Abstract: A method for producing a three-dimensional preform from reinforcing fibers for producing a component from a fiber-reinforced plastic comprises the steps of introducing at least one layer of fibers having a binder into a draping mold, forming the at least one layer of fibers by at least one forming element which is displaceable along the draping mold, applying an airtight film to the at least one layer of fibers during or directly after the forming, creating a negative pressure in the intermediate space between the airtight film and the draping mold, activating the binder and removing the negative pressure after curing of the binder.

Abstract: An air intake system comprising an air duct suitable for providing airflow to the inside of an aircraft, preferably to an auxiliary power unit; an inlet arranged at one end of the air duct; a skin surrounding the inlet; a plurality of slots arranged on the skin; a driving arrangement, a flap door connected to the driving arrangement, and a plurality of fins connected to the driving means. The driving arrangement is configured for moving the flap door between at least two positions, the positions being a closed position wherein the flap door closes the inlet, and an opened position wherein the flap door is driven away from the closed position. The driving arrangement is also configured for moving the plurality of fins such that the plurality of fins protrudes through the slots.

Abstract: A system for lacquer transfer is disclose having a device for lacquer transfer. The device includes a frame, a transfer roller with a circumferential lateral wall, and a slit nozzle for dispensing lacquer. The slit nozzle is connected to the frame. An outside contact surface of the lateral wall includes several depressions. The transfer roller is mounted rotatably to the frame. The slit nozzle is arranged contactless to or in direct contact with the outside contact surface of the lateral wall for dispensing lacquer into respective depressions in the lateral wall while the transfer roller is rotated. The transfer roller is configured to roll with the outside contact surface on a work surface of a work piece for transferring the lacquer from the depressions to the work surface.

Abstract: A junction of a pylon with an aircraft wing, the pylon including a primary structure extending from front to rear along a longitudinal axis and in the form of a box with a rear face and an upper spar forming an upper face of the box, a longitudinal median plane separating the primary structure into two parts, left and right, the junction comprising a rear attachment system for attaching the pylon to the wing, this system being arranged at the rear of the primary structure, the rear attachment system including a shoe attached beneath the wing, the shoe being connected, via at least one articulated connecting rod, to a fitting attached to the rear face of the pylon by an articulation whose articulation pin, termed the horizontal articulation pin, is perpendicular to the longitudinal median plane, and the shoe being connected to the upper spar via a force reacting system.

Abstract: A method of using solid profile rods instead of the usual filament coils for additive manufacturing methods such as 3D printing for industrial applications such as aircraft manufacturing, and to enable a more rapid production of fiber-composite components. The additive manufacturing device, or the 3D printer which generates the component layer by layer, respectively, comprises a material magazine in which a plurality of profile rods are stored. The profile rods are pre-tailored and are adapted to the component layer by layer. The profile rods, when printing, are successively retrieved from the material magazine and, by way of an infeed installation, guided to the nozzle of the additive manufacturing installation and subsequently applied to the printing bed so as to form the component layer by layer.

Abstract: In order to simplify the kinematics involved in opening an aircraft door, a plurality of mobile stop members is provided at the periphery of the door, these being intended to press against complementary stop arrangement provided on the door frame. A door control device is configured to bring the door from its closed position into a set-back intermediate position by moving it towards the interior of the compartment, and a stop arrangement control device is configured to allow the mobile stop members to be moved, when the door is occupying its set-back intermediate position, from a deployed locking position to a retracted unlocking position, allowing the door to be moved outward through the opening in the fuselage.

Abstract: An aircraft landing gear is disclosed having a first oleo strut include a sleeve portion and a slider portion, the slider portion being slidable within a hydraulic fluid chamber of the sleeve portion, and a second, similar oleo strut. The landing gear also includes a hydraulic fluid balancer having a balance chamber separated into first and second end sections, wherein the hydraulic fluid chamber of the sleeve portion of the first oleo strut is fluidly connected to the first section of the balance chamber and the hydraulic fluid chamber of the sleeve portion of the second oleo strut is fluidly connected to the second section of the balance chamber of the hydraulic fluid balancer.

Abstract: A stowage and removal system is provided for a receiving space for container storage in a vehicle. It has a rail system in a bottom region of the receiving space, on which a transfer plate can be moved and which can assume a storage position and an entry and removal position for the container. The container storage position is provided with its rear wall in a region of the receiving space rear wall. The entry and removal position is provided in the region of a push-in opening, lying opposite the rear wall, for pushing in and removing a container into or from the receiving space.

Abstract: A computer system is provided for processing ultrasonic data of an ultrasonic probe applied to an area of an aircraft component that includes carbon fiber reinforced polymer. C-scan data is obtained and a preliminary mesh is defined over the C-scan data by taking into account the underlying structural or mechanical characteristics of the analyzed component. The mesh is further refined and data gathered for each mesh cell. A heat map is generated based on the mesh.

Abstract: A laminated glazing includes a first and a second glass sheet that are bonded by a first interlayer adhesive layer, a peripheral zone of the laminated glazing being covered by a stepped metal element, the laminated glazing including a heating network of wires and/or a heating electrically conductive layer that is provided with busbars, a plurality of probes and other optional electrical elements that are linked to an electrical power supply via the connector of the laminated glazing, an electrical conductor linking the stepped metal element to a busbar of the heating network of wires and/or of the heating electrically conductive layer; and/or to the cap of the connector of the laminated glazing, which is linked to the ground of the structure for mounting the laminated glazing; and/or to a contact of the connector.

Abstract: A trolley lift for connecting a lower aircraft deck to an upper aircraft deck. The trolley lift comprises a platform configured to accommodate at least one trolley, wherein the platform delimits a lift compartment at the bottom, and a cover which delimits the lift compartment at the top. In particular, on a side facing away from the lift compartment, the cover at least partly forms a floor of the upper aircraft deck. Furthermore, an aircraft area having a trolley lift and an aircraft having a trolley lift and/or an aircraft area are described.

Abstract: An assembly for an aircraft, the assembly including a pylon with a lateral wall pierced by a window, a tank with a neck blocked by a film and carrying a first anchoring arrangement, and a fixing arrangement for fixing at least a part of the tank bearing the neck inside the pylon, a discharge pipe, and a discharge head. The head includes an explosive cartridge and a hole with a second anchoring arrangement in which discharges the discharge pipe. The discharge head is fixed inside the pylon facing the window. The explosive cartridge is designed to generate in the hole a shockwave sufficient to rupture the film. An assembly of this kind enables simple and rapid removal of the tank from and installation thereof inside the pylon.

Abstract: A system for fastening two components is disclosed having a mechanical connection device including two tenons that each extend from an opposite face of an interposed plate, each of the tenons having two appendages forming coupling arms, each appendage being positioned on either side of the tenon. The appendages of one tenon being positioned in a different longitudinal direction than the appendages of the other tenon, each appendage having a coupling component to connect to a device for locking the tenons and two end fittings that each have a slot in which each of the tenons of the connection device is able to be fitted, each appendage protruding out of the slot on either side thereof.

Abstract: A method for producing a frame component for a door frame structure of an aircraft. A connecting zone is generated on a first and a second assembly surface of a connecting component in each case by generating a surface texture on the assembly surfaces, wherein the connecting component is formed from a metal material. The assembly surfaces of the connecting component are placed against a door frame member and against an attachment member, wherein the door frame member and the attachment member are each formed from a fiber-reinforced thermoplastics material. Furthermore, the connecting component and the door frame member are welded, and the connecting component and the attachment member are welded. A frame component and a door frame structure are also described.

Abstract: An aircraft door, an aircraft region and an aircraft with an aircraft door. The aircraft door through which passengers enter and leave the aircraft and is held towards the outer side by stops and is locked exclusively on a hinge side opposite the stops. Also, an aircraft region and an aircraft with such an aircraft door.

Abstract: A method is proposed for installing system components in a portion of an aircraft fuselage. The method provides at least one planar structural arrangement to be secured on or in the aircraft fuselage, secures system components on the structural arrangement, couples system lines to the system components and arranges the system lines on the structural arrangement. The method includes positioning of the structural arrangement with the system components and system lines arranged thereon at a designated installation location of the structural arrangement, and mechanical coupling of the structural arrangement to the aircraft fuselage.

Abstract: A cooling and gas dehumidifying system comprising a cooling circuit in which a thermal fluid is circulated. The system further comprises a cooling arrangement arranged in the cooling circuit and configured to cool the thermal fluid flowing therethrough. A consumer gives up heat energy to the thermal fluid flowing through the cooling circuit. A gas dehumidifier having a heat exchanger arrangement is configured to be thermally coupled in a gas dehumidifying operating state with the thermal fluid flowing through the cooling circuit downstream of the cooling arrangement and having a first temperature, and thereby give up heat energy to the thermal fluid, and to be thermally coupled in a de-icing operating state with the thermal fluid flowing through the cooling circuit downstream of the consumer and having a second temperature, and thereby absorb heat energy from the thermal fluid, the second temperature being higher than the first temperature.

Abstract: A dynamic runway illumination system, including a light source having an addressable light beam direction, and a control unit configured to receive aircraft attitude information and the orientation of the runway selected for takeoff or landing, obtain horizontal and vertical axes, the horizontal axis being collinear with the takeoff or landing longitudinal direction, determine the actual and the reference aircraft trajectories, obtain the actual and the reference vertical approach angles, and the actual horizontal approach angle, and actuate onto the light source to perform an angular movement in the light beam direction of an absolute value of the actual vertical approach angle minus the absolute value of the reference vertical approach angle about the vertical axis, and an angular movement of an absolute value of the actual horizontal approach angle about the horizontal axis, to vertically and horizontally align the beam of the light source towards the runway direction.

Abstract: A propulsion assembly including a primary structure of a pylon having right and left extensions projecting with respect to right and left lateral panels of the primary structure and also right and left brackets, each having a first flank connected to the right or left lateral panel of the primary structure and a second flank pressed against the right or left extension, a front engine mount having first and second links, each connected to an engine and directly to the front transverse reinforcement by a first or second reinforcement connection pin passing through the right or left extension and the second flank of the right or left bracket.

Abstract: A propulsion assembly for an aircraft, comprising a pylon to be secured below a wing of the aircraft and having a front face and a lower face, and a turbomachine comprising, from upstream to downstream in a direction of a flow of air passing through the turbomachine during operation, a fan and an engine driving the fan. The fan is faired by a fan casing and the engine is faired, from upstream to downstream, by an intermediate casing and an engine casing, the intermediate casing having a hub and an outer ring extending the fan casing, the ring being spaced apart radially from the hub and secured to the latter by arms extending in an air duct. The propulsion assembly comprises a front engine attachment secured between the pylon front face and the hub and a rear engine attachment secured between the pylon lower face and the engine casing.