Description and Operation
Miscellaneous Equipment Attachment Fittings
Seat Attachment Fittings

Passenger Cabin and Cargo Compartment Tracks................................................. 53-42-11

AERODYNAMIC FAIRINGS
FILLET FAIRINGS ...................................................................................................... 53-51-0 Description and Operation Wing to Body Fairings
Wing-to-Body Fairing Blowout Panel ....................................................................... 53-51-11 Removal/Installation
Aft Wing-to-Body Fairing.......................................................................................... 53-51-21 Removal/Installation Subject Subject No.
5C8 
Contents 53 Page 2  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/89 

NOSE RADOME ......................................................................................................... 53-52-0 Description and Operation Removal/Installation Inspection/Check Cleaning/Painting Approved Repairs
Nose Radome Erosion Coating ............................................................................... 53-52-21 Approved Repairs
Glide Slope Antenna Director Bar............................................................................ 53-52-31 Removal/Installation
TAIL CONE ................................................................................................................. 53-53-0 Removal/Installation
*[1] GJ B2524
5C8 
Feb 20/89  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Contents 53 Page 3/4 

FUSELAGE - DESCRIPTION AND OPERATION
1. General
A.  The fuselage is a semi-monocoque structure consisting of skin reinforced by circumferential frames and longitudinal stringers. Major fuselage components are illustrated in figure 1.
B.  A typical section through the fuselage consists of an upper oval lobe and a lower oval lobe which intersect approximately at the floor level. At the intersection the fuselage is reinforced by transverse floor beams. Above this floor structure, which extends from the front pressure bulkhead at body station 178 to the rear pressure bulkhead at body station 1016, the upper lobe of the fuselage encloses the cabin and is basically a continuous shell, with cutouts in the skin for doors and windows. Below the floor the continuity of the lower lobe, which encloses the cargo compartments, is interrupted by several major structural features: the nose landing gear wheel well, the cavity for the center wing box and the main landing gear wheel well. Aft of the rear pressure bulkhead the floor is discontinued and this section of the fuselage, which tapers towards its aft end, supports the vertical fin, the horizontal stabilizer, a tail skid and contains a compartment with fireproof walls for the APU.
C.  The various loads on the fuselage are due to combinations of flight, static, landing and pressure loads. Basically the fuselage resembles a hollow tubular beam supported approximately at the center by the wing. This condition applies an overall bending load, to which may be added torsion applied by various flight maneuvers, and which is further complicated by pressurization loads acting on the whole body shell between stations 178 and 1016. Special design features maintain structural continuity between body stations 540 and 727, where the cavities for the center wing box and the main landing gear interrupt the lower half of the basically tubular fuselage. A keel beam, connects the bottom of the fuselage frame at station 540 with the bottom of the frame at station 664 and passes below the center wing box.
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Apr 15/66  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  53-00 Page 1 

D.  The pressure wall over the center wing box area is formed by the upper surface of the wing itself, which also supports longitudinal cabin floor beams. A keel beam across the main landing gear wheel well connects the fuselage frames at stations 664 and 727. Over this area the floor structure is plated and reinforced to form the pressure wall. A wing to fuselage connection exists by means of two six-flanged chords running between body stations 540 and 664, at buttock line 70.85 along the upper edges of the wing. The fuselage skin attaches to the upper flange of the six-flanged extrusions while the other five flanges are connections for the wing boxes to the center wing box. Main landing gear loads, other than those borne by the wing, are transmitted to the fuselage structure by the inboard ends of the landing gear support beams which are connected to fuselage structure at body station 706. All openings in the fuselage shell, such as those for doors and windows, are reinforced locally to maintain proper distribution of loads around the openings. The whole fuselage structure is designed on the fail-safe principle which provides alternate load paths to ensure that the entire fuselage is not jeopardized by the failure of any one member.
　
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