HORIZONTAL STABILIZER LEADING EDGES - REMOVAL/INSTALLATION
1. Remove Horizontal Stabilizer Leading Edge
A. Remove bolts attaching lower surface of leading edge to front spar.
B. Remove bolts attaching upper surface of leading edge to front spar.
CAUTION:  DO NOT ALLOW LEADING EDGE TO SLIP OFF FRONT SPAR UNTIL ALL ATTACHING BOLTS ARE REMOVED.
C. Support each end of leading edge.
D. Remove leading edge.
2. Install Horizontal Stabilizer Leading Edge
A. Place leading edge in position on stabilizer front spar.
B. Install bolts attaching upper surface of leading edge to front spar.
C. Install bolts attaching lower surface of leading edge to front spar.
NOTE: Tighten bolts within torque range of 23 to 28 pound-inches.
500 
May 15/68  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-41-21 Page 401 

HORIZONTAL STABILIZER CENTER SECTION HINGE FITTING . REMOVAL/INSTALLATION
1.  General
A.  The design of horizontal stabilizer permits removal of horizontal stabilizer center section hinge fitting without removal of the outboard stabilizer sections.
B.  The following procedure covers removal of both right and left hinge fitting with exceptions noted where applicable. Installation of hinge fitting on one side should be completed before attempting work on opposite side.
2.  Equipment and Materials
A.  Horizontal Stabilizer Hinge Pin Removal Tool . F80047-1
B.  Horizontal Stabilizer Thread Protector . F80183-1
C.  Stabilizer Trim Lock . F71336-501
D.  Dial Indication Depth Gage
E.  Grease . BMS 3-24 (Ref 20-30-21)
3.  Prepare Horizontal Stabilizer Center Section Hinge Fitting for Removal
A.  Position stabilizer to maximum leading edge down position.
B.  Position horizontal stabilizer trim cutout switches to CUTOUT.
C.  On circuit breaker panel P6, open following circuit breakers:
(1)  
Autopilot stabilizer trim servo

(2)  
Stabilizer trim actuator

D.  In area of jackscrew gearbox, disconnect electrical plug from electric actuator and autopilot actuator.
E.  Install stabilizer trim lock assembly (Fig. 401).
F.  Open aft unpressurized compartment and stabilizer trim access door 3701.
G.  Remove stabilizer access panel 9105 or 9205 and end side door (detail A).
H.  Remove lower rear spar and trailing edge gap covers to permit access to the hinge.
I.  Provide adequate support of stabilizer structure and center section assembly (Fig. 402) in area of hinge components to ensure holding of all components in proper alignment during removal and replacement.
4.  Remove Horizontal Stabilizer Center Section Hinge Fitting
A.  Remove both cotter pins, nut (8, Fig. 402), and washer (9).
B.  Remove nut (7) and bushing spacer (6).
C.  Remove locking plate (11).
D.  Install washer (9) and nut (8).
E.  Attach horizontal stabilizer hinge pin removal tool and push hinge pin (1), bushing retainer (17), and hinge pin (2) out.
F.  Remove both positioning hinge bushings (10 and 16). A bushing spacer (3), if used, will come off with adjustable positioning hinge bushing (16) when removing the hinge fitting on the right side. 
G.  Remove outboard hinge fitting (12) by removing 14 bolts.
500 
Apr 01/97  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-41-31 Page 401 

F94307
Horizontal Stabilizer Center Section Hinge Fitting -Preparation for Removal  500 
27-41-31  Figure 401  Aug 01/96 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

5. Install Horizontal Stabilizer Center Section Hinge Fitting
A.  Install outboard hinge fitting (12) except omit forward bolt under center section hinge.
B.  Use a dial indication depth gage through bolt hole in outboard hinge fitting (12) to check and record dimension between center section (5) and outboard hinge fitting.
CAUTION:  STABILIZER IS TO BE IN A FREE STATE TO PREVENT PRELOAD ON BEARING. STABILIZER SUPPORT EQUIPMENT MUST PREVENT INTRODUCTION OF A SIDE LOAD ON STABILIZER.
C.  Install the bushing (16):
(1)  
For the right-hand hinge, install the bushing spacer (3) and the bushing (16).

(2)  
For the left-hand hinge, install the bushing (16).

(3)  
Finger-tighten the bushing (16) until a snug contact is made with faying surface of bearing (4).

(4)  
Check dimension previously recorded in step B. with dial indication depth gage to ensure proper contact between bushing (16) and bearing (4).
　
中國航空網(wǎng) m.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(149)