Abstract: A spacer element serving to obtain a spacer washer positioned between first and second parts of an assembly. The spacer element includes a body having the same geometry as the spacer washer that is to be obtained and a circular score line whose diameter is equal to the internal diameter of the spacer washer that is to be obtained, this score line being configured to break upon insertion of a shank of a connection element, and a centering pad configured to center the score line with respect to the through-orifices of the first and second parts that are configured to accommodate the shank of a connection element when the centering pad is inserted into one of the through-orifices.

Abstract: A method for producing a label for affixing in a vehicle. The method includes printing of a substrate layer to yield a basic label form; production of an adhesive film with a first adhesive layer; and sticking the adhesive film to the basic label form using a second adhesive layer to produce the label. Also described is a label kit including a basic label form with a printed substrate layer and an adhesive film, wherein the adhesive film is configured to be stuck to a printed side of the substrate layer of the basic label form.

Abstract: A measuring device able to be closely attached to an outer wall of a movable or fixed object located in an air flow. The measuring device comprises a flexible envelope having a cavity provided with an opening orifice. At least one optical fiber is provided in the cavity, the opening orifice of which is closed by the wall on which the envelope is applied. In this way, the fiber is positioned as closely as possible to the wall for which measurements are desired.

Abstract: A cabin lining element for an aircraft cabin which is arranged in the interior of an aircraft fuselage structure, having a fuselage structure side and a cabin side. The cabin lining element comprises an electrically contactable heating lacquer layer at least in regions on its fuselage structure side. A rib is provided for an aircraft fuselage structure, having at least one foot portion on the outer skin facing side and a cabin facing side head portion. The rib comprises an electrically contactable heating lacquer layer at least in regions on a side of the head portion facing the cabin. As a result of the heating lacquer layer, it is possible to omit insulation which otherwise surrounds the rib heads and, as a consequence, to enlarge the width of the cabin.

Abstract: A liner segment for a frame bay of a fuel tank structure includes a liner segment base body adapted to float on fuel in the fuel tank structure, a liner segment side wall extending from the liner segment base body, a multitude of drainage holes arranged in the liner segment base body, and adapted to provide a bidirectional fluid connection from an upper side to a bottom side of the liner segment facing the fuel tank structure, a valve, arranged in a cut out of the liner segment and adapted to provide an unidirectional fluid connection from the bottom side of the liner segment to the upper side of the liner segment, such that the unidirectional fluid connection is blocked in the opposite direction, such that a remaining portion of fuel within the fuel tank structure is reduced.

Abstract: An aircraft system includes a support structure, an aerodynamic component, a first coupling unit and a second coupling unit. The first coupling unit includes a first coupling mechanism movably coupling the aerodynamic component to a first coupling point at the support structure, and a second coupling mechanism coupling the aerodynamic component to a second coupling point at the support structure. The first and second coupling points are spatially separated from each other, wherein the first coupling mechanism and the second coupling mechanism interact with each other to enable a rotational movement of the aerodynamic component with respect to the support structure such that, during the rotational movement of the aerodynamic component, a center of rotation of the aerodynamic component is translated from a neutral position to an adjusted position. The second coupling unit pivotably moves the aerodynamic component about a pivot axis at the support structure.

Abstract: An aircraft braking controller for an aircraft, the aircraft braking controller configured to determine a position of at least a part of a landing gear of the aircraft during retraction of the landing gear into the aircraft, and control braking of a wheel of the landing gear based on the position determined.

Abstract: A method of manufacturing an aerodynamic structure, for example, an aircraft wing tip, is disclosed. The method includes providing an upper cover having a plurality of lugs, providing a lower cover having a plurality of lugs, measuring the distance between a lug on the upper cover and corresponding lug on the lower cover, selecting, from the plurality of different sized links, a link suitably sized to correspond to the measured distance between the lug on the upper cover and corresponding lug on the lower cover, connecting the selected link to the lug on the upper cover and corresponding lug on the lower cover; and repeating those steps such that each lug on the upper cover is joined to a corresponding lug on the lower cover.

Abstract: A computer implemented method of determining a tire pressure is disclosed including the steps of receiving data of a recent stable point comprising both a tire gas pressure and a temperature; receiving data of a desired temperature, at which a current pressure is desired to be determined; and determining the current pressure based on the data of the recent stable point and the desired temperature.

Abstract: A wing for an aircraft is disclosed including a fixed wing, a high-lift device and a hold-down arrangement arranged between two supports of the high lift device having a first hold-down element attached to the high-lift device and a second hold-down element attached to the fixed wing. The first hold-down element contacts the second hold-down element when the high-lift device is in a retracted position in which it prevents a trailing edge of the high-lift device from detaching from an upper surface of the fixed wing when the fixed wing deforms in the spanwise direction. One of the hold-down elements is a load-limited hold-down element which comprises a hydraulic element that is configured to allow the high-lift device to move away from the fixed wing when a load acting through the hold-down arrangement exceeds an operational threshold.

Abstract: An aerodynamic control surface assembly includes a structure (2) with an aerodynamic surface (8) and a curved aerodynamic control surface (20) configured to move between an extended (24) and a retracted position (22). The aerodynamic control surface is arranged to deploy through an aperture (18) in the aerodynamic surface and into an oncoming airflow (A). An actuation mechanism (52, 152, 252) coupled to the aerodynamic control surface (20) moves the aerodynamic control surface (20) between extended and retracted positions. The actuation mechanism (52, 152, 252) is configured such that the control surface (20) follows a curved kinematic path (40, 140, 240) as the control surface moves between the extended (24) and retracted positions (22). The actuation mechanism (52, 152, 252) remains fully behind the aerodynamic surface (8) throughout the movement of the aerodynamic control surface (20) between the extended (24) and retracted positions (22).

Abstract: A luggage compartment, for use in a vehicle, having a housing with an inner volume defining a storage space of the luggage compartment and a flap which is attached to the housing with at least one fastening device. The fastening device has a first portion attached to the flap and a second portion, wherein the second portion of the fastening device is releasably coupled to the first portion of the fastening device and attached to an outer surface of a top wall of the housing. Also a cabin component assembly with the luggage compartment and a ceiling panel arranged adjacent to the top wall of the housing of the luggage compartment and an aircraft with the cabin component assembly.

Abstract: A head of a cutting device includes a base configured to be fixed to a machine tool, a cylindrical suction nozzle integral with the base, a connector integral with the base and configured to receive a suction pipe. The suction nozzle is perforated by at least one oblong hole, for example parallel to an axis of the suction nozzle.

Abstract: An apparatus for monitoring the condition of a pneumatic tyre including a pressure sensor(s) to measure an internal pressure within the tyre. A speed sensor(s) measures a rotational speed of the tyre. A controller is configured to receive data from the pressure sensor and the speed sensor and output indications related to a condition of the tyre. The controller determines the output indications by tracking the internal pressure with respect to time during use of the tyre, identifying at least one change in internal tyre pressure in a time interval. The time interval is between a first reference time and a second reference time, the reference times corresponding to points at which the speed sensor indicates different rotational speeds of the tyre. The controller further monitors the pressure change as a function of rotational speed of the tyre to provide an indicator of tyre condition.

Abstract: An aircraft propulsion assembly having an engine, a nacelle positioned around the engine, an annular duct delimited by the engine and the nacelle for a bypass flow of cold air, at least one bifurcation passing through the annular duct for connecting the engine and the nacelle and having a leading edge and a primary structure of a pylon housed in the bifurcation and configured to connect the engine to an aircraft wing. The propulsion assembly has at least one heat exchange device including a plate heat exchanger, having a hexagonal longitudinal section and positioned in the bifurcation. According to one configuration, the heat exchanger is a countercurrent heat exchanger.

Abstract: An aircraft including a floor positioned above a central wing box and in a front fuselage portion positioned in front of the central wing box. The floor includes at least one rail which has at least first and second rail portions and at least one articulation connecting the first and second rail portions and configured to allow a pivoting movement, about a transverse and horizontal pivot pin, between the connected first and second rail portions. By virtue of this articulation, it is possible to integrate the rails into the floor and not to position them on the floor.

Abstract: An aircraft barrier system separating, within an aircraft, a secure area from a passenger cabin of the aircraft, comprises a barrier installed inside the passenger cabin and configured to move between an open position and a closed position, a latch mounted to the barrier, and a locking device comprising a latching clamp configured to lock the latch when the barrier is in the closed position. The aircraft barrier system further comprises a release mechanism configured to move the latching clamp from a locking state locking the latch to an unlocking state releasing the latch, wherein the release mechanism is further configured to delay the moving of the latching clamp from the locking state to the unlocking state. Also, an aircraft area and an aircraft having such aircraft barrier system.

Abstract: A rib foot cleat for sealing around a stringer passing through a rib mouse hole in an aircraft assembly. The rib foot cleat has a body for attaching to a rib at a rib mouse hole and defines a cleat channel configured to be arranged over the stringer. The rib foot cleat also has an injection hole through the cleat body which is in fluid communication with the cleat channel, to allow sealant material to be injected through the injection hole in to the cleat channel for sealing around the stringer.

Abstract: A tire monitoring device configured to be mounted on a wheel and including: a pressure sensor for sensing an inflation pressure of a tire on the wheel; a wireless communication interface configured to receive data indicative of a command to indicate tire pressure, wherein the wireless communication interface is configured to communicate with at least one other tire monitoring device; a storage storing a predetermined pressure value; an indicator configured to provide a first indication and a second indication, wherein the first indication is different from the second indication; and a processing system configured to operate the indicator to provide the first indication or the second indication responsive to receipt of the command to indicate tire pressure, and based at least in part on the inflation pressure and the predetermined pressure value.

Abstract: A bulkhead fitting device configured to sealingly link a conduit and a wall traversed by the conduit. This bulkhead fitting device includes a first ring sealingly linked to the conduit, a second ring having a flat, ring-shaped sealing face configured to be pressed against a contact face of the wall or of an intermediate part linked to the wall, an elastically deformable intermediate annular portion sealingly linking the first and second rings, a holding system configured to press the sealing face against the contact face. This bulkhead fitting device guarantees an optimum seal while enabling the absorption of forces and slight relative movements between the conduit and the wall. The device also helps to limit the propagation of vibration.