Abstract: A method and system for configuring functionalities of an aircraft cockpit. The configuration system includes at least one processing unit to acquire profiles, to determine at least one combination of functionalities corresponding to the acquired profiles, based on a mapping table, and to activate at least the determined combination of functionalities. The configuration system makes it possible to adapt the functionalities of the cockpit of the aircraft to the profiles.

Abstract: The present disclosure relates to a method for servicing an aircraft by a ground service unit. The method comprises reading a wireless parameter signal from a transponder at the aircraft, decoding the wireless parameter signal to derive at least one aircraft parameter of a water supply system and/or a waste system of the aircraft, moving a servicing equipment interface to a service panel of the aircraft, connecting the servicing equipment interface to a coupling at the service panel, servicing the aircraft via the servicing equipment interface corresponding to the at least one aircraft parameter, and writing a service parameter into the transponder at the aircraft.

Abstract: An electrical connector for connecting electrical conductors in an aircraft includes a pin having a first contact surface and a socket to receive the pin. The socket has a second contact surface contacting a first contact surface of the pin when the pin is in the socket. A securing part is positioned to apply a contact or clamping force pressing the contact surfaces against each other. The securing part includes a shape memory alloy to exist in a martensite an austenite phase depending on temperature of the securing part, wherein the securing part assumes a first pre-set shape when the temperature is below a first temperature threshold, and a second pre-set shape when the temperature is above a second temperature threshold higher than the first temperature threshold, wherein the contact or clamping force applied by the securing part in the second pre-set shape is greater than in the first pre-set shape.

Abstract: A heated leading-edge structure for an aircraft includes a leading-edge panel having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface, a rear panel arranged at least partially arranged at a distance to the inner surface, a closed chamber inside the leading-edge structure, a heating device attached inside the chamber, and an air conveying device in fluid communication with the heating device. The air conveying device is configured to convey air from inside the chamber through the heating device to be heated and returned to the chamber, such that a circulating flow of heated air is created inside the chamber.

Abstract: A hydraulic brake system for activating the wheel brakes of an aircraft landing gear assembly includes a hydraulic fluid supply line and an associated return line. There is a valve which separates a source of hydraulic fluid from a portion of the return line and an associated leak path associated with the valve that in use maintains the pressure and/or volume of hydraulic fluid in the portion of the return line above a minimum acceptable level. The leak path may be provided by a hole drilled in a part (e.g. the poppet) of a non-return check valve.

Abstract: A propulsion assembly having a combustion chamber and a turbine, a nacelle with a front cowl facing the turbine, with a window passing through it, and a rear cowl to the rear of the turbine, a fire barrier between the front cowl and the rear cowl, a dihydrogen supply pipe meandering from the inside of the rear cowl, then in a sealed manner through the fire barrier, then through the window as far as the combustion chamber, wherein the supply pipe has an intermediate section between the fire barrier and the window, and a plate fastened in a sealed manner to the intermediate section and fastened in a sealed manner to the front cowl around the window.

Abstract: An assembly including a wing with a pressure-side panel and a suction-side panel through which two bores pass, an engine pylon including a blade with three bores and two fastening lugs, each of which has a sixth bore, two first shackles fastened between the blade and the suction-side panel, two second shackles fastened between the blade and the suction-side panel and two fittings, which are fastened beneath the pressure-side panel and each have a female clevis for housing a fastening lug therein.

Abstract: An engine pylon has a structure for fastening an aircraft engine beneath a wing and has two lateral faces. The structure has a tunnel laterally passing through it, between and through the lateral faces, and the engine pylon has a spreader housed in the tunnel and fastened in an articulated manner to each lateral face. A first end of the spreader has a first bore. A second end of the spreader has two second bores each forming a connection point with the engine. A rod is fastened in an articulated manner to the first bore and has two third bores each forming a connection point with the engine. Such an engine pylon has the ability to attach the engine, with reduced vertical bulk and with less drag.

Abstract: A propulsion assembly for an aircraft, having a turbomachine, a pylon, and a device for reacting thrust forces having a main fitting, a spreader pivoting on the main fitting and having an opening, two rods articulated to the turbomachine and to the spreader, a secondary fitting fastened beneath the pylon and having a secondary female clevis constituted of two secondary arms passed through by holes of oblong shape and aligned along a secondary axis (R2), wherein the spreader is housed in the secondary female clevis of the secondary fitting, wherein the opening is coaxial with the secondary axis (R2), and a backup connection pin inserted with a tight fit into the opening and with clearance into the holes. Also an aircraft with such a propulsion assembly.

Abstract: An acoustic panel including first and second cellular structures, the first cellular structure including a set-back portion to form a recess dimensioned to accommodate the second cellular structure such that first faces of the first and second cellular structures, in contact with a first, acoustically resistive layer, are coplanar and that first edge faces of the first and second cellular structures are coplanar when the second edge face of the second cellular structure is in contact with the set-back portion. By virtue of the set-back portion, the first and second cellular structures are positioned correctly with respect to one another, thus contributing to an optimization of the acoustic treatment.

Abstract: A method and a system for stripping a part which includes visualizing a zone to be stripped on a screen using a camera, aligning a center of the zone to be stripped with a pattern overlaid on the screen, defining a stripping dimension around the center of the zone to be stripped and controlling a laser source to have the laser source strip the zone to be stripped within that dimension. Such a method makes it possible to correctly visualize the positioning of the laser source with respect to the zone to be stripped before the stripping operation.

Abstract: A propulsion assembly for an aircraft having a chassis in the form of a cage with bars, a turbine, a dihydrogen supply pipe winding inside a nacelle as far as the rear of the turbine, with a radial step towards the outside of the nacelle, a rail with a radial step towards the outside of the nacelle, a bypass pipe connected between the two radial steps outside the nacelle, and a protection plate fastened to the bars, and an absorber between the protection plate and the related bar.

Abstract: A temporary pintle support which can attach between upper prongs of a landing gear, and which is arranged to hold pintle pins prior to installation of the landing gear assembly at an aircraft. The pintle support is attached at the landing gear to align the pintle pins with their respective attachment bearings on each of the prongs. The pintle support may be removed once the pintle pins are fully inserted.

Abstract: A variable fairing for covering a hydrogen duct system installation on the outside of an aircraft part, wherein the fairing comprises at least one fairing body to be mounted on the aircraft part, an air inlet and an air outlet and at least one movable closure mechanism configured to open and close a top portion of the fairing.

Abstract: An engine protection cover device for airtight sealing an engine of an aircraft or spacecraft includes an air intake cover being inflatable to correspond to the internal dimension of the air intake for airtight sealing the same, wherein the air intake cover includes an airtight sealable access opening for attaching or passing through an air dryer for drying the air inside the engine. An aircraft or spacecraft is disclosed with such an engine protection cover device.

Abstract: An aircraft wing including a flap system mounted at a leading or trailing edge of the wing and includes at least two movable flap devices spaced apart in a spanwise direction Y from each other, each movable flap device supported by at least one support station and driven about a hinge axis by at least one drive system. The flap system includes a synchronizing torque element connected to the movable flap devices, wherein the synchronizing torque element is configured to transmit a torque between the movable flap devices to actuate a rotational movement of the movable flap devices, and wherein the synchronizing torque element is positioned between the movable flap devices and around an adjacent system or structural component that is also positioned between the movable flap devices.

Abstract: A fastening system to attach a fixture to a monument installed in a passenger cabin including a wall portion of the monument having at least one first fastening element; and a frame having at least one second fastening element and which is configured to cover the fixture, at least in part, in a fastened state. The first and second fastening elements are configured to engage with one another and be movable relative to one another in a pre-assembled state, and to fix one another in the fastened state. The fastened state can be produced in that, in the pre-assembled state, the frame is moved relative to the wall portion in a fastening direction extending at least substantially parallel to a main extension plane of the wall portion. A method for attaching a fixture to a monument provided for installation in a passenger cabin via a fastening system is provided.

Abstract: An aircraft fuselage door with an internal and external panel, and an aircraft fuselage part with the door. The door includes a movable internal panel to be subjected to pressurization and an aerodynamic external panel, the external panel being on an external face of the internal panel by covering the surface of the external face and elastically linked to the internal panel to form an internal free space between them, the internal panel being movable relative to the external panel. The external panel includes a centering piece to ensure a self-centering function of the door allowing the internal panel to move independently with regard to the external panel when the door is in a closed position so a clearance between the periphery of the outer panel and the fuselage can be reduced, thereby reducing drag at the outer surface of the door and improving the aerodynamic performance of the aircraft.

Abstract: A measurement bar includes a sheath, a leading edge having a plurality of cavities, a steady pressure sensor generating first data and an unsteady pressure sensor generating second data in each of the cavities, an electronic circuit including the steady pressure sensor and the unsteady pressure sensor of each of the cavities, a processing unit configured to merge the first data and the second data, and a second communication module configured to transmit the first data, the second data and the merged first data and second data to a user device. Thus, it is possible to monitor unsteady aerodynamic phenomena.

Abstract: A simulation method of simulating correction parameters for aligning a first mating surface of a first section and a second mating surface of a second section of an apparatus or an aircraft airframe, with respect to each other, including obtaining design coordinates of a simulation set of measurement points on the first and second sections, measuring concrete coordinates of some of the measurement points when the first and second mating surfaces are arranged to face each other within a predefined distance range from each other, comparing the design coordinates to the concrete coordinates, and deriving at least one correction parameter from the comparison. An assembly method for assembling a first section and a second section of an apparatus, a corresponding assembly program, a computer-readable data carrier, a computing device and a respective assembly arrangement for assembling a first section and a second section of an apparatus are provided.