Abstract: A door arrangement for an aircraft comprising a door designed to close an aperture in an outer skin of the aircraft, and a articulated arm which is fixed by a first end to the door and which is designed to move the door in at least two translational directions and at least two rotational directions. An aircraft area with this door arrangement and an aircraft having such an aircraft area are furthermore provided. The aircraft area comprises a door aperture arranged in an outer skin of an aircraft, and a door arrangement. Here the door of the door arrangement may be designed to close the door aperture from an inside of the outer skin, and the articulated arm of the door arrangement may be fixed to the aircraft area.

Abstract: An aircraft rear engine attachment connecting a primary structure of a pylon and an engine of an aircraft. The rear engine attachment includes first and second rods, each of them including at least two parts, a first part including at least one support orifice, accommodating a support link bar, configured to connect the rod directly or indirectly to the primary structure, at least one second part including at least one engine orifice, accommodating an engine link bar, configured to connect the rod directly or indirectly to the engine, and also detachable link elements for connecting the first and second parts oriented parallel to the direction of the rod.

Abstract: An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises a stop plate, connected by at least one removable link to the primary structure, which closes the first hole, at least in part.

Abstract: An indicator generating method for generating an indicator which is suitable for maintenance prediction of a water heating system is proposed. A power state indication device generates a high power consumption signal if a heating device of the water heating system is activated. The time duration of the activation is such an indicator, if no water flow is present. Furthermore, the time interval between subsequent activations is such an indicator. A predictive maintenance method processes these condition-based indicators and determines a remaining useful lifetime according to a predictive maintenance model. The predictive maintenance device outputs a maintenance signal indicating required maintenance, if the remaining useful lifetime drops below a predetermined threshold. The methods may be performed by water heating systems or beverage makers.

Abstract: A front engine attachment system for an aircraft engine, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam has front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate. Each link-rod system is fastened to the intermediate plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.

Abstract: An aircraft air conditioning system comprising an ambient air line, for ambient air to flow through, connected to supply ambient air to a mixer of the aircraft air conditioning system. An ambient air compressor is arranged in the ambient air line for compressing the ambient air flowing there through. A refrigerating apparatus comprises a refrigerant circuit for a refrigerant to flow through, including a refrigerant compressor arranged in the refrigerant circuit. The refrigerant circuit is coupled thermally to the ambient air line to transfer heat from the ambient air to the refrigerant before the ambient air is supplied to the mixer. A cabin exhaust air turbine is connected to a cabin exhaust air line, is coupled to the ambient air compressor arranged in the ambient air line, and is configured to expand the cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor.

Abstract: An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud provided with at least one acoustic panel, an air intake lip forming a leading edge of the nacelle, the protection system comprising a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the acoustic panel or panels.

Abstract: A stowage and removal system for an accommodation space for storing rollable containers in a vehicle is provided. It preferably has a rail system in the floor region of the accommodation space, on which rail system a transfer plate is movable, which transfer plate can assume a storage position and an insertion and removal position for the container. The storage position of the container is provided with its rear wall in the region of the rear wall of the accommodation space. The insertion and removal position is provided in the region of an insertion opening, arranged oppositely in relation to the rear wall, for the insertion and removal of a container into the accommodation space.

Abstract: A method for forming fiber composite preforms, the preform (1) include a web (2), a flange (3) and a bent part (2.1), and the method includes: laying-up a laminate (4) onto a tooling (5), the laminate (4) comprising lateral and transverse edges (4.1, 4.2) and the tooling (5) comprising a male part (7) comprising a surface (7.1) and a lateral wall (7.2), the web (2) being configured to be located over the surface (7.1) of the male part (7) and the flange (3) being configured to be located over the lateral wall (7.2) of the male part (7); forming the preform (1) over the male part (7); clamping the lateral edges (4.2) of the laminate (4) to the tooling (5) such that the web (2) and the flange (3) of the laid-up laminate (4) are kept under tensional loads, and bending a longitudinal portion of the male part (7).

Abstract: A boom for an electrical harness, including a straight bar extending in a longitudinal direction, and several supports distributed along and attached to the bar, to which supports at least one electrical harness is connected in operation. The bar includes at least two parts configured to slide relative to one another in the longitudinal direction so that a length of the bar can be adjusted.

Abstract: An internal structure of a primary exhaust duct of a turbomachine, which has a primary wall allowing air to pass through orifices and forming an internal surface of the primary exhaust duct, an interior skin arranged inside the primary wall, and at least one separator of which a first edge region is attached to the interior skin and which has two geometries. A change from the first geometry to the second takes place when the temperature of the separator exceeds a first temperature, and the change from the second to the first takes place when the temperature of the separator drops below a second temperature. The coefficient of expansion of the separator is greater than that of the interior skin. The variation in the geometry of the separators depending on the temperature of the engine eases assembly at ambient temperature due to the compression of the separators.

Abstract: A drive system 20, 20? for rotating a wheel 11, 11? of an aircraft landing gear 10, 10?, is disclosed having a drive element 24, 24?, a motor 21, 21? operable to rotate the drive element, and a driven gear 25, 25? adapted to be attached to the wheel. The drive system has a drive configuration in which the drive element is capable of meshing with the driven gear to drive the driven gear, wherein the drive system further comprises a transmission error measurement apparatus 30, 40, the apparatus configured to obtain, over time, measurement data of one or more characteristics of the drive system when in the drive configuration, the measurement data providing an indication of a transmission error between a torque commanded by the motor and a resulting torque at the driven gear. An aircraft 100 and a method of providing an indication of a transmission error in a drive system is disclosed.

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a pylon configured to be fastened beneath a wing of the aircraft, a turbomachine having a longitudinal direction, a median plane and a transverse plane, and a nacelle surrounding the turbomachine and having a load support disposed in the top part of the nacelle. The load support has a structural part fastened to the pylon and an aerodynamic part capping the structural part. The aerodynamic part has, at the front, a front part fastened to the structural part and, at the rear, a rear part fastened to the pylon. Separating the load support into two parts makes it possible to reduce the movements of the aerodynamic part capping the structural part of the load support.

Abstract: Seal member arrangements having at least one seal plate are disposed over stringer receiving recesses in ribs of an aircraft. A tool for locating a seal member arrangement over a stringer-receiving recess in a rib of an aircraft assembly. The tool system has a holder configured to hold the seal member arrangement over the recess. A biasing arrangement is configured to act on the holder to bias the seal member arrangement into an aligned position with a stringer received in the recess. A fixing arrangement is configured to act on the seal member arrangement to fix the seal member arrangement in the aligned position. A sealing kit, an aircraft assembly, a method of fixing a seal member arrangement over a stringer-receiving recess in a rib of an aircraft are also disclosed.

Abstract: A device for lacquer transfer is disclosed having a frame, a nozzle with a dispensing end for dispensing lacquer, and a transfer roller with a circumferential lateral wall, a circumferential outer contact surface of the lateral wall comprises several depressions, wherein the nozzle and the transfer roller are arranged such that lacquer is dispensable from the dispensing end onto the outer contact surface and into the depressions, wherein the transfer roller is configured to roll with the outer contact surface on a work surface of a workpiece for transferring the lacquer from the outer contact surface and from the depressions to the work surface of the workpiece. A first hardening unit is formed as a UV-light unit configured for partially hardening the lacquer in a contactless way by emitting UV-light, the first hardening unit is arranged within an interior space defined by the transfer roller.

Abstract: An overheat detection system for an aircraft, the system comprising a first bleed monitoring computer, BMC1, configured to identify leakages in a pneumatic system, the BMC1 including a first optical controller, a second bleed monitoring computer, BMC2, the BMC2 including a second optical controller, an optical fiber link connecting the first optical controller of the BMC1 and the second optical controller of the BMC2 for communication between the BMC1 and the BCM2 and between the first optical controller and the second optical controller, wherein the first and the second optical controllers are configured to detect overheat of the optical fiber link based on a wavelength shift of a modulated optical signal transmitted through the optical fiber link, and transmit signals to the first BMC1 and the second BMC2 based at least on the detected overheat.

Abstract: A component which is configured to be joined to a further component in a preselected relative orientation is disclosed. The further component has an interface surface and the component is configured to contact the interface surface when joined to the further component. The component includes a surface disposed on a side of the component intended to face the interface surface when the components are joined, a plurality of recesses formed in the surface, and a plurality of spacer elements. Each recess has a preselected orientation relative to the component, the preselected orientation being selected in dependence on the preselected relative orientation. Each spacer element comprises a contact surface configured to contact the interface surface when the components are joined. Each spacer element is disposed in one of the recesses such that the orientation of a given contact surface is defined by the orientation of the corresponding recess.

Abstract: A flow body for a vehicle having a flow surface, as well as a skin system attached to the flow surface is proposed. The skin system has a top layer and a foam arrangement positioned between the flow surface and the top layer, wherein the top layer includes an elastic, surface-like material, wherein the foam arrangement includes a first layer of an elastic, compressible open cell foam, wherein the foam arrangement is bonded to the top layer. The skin system has a static shape in an unloaded state, in which the shape defines an outer surface geometry that directly follows the geometry of the respective flow surface, and the skin system has a deflected shape when the flow body is subjected to turbulent air flow. The deflected shape at least temporarily compresses the foam arrangement.

Abstract: An adjustable fixed structure attachment system 200 for an aircraft wing, the attachment system 200 including a bracket 210 having: a wall 212 for connection to a wing box, a protrusion 214 protruding from the wall 212, and a slot 216 extending through the protrusion 214, wherein the slot 216 has a height and a width, and a bush 220 having a bore 222 extending therethrough for receipt of a pin, wherein the bush 222 is insertable into the slot 216 and dimensioned relative to the slot 216 so that the bush 220 is substantially immovable in a width-wise direction of the slot 216, and is moveable in a height-wise direction of the slot 216 to thereby vary a position of the bush 220 within the slot 216.

Abstract: A system for displaying the state of an aircraft cargo door. The cargo door is configured pivot between a closed position and an open position, the closed and open positions defining a pivoting range. The cargo door is lockable both in the closed position and in the open position. The cargo door is in a regular state when locked in the closed position or the open position. The cargo door is in a warning state when in the pivoting range between the closed position and open position. The cargo door is in a faulty state when unlocked in the closed position or unlocked in the open position or when there is an obstacle in the pivoting range. The cargo door comprises at least one indicator configured to display the respective state of the cargo door, the indicator being detectable from a distance of at least 7.5 m.