Rear Fuselage Figure 001 
R  EFF : 001-049, 051-099, 101-149, 221-221, 224-224, 228-228,  53-40-00 Page 4 May 01/05
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 Rear Fuselage Figure 001A 
R  EFF : 151-199, 201-220, 222-223, 225-227, 229-299, 401-499,  53-40-00 Page 5 Aug 01/05
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R R  Rear Fuselage Figure 001B
 EFF :  301-399,  53-40-00 Page 6 May 01/04
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 **ON A/C ALL
 C. Dorsal Fin The dorsal fin (Ref. 53-45-00) is a fairing, which is installed at the leading edge of the vertical stabilizer-to-fuselage joint. The fairing permits the airflow to flow smoothly around the joint, and keeps the air turbulence to a minimum.
 D. Drains Drain valves (Ref. 53-49-00) are installed in the bottom of the fuselage, at locations where it is possible for water and condensation to collect. Drain holes in the internal structure let the water and condensation flow to the drain valves.
 EFF : ALL
53-40-00Page 7

 MAIN STRUCTURE - DESCRIPTION AND OPERATION__________________________________________
 1. General_______
 The main structure of the rear-fuselage is primary, made of aluminum-alloy.
 It has skin plates, frames, stringers and skin stiffeners, they are riveted
 together to make the fuselage shell. Top beams and seat tracks, riveted to
 crossbeams make the cabin floor stronger. Support struts and diagonal braces
 make the fuselage structure stronger.
 2. Component Location__________________ 
R  (Ref. Fig. 001)
 3. Description___________ 
R  A. Skin Plates 
R  The skin plates are made of aluminum-alloy sheets and stringers which are 
R  riveted to them make them stronger. Skin plates are preformed to the 
R  contour of the fuselage before they are riveted to the frames. 
R  B. Frames 
R  The frames are the stiffeners that go around the fuselage shell. They are 
R  made of aluminum-alloy sections which are formed or machined. Clips, with 
R  cut-outs for stringers, are riveted between the frames and the skin 
R  plates. Door frames and beams make the frame structure stronger in the 
R  area of the aft passenger/crew and cargo compartment(s) doors. 
R  C. Stringers and Skin Stiffeners 
R  The stringers are the longitudinal stiffeners of the fuselage shell. They 
R  are made of aluminum-alloy Z-sections which are formed, extruded or 
R  machined. They are riveted between the frames and the skin plates. Skin 
R  stiffeners make the skin stronger in areas where there are no stringers. 
R  The skin stiffeners are riveted to the skin. 
R  D. Crossbeams 
R  The crossbeams are made of aluminum-alloy C-sections which are extruded. 
R  They are riveted to the frames. They are the primary structure of the 
R  cabin floor. Support struts which are riveted to the crossbeams make them 
R  stronger. 
R  E. Top Beams and Seat Tracks 
R  The top beams are the longitudinal stiffeners of the cabin floor 
R  structure, they are riveted to the crossbeams. Seat tracks are riveted in 
R  pairs to the crossbeams and they are also part of the cabin floor 
R  main-structure.

 EFF : ALL
53-41-00Page 1
Aug 01/04

 Rear Fuselage Main-Structure
 Figure 001 (SHEET 1)
 EFF :  ALL  53-41-00 Page 2 
Feb 01/98
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 Rear Fuselage Main-Structure
 Figure 001 (SHEET 2)
 EFF :  ALL  53-41-00 Page 3 
Feb 01/98
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R  F. Floor Panels 
R  The floor panels are made of honeycomb core which is bonded between 
R  Glassfiber Reinforced-Polyester or aluminum sheets. Screws attach the 
R  floor panels to the floor structure. 
R  G. Junction Rear-Fuselage/Cone Rear-Fuselage 
R  (1) The junction of the rear-fuselage/cone rear-fuselage is located at 
R  STA3365/FR70. At this station the rear pressure bulkhead is 
R  installed. 
R  (2) The rear pressure-bulkhead has a frame made of aluminum alloy which 
R  is machined. The segments, made of aluminum-alloy sheets, are riveted 
R  to the frame to make a pressure diaphragm. 
　
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