Abstract: An aircraft fuselage structure is disclosed herein and includes an outer skin, with circumferential ribs, such that a recess is provided for receiving a wing torsion box in the outer skin, and the ribs are interrupted in the region of the recess. An object of the disclosure includes providing an aircraft fuselage structure designed such that the wing torsion box is able to extend at least partially through the upper region of the fuselage, without the stability of the fuselage being significantly reduced. This can include providing first longitudinal members which are adjacent to the recess and which extend along the longitudinal edges beyond the entire length thereof. End regions of the first longitudinal members are connected to ribs which extend circumferentially at intervals from the transverse edges of the recess along the outer skin over the vertical longitudinal central plane.

Abstract: The invention relates to a bearing application for staircases in an aircraft with at least two decks. According to the invention at least two bearings, each with at least partially different possibilities of movement about and along or parallel to the x-axis, y-axis and z-axis of a system of coordinates, are arranged on each staircase at the lower and upper staircase end (rotatory and/or translational movements). Due to the presence of at least four bearings on each staircase, the relative movements between decks can be compensated for. Consequently the static design of the staircases can be limited to the intrinsic weight and operation-related loads by the mass of the users, thereby providing weight savings.

Abstract: An aircraft fuselage structure is disclosed herein and includes an outer skin, with circumferential ribs, such that a recess is provided for receiving a wing torsion box in the outer skin, and the ribs are interrupted in the region of the recess. An object of the disclosure includes providing an aircraft fuselage structure designed such that the wing torsion box is able to extend at least partially through the upper region of the fuselage, without the stability of the fuselage being significantly reduced. This can include providing first longitudinal members which are adjacent to the recess and which extend along the longitudinal edges beyond the entire length thereof. End regions of the first longitudinal members are connected to ribs which extend circumferentially at intervals from the transverse edges of the recess along the outer skin over the vertical longitudinal central plane.

Abstract: An aerofoil connection on a fuselage airframe comprising a plurality of double-jointed coupling members. In each case at least two z-coupling members extending substantially parallel to a vertical axis of the aircraft and in each case at least two xz-coupling members are arranged in the region of two longitudinal edges of a fuselage airframe recess wherein the xz-coupling members are configured in each case for a first maximum of a load in the event of a crash and of a load in normal flight operation parallel to a longitudinal axis of the aircraft, and for a second maximum of a load in the event of a crash and of a load in normal flight operation parallel to the vertical axis. The xz-coupling members are capable of absorbing force components parallel to the x-axis as well as force components which arise parallel to the z-axis.

Abstract: An aerofoil connection on a fuselage airframe comprising a plurality of double-jointed coupling members. In each case at least two z-coupling members extending substantially parallel to a vertical axis of the aircraft and in each case at least two xz-coupling members are arranged in the region of two longitudinal edges of a fuselage airframe recess wherein the xz-coupling members are configured in each case for a first maximum of a load in the event of a crash and of a load in normal flight operation parallel to a longitudinal axis of the aircraft, and for a second maximum of a load in the event of a crash and of a load in normal flight operation parallel to the vertical axis. The xz-coupling members are capable of absorbing force components parallel to the x-axis as well as force components which arise parallel to the z-axis.

Abstract: The invention relates to a bearing application for staircases in an aircraft with at least two decks. According to the invention at least two bearings, each with at least partially different possibilities of movement about and along or parallel to the x-axis, y-axis and z-axis of a system of coordinates, are arranged on each staircase at the lower and upper staircase end (rotatory and/or translational movements). Due to the presence of at least four bearings on each staircase, the relative movements between decks can be compensated for. Consequently the static design of the staircases can be limited to the intrinsic weight and operation-related loads by the mass of the users, thereby providing weight savings.