Abstract: There is provided an aircraft folding seat, comprising a frame which pivots about a vertical axis and on which are mounted a seat-rest and a back-rest. The flight deck provided comprises control and/or viewing devices, at least one seat, an access door and a corridor for access to the at least one seat which is closed at its opposite end to the at least one seat by the access door. A folding seat is mounted in the corridor such that it can pivot and adopt a first position in which it closes the corridor so forming a lock enclosure with the access door and a folded back second position enabling access to the at least one seat from the corridor.

Abstract: An aircraft nose comprising a primary fuselage structure, and housed inside said structure, a cockpit, and an avionics bay containing a plurality of avionics racks designed to receive electrical and/or electronic equipment. The cockpit and the avionics bay are each made in the form of a distinct module that is suitable for being installed in a single operation inside the primary fuselage structure. The use of modules for integrating in the aircraft nose makes it possible to reduce considerably the time required for fitting out the nose on the final assembly line of the aircraft.

Abstract: A breaker strut of an aircraft landing gear, including means to adjust the length of at least one of its lower and upper portions and/or a space allowing a nesting of the lower and upper portions in the folded position of the strut. A landing gear including such a strut and/or retraction means including two slider-crank mechanisms which are phase shifted by a non-zero angle ? allowing a reduction of the variations of torque C applied to the undercarriage of the gear as it moves between the lowered and raised states of the latter.

Abstract: The invention relates to an overhead panel able to be positioned in an aircraft cockpit, which includes an assembly of independent submodules (67), each of which is associated with a particular system or a particular function of the aeroplane, incorporated in a rigid self-supporting module (60), including a front face (65) to which the submodules (67) are attached, and two side faces fitted with peripheral electrical connectors (63) intended to be connected to different systems of the aeroplane. The invention also relates to a method of manufacture of such a panel.

Abstract: A piece of furniture for an aircraft, including a plurality of carriages a first section forming an interface of use for a user with which at least one carriage may be taken and/or deposited in the piece of furniture and a second section allowing the said carriages to be circulated along at least first and second main directions substantially perpendicular to each other, at least in a plane of the aircraft for storing and/or delivering to the user at least one carriage, the first section and/or the second section including an arrangement for distributing at least one carriage from the second section towards the first section and vice versa.

Abstract: A ventilation system for an avionics bay has two strut assemblies for stiffening the floor of the cockpit, each strut assembly being arranged symmetrically regarding to the central plane of the aircraft, and means of distribution of the blowing air in the cabinets of the bay from the strut assemblies. The extraction circuit includes exhaust ducts integrated in the cabinets and couples together by tight inter-cabinets junctions in an overall configuration of maximized compactness.

Abstract: A power breaker strip comprising a strip support and a plurality of interphase spacer elements, and a plurality of interline spacer elements, assembled with the plurality of interphase spacer elements such that each interline spacer element extends at least partly between two consecutive interphase spacer elements. The interphase spacer elements and the interline spacer elements together delimit a plurality of per pitch zones of the strip in which connection terminals of several lines of electrical cables can be inserted.

Abstract: The subject matter disclosed herein relates to the field of aircraft systems installation. More specifically, the subject matter disclosed herein relates to the installation of avionics cabinets, electrical master boxes and IFE bays. Compared with the arrangements known from the prior art, the subject matter disclosed herein includes relocating at least some of the systems cabinets toward the front of the aircraft by making use of the space available in the area around the landing gear compartment. To do so, the subject matter disclosed herein uses systems cabinets that incorporate a structural function. It thus allows a reduction in the aerodynamic drag of the aircraft.

Abstract: A device for positioning a first piece relative to a second piece. The first piece comprises a free end with a first bore and the second piece comprises an engagement part with a second bore intended to come into correspondence with the first bore. The first and second bore are drilled to the definitive diameter thereof prior to the relative positioning thereof. The device comprises one or more positioning elements, which are able to position the first bore relative to the second bore along at least one of three geometric axes.

Abstract: The invention relates to a seat back for an aircraft comprising a structural column bearing a plurality of devices for supporting an occupant of the seat, these devices being distributed along the structural column and oriented transversely relatively to the structural column so as to each protrude on either side of this column. This solution can reduce the mass and dimensions, while providing satisfactory comfort for the occupant.

Abstract: The invention relates to a secure access airlock enabling the communication between several rooms of an aircraft, the secure airlock being installed in an area of the aircraft between a first room and at least one second room, characterized in that it includes two mobile partitions provided in the form of portions of concentric cylinders, each of the partitions being capable of being moved, separately from one another, about a common axis, so as to provide a single opening therebetween which makes it possible to access either of the rooms, the two partitions being capable of moving over two concentric cylinders having different diameters.

Abstract: A landing gear has a rigid structure and a gear compartment. A leg has a wheeled first end on a rolling shaft, and a second end secured on the rigid structure. The leg rotates between a rolling position, letting the aircraft rolls, and a landing gear storage position. A brace has a first end secured on the rigid structure. A guide bar has a first end pivotably secured on the leg, and a second end secured on the second end of the brace by a pivot shaft. A jack is secured between the brace by a pivot connection with a shaft parallel to the rolling shaft, and the guide bar, by a pivot connection with a shaft parallel to the rolling shaft. A locking system locks either a second end of the brace or the second end of the guide bar against the leg in the rolling position.

Abstract: An aircraft throttle control system having a control lever. The control system comprises an emitter unit having the pivot-mounted control lever and a receiver unit having a pivot-mounted lever, and a linkage connecting the control lever to the lever, and transmitting movement between the control lever and the lever. That makes it possible to optimize the space in a flight deck and typically makes it possible to dispense with the central pedestal generally present in the middle of flight decks while at the same time maintaining conventional ergonomics for controlling the throttle for example. A flight deck element is also disclosed having a fixed structure to which the control system is rigidly connected, to an associated flight deck and to an aircraft equipped with such a flight deck.

Abstract: The system supplies oxygen for a flight crew member of an aircraft and has an oxygen source, an oxygen mask, and a circuit connecting the oxygen source to the oxygen mask. The system is integrated into an aircraft seat, which has at least one foot bearing a sitting surface and a back. The oxygen source may be a cylinder of gaseous oxygen under pressure. The oxygen mask can be housed in a compartment inside the sitting surface of the seat.

Abstract: A high-lift trailing edge flap system for an aircraft wing unit is provided. In high-lift trailing edge flap system, the backward movement and the inclination of the trailing edge flap in the extended position are dissociated in order to allow for the incorporation of the actuating mechanism into the wing in the stowed position.

Abstract: A cabinet designed to accommodate at least one item of electronic equipment and a system for interconnecting such a cabinet with the external networks for blowing and extracting air. The system includes at least one of a blowing inlet and an extracting outlet including a plurality of orifices and at least one hollow structural upright as a part of the blowing circuit or of the extracting circuit.

Abstract: A headrest includes a first part referred to as the lower part, equipped with a connecting unit enabling an adjustable connection of the headrest to the seat back of a pilot seat, and a second part referred to as the upper part, located opposite the lower part, as well as a front face intended to serve as a support surface for the head of a user. A receptacle, connected to the mask, stores an oxygen mask and/or a supply line. The upper part of the headrest forms a hinged cover on the lower part of the headrest and it closes the receptacle. A seat, a cockpit, and an aircraft include such headrest.

Abstract: A power breaker strip comprising a strip support and a plurality of interphase spacer elements, and a plurality of interline spacer elements, assembled with the plurality of interphase spacer elements such that each interline spacer element extends at least partly between two consecutive interphase spacer elements. The interphase spacer elements and the interline spacer elements together delimit a plurality of per pitch zones of the strip in which connection terminals of several lines of electrical cables can be inserted.

Abstract: An electrical core comprising an assembly of power management and distribution contactors is provided. The power management contactors are attached to a first support element and the distribution contactors are carried by a second support element superimposed on the first so as to form a multilayer assembly. The distribution contactors are arranged in double symmetry about two axes perpendicular to one another. They are mechanically linked through a mechanical linkage element extending between two rows of contactors and which carries electrical connection elements connecting the contactors to an element for connecting to a power source. The contactors are assembled in modules according to their type. In particular, the management module comprises at least one modular element common to the power management contactors which is suitable for performing a given secondary function other than the function of establishing a contact.

Abstract: A forward part of an aircraft comprising a fuselage and a landing gear well housing a forward landing gear comprising a breaker strut designed to adopt an extended configuration when the landing gear is extended, configuration in which said breaker strut lies in a strut plane parallel to the transverse direction of the forward part. The forward part comprises a transverse beam resisting strut reactions located above the landing gear well and mounted on the fuselage at its two ends, the beam having a globally rectangular cross-section, in which the median plane parallel to the length of the rectangle is coincident with said strut plane.