737 AMM 飞机维护手册飞行操纵 FLIGHT CONTROLS 2(83)_航空信息_民用航空_通用航空

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facing outboard and inboard bolt with head facing inboard. b) Install nut and washer on each tab push rod aft mounting bolt. c) If castellated nuts are used, torque nuts 30 to 50 inch-pounds. Ensure the
torque remains at 30 to 50 inch-pounds after alignment of cotter pin holes. If self-locking, non-castellated nuts are used, run-on torque must be between 3.5 and 30 inch-pounds. Replace any self-locking nut that does not meet this requirement. Torque nut 50 to 80 inch-pounds.
3) Install retainer shield.
4) On airplanes with four return springs, check that dimension given in Detail B, Fig. 409 is observed.
(9) Measure breakaway forces required to move elevator. Use spring scale and rib block and apply force to elevator rear spar, adjacent to inboard rib.
(a)
Slowly rotate elevator by hand through full travel up and down and check for roughness or binding.

(b)
If the elevator moves after releasing it at the neutral position (index mark), record the maximum force required to slowly move it back to the neutral position (Fig. 406).

(d)
Difference between these forces shall not exceed 1.0 pound.

500
27-31-12 Page 408 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99

500 Elevator Hinges
Oct 20/89 Figure 404 27-31-12
Page 409
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

Elevator Hinges 500
27-31-12 Figure 405 Oct 20/89
Page 410
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

G09274
500 Elevator Control Linkage
Oct 20/84 Figure 406 27-31-12
Page 411
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

(10) Attach elevator control pushrod to elevator as follows (Fig. 406):
CAUTION: DO NOT PERMIT INNER RACE OF OUTPUT TORQUE TUBE CRANK AND ELEVATOR MAST FITTING BEARINGS TO ROTATE TO A POSITION WHERE ROLLERS MAY DROP OUT THROUGH HOLE IN INNER RACE.
(a)
Return elevators to neutral position.

(b)
With head facing inboard, insert bolt from inside tail code through circular access opening, through control pushrod and elevator lug.

CAUTION: AFTER SETTING TORQUE ON SECOND LOCKNUT, DO NOT ATTEMPT TO RESET TORQUE ON FIRST LOCKNUT.

(d)
Remove rigging pin E-5 from aft control quadrant.

(e)
Restore airplane to normal hydraulic configuration (Ref 27-31-0).

(f)
Adjust and test elevator and tab per 27-31-0, A/T.

(g)
Close or replace all access doors and panels.

500
27-31-12 Page 412 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/84

G09277 G09278G09281 G09283
500 Balance Panel Installation
Oct 20/84 Figure 407 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-12 Page 413

Stabilizer Trim Jackscrew Setting 500
27-31-12 Figure 408 Oct 20/84
Page 414
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

500 Elevator Tab Lock Linkage Installation
Oct 20/84 Figure 409 (Sheet 1) 27-31-12
Page 415
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

Elevator Tab Lock Linkage Installation 500
27-31-12 Figure 409 (Sheet 2) Oct 20/84
Page 416
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

ELEVATOR - INSPECTION/CHECK
EFFECTIVITY
Airplanes with Graphite Elevators
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 (for the elevator linkage wear limits, go to AMM 27-31-11/601).
2. Elevator Hinge Wear Limits

500 Elevator Hinge Wear Limits
Feb 20/94 Figure 601 (Sheet 1) 27-31-12
Page 601

BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
　
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