Abstract: An aircraft pressure bulkhead electrical connector comprising a first connection terminal proximate at least one side of the electrical connector and a pressure seal arranged to maintain an applied air pressure differential across the electrical connector in use.

Abstract: A redundant gas supply or oxygen supply for an aircraft comprising two main lines and a group supply line that is connected to one consumer or to a multitude of consumers. In each case a connecting line connects the respective one main line to the group supply line. Flow limiters and nonreturn valves can be provided in the connecting lines.

Abstract: A measuring device for an aircraft is provided in order to determine physical properties of aerosol particles in real time. The device includes a heating device that separates volatile and solid aerosol particles, and a particle sensor that measures acquired data. The physical properties of the solid aerosol particles are determined with an analyzer. The determined analytical data is forwarded to other internal aircraft systems via a communication interface. Due to the formation of a measuring data or analytical data network with several airliners equipped with the measuring device, accurate and up-to-date information on the particle pollution, for example, along flight paths, can be obtained and used for defining no-fly zones, if so required.

Abstract: An actuator is arranged to move an aircraft component such as a landing gear leg, flap or aileron between a first position and a second position, net load from external forces acting on the aircraft component tending to drive it towards the first position. The actuator comprises a threaded screw and a threaded nut. A main prime mover is configured to apply torque to the screw or nut acting in opposition to the net load under normal operating conditions. An emergency prime mover is configured to apply torque to the screw or nut acting in the same sense as the net load under emergency operating conditions in which the interface between the nut and the screw has become partially jammed to the extent that the component cannot be moved from the second position to the first position by operation of the net load alone.

Abstract: An aircraft nacelle in which a power plant with an outside surface is arranged, whereby the nacelle has an inside wall that with the outside surface of the power plant delimits a secondary annular pipe, at least one moving part so as to create at least one lateral opening, and a thrust reversal device that has at least one moving physical obstacle that can occupy a first retracted state in which it does not deflect the stream that circulates in the secondary pipe and another deployed state in which it at least partially deflects the stream that circulates in the secondary annular pipe toward the at least one side opening, characterized in that it includes a ring that is arranged in the secondary pipe, distant from the inside wall of the nacelle and the outside surface of the power plant that supports the at least one moving physical obstacle.

Abstract: A supply system for supplying energy in an aircraft includes at least one electrical line including at least one core connectable to a pole of a current source, an electrically conductive shield, and a detection unit having at least two electrical inputs. The shield surrounds the at least one core under a distance and creates an intermediate space between the at least one core and the shield. At least one port of the detection unit is connected to the at least one core. At least another port of the detection unit is connected to at least one of the shield and the at least one core. The detection unit is adapted for detecting a differential current over the at least one core or an absolute current between the shield and a ground potential for generating a warning signal if a predetermined threshold value for the detected current value is exceeded.

Abstract: A method for fibre placement with the aid of a roller is provided. The roller is able to pivot about a rotation axis and to lay a plurality of first pre-impregnated fibres on second pre-impregnated fibres of a laying surface by rolling over said laying surface. The first fibres being distributed along a lower generatrix of the roller and being in contact with an outer surface of said roller over a contact arc. The method includes cooling the first pre-impregnated fibres in contact with the roller so as to enable them to slide on the outer surface of the roller and heating the second pre-impregnated fibres of the laying surface that are located at the front of the roller so as to promote the adhesion of the first fibres to the second fibres of the laying surface.

Abstract: A method and system for managing automatic guidance of an aircraft during a complete engine failure. Said system includes means for monitoring engines so as to be able to detect a complete failure of the engines; means for detecting whether the aircraft is in flight; means for detecting whether the aircraft is in a different guidance mode from a guidance mode configured to make the aircraft descend with a reduced engine thrust and a fixed speed; and control means for automatically bringing guidance means of the aircraft into a guidance configuration compatible with the situation associated with the complete failure of the engines.

Abstract: A method of aiding the piloting of an airplane ensures the availability of an automatic pilot and a thrust regulation system on board the airplane. To this end, the method includes determining first information by measuring the actual airspeed of the airplane, and this first information is used to control the automatic pilot and the thrust regulation system in a primary mode during normal operations of the airplane. When the first information is lost by becoming unavailable or unreliable, the automatic pilot and the thrust regulation system are each controlled in a secondary mode by control parameters determined using additional flight data independent from the actual airspeed of the airplane and the first information. Consequently, an alternative or redundant control is supplied for ensuring the continued operation of an automatic pilot without necessary intervention from crew members on board the airplane.

Abstract: A method for estimating a loading criterion relating to the load experienced by a structural component of an aircraft, and assistance with detecting a so-called “hard” landing. The method includes measuring parameters of the aircraft and calculating at least one loading criterion for the loading of the structural component using at least one neural network receiving the parameters as input. Assistance with detecting a hard landing then includes determining of a time of impact of the aircraft on a landing strip from the measured parameters, then estimating a plurality of the parameters at the determined time of impact so as to calculate the at least one loading criterion relating to the loading of the structural component.

Abstract: A system for dissipating a lightning current produced by a thunderstorm discharge on an avionic equipment installed on the external skin of an aircraft, the external skin being made of a composite material covered with a layer of expanded metal and including an orifice in which there is positioned an aerodynamic plate covering the avionic equipment. The aerodynamic plate is attached to the external skin by a doubler. The system includes at least one metal plate at least partially surrounding the aerodynamic plate and mounted so as to ensure electrical continuity between the doubler and the layer of expanded metal so as to dissipate the lightning current into the layer of expanded metal.

Abstract: An aircraft glazing component is provided having at least a partially transparent body and a visual wear indicator positioned on or in the body which indicator is configured such that a predetermined amount of erosion on the body changes the appearance of the indicator.

Abstract: A re-usable retainer designed to be used in the curing process of co-bonding uncured stringers. The re-usable retainer is made of metal so it is not necessary to manufacture one retainer for each manufactured stringer. The metallic retainer is placed in direct contact with the uncured resin so the cured stringer has a very good surface quality. The re-usable retainer has a special shape that allows a mild transition of the vacuum bag that avoids vacuum bag breakages. The re-usable retainer is easy to install and to remove.

Abstract: An aircraft fuselage structure with frames (11) running transversely with respect to the longitudinal direction of the fuselage, and main deck cross members (14) is disclosed. The aircraft fuselage structure contains premanufactured integral units (10) which each comprise at least the lower region of the fuselage frame (11) and the main deck cross member (14), the fuselage frame (11) and a region (14a) of the main deck cross member (14) that spans at least an essential part of the width of the main deck and merges on both sides into the fuselage frame (11) being premanufactured in the form of an integral component.

Abstract: A system is provided for collecting defect data of components in a passenger cabin of a vehicle that includes, but is not limited to a component identification device for identifying an affected component, and a malfunction selection device, connected to the component identification device, for selecting a malfunction of the identified component from a predefined quantity of component-specific malfunctions. The system includes, but is not limited to a locating device for acquiring a position of the affected component in the passenger cabin, with the aforesaid being connected to the component identification device. In this manner, by means of devices that are very simple to use, imprecise positioning information, component information and malfunction information can be avoided.

Abstract: A window replacement for filling a window frame in an aircraft is provided, in particular a passenger aircraft, the window replacement being fixable by a retainer in the window frame in place of the window assembly when the window assembly is removed. The window replacement includes a panel-shaped element with at least a single curvature, the panel-shaped element being made of a synthetic material. The window replacement is formed by a monolithic panel-shaped element. The panel-shaped element of the window replacement may also be formed by a sandwich panel. This allows a weight reduction in comparison with a window replacement of a metallic material.

Abstract: A rail cover for a seat rail includes a cover element for completely covering a longitudinal portion of the seat rail. The cover element extends at least in part in a plane of extension that is formed by a longitudinal direction and a transverse direction of the rail cover and includes a first, rigid, longitudinal portion and a second longitudinal portion that follows on from the first longitudinal portion. The first longitudinal portion and the second longitudinal portion are mechanically coupled together by means of a flexible portion, wherein the second longitudinal portion is designed to carry out a pivoting movement in a direction across the plane of extension.

Abstract: A method and device for loading and executing a plurality of instructions in an avionics system including a processor including at least two cores and a memory controller, each of the cores including a private memory. The plurality of instructions is loaded and executed by execution slots such that, during a first execution slot, a first core has access to the memory controller for transmitting at least one piece of data stored in the private memory thereof and for receiving and storing at least one datum and an instruction from the plurality of instructions in the private memory thereof, while the second core does not have access to the memory controller and executes at least one instruction previously stored in the private memory thereof and such that, during a second execution slot, the roles of the two cores are reversed.

Abstract: A high-lift system with a main wing and adjustable flaps as well as guiding devices for holding the adjustable flaps and adjustment devices for adjusting the adjustable flaps, wherein the respective guiding device and/or adjustment device at least in part include/includes a fairing, including a flow influencing device for influencing the flow around the high-lift system, with at least one inlet line with at least one inlet that is situated on or below the bottom of the high-lift system, wherein, furthermore, at least one outlet line for air is provided that includes a fluid-communicating connection to the inlet line and includes at least one outlet situated at the top in the region of at least one adjustable flap of the high-lift system.

Abstract: A detection device for shocks on a part comprises a base intended to be fixed by a lower face onto a surface of the part where the occurrence of a shock is to be detected and comprises one or more detectors fixed at the base and protruding with respect to the base, a detector being deformed in a persistent way with a magnitude equal to or greater than a threshold magnitude when it is subjected to a shock with an energy equal to or greater than a threshold energy. Under the effect of such a shock with energy or greater, a detector is simply deformed or broken such that the visual inspection allows the occurrence of the shock to be detected.