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1.  General
A.  The lockwire installed in the horizontal stabilizer center section hinge fitting retainer nuts must be installed to prevent the retainer nuts from backing off. Several cases of bearing surface damage to the center section bulkhead area have been reported. It is not recommended that replacement of the lockwire be deferred until the next scheduled overhaul. 
2.  Equipment and Material
A.  Dial Indication Depth Gage
B.  Grease . BMS 3-24 (Ref 20-30-21)
3.  Remove Outboard Hinge Fitting (Fig. 801)
A.  Position stabilizer to maximum leading edge down position.
B.  Position horizontal stabilizer trim cutout switches to CUTOUT.
C.  Open following circuit breakers on circuit breaker panel P6:
(1)  
Autopilot stabilizer trim servo

(2)  
Stabilizer trim actuator

D.  Open aft unpressurized compartment and stabilizer trim access door 3701.
E.  Remove stabilizer access panel 9105 or 9205 and end side door (detail A).
F.  Remove lower rear spar and trailing edge gap covers to permit access to the hinge.
G.  Provide adequate support of stabilizer structure and center section assembly in area of hinge components to ensure holding of all components in proper alignment during removal and replacement.
H.  Remove both cotter pins, nut (8), and washer (9).
I.  Remove nut (7) and bushing spacer (6).
J.  Remove locking plate (11).
K.  Install washer (9) and nut (8).
L.  Remove positioning hinge bushing (10).
M.  Remove outboard hinge fitting (12) by removing 14 bolts.
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Apr 01/97  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-41-31 Page 801 

4.  Replace Lockwire
A.  Station one person inside airplane at hinge and one outside.
B.  Remove old lockwire.
C.  Install new lockwire and lockwire nuts to center section per double twist method.
5.  Install Outboard Hinge Fitting (Fig. 801)
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.  Insert positioning hinge bushing (10). Lubricate bushing on inside and outside prior to installation.
D.  Install bushing spacer (6) and nut (7). Finger-tighten nut.
E.  Install locking plate (11).
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27-41-31 Page 802  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jan 20/83 

F.  Temporarily remove bushing retainer (17) and apply torque to nut (7) of 300 to 600 pound-inches. If cotter pin holes do not align, tighten nut further to a maximum of 30 degrees rotation to first cotter pin hole.
CAUTION: DO NOT APPLY TORQUE TO BOLT HEAD.
G.  Use dial indication depth gage to check dimension previously recorded in step 5.B. between center section (5) and outboard hinge fitting (12). Dimension must be within + 0.005 inch. If so, install outboard hinge fitting forward bolt under center section hinge.
H.  Remove locking plate (11) and check gap between body structure and positioning hinge bushing (10). This gap must be 0.12 +0.07/-0.08 inch. If so, reinstall locking plate.
I.  Reinstall bushing retainer (17) with hinge insert pin (1). Rotate hinge insert pin until cotter pin hole is aligned with cotter pin hole defined in step F.
J.  Install washer (9) and nut (8) and tighten a maximum of 50 pound-inches. If cotter pin hole does not align, back off a maximum of 30 degrees to first cotter pin hole.
CAUTION: DO NOT TURN BOLTHEAD.
K.  Install cotter pins in nuts (7) and (8).
L.  Using stabilizer trim control wheel check that stabilizer will smoothly operate through full travel between jackscrew stops.
M.  Check that gap between jackscrew support fitting and fuselage structure just aft of jackscrew is
0.01 to 0.05 inch on both sides of stabilizer.
N.  Replace end side door and stabilizer access panel. Close stabilizer trim access door.
O.  Replace lower rear spar and trailing edge gap covers.
P.  Reconnect electric plugs of electric actuator and autopilot actuator.
Q.  Position horizontal stabilizer trim cutout switches to NORMAL.
R.  Close all circuit breakers opened on panel P6.
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Jan 20/83  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-41-31 Page 803 
　
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