(2)
Clean mating surfaces at forward attach bolt to provide electrical bonding.
(3)
Engage actuator splined shaft with internal spline of jackscrew gearbox and position the actuator for fastening.
(4)
Install actuator mounting bolts (15) and secure with washers and locknuts. Install forward mounting bolt for autopilot actuator with head down.
(5)
Install clamp to bolt clip at bolt (12) on gearbox cover.
(6)
Install electric connector (11).
(7)
Check that electrical resistance between actuator housing and airplane structure is 0.0025
ohm maximum. AA. Test stabilizer trim system.
(1)
Check that control column is in neutral and is unrestrained.
(2)
Test stabilizer manual travel limits.
(a)
Rotate captain's stabilizer trim wheel counterclockwise until stabilizer trim jackscrew up stop is just contacted.
(b)
Check that B dimension is 45.84 +0.10-inches (Fig. 403).
(e)
Check that stabilizer trim indicator indicates 0.0 +1/2 units AIRPLANE NOSEDOWN trim.
(d)
Turn captain's stabilizer trim wheel clockwise until lower stop is just contacted and check that B dimension is 21-32 +0.10 inches.
(e)
Check that stabilizer trim indicator indicates 17 +1/2 units AIRPLANE NOSE UP trim.
(f)
Check that position indicator on right side-agrees with indicator on left side at all stabilizer positions within 1/2 trim unit.
(3)
Check maximum force required during manual trimming at several places from one extreme of travel to other in both directions. Check that force does not exceed 14.7 pounds (60 pound-inches torque) measured at trim wheel handle.
(4)
Manually operate system through one complete cycle and check that system runs smoothly without binding.
(5)
Provide electrical power.
(6)
Check that all stabilizer trim control circuit breakers on P6 are closed.
(7)
Position left stabilizer trim switch to AIRPLANE NOSE DOWN and check that stabilizer leading edge moves up until limit switch is actuated. Check that stabilizer B dimension is between 41.71 and 41.99 inches.
CAUTION: DO NOT EXCEED ELECTRIC ACTUATOR DUTY CYCLE OF 2 MINUTES ON AND 13 MINUTES OFF.
(8)
Position left stabilizer trim switch to AIRPLANE NOSE UP and check following:
(a)
Stabilizer leading edge moves down until limit switch is actuated.
(b)
Stabilizer B dimension is between 27-62 and 27-98 inches after limit switch actuation.
(c)
Time to operate system from upper limit switch to lower limit switch is 13 to 19 seconds and that operation is smooth and free from chatter.
501
Jun 20/87 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-41-81 Page 413
582
27-41-81 Page 414 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/86
NOTE: Initial surges or chatter may be experienced due to cable stretch and mass of front end system.
(9)
Position left stabilizer trim switch to AIRPLANE NOSE DOWN and check that time for stabilizer to move to upper limit switch actuation point is 13 to 19 seconds and that operation is smooth and free from chatter (Ref NOTE, step (8)(c)).
(10)
Repeat step (8)(a) with right stabilizer trim switch., except check only that stabilizer leading edge moves down.
(11)
Repeat step (7), except check only that stabilizer leading edge moves up.
(12)
Position stabilizer at neutral.
(13)
Remove electrical power, if no longer required.
502
Nov 01/74 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-41-81 Page 415
STABILIZER BALL NUT AND JACKSCREW GEARBOX - INSPECTION/CHECK
1. General
A. This data consists of illustrations and wear limits charts. There will be no procedure given in this section for gaining access to, or removing and replacing the component after inspection for wear. Refer to Component Removal/Installation for this information.
2. Upper Gimbal Wear Limits (See figure 601.)
G10908 A06656
516 Upper Gimbal Wear Limits
Feb 01/74 Figure 601 (Sheet 1) 27-41-81
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Upper Gimbal Wear Limits 500
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