Abstract: A device and method for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces.

Abstract: A fuselage element including a fuselage segment including a skin and a junction means for connecting the skin to an adjacent fuselage segment. The fuselage segment extends along a longitudinal axis of the fuselage, and the skin includes a first section at at least one end of the fuselage segment. The fuselage segment includes at least one longitudinal stiffening element for the fuselage. A junction member is arranged so as to contact an outer surface of the first section of the skin, and the stiffening element partially extends to the junction member along the longitudinal axis.

Abstract: Device for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces. Set of fuselage sections assembled by means of a device of the type described above. Method of assembling two fuselage sections by means of a device of the type described above.

Abstract: A landing gear mounted under an aircraft wing is provided. The aircraft can comprise a fuselage and wings each comprising at least one longitudinal spar connected to a wing box being part of the structure of the fuselage. The landing gear can comprise one leg that pivots, on its upper end, around a rotation axis to occupy at least one extended position and one retracted position and which is provided, on its lower end, with rolling means, the leg being connected, on its upper end, to the longitudinal spar of said wing. The landing gear can also comprise at least one inclined front strut connected, on its lower end, to said leg and connected, on its upper end, to the structure of the fuselage thru connecting means. The connecting means can comprise a sliding bearing crossed by at least one part of the upper end of said strut.

Abstract: The invention relates to a fuselage element comprising a fuselage segment (1a) comprising a skin (3a), and junction means (6) for connecting the skin of said segment (1a) to an adjacent segment (1b). The segment (1a) extends along the longitudinal axis (X) of the fuselage, and the skin (3) includes at least one first section (10) at least one end of said segment (1a). The fuselage segment (1a) comprises at least one longitudinal stiffening element (5a) for the fuselage. The junction means (60) are arranged so as to contact an outer surface (30) of said first section (10) of the skin (3a), and the stiffening element (5a) partially extends at the junction means (6) along the longitudinal axis (X).