Abstract: A line system for an aircraft cabin has a line channel with a first surface and a second surface facing in an opposite direction with respect to the first surface. The line system also includes at least one conductor running in the line channel a plurality of first plug channels which enable contacting of the at least one conductor through the first surface, and at least one second plug channel which enables contacting of the at least one conductor through the second surface. At and at least one connector plug with an elongated contact pin which contacts the at least one conductor through the second plug channel, the contact pin having a first section situated in the second plug channel and a second section situated outside the second plug channel.

Abstract: An optimization method and device for a take-off procedure of an aircraft. The device (1) comprising means (2, 10) for determining optimum values for take-off parameters and adapting them for the actual take-off conditions.

Abstract: Disclosed herein is a folding transport cart which in a parking configuration has a minimum extension and in an operative configuration has a maximum extension in a transverse direction. A folding transport cart can comprise: two side parts which extend substantially perpendicular to the transverse direction of the transport cart, and a folding base part which comprises two flat base segments which are each connected on one base side axis for articulated movement to one side part and are connected on a common base central axis for articulated movement to one another. In order to ensure reliable folding and unfolding the transport cart can comprise a base locking mechanism for locking the folding base part in the operative configuration and a cover part which is connected for articulated movement to one of the side parts.

Abstract: A nose landing gear arrangement including a leg assembly with a pivot axis A at one end thereof and a landing gear wheel mounting at the other end thereof. Two stays are provided, each stay being mounted at one end thereof to the leg assembly and mountable at the other end thereof to an aircraft. Each stay includes an upper stay part and a lower stay part which are hinged together by means of a simple hinge. The upper stay part has a cardan joint at its end spaced from the hinge to enable hinged mounting to an aircraft. The lower stay part has a cardan joint at its lower end spaced from the hinge, the cardan joint of the lower stay part hingedly mounting the lower stay part to the leg assembly. The leg assembly and the stays are arranged so that the stays extend from the leg assembly on opposite sides thereof and the stays fold into a stowed position so that they lie substantially alongside the leg assembly when the leg assembly is retracted.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flame barrier means, when refuelling.

Abstract: A method of manufacturing a structure, the method comprising: forming a panel assembly by bonding a stack of thickness control plies of composite material to a laminar composite panel, the stack of thickness control plies having a first edge proximate an edge of the laminar composite panel, a second edge opposite the first edge, and a ramp where the thickness of the stack of thickness control plies decreases towards the first or second edge; measuring the thickness of the laminate composite panel or the panel assembly; controlling the number of thickness control plies in accordance with the measured thickness; attaching a first component to the panel assembly, the first component having a surface which engages the laminar composite panel and a ramp which engages the ramp in the stack of thickness control plies; and attaching the laminar composite panel at or near its edge to a further component.

Abstract: The invention relates to a method for tolerance compensation between two fiber composite component parts (1, 3) for aircraft. In order to compensate in simplified fashion tolerances between two fiber composite component parts being joined, the method according to the invention has the steps: a) manufacturing the first fiber composite component part (1) wherein an assembly surface (2) can have tolerance deviations, b) manufacturing a tooling insert (7) from a surface geometry of the assembly surface (2) c) manufacturing the second fiber composite component part (3) by means of the tooling insert (7) wherein a surface geometry of a contact surface (9) of the second fiber composite component part (3) corresponds substantially with the surface geometry of the assembly surface (2), and d) joining the first fiber composite component part (1) to the second fiber composite component part (3) in the area of the assembly surface (2) and contact surface (9).

Abstract: The invention in particular has as an object supervising a scheduler for the management of processing time sharing in a multitask data-processing system comprising a computation unit having a standard execution mode and a preferred execution mode for executing a plurality of applications. The execution time for the said plurality of applications is divided into a plurality of periods and a minimal time for access per period to the said computation unit is determined for at least one application of the said plurality of applications. For at least one period, the said preferred execution mode is associated with the said at least one application and the said at least one application is executed according to at least the said minimal time for access to the said computation unit. For the said at least one period, the said standard execution mode is associated with the applications of the said plurality of applications and at least any one of the applications of the said plurality of applications is executed.

Abstract: A method and a device for centralized management of warnings in an aircraft including a centralized system for management of warnings and a plurality of warning presentation interfaces. The method includes determining at least one warning in the centralized system according to at least one alarm activation signal received, presenting the at least one warning by a first interface of the plurality of warning presentation interfaces, filtering the at least one determined warning to determine whether to also present the at least one determined warning by a second interface of the plurality of warning presentation interfaces, the second interface being separate from the first interface, and presenting, by the second interface, the at least one determined warning, in response to a determination by the filtering that the at least one determined warning is to also be presented by the second interface.

Abstract: A method and system for aiding the taxiing of an aircraft on an airport domain enables automatic planning and execution of taxiing. The system includes a trajectory generating device for generating a taxiing trajectory of the aircraft on the airport domain, with the aid of a navigation data base, and piloting aiding devices that use the trajectory for aiding the taxiing of the aircraft. For example, the piloting aiding devices may include an automatic piloting/taxiing device and a display device.

Abstract: An aircraft propulsion unit including a turbojet and a heat exchanger located above the turbojet and drawing a cooling air stream and a hot air stream in the turbojet. Wherein the cooling air intake and hot air intake surfaces in the housing are directed forward of the turbojet and have normal lines inclined relative to the axis of the turbojet. The embodiment also concerns an aircraft equipped with at least one such propulsion unit.

Abstract: An aircraft engine pylon aft aerodynamic fairing includes upper spars, transverse stiffening ribs, lower spars and a trailing edge where the upper spars and lower spars join together. In this fairing, a profiled structure is formed according to a profile open to the outside of the fairing. In a first end portion, the profiled structure comes to be enclosed between an end portion of the lower spars and the ends of at least one transverse stiffening ribs flush with the lower spars. This structure extends between the lower spars and the upper spars over a straight central portion inclined relative to the first end portion, and comes in a second end portion flush against a portion of the upper spars, parallel to the first end.

Abstract: A device for locking an engine on a pylon includes two systems attaching the engine to the pylon, located in attachment regions spaced out in a longitudinal direction of the engine. A second region is adjacent to a center of gravity plane of the engine and closer to a fan than a first region. A first system attaching to the first region is rigid towards torsional, transverse and vertical engine forces. The first region is located at a separation between two compressors of the engine or two turbines, whether the fan is at a rear or front of the engine respectively, the separation being adjacent to a node of a first engine flexural mode. A second system attaching to the second region is rigid towards transverse and vertical forces but less rigid than the first system. The device also includes a third system withstanding thrust forces in the longitudinal direction.

Abstract: A hatrack module with a moveable hatrack comprises a housing with a hatrack accommodation space, a hatrack with laterally arranged guide elements and optionally at least one passenger service unit, wherein each guide rail is arranged on one sidewall of the hatrack accommodation space, and wherein the guide elements of the hatrack can be made to engage the guide rails on the housing.

Abstract: A lateral coupling device for holding and guiding at least one aerodynamic body relative to the main wing in its wingspread direction during the adjustment thereof features: a coupling connection, a first coupling joint for coupling a first end of the coupling connection to the main wing or an aircraft component connected thereto or another aerodynamic body, as well as a second coupling joint for coupling the second end of the coupling connection to the aerodynamic body, where the lateral coupling device has a total of five degrees of freedom and allows an adjusting motion of the aerodynamic body relative to the main wing transverse to the wingspread direction thereof.

Abstract: A system for managing heat fluxes of an aircraft is provided, including a fuel tank supplying a turbomachine with fuel via a fuel supply circuit; a cell cooling circuit connected to a thermal effluents source, which integrates a first heat exchanger ensuring heat transfer between a coolant circulating in the cell cooling circuit and air flow channeled into a cooling air channel extending from an air intake to an exhaust; and a second heat exchanger ensuring a heat transfer between the coolant circulating in the cell cooling circuit and the fuel. The air intake includes a blocker to open/close it. The system includes a fuel transfer circuit, which connects the fuel tank to the second heat exchanger and provides fuel to the second heat exchanger, including a valve selectively changing a fuel supply direction from the second heat exchanger between the directions of the tank and the fuel supply circuit.

Abstract: The invention relates to a powered wheel system for an aircraft, comprising at least one undercarriage with several rotatably held wheels, with the powered wheel system comprising two or more motors of which in each case at least one motor is coupled to at least one of the wheels, and comprising at least one control device that is coupled to the motors. A control device is equipped to control operation of the motors independently of each other as far as their respective rotary speeds and direction of rotation are concerned, so that the system is able, among other things, to effect taxiing; by means of rotary speed differentials on different motors to be able to steer the aircraft; prior to landing to bring the wheel circumference speeds to landing speed; and to boost the undercarriage brakes of the aircraft. Furthermore, by means of an improvement of the system according to the invention, the rotary speeds of the wheels may be determined with precision.

Abstract: The present invention relates to a tester (100) for testing operational reliability of a cockpit oxygen distribution circuit (1) having a plurality of components (20, 30, 40, 50) ensuring supply of oxygen from the cockpit oxygen distribution circuit (1) to a cockpit crew of an aircraft in an emergency situation. The tester (100) comprises means (20?, 30?, 40?, 500 for electrically connecting the tester (100), in place of at least one of the components (20, 30, 40, 50), to the cockpit oxygen distribution circuit (1), an indicator (120) for indicating that the electrical connection of the tester (100) to the cockpit oxygen distribution circuit (1) has been established in a predefined manner, and switching means (RL1, RL2, RL3, RL4) for initiating an output signal of the tester (100), wherein the output signal is indicative of an operating condition of the component (20, 30, 40, 50) when being connected to the cockpit oxygen distribution circuit (1).

Abstract: The invention relates to a bleed air supply system and a safety device for closing a valve in at least one of the several bleed air supply lines depending on an alarm signal that indicates an opening in at least one of the several bleed air supply lines. To stop the supply of bleed air irrespective of the type of the bleed air source, the safety device comprises a filter device for generating the alarm signal depending on the ground connection signal and on an opening signal from an opening signal device that indicates any opening of the bleed air supply line that is connected to the high-pressure ground connection.