F84658 F84817
Typical Basic Structure  530 
51-00  Figure 1  Feb 20/90 
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500  Airplane Section Numbers 
Nov 15/66  Figure 2  51-00 
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

C.  Body section 48 of the fuselage is not pressurized and extends aft from the rear pressure bulkhead at body station 1016. The vertical fin structure and the horizontal stabilizer structure are supported by the 48 section. The APU is installed in a fireproof compartment below the horizontal stabilizer.
3.  Wings
A.  The structure of the wing, between left and right tips, consists basically of the left wing box, the center wing box, and the right wing box. The left and right wing boxes are cantilevered from the center wing box which carries, and is enclosed within, the fuselage. The thickness and chord of each wing tapers down towards the tip and, in plane view, both wings sweep back from the center wing box.
B.  The surfaces of the left and right wing boxes consist of upper and lower skin panels and front and rear spars. Throughout the left, center and right wing boxes, the skin panels are reinforced by spanwise stringers, and the spars by vertical stiffeners. The left and right wing boxes are reinforced by a series of chordwise ribs, and are sealed to serve as fuel tanks. The center wing box is reinforced by spanwise beams. The left and right wing boxes are attached to the center wing box by splice plates and chords. (See figure 3.) Another connection is by means of four fittings described in Chapter 57, Wing Terminal Fittings. These different types of connection make the wing structure fail-safe. The chords are four longitudinal members running between the bulkheads at stations 540 and 664, and at body buttock line 70.85 along the upper and lower edges of the wing. The two upper chords have six flanges to which the fuselage skin, the wing box skin and stringers, the center wing box skin and stringers, and the wing root ribs all attach. The two lower chords are T-sections. The wing root ribs attach to the webs of these chords and heavy splice plates attach to the flanges. The skins of the center wing box and the wing boxes attach to the splice plates. The stringers attach, on both sides of the web of the T-section, to the splice plates by means of fittings. There is no connection of the fuselage skin to the lower chords.
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C.  On each wing, the leading edge structure is cantilevered forward from the wing front spar. The trailing edge structure is cantilevered aft from the wing rear spar and supported additionally, at the inboard end of the wing, by the landing gear support beam. This beam is attached at its inboard end to the fuselage frame at body stations 695 and 706 and at its outboard end to the rear face of the wing rear spar. A bearing approximately midway along the landing gear support beam, together with one forward of it attached to the wing rear spar, form the axis of main landing gear rotation and are the points at which landing loads are transmitted to the wing structure.
D.  Five control surfaces are supported by the leading edge structure of each wing: two flaps are hinged from the inboard one-third of the win g span, and along the outboard two-thirds three extendable slats are installed. The control surfaces along the trailing edge of each wing consist of inboard and outboard flaps, an aileron and a total of four spoilers.
4.  Wing to Fuselage Attachment
A.  A connection exists between the wing and the fuselage by means of six flanged chords running between the bulkheads at stations 540 and 664, and at buttock line 70.85 along the upper edges of the wing. Refer to figure 3.
B.  The bulkhead at body station 540 and the center wing box front spar are integrated into one piece and the bulkhead at body station 664 and the center wing box rear spar are also integrated into on e piece.
C.  A connection exists between the lower surface of the center wing box and the fuselage keel beam which passes beneath it.
D.  Other points of attachment between the fuselage and the wings include the main landing gear support beams, the longitudinal floor beams, and the wing to body fairings. The wing to body fairings are attached to the fuselage and to the left and right wing upper surfaces.
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May 15/67  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  51-00 Page 5 
　
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