Abstract: The invention relates to a flight data recorder. It is equipped with capsules designed to break at determined depths. The capsules release hydraulic tracing elements, generating a luminous streak in the water, when they are broken, so that the searches for the flight data recorders, or black boxes, are made easier.

Abstract: A method for measuring a position of an element of a structure includes the steps of: attaching a receiving device to the element at a measurement position; attaching a first reference device to the receiving device; determining a first measurement point with a first measurement device adapted to measure a position of the first reference device; removing the first reference device; attaching a second reference device to the receiving device; and determining a second measurement point with a second measurement device adapted to measure a position of the second reference device.

Abstract: The invention relates to a modular assembly for fastening electronic modules carried on board an aircraft, characterized in that it comprises: a frame (10) having a more or less planar vertical front surface, comprising several mechanical fastening interfaces each intended for mechanically fastening an electronic module, at least one electronic module (80) comprising a mechanical fastening interface and which is attached to the front surface of the frame in suspended position via cooperation of the mechanical fastening interface of the said at least one electronic module with one of the mechanical fastening interfaces of the frame.

Abstract: The flight control system comprises: at least one actuator (13) for a mobile surface of the said aircraft; a flight control module (12) in communication with the said actuator (13), the said module comprising at least a first and a second computer (14-1, 14-2, 14-3, 15-1, 15-2, 15-3), each computer being adapted for calculating a control command established according to at least one predetermined law for control of the said flight surface; the said actuator (13) comprising logical means (18, 19) adapted for comparing the commands of the said computers (14-1, 14-2, 14-3, 15-1, 15-2, 15-3) and for determining on the basis of these commands the action to be executed on the said mobile surface. The aircraft comprises such a system.

Abstract: A support assembly for guiding a flap on an aircraft wing during deployment of the flap. The assembly includes an arcuate guide track mountable to an aircraft wing and defining a two-dimensional path, a carriage mounted on the guide track so as to slide along the track during flap deployment, a part-spherical bearing, and a shaft having one end attachable to a flap and the opposite end coupled to the carriage via said part-spherical bearing. The shaft is free to pivot relative to the carriage about a center of the part-spherical bearing in all directions, as the carriage slides along the track.

Abstract: Fuel in an aircraft fuselage fuel tank is cooled by means of cold air flowing from the exterior of the aircraft to a cooling region inside the aircraft. The cooling region may be (a) located to the exterior of the fuel tank, (b) in thermal communication with the fuel tank and (c) in fluid communication with a region downstream of, and remote from, said cooling region, for example, an exhaust port on the outside of the aircraft. The flow of air may be caused by air entering a ram air intake, into which air passes as a result of the motion of the airborne aircraft relative to the surrounding air.

Abstract: A method of making an aircraft component is provided, wherein the method comprises the steps of: providing a mold (1) for the receipt of a material (3) from which the aircraft component is to be made providing the mold with said material providing an intensification tool (14) in spaced relationship to the mold and heating the material, tool and mold so that the tool expands and applies pressure to the material and so as to form the component and wherein the linear coefficient of thermal expansion of the tool in a first direction is matched to the coefficient of thermal expansion of the component in the first direction, and the coefficient of thermal expansion of the tool in a second direction is greater than the coefficient of thermal expansion of the component in the second direction, the tool being provided with at least one contacting surface for contacting the material and through which pressure is applied to the material, the expansion of the tool in the second direction causing the at least one contact

Abstract: A system for automatically managing engine control modes of a multi-engine aircraft is disclosed. The system (1) can comprise means (5, 7, 8, 9, 10) for automatically switching all the controlling units (2) of the engines of the aircraft to an alternative controlling mode, as soon as one of such controlling units (2) is brought to such an alternative controlling mode.

Abstract: According to an exemplary embodiment of the invention a fuselage segment of an aircraft fuselage is provided, which aircraft fuselage comprises four different radii of curvature, wherein two radii of curvature comprise center points that are not situated on a vertical symmetry axis of the fuselage segment.

Abstract: An aerodynamic body with an aerodynamic body surface that creates a contoured surface for a fluid to stream around, with a device to influence the flow of the fluid streaming around the aerodynamic surface. The flow-influencing device includes a passage to link the fluid streaming around the aerodynamic surface with an actuator space of an aspirating and purging device situated in the aerodynamic body, and an indentation that is situated next to the passage, which is formed by a recessed section of the aerodynamic surface on a flow-influencing region within the contoured surface of the aerodynamic surface, so that a boundary wall is configured as part of the recessed surface lying opposite the indentation. The aspirating and purging device can generate a swirl in the flow of the fluid streaming around the aerodynamic surface, the rotational axis of which is directed along the assumed aerodynamic body chord direction.

Abstract: A holding device for attaching at least one fixture to a fuselage cell structure of an aircraft, includes a basic element attached to the fuselage cell structure, to which at least one fixture element to accommodate the fixture is fastened, wherein the basic element is embodied as a hook-and-loop element, the hook-and-loop bristles of which co-act with corresponding hook-and-loop bristles of at least one fixture element, which is also embodied as a hook-and-loop element thus forming a hook-and-loop connection, wherein the space between the interengaging hook-and-loop bristles is filled with an adhesive.

Abstract: An aircraft nacelle air intake includes a duct extending around the circumference of the air intake and elements (24) for the localized injection of hot air into the duct to make the hot air circulate in the duct along its circumference, characterized in that the injection elements (24) include a collector tank in a plane secant with the direction of the stream of air flowing through the duct including at least one hole (44) allowing the air stream flowing in the duct to pass through it and a plurality of injection orifices (46) which are connected to a hot air supply and arranged around the passage hole or around and/or between the passage holes (44).

Abstract: A device for adapting aerodynamic characteristics of a wing element, includes a winglet, movably attachable to a wing element. The winglet or parts of the winglet may be rotatable in relation to the wing element such that an associated rotary axis with a main direction of extension of the wing element encompasses an angle that differs from an angle of 90°. In addition, a method is disclosed.

Abstract: A method and device to help an aircraft change altitude in case of reduced separations is disclosed. The device, embarked on board the airplane, comprises means for determining a performing time range during which the altitude change maneuver within reduced spacings being desired by the pilots is able to be performed.

Abstract: An electrical actuator limits the speed of the electric motor which controls the hydraulic pump of the actuator, during the opening of a pressure relief valve. To this end, the electrical actuator applies an auxiliary set-point speed value to the electric motor to avoid damage that may be caused by overheat at the actuator.

Abstract: An aircraft cabin curtain rail assembly kit includes a plurality of curtain rail components with linear curtain rail sections and curved curtain rail sections with an angle of curvature in a range of 0-90°. Each curtain rail component has a first end and a second end. On the first end, a recess for receiving a fixation protrusion of another curtain rail component is arranged and, on the second end, a fixation protrusion for inserting into a recess of another curtain rail component is present. The recess and the fixation protrusion include a fastening means for fixating the recess and the fixation protrusion relative to each other. Each curtain rail component includes a holder slit for attaching the respective curtain rail component to an object and a curtain slit for guiding curtain rail guiding means in the curtain rail component.

Abstract: An aircraft nacelle includes an air intake (12) followed at the upper part by a part (14) integral with the mast, called a cap, and at least one door (16) with a curved profile, and a device for encircling it in the form of at least one flexible element (38), guide elements (40) for allowing the at least one flexible element (38) to follow the curved profile of the at least one door, a first anchoring point (42) of the at least one flexible element (38) integral with a first edge (78) of the cap and another anchoring point of the at least one flexible element (38) integral with a second edge (80) of the cap, whereby the anchoring points (42) allow a relative translational movement, in a direction that is parallel to the longitudinal axis of the nacelle, between the cap (14) and the at least one door (16).

Abstract: A method for testing or evaluating the configuration of at least one equipment item in an aircraft includes receiving at least one command to test or evaluate the configuration of the at least one equipment item via a network interface of a less secure part of an on-board information system of the aircraft. The network interface is capable of exchanging data with an information system external to the aircraft. The method also includes encoding the at least one received command and transmitting the encoded command to the secured part of the information system of the aircraft. In response to reception of the encoded command, the at least one encoded test command is filtered. In response to the filtering, the encoded command is translated and executed in relation to at least one first maintenance function of the secured part.

Abstract: An assembly for connecting a first body to a second body includes a first element having a connection end to the first body and a first tubular portion, and a second element having a connection end to the second body and a second tubular portion extending along the longitudinal axis. The first tubular portion and the second tubular portion are interlocked by at least one complementary tubular portion nested in the first tubular portion and around the second tubular portion. A rigid piece connects the first body to the second body and is fastened to the first and second bodies. One of the first and second bodies is connected with functional play at one of the two attachment points of the rigid connecting piece, wherein the rigid connecting piece is formed of two flat rigid pieces extending on both sides of the first and second elements along the longitudinal axis.

Abstract: An aircraft nacelle comprising a power plant having a pipe with an aerodynamic surface, an air intake having an inside pipe with an aerodynamic surface, and an annular support of at least one measuring device having an aerodynamic surface, wherein the annular support is removably-inserted between the power plant and the air intake. In particular, the annular support is inserted downstream of the air intake and upstream of the power plant in a direction of flow of the stream of air, in such a way as to ensure continuity of the aerodynamic surfaces.