Abstract: A rudder bar for an aircraft comprising a floor, a steering connecting rod and a braking connecting rod. The rudder bar comprises a base fixed above the floor, a pedal arm mounted rotatably on the base about a first axis of rotation and having a lower end and an upper end, a pedal mounted rotatably on the lower end about a second axis of rotation, a first transmission assembly configured to transmit a movement to the steering connecting rod when the pedal arm pivots about the first axis of rotation, and a second transmission assembly configured to transmit a movement to the braking connecting rod when the pedal pivots about the second axis of rotation.

Abstract: An aircraft nacelle comprising a first and a second cowl mounted pivotably about an axis substantially parallel to a longitudinal axis of the nacelle and lockable to one another by at least one locking mechanism. The nacelle further comprises a device for providing a visual warning of a locking defect of the cowls. The device comprises a movable bolt associated with the locking mechanism and a movable edge plate mounted on the nacelle in line with said bolt with which it is associated, the movable edge plate being movable under the action of an operator between a protruding position, in which the edge plate is protruding from the nacelle and a locking mechanism is in an unlocked position, and a retracted position, in which the edge plate is immobilized within the nacelle by the bolt and the action of the locking of a locking mechanism.

Abstract: An aircraft landing gear longitudinal force control system for an aircraft having landing gears with braking and/or driving wheel(s). The system includes an error-based force controller having feedback for minimising any error between the demanded force and the actual force achieved by the force control system. The feedback may be derived from force sensors on the landing gear for direct measurement of the landing gear longitudinal force. The force control system may include an aircraft level landing gear total force controller and/or a landing gear level force controller for each actuated landing gear.

Abstract: An aircraft turbojet engine nacelle comprising an air intake assembly of substantially annular shape, the air intake assembly comprising an external wall and an internal wall which are connected to one another upstream by an air intake lip and downstream by an annular rear structure. The annular rear structure comprises, arranged concentrically, one or more monolithic panels forming a first annular zone and comprising one or more hollow casings forming at least a second annular zone, and at least one connecting ring which provides the connection with at least one of the external and internal walls. The annular rear structure thus has increased structural mechanical strength.

Abstract: In an aircraft duct formed with pipes connected in pairs via connectors in which the pipes are mounted with the possibility of axial displacement, there exists a risk that a pipe of the duct, with a dimension greater that the dimension of the nominal pipe, is mounted instead and in place of the latter. In this case, the wrongly mounted pipe would risk not having sufficient clearance in axial translation. In order to solve this problem, it is disclosed to equip one of the relevant connectors with an obstacle limiting the travel of the nominal pipe and preventing the mounting of a pipe with a greater dimension belonging to the duct. A method for assembling an aircraft portion is also proposed, in order to benefit from the particularities of the duct.

Abstract: A method for producing, in a composite material, a component that has a re-entrant angle, includes stacking layers of fibers which have been pre-impregnated with a resin so as to obtain a preform and placing the preform in a tooling fixture in order to subject it to a polymerization cycle including a temperature cycle, with a temperature-increase phase and at least one soak at which the temperature is maintained, and a pressure cycle on the outside of the tooling fixture with a pressure-increase phase and a pressure-hold phase, with the layers of pre-impregnated fibers being able to slip against one another when the temperature of the temperature cycle is equal to or higher than a threshold temperature Tf dependent on the resin. The temperature-increase phase includes a soak at a temperature higher than or equal to Tf, the soak beginning before the end of the pressure-increase phase.

Abstract: An activation device comprising a computation unit configured to compute a stall margin of the aircraft, an information reception unit configured to receive information indicating if an automatic angle-of-attack protection system of the aircraft is active or inactive, and an activation unit configured to activate the display of the stall margin indicator only if the automatic angle-of-attack protection system is inactive.

Abstract: In order to assist fitting of doors to the landing gear housing and adjusting their position, an aircraft nose is provided comprising a connecting frame between the landing gear housing and the outer skin of the fuselage, the connecting frame extending around an opening in the outer skin and comprising a skirt bearing against the outer skin of the fuselage and attached thereto, the skirt defining a passage for landing gear which is configured to be closed off by doors when the landing gear are in a closed position, and supporting members extending between the fuselage and the doors.

Abstract: A method and a system for the detection and passivation of an electric arc on at least one connecting element of an electrical device. The system comprises an acoustic acquisition channel configured for the acquisition of acoustic signals emitted by the connecting element, an electric acquisition channel configured for the acquisition of electric signals which are representative of the electric current intensities supplying the connecting element, and a correlator coupled to the acoustic and electric acquisition channels, configured for the evaluation of a correlation between the acoustic and electric signals and for the tripping of an appropriate cut-off signal for the interruption of an electric circuit relative to the connecting element, where the correlation is representative of the initiation of an electric arc.

Abstract: A pilot assistance device includes information sources for determining automatically, in real time, a current vertical load factor of the aircraft, a computation unit for computing automatically, in real time, a flight director value using the current vertical load factor and a target vertical load factor representing a vertical load factor desired for the aircraft in the parabolic flight, the flight director value being computed in such a way as to be equal to a reference value when the current vertical load factor becomes equal to the target vertical load factor, and a display unit for presenting automatically, in real time, on a load factor scale, displayed on a screen of the cockpit of the aircraft, an indicator representative of the flight director value, computed by the computation unit, and an indicator indicating the reference value.

Abstract: A communication system installed in an aircraft, the system comprising a transmitter configured to transmit audio data signals to a ground recording station provided with memories for the recording of the data, at least one audio assembly per pilot of the aircraft for transmitting and receiving audio data signals, a CVR recorder and an audio management unit connected to each audio assembly, to the CVR recorder and to the transmitter, the unit being configured to transfer the audio signals received or transmitted by an audio assembly to the transmitter and to the CVR recorder. Each audio assembly comprises an in-use detection system connected to the transmitter and configured to transmit to the transmitter a signal representative of the in-use state of the audio assembly. The transmitter transmits the audio data signals received from the management unit to the ground recording station on reception of the signal.

Abstract: A process for direct fabrication of a part at a predetermined structural position. The process comprises: a) scanning, via a three-dimensional scanner, the structure in the region of the predetermined position; b) comparing a virtual surface mesh of the predetermined position with a real surface mesh of the predetermined position, the real surface mesh calculated based on data obtained from the scanning; c) determining the gaps between the two meshes; d) calculating the data for modeling an inserted part, the dimensions of which fill up the determined gaps, to obtain an inserted part model; e) merging of a virtual model of a part, linked with the predetermined position, with the inserted part model, to obtain a model adjusted to the geometry of the structure in the region of the predetermined position; f) fabricating, by material deposition, an adjusted part at the predetermined position based on the adjusted model.

Abstract: An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis said assembly comprising a blocking device. The blocking device comprising a screw with a first cylindrical portion which is screwed into an extension of the second sleeve and against which the second end of the articulation spindle can come to press, and a second portion, in the extension of the first portion, with a smaller cross section than said first cylindrical portion, a locking washer which is interposed between the second portion of the screw and the extension of the second sleeve in a locked position, and a longilinear element which passes through the screw and the second sleeve in a locked state.

Abstract: A method for locating external surface impacts on a body. The steps are: modeling the body in a control unit first database to obtain a virtual body model in a virtual system of reference axes; modeling, in a second database, a plurality of clouds of points in the virtual system, each cloud defining an inspection zone representing an external surface portion; selecting an inspection zone; transferring the coordinates of each point of the first and second databases to a geographic system of reference axes; determining geographic coordinates of an initial position of a range finder equipped flying drone communicating with the processing unit; calculating a drone flight plan to scan the selected inspection zone; creating a 3D meshing of the scanned inspection zone; detecting the impacts by comparing the 3D meshing and the virtual aircraft model and calculating the coordinates of each impact in the geographic and virtual systems.

Abstract: A device and a method for cleaning a hydraulic control circuit such as the hydraulic circuit serving to control a hydraulic element, for example, a cylinder/damper assembly used for controlling the angle of an aircraft landing gear assembly and providing shock absorption on landing. The device comprises a cleaning circuit comprising a filter that is connected to the control circuit instead of the controlled element.

Abstract: A method for producing a reinforcement member of composite material. The method includes producing a planar preform by stacking sheets of pre-impregnated fibers, heating the preform, and deforming the preform on a mold surmounted by an upper die whose shape confirms to a central portion of the reinforcement member to be obtained. The reinforcement member wings are in contact with the mold at two opposite lateral sides of the upper die after deformation. The deformed preform is also baked. Prior to deformation of the preform, a coating is applied promoting a sliding between the preform and the mold during the deformation. The coating comprises two tear-off strips superimposed on each other. A first tear-off strip is in the form of a pre-impregnated material in contact with the preform and a second tear-off strip is in the form of a dry material superimposed on the first tear-off strip.

Abstract: A method of braking left and right landing gear wheels on respective left and right sides of an aircraft. A desired left braking parameter (L) is received for the left wheel and a desired right braking parameter (R) is received for the right wheel. The left wheel is braked with a reduced left braking parameter (L?) which is less than the desired left braking parameter (L), and the right wheel is braked with a reduced right braking parameter (R?) which is less than the desired right braking parameter (R). A difference between the braking parameters is maintained so that L??R?=L?R.

Abstract: A machine tool adapted to perform operations, for example, machining, on a surface of a part of large size is provided. The machine tool comprises a longitudinal rail and a transverse arm, orthogonal to the longitudinal rail, slidingly fastened at a first end to the longitudinal rail. A second end of the transverse arm is provided with a unit comprising a holding device enabling the unit to be held in position on the part during an operation. The transverse arm bearing a tool is thus precisely positioned on the part on which the operations are carried out.

Abstract: An aircraft fuselage comprising a structure, a skin connected to the structure and forming a barrier between the interior and the exterior of the fuselage, an external coating being plated or placed against said skin, wherein the external coating comprises a thermal insulator that covers the fuselage at least in part and has at least one foam insulating layer. The external coating comprises a plurality of juxtaposed panels adhesively bonded to the fuselage and/or secured to the fuselage by mechanical fixings.

Abstract: A method of manufacturing a plurality of reinforcing element preforms, involving the steps of: positioning reinforcing elements on the external surface of a die; assembling the reinforcing elements thus positioned with one another so as to form a textile sleeve with a longitudinal axis and surrounding the die; moving the sleeve longitudinally toward a multi-cavity mandrel having an elongate overall shape, the multi-cavity mandrel having on its external surface a plurality of longitudinal cavities which are distributed, when viewed in cross section, around the periphery of the external surface; forming the sleeve on the plurality of peripheral cavities so that the sleeve conforms to the shape of the multi-cavity mandrel and thus adopts the shape of a set of reinforcing element preforms.