C.  Set horizontal stabilizer B dimension at 41.57 ±0.01 inches, using trammel bar (Fig. 407).
D.  Install rigging pin E-5 in aft control quadrant (Fig. 405).
4.  Remove Elevator
A.  Detach elevator control pushrod from elevator (Fig. 405). Remove bolts through circular access opening in tail cone adjacent to bolthead.
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. IF ELEVATOR CONTROL PUSHRODS ARE REMOVED FROM AIRPLANE, THE PUSHRODS MUST BE INSTALLED WITH THE FORE/AFT ORIENTATION SHOWN IN FIG.
405. IF PUSHRODS ARE DISASSEMBLED, SUITABLY IDENTIFY EACH INDIVIDUAL ITEM TO AVOID MISMATCHING PARTS DURING ASSEMBLY.
G42395
Access Panel Locations  501 
27-31-11Page 402   Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/93 

B.  Disconnect tab pushrods and tab lockout mechanism as follows (Fig. 408):
(1)  
Remove elevator tab lock linkage bolt retainer shield to obtain access for removal of frame attach bolts.

(2)  
Remove tab pushrod aft mounting bolt (2 places).

(3)  
Remove two bolts securing aft end of frame to elevator front spar.

(a)  Disconnect tab lock mechanism return springs if clearance is not adequate to remove bolts.
C.  At stabilizer trailing edge ribs No. 1 thru 6, remove elevator to stabilizer gap seals (Fig. 402).
D.  Remove six bolts securing aft portion of each balance panel hinge to elevator nose. Detach balance panels from elevator (Fig. 406).
E.  Remove elevator hinge fitting No. 4 from elevator front spar and from stabilizer trailing edge (Fig. 403).
F.  Secure elevator hoisting adapter to elevator front spar at front hinge fitting No. 4 location (Fig. 404).
G.  Attach sling to elevator hoisting adapter and take up slack in line.
H.  Remove elevator hinge fitting No. 1 thru 3, No. 5 and 6 from elevator front spar (Fig. 403).
I.  Remove elevator from airplane.
NOTE:  Weight of elevator with tab and balance panels installed, is approximately 225 pounds.
527 
Feb 20/85  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-11 Page 403 

J.  If a different elevator is to be installed, perform the following steps: For installing original elevator, proceed to step 5.A.
(1)  
Separate elevator hinge fittings from stabilizer hinge fittings by removing hinge bearing bolts from all hinge fittings. Retain bolts, nuts, washers and bonding jumpers for subsequent installation.

(2)  
Detach hoisting adapter from elevator front spar.

(3)  
Insert hinge mounting bolts finger-tight and install elevator hinge fittings at original locations on elevator front spar (Fig. 403).

(4)  
Install elevator to stabilizer gap seals adjacent to hinge fittings and along edge of elevator nose at stabilizer trailing edge ribs No. 1 thru 6 (Fig. 402).

(5)  
Refer to figure 401 and replace the following access panels: Tab pushrod access panel, elevator tab lock mechanism upper and lower access panels, and elevator hinge fitting upper and lower access panels.

5.  Prepare for Installation
A.  Check elevator hinge bearings, hinge bearing bolts, and elevator control linkage for allowable wear (Ref Elevator - Inspection/Check).
CAUTION:  ELEVATOR CONTROL PUSHROD, PUSHROD BOLT AND ROD END BOLT ARE DUAL LOAD PATH COMPONENTS. INSPECT INNER AND OUTER RODS/BOLTS FOR DAMAGE PRIOR TO INSTALLATION.
B.  If new elevator is being installed, perform the following steps on new elevator. If original elevator is being installed, proceed to step 5.C.
(1)  
Refer to Fig. 401 and remove the following access panels: Elevator tab lock mechanism upper and lower access panels. Panels are located at elevator inboard leading edge, tab pushrod access panel, and elevator hinge fitting upper and lower access panels.

(2)  
Remove elevator to stabilizer gap seals adjacent to hinge fitting and along edge of elevator nose at stabilizer trailing edge ribs No. 1 thru 6 (Fig. 402).

(3)  
Referring to Fig. 403, remove all hinge halves from front spar of replacement elevator and assemble to stabilizer trailing edge as follows:

(a)
Lightly coat hinge bearing bolts with corrosion preventive compound.

(b)  
Al elevator hinge fitting No. 1 location, install hinge bearing bolt with head outboard. Place washer under bolt head and washer and bonding jumper under nut. Clean surface to provide electrical bonding. Tighten nut to 95-100 pound-inches torque. Align nut with cotter pin hole without exceeding 190 pound-inches torque, then install cotter pin.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 2(77)