(2)
Install bolt (8), washer (26) and nut (25).

(3)
Install cotter pin (24).

D. Connect the lower outboard end.
(1)
Install the thrust brace link (27) to fitting (9).

(2)
Install bolt (23), washer (13) and nut (12).

(3)
Install cotter pin (11).

500 
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A95671 A97512 A95673
500  Thrust Brace Link Assembly 
Oct 20/92  Figure 401 (Sheet 1)  55-10-10 
Page 403 
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Thrust Brace Link Assembly  500 
55-10-10  Figure 401 (Sheet 2)  Feb 20/93 
Page 404 
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500  Horizontal Stabilizer Center Section - Removal/Installation 
Feb 20/93  Figure 402  55-10-10 
Page 405 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

ELEVATOR - DESCRIPTION AND OPERATION
1. General
A.  The elevators are hinged on the aft edge of the stabilizer structure and include control tabs. Refer to Chapter 55 of the Structural Repair Manual for skin identification.
2.  Elevators
A.  The basic structure of the elevator is dual spar at the inboard end and mono spar at the outboard end, with all areas reinforced with ribs (Fig. 1). The elevators are attached to hinge ribs extending aft from the rear spar of the stabilizer by elevator hinges on the front spar of the elevator. The elevator nose and balance panels project forward of the hinge line and are housed in the spaces between the hinge ribs on the stabilizer rear spar. On some airplanes, aluminum conductive frames are outside the skin, with splice plates used to join the elevator tip fairing with the aluminum frames.
3.  Elevator Control Tabs
A.  The elevator control tabs are single spar structures located in cutouts in the trailing edges of the elevators (Fig. 1). A honeycomb panel trailing edge is attached to the aft side of the spar and extends aft in a tapering shape.
524 
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Elevator and Tab Structure  523 
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VERTICAL STABILIZER (FIN) - DESCRIPTION AND OPERATION
1. General
A.  The vertical fin is attached to body section 48. The fin may be removed from the airplane. The leading edge is detachable. The dorsal fin is not structurally connected to the main vertical fin and may be removed as a separate unit.
2.  Vertical Fin Structure
A.  The front and rear spars, the ribs and the skin of the vertical fin form a beam which is the main structural member of the fin. (See figure 1.) Attachment of the fin to the fuselage is by front and rear spar fittings at body stations 1016 and 1088, with no structural tie between the fin skin and the fuselage. 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 rudder. The left and right surfaces of the area between the rear spar and the rudder hinge bearings are covered by skin panels attached to the ribs to form a trailing edge fairing part of which is removable for maintenance purposes.
C.  A removable leading edge structure is attached to the forward side of the fin front spar. A fairing is attached at the top of the fin.  Removable panels are provided to allow access by maintenance personnel to the interior of the fin structure and the systems contained within it.
523 
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 Vertical Fin Structure  500 
55-30-0Page 2   Figure 1 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Nov 15/66 

VERTICAL STABILIZER (FIN) - REMOVAL/INSTALLATION
1. General
A.  There are two different sling assemblies which can be used to remove and install the fin. The F80035-( ) sling can be used with the rudder either installed or removed. After removal with the F80035-( ) sling, the fin must be supported in a vertical position. The C55004-1 sling can be used only with the rudder installed on the fin. After the fin is removed with the C55004-1 sling, the fin can be put on its side. This procedure must be performed in a hangar.
　
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