Abstract: Fixing means is disclosed for securing an equipment element to a substrate.

Abstract: The device (1) comprises means (15) for computing deviations of a flight parameter with respect to a reference flight plan, by taking account of predictions, respectively for a plurality of flight data representing different origins, and display means (5) for simultaneously presenting the set of said deviations on a screen (6) of the flight deck of the aircraft, each time indicating the corresponding origin.

Abstract: Diagnostic system including a sensor device with a sensor for generating signals corresponding to a first operational condition, a control device with a timer and function for performance of measurements, and a signal transmission device. The system includes a device for determination of a second operational condition of the system component and configured where the sensor value of the signal transmission device corresponding to the first operational condition is furnished when the sensor value corresponding to a second operational condition of the transmission mechanism is higher or lower than a comparative value, and housing component of a lubricant container and a closure device for sealing an opening of the housing component from a lubricant present in the operational use thereof in an internal space thereof, having arranged therein: at least one sensor device including at least one sensor for determining the water content in the lubricant.

Abstract: A supply system for providing at least oxygen depleted air and water in a vehicle includes a catalytic converter, at least one hydrogen supply means, at least one air supply means, at least one outlet for oxygen depleted air, and a control unit coupled with the catalytic converter. The catalytic converter is couplable with the hydrogen supply means and is adapted for producing water under consumption of hydrogen from the at least one hydrogen supply means and oxygen. The catalytic converter is further couplable with the at least one air supply means for additionally producing oxygen depleted air. Further, the control unit is adapted for selectively operating the catalytic converter based on a demand of water and oxygen depleted air.

Abstract: In a method for forming an electrolyte film on an electrode surface, the liquid electrolyte is sprayed into a cavity to form an electrolyte mist; the electrolyte mist exits the cavity through an opening and then flows across the electrode surface, which is directed downward at an angle behind the opening, whereby an electrolyte film is formed on the electrode surface and wherein the thickness of the electrolyte film is set by means of the angle of inclination of the electrode surface. A corresponding device includes an electrolyte tank communicating with a mist chamber for accommodating sprayed electrolyte by means of a spraying apparatus, wherein the mist chamber comprises a mist outlet. Furthermore, a retainer for fixing the electrode surface at a specifiable angle of inclination is provided, so that electrolyte mist, which can exit through the mist outlet, flows across the electrode surface to form an electrolyte film.

Abstract: A device for attaching an aircraft cabin module, which device comprises a component with limbs for the releasable locking of a plug pin, fitted to the aircraft cabin module, and a plurality of electrical contacts. The component is configured in U shape as the rail component, the limbs thereof having locking points for the releasable locking of the plug pin fitted to the aircraft cabin module and the center portion thereof connecting the two limbs comprising the electrical contacts for the voltage supply and for the exchange of data with the aircraft cabin module.

Abstract: A method for emergency ventilation of an aircraft cabin is provided. The method includes controlling a first valve to supply air from the aircraft environment into a first aircraft fuselage area through the opened first valve and into the aircraft cabin. The method further includes controlling a second valve to conduct air from the aircraft cabin into a second aircraft fuselage area and out to the aircraft environment through the opened second valve. In their normal operation, the first and second valves serve as air outlet valves of an aircraft cabin pressure control system. The method further includes controlling a recirculation fan of an air-conditioning system to draw air supplied through the first valve into a mixing chamber of the air-conditioning system and to direct air from the mixing chamber into the aircraft cabin.

Abstract: An aircraft (11) with at least an inflatable device (41) installed in a cavity (21) in its external surface which is equipped with a door (25) for opening/closing said cavity (21) is provided. The inflatable device (41), comprising a cushion (45) and a gas generator is configured for filling the cavity (21) with the cushion (45) when it is inflated with the gas supplied by said gas generator, without protruding from the cavity (21) for reducing the downstream air flow disturbances generated by said cavity (21) when the door (25) is open. The inflatable device (41) includes control means for inflating the cushion (45) in predetermined circumstances, being the door (25) open. The invention is particularly applicable to the cavities of the Main Landing Gear (31) for avoiding power losses to a Ram Air Turbine (51) placed behind it.

Abstract: Detection and location of electrical faults in a network of metal structures which can receive electric cables and allow return of current by the cables. The reflectometry-based method involves injecting a probe signal into a cable coupled to the structures and analyzing the signal reflected by the anomalies. A conductive element is provided for carrying the probe signal at a constant distance from each structure. In one aspect, an insulated conductive element is arranged inside the metal structure and is built into a longitudinal groove in a surface for receiving a longitudinal plastic holder wedged into the structure. The reflected signal from the conductive element is compared to a threshold above which an anomaly is detected, and the anomaly is located by topological correlation. The invention is useful for airplane raceways having a composite skin.

Abstract: An aircraft assembly comprising: a pair of covers; a spar web extending between the covers in a thickness direction, the spar web having a length which extends in a span-wise direction; and a container which extends from the spar web and houses at least part of a system component. The container comprises first and second side walls which are spaced apart from each other across the spar web in the thickness direction, and inboard and outboard walls which are spaced apart from each other along the spar web in the span-wise direction. The spar web and at least part of the container are integrally formed as a single piece.

Abstract: A device and a method for calibrating load sensors which are provided at least one load cross-section of an aerofoil or control surface of an aircraft, the load sensors being calibrated on the basis of load coefficients (?i) of the load sensors, which load coefficients a calculation unit calculates by evaluating a linear system of equations formed by means of mechanical loading of the aerofoil or control surface.

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: An airframe structural element, such as an aircraft rib, is disclosed that comprises an integral pipe connector element for connecting pipes through the structural element. The pipe connection means provided by the pipe connector element may be aligned on a common axis with a pipe connection means provided by an adjacent airframe structural element.

Abstract: Method for connecting two intermediate products for forming a fiber composite product, wherein the two intermediate products respectively are composite fiber material with a layer of matrix material and reinforcing fibers extending therein by connecting areas that adjoin one another in an overlapping region of the interconnected intermediate products, with the method including applying an adhesive layer with an adhesive film with connecting particles onto the connecting areas of the intermediate products, arranging the second intermediate product on the first intermediate product or vice versa so the connecting areas at least partially overlap one another, and connecting the two intermediate products. A structural component is also disclosed with at least a first and a second fiber-reinforced intermediate product.

Abstract: The present invention relates to a high lift system for an aircraft, comprising a flap, which is arranged on a wing box and which can be moved between a retracted position and at least one extended position relative to the wing box by means of a drive device, a support construction, which is arranged on the wing box in the area of the drive device and to which the flap is coupled and which comprises a movable support element, which can be moved to move the flap relative to the wing box, and an acceleration sensor arranged in the area of the flap or the movable support element for detecting accelerations of the flap.

Abstract: A flow limiter comprises a line segment with an air inlet and an air outlet and at least one resistance element. The resistance element is positioned within the line segment and impresses a predetermined flow resistance on an air flow that extends from the air inlet to the air outlet. Preferably, the resistance element extends at least in part in an axial direction of the line segment. Such a flow limiter is used to adjust an air volume flow and comprises particularly low generation of intrinsic noise.

Abstract: A measurement method for determining the position of an omega profile component placed on a shell component of an aircraft, in which the ACTUAL position of the omega profile component relative to the shell component is optically acquired in a contactless manner, so as to subsequently compare the latter with a defined DESIRED position, wherein several adjacently spaced apart measuring points are established at two mutually opposing flank sides of the profile cross section of the omega profile component, through which a regression line is run according to the path measurement principle based on coordinates, whose point of intersection is drawn upon to determine the orthogonal position of the omega profile component relative to the shell component.

Abstract: Device intended for a double glazing including at least one outer glazing and one inner glazing separated by an intermediary space filled with a gas, used to isolate an inside environment from an outside environment, a pressure variation being liable to occur between these environments, for example in the case of an aircraft in flight, includes means for conserving the outer glazing and the inner glazing of this double glazing mainly parallel, independently of this pressure variation. The invention also concerns a double glazing including this device, the process for maintaining parallelism and software using the process.

Abstract: A housing-free hatrack for a passenger cabin of an aircraft includes a hatrack body, at least one fixing brace and a support which is arranged between the hatrack body and one end of the fixing brace in such a way that the hatrack body is pivotable about a pivot axis. The other end of the fixing brace may be connected to a frame of an aircraft structure of the aircraft. This hatrack dispenses with the double-walled construction of conventional hatracks and the hatrack is therefore directly fixed to the structure of the aircraft.

Abstract: A joint between a pair of aircraft components comprising a first component; a second component bonded to the first component over a bonded area, the bonded area terminating at an edge; a non-bonded area located between the edge of the bonded area and an edge of the second component, the components not being bonded over the non-bonded area; and one or more fasteners passing through the non-bonded area and fastening the first component to the second component.