Abstract: A fuselage rear end of an aircraft, comprising a structural part comprising a skin and longitudinal and transversal reinforcing members and a fairing. The structural part longitudinally spans over the whole rear end and comprises a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section. The fairing is located below the second portion of the structural part.

Abstract: A fuselage rear end of an aircraft, comprising a structural part comprising a skin and longitudinal and transversal reinforcing members and a fairing. The structural part longitudinally spans over the whole rear end and comprises a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section. The fairing is located below the second portion of the structural part.

Abstract: An aircraft fuselage part (31) located in a section of an aircraft (11) having a propulsion system (13) attached by upstream pylons (17), the fuselage part includes a skin (35); a plurality of frames (37) arranged perpendicularly to a longitudinal axis (33); a single or internally divided upper longitudinal box (41) and a single or internally divided lower longitudinal box (51) which are configured to form with the skin (35) a multi-cell structure, belonging in each cell the external side to the skin (35) and the internal sides to the longitudinal boxes (41, 51); a plurality of lateral beams (61) that are interconnected with the frames (37) to form together with the skin (35) a structural unity. The fuselage components (35, 37, 41, 51, 61) are dimensioned so that the aircraft can withstand the effect of pre-defined failure events keeping a sufficient number of closed cells.

Abstract: The aircraft fuselage part (31) located in a section of an aircraft (11) having attached a propulsion system (13) by means of upstream pylons (17) that comprises: a skin (35); a plurality of frames (37) arranged perpendicularly to the longitudinal axis (33), a single or internally divided upper longitudinal box (41) and a single or internally divided lower longitudinal box (51) which are configured to form with the skin (35) a multi-cell structure, belonging in each cell the external side to the skin (35) and the internal sides to said longitudinal boxes (41, 51); a plurality of lateral beams (61) that are interconnected with said frames (37) to form together with the skin (35) a structural unity. Said fuselage components (35, 37, 41, 51, 61) are dimensioned so that the aircraft can withstand the effect of pre-defined failure events keeping a sufficient number of closed cells.