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AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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F. Flap Control Quadrant Installation
SUBTASK 27-51-62-820-001
(1) Install the rig pin [18] in the flap control unit [9]:
NOTE: This will make sure the flap control unit [9] is in the adjusted position.
(a) Remove the screws [16] and washers [21] and the lower pan [17] from the flap control unit
[9].
(b) Install the rig pin [18] through the cam follower arm and the valve cam.
SUBTASK 27-51-62-420-001
(2) Install the quadrant [5] on the flap control unit [9]:
(a) Put the quadrant [5] in its position on the input shaft [12] for the flap control unit [9].
(b) Apply grease, D00633 to the threads on the input shaft [12].
(c) Install the washer [15] and nut [11] on the input shaft [12].
(d) Tighten the nut [11] to 250-300 pound-inches (28.3-33.8 newton-meters) more than the runon
torque.
SUBTASK 27-51-62-420-002
(3) Connect the cable assembly [1] WFA and WFB to the quadrant [5]:
(a) Put the flap control lever [19] in the rigged position:
1) Put a 0.19 in. (4.83 mm) thick rigging block [20] between the detent pin on the flap
control lever [19] and the upstop on the detent plate.
NOTE: Make sure the rigging block [20] does not go into the flap UP detent.
2) Install a clamp to hold the quadrant [5] against the aft side of the stop [13] on the flap
control unit [9].
(b) Put the cable assembly [1] in its position on the quadrant [5].
NOTE: The cable assembly [1] attaches to the quadrant [5] in two locations. There is a
loop of cable that goes through the straps [10].
(c) Install the pins [4] and straps [10] to attach the cable assembly [1] to the quadrant [5].
(d) Install the pin [6], spacers [7] and pin [8] on the quadrant [5].
(e) Use the turnbuckles [3] to tighten the cable assembly [1] until the tension is 275 ±15
pounds (1223 ±67 newtons).
NOTE: You will adjust the cable assembly [1] to the final tension and remove the tools
from the flap control unit during the flap control system adjustment procedure.
SUBTASK 27-51-62-820-002
(4) Do this task: Trailing Edge Flap Control System Adjustment, TASK 27-51-00-820-801.
NOTE: This task includes the removal of the rig pin and the clamp from the flap control unit [9]
and the removal of the rigging tool from the flap control lever.
SUBTASK 27-51-62-420-003
(5) Install the locking clips [2] on the turnbuckles [3] for cable assembly [1] WFA and WFB.
G. Put the Airplane Back to Its Usual Condition
SUBTASK 27-51-62-410-001
(1) Install the lower pan [17] on the flap control unit [9]:
(a) Put the lower pan [17] in its location on the flap control unit [9].
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
(b) Apply compound, C00913 to the shank and threads of the screws [16].
(c) Install the washers [21] and screws [16] to attach the lower pan [17].
SUBTASK 27-51-62-410-002
(2) To get access to the turnbuckles[3], do this task:
Close this access panel:
Number Name/Location
112A Forward Access Door
or install this access panel:
Number Name/Location
114AC Fwd Nose Wheel Well Upper Access Panel
SUBTASK 27-51-62-410-003
(3) Install the floor panel above the flap control unit [9], do this task: Passenger Cabin Floor Panel
Installation, TASK 53-21-00-400-801.
------------------------- END OF TASK ---------------------------
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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FLAP LIMIT SWITCHES - REMOVAL/INSTALLATION
1. General
A. This procedure has these tasks:
(1) A removal of the flap limit switches
(2) An installation of the flap limit switches.
B. This procedure is applicable to these switches on the flap control unit:
(1) S245 TE Flaps UP Switch
(2) S246 TE Flaps DOWN Switch
(3) S1051 TE Flaps UP Switch
C. The S138 Landing Warning Switch is also installed on the flap control unit. The removal procedure is
covered in (TASK 31-51-01-000-801).
TASK 27-51-63-000-801
2. Flap Limit Switch Removal
(Figure 401)
A. General
(1) This task is applicable to the TE Flaps UP switch, S245, the TE Flaps DOWN switch, S246 and the
TE Flaps UP switch S1051.
B. References
Reference Title
27-51-00-040-801 Trailing Edge Flap System Deactivation (P/B 201)
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737-600-700-800-900 飞机维护手册5 AIRCRAFT MAINTENANCE MANUA(103)
