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a zone pressure limit-structure. The limit includes the top skin panel of the wing center-box section and two adjacent diaphragms. The forward diaphragm extends from FR35.8 to the wing box. The rear diaphragm extends from the wing box to FR46. Pressure limit bulkheads are installed in the wing-box front spar and in the lower part of FR35.8 and FR46,
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the center fuselage shell, which is made of skin-panels, frames, stringers and skin stiffeners,
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the passenger-compartment floor structure, made of longitudinal beams, seat and support tracks, support struts and floor panels.
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CES
MAIN STRUCTURE - DESCRIPTION AND OPERATION
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1. General
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The center fuselage main-structure includes:
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the wing center box which makes the wing-to-fuselage joint and is
installed in the lower center-fuselage shell,
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the belly fairing structure installed on the lower exterior of the
fuselage shell,
-skin panels which make the outer skin of the fuselage shell,
-frames which are the stiffeners around the fuselage shell,
-stringers and skin stiffeners to make the skin stronger,
-floor and pressure-limit structures. The floor structure makes the passenger compartment floor above the wing center box and the main-landing gear bay pressure limit-zone. The pressure limit structure makes a diaphragm between the upper (pressurized) and lower (unpressurized) areas of the center fuselage,
-seat tracks for the installation of the passenger compartment seats.
2. Description
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A. Wing Center Box
(Ref. Fig. 001)
The primary components of the wing center box include:
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two root ribs, one left and one right. The root ribs give external attach points and internal structural strength to FR37 thru FR41,
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two spars, one front and one rear. Two primary fuselage frames interface with the spars to make the wing-to-fuselage joint. FR36 is connected to the front spar and FR42 is connected to the rear spar. (The front spar is also a pressure bulkhead in the pressure limit zone).
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two skin panels, one top and one bottom. The top skin panel is part of the pressure limit-zone structure. The bottom skin panel is closed by the belly fairing structure. The box is made stronger by internal truss ribs. The truss ribs are installed along the length of the inner structure and extend between the front and rear spars. The complete wing center box-assembly reacts to wing bending moment. It transmits external wing shear and torsion into the fuselage. Some is transmitted through the root ribs, but most transmits through the two spars and primary frames, FR36 and FR42. Two triangular holes in the rear spar give hand access into the wing center box-structure. You can get access to the holes forward of the main landing-gear bay. Light-alloy panels close the holes. An integral fuel tank (option) can be installed in the wing center box-structure.
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53-31-00Page 1
Wing Center Box - Component Location
Figure 001
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B. Belly Fairing The belly fairing is installed on the exterior of the lower center fuselage. The structure is an extension to the fuselage and gives easy access to the air conditioning and hydraulic services equipment Ref. Task 53-35-00.
C. Center Fuselage
The center fuselage is constructed of:
-frames which give the shape and rigidity to the semi-monocoque structure,
-skin panels preformed to the contour of the fuselage and riveted to the frames to make the fuselage shell,
-stringers and skin stiffeners to make the fuselage skin stronger,
-floor structures to hold the passenger compartment floor above the pressure limit zone.
R **ON A/C 001-049, 051-099, 101-149, 201-299,
(1) Frames (Ref. Fig. 002) Frames are the circular stiffeners around the fuselage shell. All but the two primary wing box frames are made of aluminum-alloy sections. The top part of each frame is formed from sheet and the lower part is machined from plate. The two wing box frames, FR36 and FR42, are machined from forgings. Clips, with cutouts for stringers, are riveted between the frames and the skin panels. The center fuselage is constructed of the following frames:
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