G42346G09324
Stabilizer Trim Jackscrew Setting  500 
27-31-41  Figure 501  Feb 20/93 
Page 502 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500  Elevator Control Pushrod Attachment 
Aug 15/67  Figure 502 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-41 Page 503 

(g)  Move each elevator by hand through full travel in both directions. Movement shall be smooth and without binding.
(2)  
Measure elevator limits of travel in both directions.

(a)  
Move right elevator up through full travel. Elevator trailing edge shall deflect 14.60 +0.30/-0.55 inches from index mark on tail cone.

(b)  
Move right elevator down through full travel. Elevator trailing edge shall deflect 10.55 +0.60/-0.30 inches from index mark on tail cone.

(c)  
Move left elevator up through full travel. Elevator trailing edge shall deflect 14.60 +0.30/-0.55 inches from index mark on tail cone.

(d)  
Move left elevator down through full travel. Elevator trailing edge shall deflect 10.55 +0.60/-0.30 inches from index mark on tail cone.

(3)  
Connect each elevator control pushrod to its respective elevator as follows:

CAUTION:  DO NOT PERMIT INNER RACE OF ELEVATOR MAST FITTING BEARING TO ROTATE TO A POSITION WHERE ROLLERS MAY DROP OUT THROUGH HOLE IN INNER RACE.
(a)  
Check that both elevators are positioned with trailing edge fully down.

(b)  
Release the control columns. Slowly rotate control columns fully forward and secure in this position. Tag the columns.

CAUTION:  PROVIDE ASSISTANCE AT EACH ELEVATOR TO GUIDE ELEVATOR CONTROL PUSHROD CLEVIS ONTO ELEVATOR LUG AS CONTROL COLUMNS ARE ROTATED.

(c)  
Connect each elevator control pushrod to its respective elevator. Install each mounting bolt with head facing inboard. Tighten first locknut within 500 to 600 pound-inch torque, then tighten second locknut within 150 to 220 pound-inch torque.

CAUTION:  AFTER SETTING TORQUE ON SECOND LOCKNUT, DO NOT ATTEMPT TO RESET TORQUE ON FIRST LOCKNUT.
(4)  Release control columns and allow columns to return to neutral position.
500 
27-31-41 Page 504  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/92 

ELEVATOR BALANCE PANELS - INSPECTION/CHECK
1.  General
A.  This data consists of illustrations and wear limits. There will be no procedure given in this section for gaining access to, or removing and replacing the components after inspection for wear. Refer to Component Removal/Installation for this information.
2.  Elevator Balance Panel Wear Limits
G09484
502  Elevator Balance Panel Wear Limits 
Jan 20/83  Figure 601 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-41 Page 601 

CONTROL COLUMN - REMOVAL/INSTALLATION
1.  General
A.  The procedure herein should not be enlarged upon. Further disassembly of the control column, while installed in the airplane, could result in damage to the equipment and restriction of the control system. Instructions for complete disassembly of the control column are contained in the Overhaul Manual.
B.  For replacement of the control wheel refer to 27-11-41 R/I.
2.  Equipment and Materials
A.  Control Column Protractor Assembly-4MIT65B80307-1 (Preferred) or F52485-500
(Optional) which is used with the following adapters:

(a)  
Aileron Control Wheel Protractor Mount-F72790

(b)  
Forward Thrust Lever Protractor Adapter-F72952-2

B.  Hole Filling Compound - BMS 5-16 (Ref 20-30-11)
C.  Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO.  F70207-( )  DIAMETER (INCHES)  LENGTH (INCHES)  FUNCTION 
E-1  -11  0.309-0.311  6.7 +0.25  FWD CONTROL QUADRANT 

3.  Prepare for Removal
A.  Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
B.  Open flight controls circuit breakers on circuit breaker panel P6 and stall warning circuit breakers in circuit breaker panel P18 and P6.
C.  Open lower nose compartment access door 1103 (Ref Chapter 12, Access Doors and Panels).
D.  Check that rigging pin E-1 can be installed in left forward control quadrant (9, Fig. 401), but do not leave rigging pin installed.
4.  Remove Control Column
A.  Remove ring assembly (3, Fig. 401) and dust seal (4).
B.  Install rigging pin E-1 in elevator left forward control quadrant (9).
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊 飛行操縱 FLIGHT CONTROLS 2(94)