Burn through resistant aircraft fuselage

Details Burn through resistant aircraft fuselage Burn through resistant aircraft fuselage

B - Operations, Transporting

64

C

B64C 1/06 (2006.01)

Patent

CA 2720088

The invention relates to an aircraft fuselage (12) comprising at least one space arranged in the aircraft fuselage and at least one wall (16). According to the invention, the wall resists burnthrough for a period of at least four minutes from outside the aircraft fuselage towards the space, wherein the region of the aircraft fuselage (12) underneath the space does not comprise burnthrough-resistant insulation. The space can be a cargo compartment of the aircraft or a passenger cabin, while the wall can be designed as a cargo compartment floor, passenger cabin floor or wing/fuselage fairing (belly- fairing). The design, according to the invention, of the aircraft fuselage results in burnthrough resistance that meets the requirements of FAR § 25.856 (b) without any additional burnthrough-resistant insulation in the aircraft fuselage.

Linvention concerne un fuselage daéronef, dans lequel est ménagé au moins un espace et comprenant au moins une paroi. Selon linvention, la paroi résiste à la perforation par le feu de lextérieur du fuselage daéronef vers lespace pendant un intervalle dau moins quatre minutes, la région du fuselage daéronef située sous lespace ne comportant pas disolant résistant à la perforation par le feu. Lespace peut être une soute de laéronef ou une cabine passagers, la paroi pouvant être conçue sous la forme dun plancher de soute, dun plancher de cabine passagers ou dun carénage aile/fuselage (carénage ventral). La conception, selon linvention, du fuselage daéronef assure une résistance à la perforation par le feu conforme aux exigences de la norme FAR § 25.856 (b) sans quil soit nécessaire dincorporer dautre isolant résistant à la perforation par le feu dans le fuselage daéronef.

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