02-420-014
(3) Install the control rod [129]:
(a) Apply compound, C00913 to the shank and threads of the bolts [130].
(b) Put the control rod [129] in its position between the carriage [135] and the crank arm [137].
NOTE: Make sure the adjustable end of the control rod [129] attaches to the crank arm
[137].
(c) Install the bolts [130], washers [131], bushings [132], washers [133] and nuts [134] to attach
the control rod [129].
NOTE: Install the bolt [130] that attaches the control rod [129] to the carriage [135] with
the head away from the center of the flap track [136]. You can install the bolt [130]
that attaches the control rod [129] to the crank arm [137] with the head in either
direction.
SUBTASK 27-59-02-820-004
(4) Do this task: Flap Skew Detection System Adjustment, TASK 27-59-00-820-801.
SUBTASK 27-59-02-020-014
(5) If the flap skew sensor [121] is installed, connect the jumper wire [128] to the flap skew sensor
[121].
(a) Install the bolt [138], washer [139] and washer [140] to attach the jumper wire [128] to the
flap skew sensor [121].
(b) Make sure the bonding resistance between the flap skew sensor [121] and the jumper wire
[128] is less than 8 milliohms.
(c) Apply a bead of sealant, A02315 or sealant, A00247 to the head of the bolt [138].
SUBTASK 27-59-02-420-015
(6) If the flap skew sensor [121] is not installed, do this task: Inboard Flap Inboard Skew Sensor
Installation, TASK 27-59-01-400-804.
SUBTASK 27-59-02-210-004
(7) Before you connect the electrical connector [123], 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 27-59-02-420-016
(8) Connect the electrical connector [123] to the flap skew sensor [121].
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-59-02
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SUBTASK 27-59-02-860-018
(9) 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 27-59-02-440-004
(10) Do this task: Trailing Edge Flap System Reactivation, TASK 27-51-00-440-801.
SUBTASK 27-59-02-860-019
(11) 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 27-59-02-730-004
(12) 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
GUN ALL 27-59-02
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SPOILER CONTROL SYSTEM - MAINTENANCE PRACTICES
1. General
A. This procedure has these tasks:
(1) Spoiler Hydraulic Systems A and B Pressurization
(2) Put the Spoiler Hydraulic Systems A and B Back to the Condition before the Pressurization
(3) Remove Pressure from the Spoiler Hydraulic Systems A and B
(4) Put the Spoiler Hydraulic Systems A and B Back to the Condition before the Pressure Removal
B. Hydraulic systems A, B must have pressure removed before maintenance is done on the spoiler
control system. This is to prevent injury to persons because of accidental operation of the control
system while you do maintenance. You must be careful to put maintenance stands and equipment
away from control surface travel.
C. Electric pump 1 pressurizes the hydraulic system B and electric pump 2 pressurizes the hydraulic
　
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