Abstract: A device for pretreating an exterior surface of an aircraft coated with an aircraft-specific base material so as to prepare the surface for a final painting with aircraft paint includes a pretreating tool. The pretreating tool has a laser head configured to activate the aircraft-specific base material using a laser. The device also includes a support construction including a robot device and a control unit configured to control and move the laser head over the surface using the robot device.

Abstract: A system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners interrupted by reinforcing frames. At aforementioned interruptions, the stresses experienced by the stiffeners must be transmitted despite the presence of the reinforcing frames. Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the disclosed embodiments include the creation of battens that cover the ends of consecutive sections of a stiffener and the skin of the fuselage, extending under the reinforcing frame in order to join aforementioned two consecutive sections.

Abstract: The present invention provides a structural component for an aircraft or a space craft having an outer skin and a first reinforcing element which runs on the outer skin along a first spatial direction. A second reinforcing element runs over the first reinforcing element in a second spatial direction. A foot element supports the second reinforcing element on the outer skin, the foot element having a feed-through opening in which the first reinforcing element is held in a positive manner. From another point of view, a method is provided for reinforcing an outer skin of an aircraft or space craft, in which a first reinforcing element is attached to the outer skin along a first spatial direction. A foot element having a feed-through opening is attached over the first reinforcing element such that the first reinforcing element is held positively in the feed-through opening. A second reinforcing element is attached to the foot element in a second spatial direction over the first reinforcing element.

Abstract: A device for determining a position of a throttle lever includes position sensors each connected to a primary flight control computer, position sensors each connected to an engine management computer, the position sensors being split into at least three groups of sensors with no common simple failure mode, and at least one interface computer, that includes at least one input to receive measurement information emitted by the computers connected to the position sensors and outputs leading to the engine management computer.

Abstract: An ACARS message communications system including at least one on-board piece of equipment harbouring an application adapted for transmitting and/or receiving ACARS messages, and a router adapted for routing, via a plurality of subnetworks, ACARS messages from and/or to the application. The piece of equipment and the router are connected to an AFDX network and the application is adapted for dynamic registration at the router, via the network, the router only routing the messages if the application is actually registered thereat.

Abstract: A backplane electronic circuit board of an electronic apparatus (10) comprises an interface connector with an external system and two interface boards (22, 23) connected to one another, a first interface board (22) being connected to the said interface connector and a second interface board (23) being intended for the connection of a set of electronic circuit boards of the said electronic apparatus (10). The backplane electronic circuit board (20) comprises reinforcement means (30, 40) installed between the said two interface boards (22, 23). Use in particular in an electronic apparatus on board an aircraft.

Abstract: A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings.

Abstract: An aircraft wheel brake assembly has a housing for attachment to the landing gear of an aircraft, a friction plate in non-rotational sliding engagement with the housing, an actuated plate for non-rotational sliding engagement with an aircraft wheel, an aircraft brake actuator comprising, a first shaft for connection to a drive source, the first shaft defining a first axis, and, a second shaft for connection to, and actuation of, the brake assembly, the second shaft defining a second axis substantially perpendicular to the first axis, in which the first shaft and second shaft are connected in driving engagement by a ball-worm gear.

Abstract: According to an exemplary embodiment of the invention, a storage module is stated that is positioned in a region between two frame elements of an aircraft and that can be moved to a folded-out state. The storage unit forms part of a crew rest compartment in an aircraft.

Abstract: A method of assembling parts to form an aircraft component, in which a first surface of a first part (for example a wing skin) is to be positioned in the assembly adjacent to a second surface of a second part (for example a rib foot). The method comprises the steps of taking measurements of the first part, taking measurements of the second part with a laser, and calculating the size and shape of the space that will be generated when the first and second parts are assembled. A shim of varying thickness in dependence upon the results of the calculating step is manufactured, for example by stereolithography, and the first and second parts are assembled with the shim positioned between the first and second parts, the varying thickness of the shim compensating for a varying spacing of the first and second surfaces.

Abstract: A method for manufacturing pieces of composite material having varied thicknesses is disclosed. The method includes a first stacking stage and a second forming and drying stage. In the second stage, a forming tool, which is adapted to the configuration of the piece, except in the zone affected by the change in thickness, is used. In the first stage, one or more pre-forms of the piece are stacked successively with some cloths having the dimensions needed for producing the change of thickness, some laminates of a peelable material, and some supplementary cloths in such a way that the resulting layers have the thickness needed to be adapted to the forming tool. At the end of the second stage, laminates resulting from the supplementary cloths and laminates of a peelable material are removed.

Abstract: An engine attachment pylon for an aircraft including a rigid structure including a box including an upper spar and a lower spar, connected to each other through two lateral panels. At least one of the upper and lower ends of the web of at least one of the two lateral panels includes at least one assembly cleat projecting sideways from the web towards the outside of the box, and assembled to the spar on which it bears through an attachment mechanism located outside the inner space in the box.

Abstract: This system makes it possible to join a substantially flat base of an element to be fixed to a top plate. It is provided with: at least one hole of elongated shape made in the top plate, a shaft extending substantially perpendicular to the base of the element to be fixed and mounted movable in rotation relative to its longitudinal axis, a fixation head of elongated shape matched to the shape of the hole made in the top plate and disposed on a first side of the base of the element to be fixed, control means for making the shaft pivot around its axis and disposed, relative to the fixation head, on the other side of the base of the element to be fixed.

Abstract: The aircraft includes at least one engine suitable for propelling the aircraft in flight, at least one motor of an undercarriage, and automatic means arranged to cause the aircraft to taxi under drive directly from the engine, while simultaneously using the motor for taxiing, other than during takeoff or landing.

Abstract: A wing arrangement includes, but is not limited to an adjustable flap, which is adjustable between a retracted position and at least one extended position, has at least one fairing element for covering a flap adjustment mechanism and at least one cover element. The fairing element extends downstream at least as far as the flap and has, in a surface facing the flap, a cutout which correlates with an intended adjustment movement of the flap. The cover element is movably arranged with respect to the fairing element and adapted such to cover the cutout in the fairing element in the retracted position of the flap and expose at least part of said cutout in an extended position.

Abstract: The aircraft includes an undercarriage having an upper portion, at least one wheel for running on the ground, and a shock absorber connecting the wheel to the upper portion. The aircraft also includes a motor for driving the wheel, the motor being rigidly fastened to the upper portion.

Abstract: According to the invention, the device (1) comprises means (3) for detecting, during an altitude capture maneuver, the emission of a first type alarm by the anti-collision system (2) and means (4) for controlling the vertical speed of said airplane (AC), after the emission of such an alarm, until the triggering of the capture phase.

Abstract: An aircraft component assembly system for the assembly of an interior component, a pipe or an electric line in an aircraft includes at least one arc-shaped frame element, a connection element that extends between a first and a second end of the frame element, and a fastening apparatus for fastening the interior component, the pipe or the electric line to the frame element or the connection element. The system also includes a first guide device that is provided on the frame element or the connection element and is devised to interact with a second guide device, which is complementary to the first guide device and provided on an aircraft structure, in such a way that the aircraft component assembly system is connectable to the aircraft structure in a manner displaceable relative to the aircraft structure.

Abstract: Sound insulating glazing device for aircrafts, ground or maritime transportation vehicles, buildings, or others, including glazing, a sealing joint in a shape and size corresponding to the edge of the glazing and designed for assembly on said edge, sound insulation, made of at least two materials, a first resilient material and a second material with less resilience than the first, the sound insulation being used against the field of said glazing, between the glazing and the sealing joint. The invention is also for aircrafts that are equipped with at least a glazing device and a soundproofing method for glazing.

Abstract: According to one exemplary embodiment of the invention, a service unit for being installed on a service channel of an aircraft is disclosed, wherein said service unit features a mounting device and a connecting device. These two devices cooperate in such a way that the mounting and the automatic connecting are realized in one step when the service unit is moved into the installation position.