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(a) Put the quadrant [5] in its position on the input shaft [12] for the flap control unit
assembly [9].
(b) Apply grease, D00633 to the threads on the input shaft [12].
(c) Install the washer [17] 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 27-51-61-420-004
(3) Connect the cable assembly [1] WFA and WFB to the quadrant [5]:
(a) Put the flap control lever [18] in the rigged position:
1) Put a 0.19 ±0.005 inch (4.83 ±0.13 mm) thick rigging block between the detent pin on
the flap control lever [18] and the upstop on the detent plate.
NOTE: Make sure the rigging block 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 assembly [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 (125 ±6.8 kilograms).
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 unit adjustment procedure.
SUBTASK 27-51-61-420-005
(4) Connect the hydraulic lines [32] (Figure 402):
(a) Remove the plugs from the ports of the leading edge control valve [35] and the trailing edge
flap control valve [34].
(b) Remove the caps from the hydraulic lines [32].
(c) Connect the hydraulic lines [32] to the leading edge control valve [35].
(d) Connect the hydraulic lines [32] to the trailing edge flap control valve [34].
SUBTASK 27-51-61-210-001
(5) Before you connect the electrical connector [33], examine the connector for corrosion.
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
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 27-51-61-420-006
(6) Connect the electrical connector [33] to the trailing edge flap control valve [34].
SUBTASK 27-51-61-420-007
(7) Connect the cables [48] WFFA and WFFB at the turnbuckles [50]:
(a) Make sure the flap power drive unit [54] is in the rigged position:
1) Make sure the black rig mark on the cable drum [52] extends past the white cable
guard [53] a minimum of 0.03 inches (0.76 millimeters) on each side.
WARNING: DO NOT RETRACT THE POWER DRIVE UNIT PAST THE RIG MARK IN THE
UP DIRECTION. YOU CAN CAUSE INJURIES TO PERSONS OR DAMAGE
TO EQUIPMENT.
2) If the power drive unit [54] is not in the rigged position, use the manual drive to move
the power drive unit [54].
(b) Connect the cables [48] to the cables [51] at the turnbuckles [50].
NOTE: Cable WFFA is the lower cable [51].
(c) Use the turnbuckles [50] to tighten the cables [48] until the tension is 125 ±10 pounds (556
±45 newtons).
NOTE: You will adjust the cables [48] to the final tension during the flap control system
adjustment procedure.
SUBTASK 27-51-61-820-002
(8) Do this task: Trailing Edge Flap Control System Adjustment, TASK 27-51-00-820-801.
NOTE: This task includes the adjustment of the cables, the removal of the rig pin and the
clamp from the flap control unit assembly [9] and the removal of the rigging tool from
the flap control lever.
SUBTASK 27-51-61-420-008
(9) Install the locking clips [2] on the turnbuckles [3] for cable assembly [1] WFA and WFB
(Figure 401).
SUBTASK 27-51-61-410-001
(10) 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
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EFFECTIVITY
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737-600-700-800-900 飞机维护手册5 AIRCRAFT MAINTENANCE MANUA(100)
