G42352
Control Column Installation 500
27-31-51Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/89
C. Disconnect wiring harness (10) at terminal strip in lower nose compartment. Remove clamps where necessary to release harness.
D. If a control column shaker is installed, remove electrical connector from shaker motor and detach connector from end of cable.
E. Remove outboard coupling bolts (8) and remove outboard coupling (7).
CAUTION: CONTROL COLUMN IS FREE TO FALL AS COUPLING IS REMOVED AND MUST BE SUPPORTED FROM TIME THE NUTS ARE LOOSENED UNTIL COLUMN IS REMOVED.
F. Lift control column clear of control well. Simultaneously thread control column shaker electrical cable down through column, removing clamps where necessary to release cable.
5. Install Control Column
A. Check that rigging pin E-1 is installed in left forward control quadrant.
B. Check that dust cover on control column is oriented per Fig. 402 and lower column into position. Set aileron control wheel at neutral to assure engaging spade (5, Fig. 401) with clevis (6).
C. Position control column forward of a perpendicular line taken from the floor of the airplane per Fig. 402.
D. Maintaining angle obtained in previous step, engage face splines on control column with splines on forward control quadrant connector (12, Fig. 401).
E. Install outboard coupling (7) and coupling retaining bolts (8). Tighten bolts within range of driving torque, then alternately tighten bolts to 50-70 pound-inches torque in approximately 10 pound-inch increments to achieve gaps equal within 0.03 inch at each end of coupling clamp.
NOTE: Check bolt length to ensure that the proper bolt is installed. Improper length bolts can cause interference, which prevents achieving full control wheel and control column travel. Substitution of next bolt length and use of washers must be identical at each end of coupling clamp.
F. Check control column angle is as specified in step C.
G. Connect wiring harness (10) to terminal strip in lower nose compartment. Install harness clamps where removed.
H. If applicable, thread control column shaker electrical cable up through column. Refit connector on cable end and plug connector into shaker motor. Install cable clamps where removed.
Nov 15/80 27-31-51 Page 403 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
I. Install dust seal (4) and ring assembly (3). Fill gaps between dust seal halves with hole filling compound. Also fill gap between notch in dust seal and cutout in floor with hole filling compound.
J. Adjust dust cover (2) as required to position edge of dust seal (4) extended slightly upward against dust cover. Loosen clamp (1) to adjust dust cover.
CAUTION: DUST COVER MAY CONTACT WIRE BUNDLE BUT MUST NOT PINCH, OR BE FORCED AGAINST, ELECTRICAL CABLE.
CAUTION: INSTALLING DUST COVER TOO HIGH ON CONTROL COLUMN MAY CAUSE BINDING OF THE CONTROL COLUMN AND/OR DAMAGE TO THE DUST COVER.
K. Remove rigging pin E-1 from elevator forward control quadrant.
L. Close access doors and replace access panels.
M. Close circuit breakers.
N. Move the control column forward and aft and rotate the aileron control wheel (11) through full travel and check for satisfactory operation.
O. Test manual mode operation (column travel and elevator and tab deflection) per AMM 27-31-0/201.
P. Check control wheel microphone switch.
(1)
Check that all interphone and interphone dual power source circuit breakers on panel P6 are closed.
(2)
Turn on both flight interphone loudspeakers.
(3)
At captain's, first officer's, and observer's audio selector panels, push and turn on INT audio switch, push INT mic selector switch.
(4)
Using boom microphone/headset assemblies or handheld microphone, establish communication between flight compartment stations by actuating each pilot's control wheel microphone switch to INT position. Check that audio is loud and clear between stations.
Q. Test stabilizer trim control switch.
(1)
Move STAB TRIM CUTOUT switch to NORMAL position.
(2)
Provide electrical power.
(3)
Close stabilizer trim actuator and stabilizer trim control circuit breakers on panel P6.
(4)
Actuate stabilizer trim control switch to AIRPLANE NOSE UP and to AIRPLANE NOSE DOWN. Check that stabilizer responds in correct direction.
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本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(95)
