Abstract: In an electrical cabinet (110) for an electrical power unit that carries out electrical power switching for at least multiple electrical power switching equipment (50), the electrical power switching equipment (50) is attached to a front of at least a support grid rack (31) arranged as a matrix with n rows and p columns, where n and p are greater than or equal to two. Each piece of equipment (50) is attached to the grid rack at a slot (34) in the grid rack, open to the front of the grid rack (31) and to the rear of the grid rack to allow installation from the front of the equipment and to allow access from the front to the rear of the grid rack through the slots (34).

Abstract: The invention aims at simplifying the electrical connections between equipment and an electrical power centre to be supplied in electricity, while enabling a good accessibility of each piece of equipment and an easier maintenance. To do so, a particular integration of this equipment is carried out so as to be able to assemble them together and connect them in a direct extension of the electrical power centre. According to one embodiment, an integration module consists in a frame and a cover, the frame having a substantially parallelepipedic shape adapted to be able to extend longitudinally along a main axis in parallel with a longitudinal main side of the electrical power centre of the structure to be supplied. Cells of constant section and a width being adjustable by movable intermediary walls, extend perpendicularly to the main axis. Such cells are adapted to receive formatted electrical equipment.

Abstract: A casing including a wall defining an internal housing which allows retraction of a corresponding landing gear into the interior of the housing. The wall separates the non-pressurized internal housing from a surrounding pressurized zone of the aircraft. The separation wall is a shell which envelops the shape of the landing gear, on the side opposite the opening of the internal housing, and the reinforcement structure includes on one hand longitudinal reinforcement elements extending on both sides of the shell and on the other hand transverse reinforcement elements connecting the longitudinal reinforcement elements. The shell has a first zone of considerable width accommodating the wheels of the landing gear, a second zone of lesser width accommodating the rod of the landing gear, and a third zone running from the second zone of lesser width, becoming wider and accommodating a portion of the mechanism for deployment/retraction of the landing gear.

Abstract: The invention relates to a landing gear casing that comprises a longitudinal box with walls defining an inner housing (24) open at the bottom and enabling the stowage of the landing gear (20) inside the housing and the deployment thereof outside the housing, the walls of the casing separating the non-pressurised inner housing from a surrounding pressurised area (18) of the aircraft, characterised in that the casing includes a primary inner frame including: several primary transverse reinforcement arcs (26, 28) inside the housing; at least one longitudinal central reinforcement arc (30a, 30b) inside the housing; wherein the walls of the casing and the reinforcement being adapted to conform to the shapes of the landing gear (20) and the stowage/expansion mechanism (22) thereof.

Abstract: A stairway used for gaining access from a theoretically horizontal lower level to a theoretically horizontal higher level, and including a succession of intermediate steps between these two levels. A subassembly of intermediate steps corresponding to the steps closest to the lower level is mobile between a first deployed position at which the lower intermediate steps are in the extension of other intermediate steps, and a raised position at which the lower intermediate steps are in a substantially vertical position.

Abstract: A securing mast for securing an engine to the wing of an aircraft, wherein the device includes two fasteners, a first end of each fastener being secured to the engine and the second end of each fastener being secured to the wing, wherein the fasteners include hinged junction means capable of modifying the geometry of the aforementioned fasteners in order to modify a distance between the engine and the wing.

Abstract: The disclosed embodiments relates to a jet engine for an aircraft, characterized in that it bears at least one stabilizer, the stabilizer being fastened on the rigid structure of said jet engine so as to form a one-piece assembly. The jet engine can also bear one or more auxiliary devices required for the operation of the jet engine. The disclosed embodiments also relates to an aircraft provided with such a jet engine, and to a method of mounting such a jet engine on an aircraft.

Abstract: An aircraft hold including a floor having a substantially flat central part and a side part disposed along each longitudinal edge of the central part and inclined in relation thereto. The aircraft hold also includes at least one bench with a seat that can move between a position in which it is substantially parallel to the central part of the floor and a position in which it is folded against a wall of the hold.

Abstract: A front landing gear storage compartment for an airplane, which includes a set of retractable landing gears including a front gear centered on a longitudinal median plane of the fuselage. The storage compartment forms an impervious partition between a pressurized zone and the housing for the front gear in its retracted position, and includes a reinforced upper face including a substantially flat zone, which is substantially horizontal when the airplane is on the ground, so as to form a floor of a pressurized area of the airplane.

Abstract: A cockpit and an aircraft including such cockpit. The cockpit includes a front section of an aircraft. Such cockpit includes a pressure bulkhead sealing the section and a pressurization system for pressurizing such section.

Abstract: In a rear cone of a fuselage of an airplane a pressurized space is arranged in the rear cone and extends up to an impervious strong wall, placed on a rear portion of the length covered by a fin. The pressurized space constitutes an area accessible to individuals and is able to constitute, in particular, a rest and service area for the crew.

Abstract: An aircraft seat assembly structure (4) comprises at least one seat structure (5) that supports at least one seat, with which seat assembly structure is associated a reference frame that is defined by a longitudinal X-axis according to which the seat structure (5) comprises a front part and a rear part, by a Y-axis that is perpendicular to the X-axis, and that forms with said X-axis a horizontal XY plane when at least one seat is horizontal, and by a Z-axis that is perpendicular to the XY plane. In the front part, the seat structure (5) comprises a torsion bar (50) that is essentially parallel to the Y-axis that is equipped at a first lateral end (502) with a front lateral fastening device (500) that is designed to be made integral with lateral attachment means (26) of a shell structure (2) of an aircraft.

Abstract: The invention relates to a ladder comprising a single post (1) provided with a fixing means (4) on the upper end (1S) thereof, said ladder comprising an anchoring means (9, 10) which is especially adapted to said fixing means (4) and is attached to the wall (7), and foldable supporting arms (3) which are connected to either side of the single post (1) in an articulated manner.

Abstract: A securing mast for securing an engine to the wing of an aircraft, wherein the device includes two fasteners, a first eng of each fastener being secured to the engine and the second end of each fastener being secured to the wing, wherein the fasteners include hinged junction means capable of modifying the geometry of the aforementioned fasteners in order to modify a distance between the engine and the wing.

Abstract: The invention concerns an electrical cabinet (1) including a housing (2), a door (3) and a hinge (4). The housing and the door support electric wires which are each routed from an electrical component located inside an electrical equipment compartment (11) formed by the housing towards the outside of the compartment to be connected to a corresponding electrical connector (17). Therefor, according to the invention the electric wires are routed through the hinge which is itself connected to the electrical connector. The hinge forms at least one passage orifice (18, 19) guiding, the electric wires from inside the compartment towards the outside of the compartment while directing them towards the electrical connector.

Abstract: A super-transporter aircraft for transporting at least one element of a secondary aircraft, wherein the structural rigidity of a fuselage of the super-transporter is at least partly imparted by the transported element. The super-transported aircraft can be equipped with a securing device for securing the transported element to the fuselage of the super-transporter aircraft, the securing device adapted to pick up the loads to which the super-transporter aircraft is subjected.

Abstract: An aircraft includes a gear compartment in which is adapted to be disposed a raisable forward landing gear, the landing gearing comprising at least one gear leg connected to the aircraft structure and supporting at least one pair of wheels disposed on opposite sides of the gear leg, an articulation part to incline at least one wheel relative to the lifting plane of the landing gear, the gear compartment including an upper panel serving as a floor, with at least one hollow shape F enclosing as closely as possible the at wheels when the landing gear is in raised position.

Abstract: A stairway used for gaining access from a theoretically horizontal lower level to a theoretically horizontal higher level, and including a succession of intermediate steps between these two levels. A subassembly of intermediate steps corresponding to the steps closest to the lower level is mobile between a first deployed position at which the lower intermediate steps are in the extension of other intermediate steps, and a raised position at which the lower intermediate steps are in a substantially vertical position.

Abstract: An aircraft cabin includes: a deck forming a plane surface on which seats are fastened; an aisle extending longitudinally in the cabin and elevated in relation to the deck; and berths served by the aisle, arranged at an angle above the seats of the deck on both sides of the aisle.