(2)
Right Side - From the two power control unit actuators, through the spring cartridge and the right body cables AA and AB, to the transfer mechanism lost motion device. A control system out of tolerance on the "right side" will transmit friction to the control wheels if one of the following two conditions exist:
(a)
The lost motion device out of adjustment and bottoming out.
(b)
Abnormal friction in transfer mechanism lost motion device spoiler control drum bearings.
B. It is possible to have a defective or misadjusted aileron PCU and still have both ailerons operate within rigging tolerance. If a defective or misadjusted PCU is suspected, test system with one hydraulic system, then with the other to isolate the faulty PCU (Ref 27-11-0, Adjustment/Test).
NOTE: Hydraulic system B powers the upper PCU, system A powers the lower PCU.
C. Measure control wheel forces per 27-11-0, A/T with both hydraulic systems on.
D. Ensure that aileron cable rig loads are correct.
E. Ensure that all rig pins can be freely inserted. Note that rig pin A/S-1 is inserted through three parts in the aileron transfer mechanism. Improper lost motion device rigging usually is the cause for excessive wheel forces in one direction only, especially noticeable in flight.
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F. Remove aileron force limiter. The force limiter shaft torque should be 0.5 pound-inch maximum. Also check that the roll force transducer wires do not bind on Captain’s control column.
G. Unhook or lift the two centering springs at the trim and feel mechanism to remove centering force. Tie back the roller arm to clear the cam. Wheel torque should be less than 13 pound-inches (2.0 pounds) at breakout, and approximately 26 pound-inches (4.0 pounds) at 75 degrees rotation.
H. Check the aileron spring cartridge by rotating the control wheel full travel with hydraulic power on. If the cartridge can be felt or observed to change in length the source of excessive friction is the flight spoiler control system or in the right side. For troubleshooting the flight spoiler, system, see 27-61-0, TS. For troubleshooting the right side, see below.
I. Disconnect the spoiler ratio changer input rod and the right end of the aileron spring cartridge in the right wheel well to isolate the spoiler system.
J. Verify that aileron PCU bus drum stop bolt gap is 0.05 inch ±0.010 inch.
K. With hydraulic power on, rotate control wheel approximately 12 degrees in each direction and check for movement of the right aft quadrant. Any movement of the right aft quadrant indicates high friction in the transfer mechanism bearings.
L. Rotate the right aft quadrant and check for binding. Ensure that the control wheel does not rotate (accomplish test within 12 degrees control wheel travel).
2. Trouble Shooting Isolation
A. The following steps isolate friction in the left side.
(1)
Loosen and disconnect the bus cables ACBA and ACBB to isolate the left cable side.
(2)
Disconnect the PCU input rods from the centering mechanism. Measure control wheel torque for changes. With hydraulics on, check rods for binding.
(3)
Loosen left body cables AA and AB (less than 20 pounds). Measure control wheel torque for changes. Cable system friction is dependent on the rig load. Relaxing cable load will help identify pulley or bearing problems.
(4)
Disconnect left body cables to isolate Captain’s column and drum. Check for binding in the control column and/or drum.
(5)
Lift Captain’s control column to disengage paddle, keeping the column wiring intact. Check control column for binding. Also check that the paddle bolt torque is between 5-10 pound-inches above run-on torque. The aileron control drum should rotate freely.
(6)
Remove floor panels and/or cargo ceiling liners to inspect left cable run. Spin all pulleys, they should spin freely.
(7)
Reconnect cable and inspect cable run. Check for hangups, deflecting fairleads or grommets and bent pulley brackets.
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B. The following steps isolate friction in the right side.
(1)
Loosen and disconnect the bus cables ACBA and ACBB, if still connected to isolate the right cable side.
(2)
Disconnect right body cables AA and AB from the right aft quadrant (27-11-91). Manually rotates the quadrant and check for binding.
(3)
Lift First Officer’s control column to disengage paddle, keeping the column wiring intact. Check control column for binding. Also check that the paddle bolt torque is between 5-10 pound-inches above run-on torque. The aileron transfer mechanism drum should rotate freely.
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