Forward Fuselage - Section 13/14 Figure 001
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Forward Fuselage - Section 13/14 Figure 001A
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R R Forward Fuselage - Section 13/14 Figure 001B
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R R Forward fuselage - Section 14A Figure 002
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R **ON A/C ALL
2. Description___________
R A. Frames (Ref. Fig. 003)
(1) Frame 24 Frame 24 provides the splice between sections 13/14 and 11/12 (Ref. 53-10-00). The core of the frame consists of curved members formed from L-section sheet metal joined by splices. The skin of the two sections is secured by a T-section edging by lockbolts to the frame core and a splice.
(2) Frame 24A This secondary frame, the top part of which is open, forms the forward vertical member of the cargo door frame. It consists of a machined curved member (located on the right side between stringers 20 and 44) and a curved member formed from Z-section sheet metal (located on the left side between stringers 31 and 44).
(3) Frames 25, 26 and 27 These frames are open at the cargo door. They consist of curved members formed from sheet metal. Three frame lower sections located above the cargo door provide the joint between the upper curved members of the frame, the cabin floor cross beams and the top frame of the cargo door.
(4) Frames 29 to 34 These closed frames consist of curved members formed from Z-section sheet metal connected by splices.
R **ON A/C 301-399,
R R R R R (5) Frame 35 Frame 35 provides the splice between sections 13/14 and 14A. The core of the frame consists of curved members formed from L-section sheet metal joined by splices. The skin of the two sections is secured by a T-section edging by lockbolts to the frame core and a splice.
R R R (6) Frames 35.1 to 35.2A These frames are open at the emergency exit. They consist of curved members formed from sheet metal.
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(7) Frames 35.3 to 35.8 These closed frames consist of curved members formed from Z-section sheet metal, connected by splices.
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B. Stringers (Ref. Fig. 003) The fuselage stringers consist of folded aluminium alloy Z-section sheet metal. They are arranged longitudinally and, together with the frames, they stiffen the fuselage ; the skin is attached to them. At the stringer 18,added lockbolts in place of rivets
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C. Skin
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(Ref. Fig. 001)
R **ON A/C 151-199, 401-499,
(Ref. Fig. 001A)
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(Ref. Fig. 003) The outer skin comprises three upper panels extending from FR24 to FR35 and fire lower panels. The two upper lateral panels include the openings for the cabin windows. The forward right lower panel includes the opening for the cargo door. The forward wing to fuselage fairings are attached to the lower section of the skin (Ref. 53-25-11). The skin panels are aluminium alloy sheets lightened by cut-outs formed by chemical milling. Skin joints are formed by overlapping the edges of the upper panel on the lower panels on stringers 6, 18, 32 and 41. They are reinforced by crack-stop plates on frame intersections. The skin is secured to the frame via frame doublers and to the stringers.
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Fuselage Section R Figure 003
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C. Skin (Ref. Fig. 001B, 002, 003) The outer skin comprises three upper panels extending from FR24 to FR35.8 and fire lower panels. The two upper lateral panels include the openings for the cabin windows. The forward right lower panel includes the opening for the cargo door. The forward wing to fuselage fairings are attached to the lower section of the skin (Ref. 53-25-11). The skin panels are aluminium alloy sheets lightened by cut-outs formed by chemical milling. Skin joints are formed by overlapping the edges of the upper panel on the lower panels on stringers 6, 18, 32 and 41. They are reinforced by crack-stop plates on frame intersections. The skin is secured to the frame via frame doublers and to the stringers.
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D. Cabin Floor Structure
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