(b)
Bulges and cracks on the skins and the ribs.

 (c)
Corrosion on the fasteners.

 (d)
Other signs of the stress.

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 S 976-005-B00
 (11)
 Make a record of all the unsatisfactory conditions before you move the borescope to a different area.

 S 416-006-B00

 (12)
 Install the access panels.

 S 446-020-B00

 (13)
 Remove the stabilizer trim lock assembly, F71336-501, from the control stand.

 S 446-016-B00

 (14)
 Set the stabilizer trim cutout switches to NORMAL.

 S 446-019-B00

 (15)
 Remove the DO-NOT-CLOSE tags and close these circuit breakers:

 (a)  
P6 Circuit Breaker Panel
 1) STABILIZER TRIM ACTUATOR
 2) STABILIZER TRIM CONT

 (b)  
P18 Circuit Breaker Panel
 1) AUTOPILOT STABILIZER TRIM SERVO

 (16)
 Pressurize the elevator hydraulics, (AMM 27-31-00/201).

 (17)
 Pressurize the rudder hydraulics, (AMM 27-21-00/201).

 S 446-018-B00
 S 446-017-B00
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A
737-300/400/500MAINTENANCE MANUAL
 HORIZONTAL STABILIZER - DESCRIPTION AND OPERATION
_________________________________________________
 1.  General_______
 A.  The horizontal stabilizer assembly consists of left and right outboard sections attached to a center section truss located within the fuselage. The stabilizer is pivoted on two hinge joints attached to a bulkhead in the fuselage. The angle of attack is adjusted by means of an electrically driven or manually operated ball nut and jackscrew attached to the forward side of the center section truss (Ref Chaper 27, Stabilizer Trim System). An aerodynamic seal fills the gap between the stabilizer left and right outboard sections and the fuselage. A sliding plate seal is located at points where the front and rear spars pass into the fuselage. A leading edge is attached to the front spar. The trailing edge and elevator hinge structure is attached at the rear spar.
 2.  Stabilizer Structure____________________
 A.  The front and rear spars, the ribs and the skin of the horizontal stabilizer outboard sections together with the center section truss form a beam which is the main structural member of the stabilizer. Attachment of the outboard sections and the center section is at the front and rear spars only, with no structural tie between the outboard section skin and the center section (Fig. 1 and 2). Refer to Chapter 55 of the Structural Repair Manual for skin identification.
 B.  The structure aft of the rear spar consists of ribs which incorporate hinge bearings for the elevator. The upper and lower surfaces of the area between the rear spar and the elevator hinge bearings are covered by skin panels attached to the ribs. Some of the skin panels are removable for maintenance purposes.
 C.  The gimbels surrounding the jackscrew ball nut are supported by a rigidly built-up framework of members on the forward face of the center section truss front spar.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
FWD
JACKSCREW SUPPORT
HINGE SUPPORT
HINGE SUPPORT
STABILIZER ATTACH FITTINGS
Horizontal Stabilizer Outboard Section to Center Section Connection Figure 1
　
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