Abstract: An aircraft duct assembly comprising at least two ducts extending along a general direction of rectilinear extent, each duct being an electrical, hydraulic or aeraulic duct connected to a duct support. The duct support comprises a first slideway element configured to cooperate with a second slideway element to form a slideway in the general direction of extent of the ducts. The duct assembly can thus be inserted, after mounting, by translation along the direction of the slideway into an aircraft fuselage portion. The mounting of the duct assembly and installation thereof in a fuselage are simplified, and the duct assembly is more reliable.

Abstract: An aircraft air conditioning system comprising an ambient air line, for ambient air to flow through, connected to supply ambient air to a mixer of the aircraft air conditioning system. An ambient air compressor is arranged in the ambient air line for compressing the ambient air flowing there through. A refrigerating apparatus comprises a refrigerant circuit for a refrigerant to flow through, including a refrigerant compressor arranged in the refrigerant circuit. The refrigerant circuit is coupled thermally to the ambient air line to transfer heat from the ambient air to the refrigerant before the ambient air is supplied to the mixer. A cabin exhaust air turbine is connected to a cabin exhaust air line, is coupled to the ambient air compressor arranged in the ambient air line, and is configured to expand the cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor.

Abstract: A ducted fan turbine engine with a nacelle and a duct for a secondary flow. The nacelle comprises a fixed structure. A mobile cowl is able to move between a forward position and a backward position to define an opening between the duct and the outside. A plurality of rollers are mounted to freely rotate on the mobile cowl. For each roller there is a flexible screen with a first edge fixed to the roller and a second edge, in which the screen is able to adopt a furled position, wound around the roller, or a deployed position deployed across the duct. A deployment mechanism is arranged to move each second edge to move the screen from the furled position to the deployed position. A furling mechanism is arranged to drive each roller in rotation to move the associated screen from the deployed position to the furled position.

Abstract: To locate an intermittent fault in a communication structure of an aircraft comprising pieces of equipment that are interconnected by cabling forming a plurality of communication media that are shared, an analyzer retrieves an error report relating to transmission errors observed on each of said communication media, performs a count of the transmission errors, per type of error and per communication chain, computes a median of the counts for communication chains comprising the same pair of wired pieces of equipment, and when, for a communication chain, the count exceeds a threshold equal to the median plus a predefined margin, generates an alarm indicating detection of an intermittent fault in association with the communication chain that led the threshold to be exceeded. Thus, intermittent faults are easily located and repaired.

Abstract: An adjustment tool for adjusting a maneuvering mechanism of a main landing gear of an aircraft, the landing gear having a plurality of wheels. The tool includes a telemeter, a locking system for locking the telemeter on the external face of a wheel, a wireless communication unit that is connected to the telemeter and makes it possible, when the tool is being used, to connect the telemeter with a control device provided with a display screen.

Abstract: An aerial workstation which comprises a seat having a sitting portion, a backrest that is connected by a first articulation that allows the backrest to pivot relative to the sitting portion, and an arm configured to position the seat in various positions and orientations in space as required. The aerial workstation makes it possible to be able to translate the seat in a cockpit in an introduction direction, and to make it pivot about a pivot axis that coincides with the direction of introduction within the cockpit.

Abstract: An aircraft portion having a floor and a fuselage structure forming an arch above the floor is disclosed in which a monument is mounted within the fuselage. The monument is suspended from the fuselage structure by at least one suspension point, so that most of the weight of the monument is taken up by the fuselage structure. The monument includes a circular or a round section configured to take up the vertical forces than the horizontal floor, which bends under vertical loads.

Abstract: A method for manufacturing a composite assembly with a continuous skin for a rear end of an aircraft by obtaining an upper part of the rear end by composite tooling. The upper part comprises a multi-spar vertical tail plane. The spars of the vertical tail plane comprise widening roots that form an upper shell of the rear end and an upper skin. Furthermore, a lower part comprises a lower shell of the rear end including semi-complete frames and stringers and a lower skin. The upper and lower parts are assembled with a joining procedure. The upper and lower skins are joined to obtain the composite assembly with the continuous skin.

Abstract: A fastening assembly suitable for being fastened to a substrate with a front face and a first hole. The fastening assembly includes a fastening plate with a second plate with front and rear faces and pierced with a second hole aligned with the first hole. The fastening plate front face is fastened to the substrate rear face. The assembly includes a nut holder with a third plate with front and rear faces and pierced with a third hole aligned with the second hole and a nut fastened to the third plate on the side of the rear face and coaxial with the third hole. The front face of the nut holder is fastened to the rear face of the fastening plate. The fastening plate includes a first fastener that engages with a second fastener of the nut holder to removably fasten the nut holder to the fastening plate.

Abstract: An aircraft seat fastening assembly, due to the use of electroactive polymers, facilitates the compensation of tolerances and the fastening of aircraft seats in the passenger cabin of the aircraft. A fixing actuator contains the electroactive polymer and can be switched electrically between a fixed state, in which a movement of a fastening region is not possible, and a non-fixed state, in which a movement of the fastening region is possible in a vertical direction. The aircraft seats can thereby be displaced in a continuously variable manner along the aircraft seat fastening rail. The aircraft seats can also be locked in a fully automated manner, and possibly from a central location. It is also conceivable to individually control the aircraft seats and/or the group(s) of seats.

Abstract: A fuel cell arrangement which comprises a fuel cell having a first inlet for a fuel and a second inlet for an oxidizing agent, and comprises a vortex tube having an inlet, a first outlet for heated gas and a second outlet for cooled gas. Here, the first outlet of the vortex tube is fluidically connected to the first inlet or the second inlet of the fuel cell. A fuel cell system may have such a fuel cell arrangement, and a vehicle may have such a fuel cell arrangement or fuel cell system.

Abstract: A landing gear system 100 for an aircraft including: a landing gear 130 that is movable between an extended position and a retracted position, the landing gear includes an extendible strut 136; a position sensor 140 configured to detect a position of a part of the extendible strut and output a signal indicative of the position; and a landing gear controller 150 that is communicably connected to the position sensor and is configured, in use, to: receive the signal from the position sensor; and, on the basis of the signal, determine that the strut has extended and the landing gear is in contact with the ground and automatically cause performance of at least a portion of a procedure to move the landing gear from the extended position to the retracted position.

Abstract: An aircraft structure (11) for flow control including a perforated panel (13) having an inner surface (15) directed to a structure interior (17), an outer surface (19) in contact with an ambient flow (21), and a plurality of micro pores (23) connecting the inner and outer surfaces (15, 19). Elongate crack stopper elements (25) are attached to the inner surface (15) of the perforated panel (13). The crack stopper elements (25) are configured to inhibit crack propagation within the perforated panel (13).

Abstract: A cooling arrangement for a kitchen provided for installation in a means of transport comprises a cooling circuit which can have a cooling medium flowing through it and in which a condenser and an evaporator are arranged. The condenser is accommodated in a condenser housing and is arranged in a first installation space which is intended to form a first sub-region of the kitchen. The evaporator is accommodated in an evaporator housing formed separately from the condenser housing, and is arranged in a second installation space which is intended to form a second sub-region of the kitchen.

Abstract: An air intake including an air duct inside an aircraft, an inlet at one end of the air duct, a flap door and driving mechanism that moves the flap door between closed and open positions. The flap door includes a barrier filter configured to filter an incoming airflow into the air duct, and wherein the driving mechanism is configured to pivot the flap door about a first end of the door.

Abstract: A flight management assembly of an aircraft and method of monitoring the flight management assembly. The assembly includes two flight management systems, and a monitoring and backup unit, each of the flight management systems configured for generating data including a trajectory and a prediction of a parameter of the aircraft, one of the flight management systems being active and the other being passive, the monitoring and backup unit configured for carrying out monitoring of at least one of the items of data generated by the active flight management system in order to verify if the item of data is valid, the flight management assembly carrying out, in case of validation of the monitored item of data, a synchronization of the monitoring and backup unit and of the passive flight management system, with data called synchronization data of the active flight management system, namely a flight plan and/or a flight trajectory.

Abstract: A front engine attachment system for an engine of an aircraft. The front engine attachment system has an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam is made up of a front plate and a rear plate that are fastened together in a removable manner. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. Each link-rod system is fastened to the rear plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.

Abstract: A method 300 for deploying an aircraft landing gear including: receiving an aircraft landing gear deployment signal 310, receiving an aircraft position signal indicative of a distance of the aircraft from an aircraft landing site 320, receiving one or more flight signals indicating one or more dynamic conditions or parameters relating to the flight of the aircraft 330, determining, based at least on the one or more flight signals, a first aircraft position, relative to the aircraft landing site, at which the landing gear deployment should commence 340, and deploying the landing gear (a) when the aircraft reaches the first aircraft position, in the event that the deployment signal is received before the aircraft reaches the first aircraft position, or (b) immediately, in the event that the deployment signal is received when the aircraft has passed the first aircraft position 350.

Abstract: A passenger seat comprises a carrier structure, a backrest and a seat element displaceably fastened to the carrier structure, relative to the backrest, in a depth direction of a seating surface of the seat element between a usable position and an out-of-use position. In the usable position, the seat element is arranged, relative to the backrest, so that a front edge of the seat element that faces away from the backrest is arranged at a first distance from a backrest surface of the backrest. In the out-of-use position, the seat element is received, at least partially, in a gap provided between a part of the carrier structure carrying the seat element and an edge of the backrest facing towards the seat element, the front edge of the seat element being arranged at a second, smaller distance from the backrest surface of the backrest than the first distance.

Abstract: A passenger seat comprises a backrest, a seat element and a size increasing mechanism which is configured to convert a weight acting on the seat element when a user sits in the passenger seat into an increase in the depth of a seat pan of the seat element that can be used by the user from a rest-position depth to a to an operational-position depth.