Abstract: An anticorrosion coating and an article coated with an anticorrosion coating, especially for use in an aircraft, and a method of producing a coated article and a vehicle, especially an aircraft, including an anticorrosion coating or at least one such coated article. An anticorrosion coating includes an aluminum alloy having 0.03-0.5% by weight of tin. A coated article produced at least partly from a material and having at least partly been coated with the anticorrosion coating including an aluminum alloy having 0.03-0.5% by weight of tin. A method of producing the anticorrosion coating is also disclosed.

Abstract: An aircraft sound diagnostic method includes a step of measurement of acoustic signals by a plurality of microphones mounted at different positions inside the aircraft, a step of recording of the measured acoustic signals, a computation step which generates a sound mapping on the basis of the measured acoustic signals, a step of comparison of the sound mapping and a reference mapping and a step of transmission of the comparison to a user device. The method makes it possible to track the trending of an abnormal noise or of an abnormal noise level and assist in determining the context thereof. An aircraft sound diagnostic device for implementing the method is also described.

Abstract: A shackle for fastening an aircraft engine including a ball joint with a pin including a ring including a first bore and a sleeve assembled in the first bore and having a second bore configured to receive the pin and the diameter of which progressively increases to have a flared inner surface at each of its ends, the fastening shackle being arranged such that a spherical outer surface of the ring bears an anti-friction coating produced on a region extending beyond the contact region with the body of the shackle, this first region being bordered by rims forming a projection around the coating, and/or the second bore bears an anti-friction coating on a region extending beyond its contact region with the pin, this region being bordered by rims forming a projection around this anti-friction coating, at the ends of the flared inner surface.

Abstract: A structural component for an aircraft including at least one heatable component section having a layer structure including an inner base structure, at least one heating layer having carbon allotropes embedded in a matrix material, at least one first group of consecutive layers including at least one anode layer, at least one first insulating layer, and at least one cathode layer having an electroactive coating. The first group of layers are arranged between the inner base structure and the at least one heating layer, and at least one protective layer is arranged outside the heating layer. The first group of layers constitute a structural battery. The at least one anode layer and the at least one cathode layer are electrically connectable with the heating layer.

Abstract: A cooling system for an aircraft, including a heat exchanger for cooling a hot fluid with cooling air, an air intake for the supply of cooling air and a Coand?-effect air amplifier for the creation of a flow of cooling air.

Abstract: A fastening system including a structure holding element fastenable to a structural component. The fastening system includes a component holding element fastenable to a component to be fastened and movable relative to the structure holding element between first and second operating positions. A first lever element is connected to the structure holding element to be rotatable about a first rotation axis and is connected to the component holding element to be rotatable about a second rotation axis. The fastening system includes a connection element, connected to the component holding element to be rotatable about a third rotation axis and connected to the structure holding element to be displaceable in translation relative to the structure holding element, such that the second rotation axis, when the component holding element is transferred from its first into its second operating position, is displaced in a plane extending perpendicularly to the second rotation axis.

Abstract: An acoustic panel comprising a cellular structure, such as a honeycomb structure, having cells that open at least onto a first frontal face of the structure. The panel comprises a capsular skin which is fastened to the first frontal face of the cellular structure next to a plurality of cells. The capsular skin including a continuous layer of material, in one piece, forming capsules that extend into the cellular structure. At least one channel is provided at the apex of each capsule for the passage of acoustic waves. Such a panel effectively attenuates the noise of aircraft engines, in particular, the low frequencies. It is extremely easy to manufacture industrially, the capsular skin being able to be obtained by molding with polymerization in situ, the polymerizable material then adhering to the cellular structure while it polymerizes.

Abstract: A system for an aircraft comprising a controller configured to obtain a first piece of information regarding whether the aircraft has achieved lift-off; to obtain a second piece of information regarding whether the aircraft is in a flight phase in an initial part of lift-off; to determine, on the basis of at least the first piece of information whether the gear is retractable, and, if the gear is retractable in an initial part of the lift-off, to trigger a landing-gear-retraction alarm taking an audio form and/or a visual form, and, if the gear is retractable after the initial part of the lift-off to optionally trigger a second landing-gear-retraction alarm taking an audio form and/or a visual form. A method implemented by the system is provided. Advantageously, an omission of the retraction of the landing gear of an aircraft is notified to its flight crew.

Abstract: To reduce the bulk of the acquisition systems embedded onboard an aircraft and dedicated to predicting failures, an acquisition system is provided comprising an avionics rack and at least one recording device, in which the avionics rack comprises a front panel provided with at least one test connector configured to be connected to all or some of the data buses of the aircraft, each recording device comprises a housing and an acquisition port, the acquisition port being provided on an outer face of the housing, the acquisition port of each recording device is engaged with a corresponding test connector of the avionics rack, each recording device is configured to acquire at least some signals applied to the acquisition port by the corresponding test connector, and to store the acquired signals.

Abstract: A propulsion assembly with an outer compartment, an inner compartment, a supply pipe and a transfer pipe between the two compartments, a suction system between the two pipes, a regulating element that regulates the flow rate of air in the suction system and a fire-fighting system having a reservoir of extinguishing fluid, a discharge pipe connected to the reservoir, and a control system between the reservoir and the discharge pipe. The discharge pipe is configured and arranged to supply the transfer pipe when the control system is in the open position. The outside air is then driven by the suction system and passes through the two compartments in a forced manner and the extinguishing fluid reaches the transfer pipe to flow into the inner compartment.

Abstract: A position detector for a passenger service unit which can be installed in a passenger service channel. The position detector includes a sensor rail which has a multiplicity of sensors and is configured to be fitted in the longitudinal direction of the passenger service channel. The position detector also includes a position marker which is configured to be fastened to the passenger service unit and to trigger a sensor signal at one of the multiplicity of sensors. A passenger service channel having a position detector and a vehicle area having a passenger service channel are also described.

Abstract: A tire monitoring device and method in which an error can be detected and indicated. The tire monitoring device includes an indicator and a wireless communication interface. The method of operating the tire monitoring device includes: receiving an instruction to measure a tire pressure via the wireless communication interface; measuring a tire pressure; determining an error status of the tire pressure monitoring device; and responsive to a determination that the error status is not indicative of an error, activating the indicator to provide an indication based on the tire pressure.

Abstract: An anchor rail for an aircraft floor includes an upper flange with a guideway and two flange wings. The rail is formed of a beam and of an anti-corrosion protection. The beam is formed at least of a body made from a first material and defining the lower stiffening structure and an upper platform. The anti-corrosion protection wholly covers an upper face of the upper platform and therewith constitutes the upper flange of the rail, thus layered. The anti-corrosion protection is at least formed of a protective sheet made of a second material more resistant to corrosion than the first material and selected from a metal and a fiber-reinforced plastic composite material. Such a rail exhibits good corrosion resistance for modest cost.

Abstract: A load carrier for an aircraft cargo hold includes a bottom element with a support surface, the load carrier being movable over a floor surface in a floor plane while the support surface faces the floor surface, the bottom element having a base surface. The support surface has rolling elements rotatable about a rotation axis oriented where a parallel to the axis runs parallel to the floor plane, and the rolling elements being retained on the bottom element where the rotation axis of each of the rolling elements can be rotated about a vertical axis running perpendicularly to the floor plane. A load carrier can include a bottom element, the support surface of which has outlet openings, through which air can exit from the support surface to form an air cushion under the support surface. A load carrier can include a bottom element the support surface of which has slider elements.

Abstract: A flow body for an aircraft includes a torsion box with spars and/or ribs and at least two skin portions for enveloping the spars and/or ribs, wherein at least one inner cell is formed in the torsion box. It is provided that a gas tank with a gas tank shell is arranged in the at least one inner cell, and that the gas tank includes fastening elements coupled to retaining elements in the relevant inner cell in order to hold the gas tank such that the gas tank shell is supported at a distance from the spars and/or ribs and the skin portions and is supported in three spatial directions.

Abstract: A method for producing an alveolar soundproofing structure in which a portion of a membrane of a diaphragm including an acoustic outlet is inserted into a hole of a perforated membrane which covers a cell of the alveolar structure, and the diaphragm is pressed into the cell with the perforated membrane becoming deformed and is fixed at that location. It also relates to the alveolar structure. Such a method enables different types of diaphragms to be inserted into different configurations of cells and enables the diaphragm to be fixed therein, in accordance with the sound frequencies to be processed.

Abstract: A drain mast for an aircraft for discharge of water from the aircraft interior with a line which extends in a line direction from a connector end to a discharge end. The connector end can connect to another line in the interior of the aircraft, through which further line water flows into the drain mast. The discharge end can discharge water into a surrounding area of the aircraft. The line includes a plastic, into which a conductive material is embedded, by which the line can be heated electrically, by a heating current being conducted through the conductive material. A proportion of the embedded conductive material in the line increases in the line direction per length unit from the connector end of the line towards the discharge end such that the heating power which is introduced into the line per length unit increases from the connector end towards the discharge end.

Abstract: A system for heating up water for a consumer unit in an aircraft, having a water reservoir and a control unit. The water reservoir has a heating device to heat water held in the water reservoir to a consumer temperature. The control unit controls the heating device so water in the water reservoir is automatically heated to or above a disinfection temperature at which germ formation in the water reservoir is eliminated or suppressed, and a temperature of the water in the water reservoir is maintained at or above the disinfection temperature for a disinfection period, the heating to the disinfection temperature being effected only during flight phases or portions of flight phases of the aircraft during which use of the consumer unit by a user is not to be expected. A corresponding method and an aircraft having such a system are disclosed.

Abstract: An aircraft brake temperature control system (BTCS) 100 for controlling a temperature of a brake 220 of a landing gear 201 of the aircraft 200. The BTCS 100 includes a controller 110 configured to cause at least one fluid moving device 230, 231, 232 to drive a flow of fluid onto the brake 220, selectively in one of a plurality of modes, to control the temperature of the brake 220. The BTCS 100 may be incorporated into an aircraft system 1000 with at least one fluid moving device 230, 231, 232, wherein the aircraft system is on an aircraft 200.

Abstract: A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) with a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing a plenum (7), an outer wall element (23) facing ambient flow (25), and a core assembly (97). The outer wall element (23) includes micro pores (31) and the inner wall element (21) includes openings (33) which form a fluid connection from ambient flow, through the core assembly (97) and to the plenum (7). The thickness of the outer wall element is reduced due to the first attachment end (17) and/or at the second attachment end (19) attached to the inner wall element (21) by both bonding and fasteners (85, 87, 89, 91).