Abstract: A front landing gear storage compartment configured for an airplane including 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 more or less flat zone, more or less horizontal when the airplane is on the ground, so as to form a floor of a pressurized area of the airplane.

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: A ladder is positioned between a first hatch of an upper level of an aircraft and a second hatch of a lower level of the aircraft. A bottom end of the ladder is mounted in rotation on a floor of the lower level. A top end of the ladder is unattached. The ladder can swivel between a first stable position and a second stable position. The top end of the ladder is provided with a safety device capable of the blocking an opening of the first hatch when the ladder is in the second stable position. For example, the safety device has a net. A first edge of the net is fixed to a first side of the first hatch. A second edge of the net is fixed to the top end of the ladder.

Abstract: A vertical tail unit for an aircraft and an aircraft equipped with the vertical tail unit. The vertical tail unit is provided with an engine. The engine extends cantilevered beyond a fin of the vertical tail unit and is secured to the fin by a mount. The mount is at least partly attached to the fin. The mount comprises for example half-hoops arranged on either side of the fin.

Abstract: The casing comprises a wall defining an internal housing open on the bottom in order to allow the retraction of a corresponding front landing gear into the interior of the housing. The said wall separates the said non-pressurized internal housing from a surrounding pressurized zone of the aircraft. A reinforcement structure is provided around the wall on the side of the surrounding pressurized zone. The separation wall is a shell coming to envelop the shape of the front landing gear, on the side opposite the opening of the internal housing, and the reinforcement structure comprises on the 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.

Abstract: A communication flap including a door for closing or freeing the access to an opening on a wall, the door having at least two leaves. A first leaf is pivotably mounted on the wall in such a way as to open and close the door, and a second leaf is pivotably mounted on the first leaf in such a way as to enable a range of movement around the first leaf. The disclosed embodiments also relate to an aircraft provided with one such flap.

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: 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: 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: The object of the invention is an aircraft comprising at least one gear compartment in which is adapted to be disposed a landing gear (24) comprising at least one wheel (36), characterized in that said gear compartment comprises an upper panel (50) with at least one hollow shape F enclosing as closely as possible said at least one wheel (36) when the landing gear is in raised position.

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: The present invention relates to a front aircraft part (1) comprising a non-pressurised landing gear housing zone (28) designed to house a front landing gear (30) in a retracted state, as well as a pressurised zone (2) adjacent to the non-pressurised landing gear housing zone. According to the invention, the pressurised zone is delimited by a set of walls among which only a substantially flat-shaped sealed partition wall (10) also participates in delimiting the non-pressurised landing gear housing zone (28).

Abstract: The invention has as its purpose an aircraft for transport of passengers having a fuselage (1) comprising a pressurized level (2) in which there are laid out the passenger cabin (20) and a lower level forming a hold (3). According to the invention, the cockpit (40) is positioned in an additional pressurized space (4) laid out below the main deck (10), at the level of the hold (3) and separated from the latter by a structure (41) withstanding possible impacts.

Abstract: This layout relates to an aircraft cabin (4) that comprises a deck (6) forming a plane surface on which seats (18) are fastened, an aisle (10) extending longitudinally in the cabin (4) and elevated in relation to the deck (6), and berths (8) served by the said aisle (10), arranged at an angle above the seats (18) of the deck (6) and on both sides of the aisle (10).

Abstract: Aircraft flight control and ground steering control system This electrical flight control system is intended for an aircraft that has a main landing gear with a front landing gear. It is provided with a handle (2) that can move around two maneuvering axes (4, 6) by means of a linkage system (8), and is movable in rotation around a longitudinal axis substantially perpendicular to the maneuvering axes, means on each of the maneuvering axes for generating a pilot-operated instruction from a movement of the movable handle around one maneuvering axis, and means for generating an instruction in order to act on the orientation of the front landing gear of the aircraft as a function of the angular position of the movable handle (2) relative to the longitudinal axis.

Abstract: The invention has as its purpose a rest unit that can be laid out inside the fuselage of an aircraft, especially for the benefit of the crew. According to the invention, this rest unit is made up of a plurality of cells (2) of elongated shape, each having longitudinal and transverse dimensions corresponding to the location of a berth (20), the said cells (2) being juxtaposed on at least two levels so as to form a module (1) of parallelepipedal outer shape. Such a module can, in particular, be incorporated in the rear cone (30) of the fuselage (3) of the aircraft.

Abstract: The tires that equip airplane wheels have elastomer treads from which a piece may detach and damage a zone of the airplane. Shredding means, situated between wheel and another part of the airplane, shred the piece of tread, which detaches from the tire and is projected onto the other part of the airplane, into several small pieces. These shredding means, such as a grid with blades that can cut the tread material, are arranged so as to disperse the pieces. A process reinforces the tolerance of an airplane to impacts of a detached piece of the tread, by shredding the piece into several small pieces between the instant when the piece is detached and the instant when the piece would have struck airplane.

Abstract: The invention concerns a vertical tail unit (5) for an aircraft (1). The vertical tail unit is provided with an engine (7). The engine extends cantilevered beyond a fin (11) of the vertical tail unit and is secured to said fin by a mount (12). Said mount is at least partly attached to the fin. The mount comprises for example half-hoops (17) arranged on either side of the fin. The invention also concerns an aircraft (1) equipped with a vertical tail unit (5) bearing a motor (7).

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, said securing device being adapted to pick up the loads to which the super-transporter aircraft is subjected.

Abstract: A long-haul airplane has a private cabin for the pilots within a storage compartment disposed on a floor below the flight deck. The private cabin is in communication with the flight deck through an opening in the floor.