CAUTION: IF PUSHROD NUTS ARE NOT TORQUED PROPERLY, THE PUSHRODS CAN BECOME DETACHED AND CAUSE DAMAGE TO THE ELEVATORS AND STABILIZERS.
(2)
See Detail A, Fig. 408, and install tab pushrods as follows:
(a)
Install tab pushrod aft mounting bolts. Install outboard bolt with head facing outboard and inboard bolt with head facing inboard.
(b)
Install nut and washer on each tab pushrod 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)
Connect tab lock mechanism return springs if disconnected.
527
27-31-11 Page 410 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
G. Measure breakaway forces required to move elevator. Use spring scale and loading block and apply force to elevator rear spar, adjacent to inboard rib.
(1)
Slowly rotate elevator by hand through full travel up and down and check for roughness or binding.
(2)
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. 405).
(3)
Record the force at the time the elevator reaches the neutral position.
(4)
The difference between these forces shall not exceed 1.0 pound.
G42398 G09183 G09187
501 Elevator Control Linkage
Feb 20/93 Figure 405 27-31-11
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Balance Panel Installation 500
27-31-11Page 412 Figure 406 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/67
500 Stabilizer Trim Jackscrew Setting
Jul 15/70 Figure 407 27-31-11
Page 413
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H. Attach elevator control pushrod to elevator as follows (Fig. 405):
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.
(1)
Return elevators to neutral position.
(2)
With head facing inboard, insert bolt from inside tail cone through circular access opening, through control pushrod and elevator lug.
(3)
Tighten first locknut 500 to 600 pound-inches torque, then tighten second locknut 150 to 220 pound-inches torque.
CAUTION: AFTER SETTING TORQUE ON SECOND LOCKNUT, DO NOT ATTEMPT TO RESET TORQUE ON FIRST LOCKNUT.
I. Remove rigging pin E-5 from aft control quadrant.
J. Restore airplane to normal hydraulic configuration (Ref 27-31-0).
K. Adjust and test elevator and tab per 27-31-0, A/T.
L. Close or replace all access doors and panels.
500
27-31-11 Page 414 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/84
G09198 G09238
527 Elevator Tab Lock Linkage Installation
Nov 01/75 Figure 408 (Sheet 1) 27-31-11
Page 415
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Elevator Tab Lock Linkage Installation 527
27-31-11 Figure 408 (Sheet 2) Nov 01/75
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ELEVATOR - INSPECTION/CHECK
EFFECTIVITY
Airplanes with Aluminum/Fiberglass 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.
2. Elevator Hinge Wear Limits
G42406
500 Elevator Hinge Wear Limits
Jun 20/90 Figure 601 (Sheet 1) 27-31-11
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G42413G09246
Elevator Hinge Wear Limits 500
27-31-11 Figure 601 (Sheet 2) Feb 20/89
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