(2)
Set stabilizer B dimension at switch actuation setting for switch being adjusted. See Table I, Fig. 501 for required B dimension.
(3)
Loosen, but do not remove hexagon locking nut securing switch arm to switch.
CAUTION: IF LOCKING NUT IS NOT LOOSENED, DAMAGE TO WORM GEAR MECHANISM CAN OCCUR DURING ADJUSTMENT.
(4)
Loosen lockscrew from worm gear on switch arm. Turn worm gear until limit switch is preloaded against cam to open position as denoted by a click.
(5)
Tighten and lockwire lockscrew. Tighten hexagon locking nut to 20-25 pound-inches.
(6)
Test limit switches per par. 4.
(7)
Close access door.
523
Feb 20/92 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-41-101 Page 501
G11145G11250
Stabilizer Trim Limit Switch Adjustment 582
27-41-101 Figure 501 (Sheet 1) Jan 20/82
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
524 Stabilizer Trim Light Switch Adjustment
Nov 15/76 Figure 501 (Sheet 2) 27-41-101
Page 503
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
4. Stabilizer Trim Limit Switch Test
A. General
(1) If the stabilizer system runs beyond the limits given in the following test, the overcoasting may be caused by electric actuator powder settled in the clutches. This usually occurs after overnight storage and/or setting of the powder when operating through full stroke to check limits. The condition is completely safe in flight as the in-flight loads on the actuator are more than ample to stop the actuator at the limit switches. Overcoasting may be corrected by operating the stabilizer as follows:
(a)
Trim the stabilizer to approximately two units away from limit. Operate stabilizer trim by alternately energizing trim switch a total of four actuations (two nose down and two nose up).
(b)
Recheck stabilizer trim limit switches per paragraph B.
NOTE: Dimension B tolerances are greater during test, than adjustment, to allow for system coast.
(2) Refer to 22-11-0, Autopilot and Yaw Damper System - Adjustment/Test, for test of autopilot limit switches.
B. Test Stabilizer Trim Limit Switches
(1)
Open stabilizer trim access door 3701.
(2)
Provide electrical power.
(3)
Check that stabilizer trim actuator and stabilizer trim control circuit breakers on panel P6 are closed.
(4)
Inch stabilizer to maximum leading edge down (airplane nose up) position. Check that 1imit switches prevent further attempts of stabilizer leading edge down travel by captain's stabilizer trim switch but allow stabilizer leading edge up (airplane nose down) travel.
(5)
Back off from maximum stabilizer leading edge down position and using captain's stabilizer trim switch run stabilizer leading edge down until limit switches are actuated. When system stops, check that dimension B is between 27.62 and 27.98 inches.
(6)
Inch stabilizer to maximum leading edge up (airplane nose down) position. Check that limit switches prevent further attempts of stabilizer leading edge up travel by captain's stabilizer trim switch but allow stabilizer leading edge down (airplane nose up) travel.
(7)
Back off from maximum stabilizer leading edge up position and using captain's stabilizer trim switch run stabilizer leading edge up until limit switches are actuated. When system stops, check that dimension B is as follows:
(a) Between 41.71 and 41.99 inches with stabilizer electric actuator limit switch and takeoff warning switch (airplane nose down) adjusted to actuate at 41.85 +0.05 inches.
(8)
Remove electrical power, if no longer required.
(9)
Close access door.
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27-41-101 Page 504 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
582
Feb 20/86 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-41-101 Page 505
STABILIZER TRIM CONTROL SWITCH - REMOVAL/INSTALLATION
1. General
A. The stabilizer trim control switch assembly includes an electrical cable routed through the control wheel handle to a terminal block in the control wheel. If a switch becomes defective the electrical cable and switch are replaced as an assembly.
2. Equipment and Materials
A. Talc
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