737-300 400 500 AMM 飞机维护手册 结构 STRUCTURES(2)

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 B.  The entire shell of the fuselage between body stations 178 and 1016 is pressurized with the exception of the cavity enclosing the nose gear wheel well, and the large cutout which accommodates the center wing box and main leanding gear well. Structural continuity is provided across this latter area by a keel beam which passes beneath the center wing box and connects to a beam across the main landing gear wheel well. The whole pressurized portion of the fuselage is provided with a floor consisting of horizontal transverse beams attached to the fuselage frames and surmounted by logitudinal seat tracks and floor panels. Local variations in this floor structure include the area over the center wing box, and the main landing gear wheel well across which the floor beams run logitudinally, and the control cabin where the floor structure has to accommodate control gear and other special equipment. When installed, the forward airstairs are contained below the floor of body section 41. The fuselage frames at body sations 540 and 664 incorporate points at which the fuselage is attached to the wing front and rear spars. The connection between the inboard end of the landing gear support beam and the fuselage is a swinging link fitting attached to the frames at body stations 695 and 706.
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A 737-300/400/500MAINTENANCE MANUAL
 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
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 A.  The structure of the wing, between left and right tips, consists 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.

Typical Basic Structure
Figure 1

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A 737-300/400/500MAINTENANCE MANUAL
BBL 70.85

STIFFENER
CENTER WING BOX LOWER SKIN
Wing to Fuselage Attachment
Figure 2

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 B.

C.
D.
A 737-300/400/500MAINTENANCE MANUAL
The surfaces of the left and right wing boxes consists 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 some 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 (Fig. 2). 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 stingers, 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.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, from the axis of main landing gear rotation and are the points at which landing loads are transmitted to the wing structure.Five control surfaces are supported by the leading edge structure of each wing: two flaps are hinged from the inboard one-third of the wing 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 five spoilers.
　
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