5B3
May 01/98 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Contents 51 Page 1
Subject Subject No.
Abrasion Resistant Molybdenum Disulfide Finish....................................................... 51-21-121
Skin and Fastener Corrosion Control.......................................................................... 51-21-131
High Temperature Coating for Titanium...................................................................... 51-21-141
Nonskid Surface.......................................................................................................... 51-21-151
Heat, Weather and Oil Resistant Inorganic Protective Coating.................................. 51-21-161
Decorative Paint System............................................................................................. 51-21-171
SEALS
SEALS AND SEALING ............................................................................................... 51-31-0 Description and Operation Definitions of Levels of Sealing
Maintenance Practices
Accelerating Curing
Apply Aerodynamic Smoother
Apply Electrical Fitting Seal
Apply Fastener Seal
Apply Faying Surface Seal
Apply Fillet Seal
Apply Fuel Seal
Apply Hole and Slot Seal
Apply Injection Seal
Prepare for Sealing
Protection of Sealing Materials
Special Sealing Method for Corrosion Protection
DRAINAGE
AIRFRAME DRAINAGE.............................................................................................. 51-41-0 Description and Operation
External Drainage - Inspection/Check ..................................................................... 51-41-11
Internal Drainage -Inspection/Check ...................................................................... 51-41-12
Fuselage Drain Valve - Removal/Installation........................................................... 51-41-13
RUB PADS
BONDED RUB PADS Phenolic and Stainless Steel Rub Pads .................................................................. 51-51-11 Approved Repairs Teflon Rub Pads ...................................................................................................... 51-51-21 Approved Repairs
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Contents 51 Page 2 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/90
STRUCTURES - DESCRIPTION AND OPERATION
1. General
A. The structure of the airplane (figure 1) is designed to provide maximum strength with minimum weight. This object has been achieved by designing alternate load paths into the structure, so that a failure of one segment cannot endanger the airplane, and also by the use of appropriately selected materials. The materials most commonly used throughout the structure are aluminum, steel and magnesium alloys. Of these the most extensively used are certain aluminum alloys, which are selected according to the particular type of load they are best suited to withstand.
B. Aluminum and fiberglass honeycomb core material is used extensively on secondary areas of structures and many of the flight surfaces.
C. Maintenance practices concerning blowout doors and panels are covered in applicable chapters on structures. See figure 4 for a comprehensive illustration of blowout doors and panels on the airplane.
2. Fuselage
A. The fuselage is a semimonocoque structure with the skin reinforced by circumferential frames and longitudinal stringers. It is composed of four sections: body sections 41, 43, 46 and 48, of which the forward three together extend from body station 178 to body station 1016 and contain all the passenger, crew, and cargo accommodations. The fourth section of the fuselage is at the aft end and provides support for the empennage. Refer to figure 2.
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 landing 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 longitudinal 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 longitudinally, and the control cabin where the floor structure has to accommodate control gear and other special equipment. The forward airstairs are installed below the floor of body section 41. The fuselage frames at body stations 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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