Abstract: The pylon, intended to support a flying vehicle engine, includes a primary structure formed by at least one longeron and one panel, the panel including at least one end part provided with a notch, the longeron being provided with an end adapted to be positioned in the notch, the panel and the longeron being assembled by welding a part of the end to a part of the notch. A welded primary structure enables minimization of the blanks of parts associated with the longerons and with the panels by avoiding having recourse to the production of edges.

Abstract: The pylon, intended to support a flying vehicle engine, includes a primary structure formed by at least one longeron and one panel, the panel including at least one end part provided with a notch, the longeron being provided with an end adapted to be positioned in the notch, the panel and the longeron being assembled by welding a part of the end to a part of the notch. A welded primary structure enables minimization of the blanks of parts associated with the longerons and with the panels by avoiding having recourse to the production of edges.

Abstract: A device for manipulating a hollow shaft configured to create a pivot link between a first element and a second element. The manipulation device comprises a cylindrical body having a diameter variable by radial contraction or radial expansion of the cylindrical body, a module for controlling the diameter of the cylindrical body configured so that the diameter of the cylindrical body has alternatively at least a first diameter suitable for the cylindrical body to be displaced in the hollow shaft and a second diameter suitable for the cylindrical body to be blocked in the hollow shaft. The cylindrical body comprises an end configured to protrude from the hollow shaft when the cylindrical body is blocked in the hollow shaft. The manipulation device allows the alignment of the orifices due to the end configuration of the cylindrical body.

Abstract: A primary structure of an aircraft power plant support pylon is disclosed having a bottom stringer and two lateral walls formed in a single piece or welded so as to form a U-shaped bottom part, and a top cover which closes the U-shaped bottom part. The U-shaped part closed by a cover makes it possible to construct a box or box structure that exhibits a rigidity suitable for taking up the forces deriving from the power plant and makes it possible to limit the number of ribs (C1 . . . C10) in the structure.

Abstract: A method for assembling a primary structure of an aircraft pylon, includes a step of fixing an angle bracket to each of the first and second lateral panels such as to obtain an L form for each of the first and second lateral panels prior to a placement of said L forms each placed against two sides of each transverse frame. This assembly technique makes it possible to reduce the mounting clearances such that it is unnecessary to fit shims, resulting in a reduction of mounting time and manufacturing costs.

Abstract: A primary support strut structure and a method of manufacturing thereof for an aircraft power plant is disclosed having a first half-shell including a first free edge, and a second half-shell having a second free edge. The first half-shell and the second half-shell are assembled together by joining the first free edge and the second free edge so as to form a box-shaped structure. The two half-shell construction results in very rigid box structure, and a reduced number of ribs in the primary structure.

Abstract: A method for assembling an aircraft pylon having a primary structure and at least one internal system at least partially positioned within the primary structure, wherein the internal system is positioned inside the primary structure before the last lateral panel of the primary structure is attached. The absence of one of the lateral panels facilitates the installation of the internal systems.

Abstract: A device for manipulating a hollow shaft configured to create a pivot link between a first element and a second element. The manipulation device comprises a cylindrical body having a diameter variable by radial contraction or radial expansion of the cylindrical body, a module for controlling the diameter of the cylindrical body configured so that the diameter of the cylindrical body has alternatively at least a first diameter suitable for the cylindrical body to be displaced in the hollow shaft and a second diameter suitable for the cylindrical body to be blocked in the hollow shaft. The cylindrical body comprises an end configured to protrude from the hollow shaft when the cylindrical body is blocked in the hollow shaft. The manipulation device allows the alignment of the orifices due to the end configuration of the cylindrical body.

Abstract: A primary structure of an aircraft power plant support pylon is disclosed having a bottom stringer and two lateral walls formed in a single piece or welded so as to form a U-shaped bottom part, and a top cover which closes the U-shaped bottom part. The U-shaped part closed by a cover makes it possible to construct a box or box structure that exhibits a rigidity suitable for taking up the forces deriving from the power plant and makes it possible to limit the number of ribs (C1 . . . C10) in the structure.

Abstract: A primary support strut structure and a method of manufacturing thereof for an aircraft power plant is disclosed having a first half-shell including a first free edge, and a second half-shell having a second free edge. The first half-shell and the second half-shell are assembled together by joining the first free edge and the second free edge so as to form a box-shaped structure. The two half-shell construction results in very rigid box structure, and a reduced number of ribs in the primary structure.

Abstract: A method for assembling a primary structure of an aircraft pylon, includes a step of fixing an angle bracket to each of the first and second lateral panels such as to obtain an L form for each of the first and second lateral panels prior to a placement of said L forms each placed against two sides of each transverse frame. This assembly technique makes it possible to reduce the mounting clearances such that it is unnecessary to fit shims, resulting in a reduction of mounting time and manufacturing costs.

Abstract: In order to reduce the congestion of the attachment means for aircraft engines in a secondary vein, a first fuselage frame has two side portions for supporting the engine, each associated with one of the two partly buried side engines, these portions being curved inwards so as to surround and follow the profile of the outer shroud of an intermediate case. The side portion is attached on this shroud through first and second attachment arrangements spaced apart from each other circumferentially, these arrangements being configured in order to allow absorption of the forces related to the torque along a longitudinal direction of the engine.