Aft Upper Structure - FR12 to FR24
Figure 002
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Nose Forward Fuselage
Figure 003
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R (3) The lower structure between FR1 and FR23 comprises:
R - a landing gear well which consists of three machined panels
R reinforced by extruded sections attached by rivets in the frame
R plane,
R - an assembly of frame curved members two of which, FR9 and FR20, are
R main frames and which make the forward and aft limit of the landing
R gear well,
R - two lower stringers which provide the joint between the lower skin
R panel and the lateral panels,
R - a lifting ring attached to the front of FR9,
R - four access door frames,
R - external power receptacle.
B. Skin
(Ref. Fig. 003)
The skin panels are formed from aluminium alloy sheets and include
cut-outs and reinforcement obtained through chemical milling.
NOTE : The skin panels above and below the windshield are made of____
titanium to provide improved protection against bird impact.
The lower section of the fuselage comprises three skin panels extending
from FR1 to FR24.
The central panel has an opening for access between frames 3 and 5 and
the opening for the nose landing gear between frames 9 and 20. The lower
right panel has two access openings between FR12 and FR14 and FR21 and
FR23.
The lower left panel has an access opening between FR13 and FR15.
The forward upper part of the fuselage (FR1 to FR12) comprises the
lateral skin panels and five upper skin panels. These panels are secured
to the windshield and side window frames.
The aft upper part of the fuselage section (FR12 to FR24) consists of
lateral skin panels and an upper skin panel. The lateral panels contain
the frames of the passenger/crew doors between FR16 and FR20. A channel
is installed above the doors.
All the skin panels are riveted together with an application of sealant.
C. Frames
(Ref. Fig. 004)
(1) Frame 1 Pressure Bulkhead
(Ref. Fig. 005)
Frame 1 which provides the forward pressure bulkhead of the fuselage,
is made with an aluminium alloy sheet reinforced by stiffeners
riveted to the forward and aft surfaces of the bulkhead. The forward
stiffeners are arranged horizontally and the aft stiffeners are
arranged horizontally and vertically.
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R R Frame Location Figure 004
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Frame 1 and Pressure Bulkhead Figure 005
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The joint between the pressure bulkhead and the outer skin is provided by edging made from formed metal sheet riveted to the edge of the frame and to the skin. The bulkhead attachment is reinforced by webs riveted to the skin and to aft stiffeners of the bulkhead, and by a box in the cockpit floor. The center part of the pressure bulkhead is thus secured to the support structure of the floor. The two radome hinge fittings and the radome latch and support fittings are attached to the upper and lower sections of the frame respectively. A protective bird-impact screen made of a honeycomb structure is secured to the forward face of the pressure bulkhead. New supports are installed on the honeycomb panel structure. A ballast of 200 kg (440.9244 lb) can be fitted to these supports.
(2)
Frame 2 (Ref. Fig. 006) The top of the frame is closed by a machined curved member the upper section of which is straight. This provides a forward attachment point for the instrument panel and the frame for the windshield. The lateral and lower curved members are formed from folded Z-section sheet.
(3)
Frame 3 Consists of machined lateral and lower curved members. Its upper section is open.
(4)
Frame 4 Consists of folded sheet lateral and lower curved members. Its upper and lower sections are open.
(5)
Frame 5 The lower curved member is machined and the lateral curved members are formed from folded sheet.
(6)
Frames 6 and 7 These frames consist of two lateral curved members and a lower curved member formed from folded sheet.
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