Abstract: An aircraft structure part having a stacked arrangement of layers with the layers being one of an at least first doubler and a basic layer of the outer skin of an aircraft fuselage, with the first doubler and the basic layer being bonded by a first intermediate bond film layer to form a step-shaped configuration of the aircraft structure part, wherein the first doubler includes a first fiber prepreg layer, in particular glass fiber prepreg layer, arranged at the perimeter of the first doubler and wherein the first fiber prepreg layer is bonded to the basic layer by at least one first bond-film segment deposited adjacent to the first fiber prepreg layer in a first wedge-shaped element at least partially incorporating the first fiber prepreg layer. A method is disclosed for providing an aircraft structure part and an aircraft fuselage provided with the aircraft structure part.

Abstract: A semi-active noise control system includes a layer configured to be part of an interior panel of an aircraft The layer includes conductive tracks, a driver arrangement, tuned mass dampers, and sensors. Each tuned mass damper has an eigenfrequency that depends on a control signal applied to the tuned mass damper and is connected to the driver arrangement via a conductive track and configured to receive control signals from the driver arrangement. Each sensor is connected to the driver arrangement via a conductive track and is configured to sense vibrations and/or acoustic sounds and send measurement signals to the driver arrangement. The driver arrangement is configured to analyze the measurement signals and to generate and send control signals to the tuned mass dampers such that the eigenfrequency of the tuned mass dampers is matched with the frequency of the vibrations and/or acoustic sounds sensed by the sensors.

Abstract: A switching device includes at least one main contactor, a control power supply and an actuator configured to cause the main contactor to change from an open to a closed state against a force generated by the spring. The contactor has a blade and at least one terminal, the blade being configured to assume a position in contact with the terminal and a position not in contact with the terminal. The switching device includes a detection system configured to determine the contact or non-contact blade position of the main contactor, to generate at least one second signal as a function of the determined blade position of the main contactor and to transmit the second signal to the control power supply. The control power supply is configured to generate a control signal configured to keep the main contactor in the closed state upon reception of the second signal.

Abstract: A fairing attachment system for a wing of an aircraft includes a high lift support structure configured to movably support a high-lift airfoil element of a wing of an aircraft relative to the wing. The system includes a fairing device extending in a lengthwise direction, configured to provide an aerodynamic housing of the high lift support structure when attached to a surface of the wing, and an adjustable attachment element configured to attach the fairing device to the high lift support structure. The adjustable attachment element is longitudinally extending and adjustable in length to compensate for tolerances of the high lift support structure relative to the wing during assembly. An aircraft wing includes the fairing attachment system. The fairing attachment system is used in a method for mounting a fairing device to a wing of an aircraft.

Abstract: An assembly of at least one extinguishing agent tank in the interior of an aircraft strut. The strut has an elongate chamber form extending in a longitudinal direction and includes a plurality of ribs which are spaced apart and arranged in parallel along the strut, each extending orthogonally to the longitudinal direction. The ribs are covered by lateral walls, at least one of the walls comprising a window opening into a space between two consecutive ribs, and via which a spherical extinguishing agent tank is installed in the interior of the strut. The assembly of the tank on the strut includes a frame arranged in the interior of the strut, facing the window and secured on each of the two consecutive ribs. The frame forms a support area on which the tank is supported. A system locks the extinguishing agent tank on the frame.

Abstract: A duct stringer assembly with a bulkhead. The duct stringer assembly has duct walls providing a duct with a closed cross-section. The duct is adapted to transport fluid. A bulkhead is in the duct, and the bulkhead is adapted to block the flow of fluid along the duct. The bulkhead has a bulkhead body, and a gasket sealing a gap between the bulkhead body and the duct walls.

Abstract: A method for mounting a vortex generator on an aerodynamic panel of an aircraft, including, before the step of assembling the vortex generator and the aerodynamic panel, a step of installing at least one shim interposed between the base of the vortex generator and the aerodynamic panel, the shim including a first face, oriented towards the aerodynamic panel during operation, that is shaped like the inner surface of the aerodynamic panel, and a second face, oriented towards the base during operation, that is shaped like the upper face of the arm of the base. This solution makes it possible to manufacture the vortex generator without taking into account the curvature of the aerodynamic panel. An aircraft is provided including at least one vortex generator mounted in this way.

Abstract: A wing for an aircraft includes a leading edge, a trailing edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create a wing box with the upper skin and the lower skin, and at least one droop nose at the leading edge, wherein the at least one droop nose is coupled with a forward end of a hinge arm that extends in a chordwise direction, and wherein a rearward end of the hinge arm is swivably supported directly at or in the wing box.

Abstract: A slat arrangement for a wing of an aircraft. The arrangement has a movable leading-edge slat and a connection section. The leading-edge slat includes a slat leading edge and a slat trailing edge. The connection section includes a receiving opening for receiving the slat trailing edge. The connection section includes an overhang having a free end. The slat trailing edge is configured to be translated under the overhang. A trailing region of the slat is configured to be elastically deformed by the overhang when the slat trailing edge is moved into the receiving opening.

Abstract: An aircraft having a fixed structure, an engine pylon, and a cowling system, a slider bearing a rear cowl and able to move in translation from an advanced position to a retracted position, a displacement system having, on either side of a median plane of the engine pylon, a guide as one with the fixed structure, a sliding element as one with the slider and sliding along each guide disposed on the same side, and a support as one with the fixed structure and having a blade parallel to the translation direction and on which a surface parallel to the translation direction of the slider rests. The presence of the mobile cowl ensures, inter alia, easy access to the inside of the engine pylon and to the systems that are housed therein.

Abstract: A system for installing a self-supporting truss structure having interconnected truss elements on an aircraft fuselage. The truss structure has radially outer closed truss nodes and radially inner releasable connecting nodes. The installation system has a carrying device, movable on a fuselage floor and with an upper receptacle, a stand for temporarily holding truss elements in predetermined relative positions, and a movement device, on the upper receptacle, and holding the stand in a settable position relative to the support surface. The stand is further away from the support in installation positions than in a transport position. The installation system is configured, with the stand in the transport position, to move the carrying device into a predetermined internal fuselage position and to lock it there, to move the stand into a suitable installation position via the movement device, and to lock the at least one lockable connecting node via a drive.

Abstract: A fluid transport device including a first line connector, second line connector and inner line component that fluidly connects the first line connector to the second line connector via respective first and second coupling ends. In a mounted state, an outer line component of the device is attached to the first line connector and to the second line connector, so the outer line component covers the first and second coupling ends. In a demounted state, the outer line component is detached from the first and second line connector, wherein the outer line component is movable relative to the inner line component to uncover the first coupling end or the second coupling end. A method for assembling and disassembling a fluid transport device is also disclosed.

Abstract: An aircraft sub-assembly manufacturing system is arranged over multiple floors of a manufacturing facility. A production line of workstations is provided at locations at both a first floor and a second floor of the facility, each of the workstations being arranged for providing manufacturing steps for the aircraft sub-assembly. Elevator apparatus is arranged to transport the assembled aircraft sub-assembly between the first floor and the second floor of the facility.

Abstract: An aircraft propulsion assembly with at least one ventilation device to cool at least one zone of the propulsion assembly. The ventilation device is regulated and includes at least one ventilation hole emerging in the zone to be cooled, at least one valve movable between a closed position where the valve shuts the ventilation hole and an open position where the valve at least partially frees the ventilation hole, at least one thermoelectric generator to generate an electric current and at least one automatic control to control the position of the valve by using the electrical current generated by the thermoelectric generator. The bleed air flow rate can be adjusted as a function of the cooling needs. An aircraft including at least one such propulsion assembly is disclosed.

Abstract: An assembly having a chassis, two supports with a plate and a guide, a nesting system with a bore, a reservoir containing an extinguishing fluid and with two fastening tabs, two bearing tabs and a peg, and a fastener. The reservoir is able to move in translation between a premounting position in which each fastening and bearing tab rests on a plate and each guide guides the fastening and bearing tabs to align the peg and the bore, and a mounting position in which each fastening tab rests on the plate, the peg is introduced into the bore, the bearing tabs no longer rest on the plates and the fastener fastens each fastening tab to the plate. Such an assembly allows the reservoir to be withdrawn and put in place quickly and easily.

Abstract: A compartment system for a vehicle cabin includes a framework assembly for attachment to a vehicle structure, and a container bin. The framework assembly includes a flat bottom section, a top part and a lateral stiffening element. The bottom section has a rear edge for attachment to the structure and a front edge opposite to the rear edge. The top part is spaced from and parallel to the bottom section front edge. The lateral stiffening element is connected to the top part and the bottom section to create the framework assembly having a front opening between the top part and the bottom section front edge. The container bin has a box-like shape and an open front side. The framework assembly and the container bin are configured to detachably attach the container bin in the framework assembly with the open front side arranged in the framework assembly front opening.

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.