Abstract: A device including an acquisition module for acquiring current parameters of the aircraft, a computational module for computing a current load factor of the aircraft, a computational module for computing a minimum load factor, a computational module for computing the difference between the current load factor and the minimum load factor, and an acoustic emission module for emitting a sound signal, the level of which increases gradually as a function of time when the difference between the current load factor and the minimum load factor is less than zero.

Abstract: An application system for depositing a fluid product on a surface. The application system comprises a frame mounted on a locomotive system ensuring the displacement of the frame over the surface, a tank mounted on the frame and receiving the fluid product to be applied, and an application head fluidically connected with the tank via a supply nozzle. The application system comprises a guiding system which comprises detectors to detect the obstacles in the environment of the application system. Such an application system allows for an even application of the fluid product over the entire surface.

Abstract: A fuel system which includes a fuel return system. The fuel return system includes a fuel return valve arranged on a return line, and the return line is intended to be mounted between an engine of an aircraft and a fuel tank of the aircraft. The return valve is configured to allow a return of fuel from the engine to the fuel tank when the engine is in operation. The fuel return system also includes a bypass valve assembly mounted in parallel to the return valve, and is configured to allow a return of fuel from the engine to the fuel tank when the engine is not in operation.

Abstract: A pipe assembly includes two pipes connected together by a joining device and a drainage system, the drainage system includes a drainage slot created in the joining device, two annular seals arranged on either side of the drainage slot over the entire periphery around a pipe, and a drainage element configured to send fluid present in the drainage slot from a first end entering the drainage slot to the other end of said drainage element.

Abstract: A method for structural component crack testing comprising: a) identifying a structural component hole and inserting a probe thereinto; b) for different emission directions, automatically performing the following: b1) controlling a probe ultrasound beam emission; b2) measuring a probe signal; b3) if the measured signal amplitude is above a predetermined threshold: determining a distance between the probe and a structural component discontinuity point; recording a data set comprising at least the distance between the probe and the discontinuity point, together with a data element corresponding to the probe emission angular direction, c) automatically searching for data sets corresponding to characteristic discontinuity points, and consequently establishing a correspondence between the probe emission angular directions and an angular reference frame linked to the component; d) based on the recorded data sets, automatically determining the discontinuity point positions; e) determining a dimensional characteristi

Abstract: An aircraft engine unit comprising an engine, a mast and an engine connection connecting the engine and the mast. The aircraft engine unit includes a front engine attachment of the engine connection which comprises at least one front rod connecting the primary structure of the mast and the core of the engine and which assures the take-up of vertical forces, and at least one connection connecting the primary structure of the mast and the fan casing of the engine and which assures the take-up of forces that are horizontal and perpendicular to the axis of rotation of the engine and/or a torque about the axis of rotation of the engine.

Abstract: A method for manufacturing a panel made of composite material incorporating a lightning protection arrangement which comprises strips with a conductive layer. The method comprises a step of laying the strips in an automated manner, the strips having a width of less than 20 mm and being distributed in a first set of mutually parallel strips that are laid in a first laying direction and a second set of mutually parallel strips that are laid in a second laying direction that intersects the first laying direction. A panel made of composite material manufactured by way of this method is also disclosed.

Abstract: The transmission of flight instructions from a ground unit to an aircraft comprising an onboard system. The ground unit is configured to generate, on the basis of flight data intended for the aircraft, at least one optical symbol containing a flight instruction. The onboard system comprises an optical reader and a flight management system. The optical reader is configured to read the optical symbol and to transfer the flight instruction contained in the symbol to the flight management system to prepare the flight of the aircraft.

Abstract: The control device of a communication system of an aircraft having a predefined number of communication channels comprises a processing unit and sets of buttons each associated with a communication channel and comprising a button for setting sound volume, a reception button and a transmission button. The number of sets of buttons is at least equal to two and less than the predefined number of communication channels of the communication system. The device comprises display areas on a display screen, a display area being associated with each set of buttons and provided to display at least the name of the communication channel associated with the set of buttons. The processing unit is configured to configure the association between each of the sets of buttons and the communication channel associated with this set of buttons according to actions of a user on at least one interactive element of the device.

Abstract: A display system for an aircraft cockpit comprises a display device configured to be secured to a user's head, a sensor to determine an orientation of the user's head, and a display computer. The computer is configured to control the display of information relating to the flight of the aircraft on the display device, to acquire information on the user's head orientation, to determine an angular offset value between a direction corresponding to the head orientation and a longitudinal axis of the aircraft, to evaluate at least one condition as a function of the angular offset value, and to control the display device display in accordance with a first display mode when the condition is verified, this first display mode corresponding to a display comprising at least one aircraft piloting assistance symbol displayed in a conforming manner, and another display mode when the condition is not verified.

Abstract: A method for optimizing the take-off parameters of an aircraft. The aircraft comprises a system for automatically controlling the high lift devices at the moment when the wheels of the aircraft leave the ground. The method comprises a step of selecting a first configuration of the high lift devices at the start of the take-off phase and a selection of an acceleration speed of the aircraft. The method is advantageous in that, on reception of an actual aircraft take-off detection signal, a control unit is configured to transmit a control command making it possible to bring the high lift devices into a second configuration, in which they are retracted relative to the first position, and consecutively accelerate the speed of the aircraft automatically to an acceleration speed entered by the pilot.

Abstract: A mobile vehicle for supplying pressurized air to an aircraft, the vehicle being configured to tow the aircraft during its movements on the ground and including a pneumatic supply system configured to supply pressurized air to the aircraft, the pneumatic supply system being manually connectable to a high-pressure connector of the aircraft and remotely disconnectable from the connector.

Abstract: A universal joint comprising a first band, a second band, and a third band. The three bands are cylindrical bands coaxial with one another with respect to a common axis. The first band and the second band are separated by a first slot, and the second band and the third band are separated by a second slot. Two connection points, which are diametrically opposed, assure the connection of the first band and of the second band. Two other connection points, which are diametrically opposed, assure the connection of the second band and of the third band. The two connection points between the first band and the second band are offset by substantially 90° in rotation about the common axis with respect to the two connection points between the second band and the third band.

Abstract: In an aircraft comprising a cockpit comprising a display screen, a camera configured to acquire images of the environment of the aircraft, as well as a display management system, a ground rolling aid system configured so as to a) acquire several successive images of the environment of the aircraft via the camera, corresponding to various ground positions of the aircraft, b) modify these images by removing at least zones corresponding to the aircraft, so as to produce modified images, c) combine several of the modified images to produce a recomposed image, d) superpose an image characteristic of the aircraft on the recomposed image so as to produce a reference image, and e) display, on the cockpit display screen, an image corresponding to the reference image.

Abstract: A method for testing the integrity of a component in a measurement area of the component, using an instrument having a flexible part and a rigid end part following the flexible part and carrying an eddy current probe. The method comprises a selection step in which a template corresponding to the measurement area is selected, a shaping step in which the flexible part is shaped against the template thus selected, a positioning step, in which the instrument thus shaped is positioned so that the eddy current probe is placed in the measurement area, and a measurement step, in which a measurement is made via the eddy current probe which has been thus positioned.

Abstract: An assembly including a first pipe length and a second accommodating mechanical pipe length, said first length being assembled in said second length by means of an interface joint, that is a conductor of electric current. As it is assumed that said first length and said second length are also conductors of electric current, the joint thus provides good sealing between the first pipe length and the second pipe length in order to prevent leakages of fluid and to prevent the formation of inopportune electric arcs due, for example, to static electricity.

Abstract: A support for a pipe which comprises a body which comprises a through-orifice for the pipe. The through-orifice has a diameter which is greater than an external diameter of the pipe. At least one base of the support is configured so as to be in contact with and connected to a fixing surface. A first ring and a second ring each have an eccentric orifice and are configured so as to be fitted one into the other in the orifice of the body about the pipe when the support is put in position. By rotating at least one of the first and second rings, the position of the axis of the pipe may be adjusted radially relative to the support.

Abstract: A method for inspecting the quality of an alignment between the elements of an assembly, and an associated device, the method of which comprises tasks consisting of measuring a first parameter with a first measuring means, said first parameter being selected from a movement parameter of at least one part of the double-access fastening means, an assembly force parameter or a torque, measuring a second parameter with a second measuring means, said second parameter being selected from the same parameters and being different from the first parameter, calculating a value of a first derivative of a function representing a change in the second parameter relative to the first parameter by suitable information processing means, and analyzing the value of the first derivative to check the alignment between the elements to be assembled.

Abstract: An aircraft engine assembly including a set of rear engine attachments comprising a first shackle hinged on a bracket secured to the engine and on a bracket made as one piece with one of the two side panels, the shackle being oriented along a vertical direction, a second shackle hinged on a bracket secured to the engine and on a bracket made as one piece with the other one of the two side panels, the second shackle being oriented along the vertical direction, and a third shackle for transversally transmitting loads, inclined relative to the vertical direction and hinged on a bracket secured to the engine and on a bracket secured to the primary structure.

Abstract: A center to assist flight management of a plurality of an entity's aircraft comprising a control unit and at least two stations and communication equipment configured to receive data signals and to transmit/receive audio signals to/from each aircraft. The control unit comprises a man-machine interface connected to a central unit, the central unit being connected to a computation unit of each station and to the communication equipment to receive data signals and to transmit/receive audio signals to/from the equipment. Each station comprises, connected to the computation unit, a screen to display the data in the data signals sent by each aircraft and an audio device for the operator to exchange audio signals with the pilots. The central unit is configured to selectively activate/deactivate, as a function of the interactions of an operator with the interface, the exchanges of audio signals with the central unit of each station.