Abstract: The invention relates to a seat assembly for a cabin of a means of transportation, having an aisle which is arranged in the longitudinal direction of the cabin, two mutually spaced cabin walls which are oriented parallel to the aisle at least in some regions and laterally delimit the cabin, two outer passenger seat regions which are separated from one another by the aisle and each of which adjoins one of the two cabin walls, wherein the outer passenger seat regions have at least one row of seats with a respective inner first seat module which faces the aisle, a central second seat module adjoining the first module, and an outer third seat module adjoining the respective cabin wall.

Abstract: An aircraft wing including a leading edge slat and a fixed aerofoil portion. The leading edge slat is moveable between a stowed position and deployed position. In the deployed position a trailing edge of the leading edge slat includes a sealed portion and an unsealed portion. The sealed portion forms a seal with the fixed aerofoil portion and the unsealed portion provides an airflow gap between the leading edge flap and the fixed aerofoil portion. The invention provides substantially the same benefits as a sealed leading edge slat whilst improving stall control behavior in local zones around the unsealed portion.

Abstract: An aircraft comprising a fuselage, first and second wings positioned on either side of the fuselage, wherein each wing includes an inner part connected to the fuselage and an outer part continuing the inner part, the end of each inner part connected to the fuselage having a height greater than half the height of the fuselage and extending over a length greater than or equal to half of a distance separating the nose and the tail of the fuselage.

Abstract: A blind fastener is disclosed having a bolt part, a sleeve part, and a tubular insulating sheath. The bolt part is at least partially received within the sleeve part. A first end of the sheath is retained on the bolt part such that relative axial movement between the first end of the sheath and the bolt part is substantially prevented. The blind fastener is movable between: a pre-installation configuration in which the sleeve part has a first axial position relative to the bolt part and a predetermined section of the sheath is adjacent an outer surface of the sleeve part; and a post-installation configuration in which the sleeve part has a second, different axial position relative to the bolt part and the predetermined section of the sheath is adjacent an inner surface of the sleeve part.

Abstract: The present invention comprises a method for detecting a leak in a vacuum assembly comprising the steps: implementation of a first detection process to identify a leak area, involving the supply of a vacuum assembly which has a plurality of sensors for detecting a parameter, the determination of values of the parameter over time during the evacuation of a cavity of the vacuum assembly, the creation of a value-time curve for each sensor of the vacuum assembly from the values detected for the respective sensors by means of an evaluation unit, the comparison of the value-time curves created with one another and identification of differences depending on the comparison by means of the evaluation unit, and the identification of a leak area in the vacuum assembly depending on the differences determined in the value-time curves and the respective position of the sensor in relation to the vacuum assembly; and implementation of a second detection process following the first detection process to detect the leak w

Abstract: A method of testing an aircraft landing gear is disclosed including: a) generating a test signal with the first tachometer, wherein the first wheel is not rotating during the generation of the test signal; b) receiving the test signal via one of the tachometer output lines; c) issuing a braking command in response to the receipt of the test signal, wherein the braking command is issued via the braking command line which is associated with the one of the tachometer output lines; and d) monitoring a response of the first or second braking system to the braking command to test for a cross-connection between the first and second braking systems. The landing gear includes first and second wheels; a first braking system having a first tachometer mounted to the first wheel and configured to generate a first tachometer signal indicating rotation of the first wheel, and a first brake configured to brake the first wheel.

Abstract: A tire inflation optimization apparatus configured to determine an optimum inflation pressure for a tire installed on an aircraft is disclosed. The apparatus includes a memory and a controller. The memory stores information relating tire gas properties to aircraft schedule parameters and a reference pressure for the tire. The controller is configured to receive future schedule information indicative of a future flight schedule for the aircraft and to determine an optimum inflation pressure for the tire based on the received future schedule information, the stored information relating tire gas properties to aircraft schedule parameters, and the stored reference pressure.

Abstract: A wing (5) including a fixed wing (7), a high-lift device (15) and a hold-down arrangement arranged (27) between two supports (23, 25) of the high lift device (15) having a first hold-down element (29) attached to the high-lift device (15) and a second hold-down element (31) attached to the fixed wing (7). The first hold-down element (29) contacts the second hold-down element (31) when the high-lift device (15) is in a retracted position in which it prevents a trailing edge (22) of the high-lift device (15) from detaching from an upper surface (19) of the fixed wing (7) when the fixed wing (7) deforms in the spanwise direction. One of the hold-down elements (29, 31) is a load-limited hold-down element (32) which transition from a first stable state to a second state when the load acting on the hold-down arrangement (27) exceeds an operational threshold.

Abstract: An aircraft including at least one hydrogen engine, at least one hydrogen supply device including at least one hydrogen tank and at least one item of equipment through which the hydrogen flows and which is positioned between the hydrogen tank and the hydrogen engine. The aircraft includes at least one sealed container sealed from the outside air, in which sealed container the equipment of the hydrogen supply device is positioned. This solution allows a safe hydrogen installation to be obtained using existing equipment.

Abstract: A mold core for producing a component of fiber composite material with a cavity makes a particularly simple and efficient demolding process possible by the mold core extending along a longitudinal axis and in the form of a hybrid core and which includes, viewed in a cross section perpendicular to the longitudinal axis, a first core portion and a second core portion, wherein the first core portion has a thickness that is substantially greater than a thickness of the second core portion. The first core portion is formed from a first material with high stiffness and low coefficient of thermal expansion, and the second core portion is formed from a second material that differs from the first material, and is configured such that, under predetermined conditions, its form changes in a predetermined manner such that removal of the mold core from a cavity in the cured component is made easier.

Abstract: A pipe support block for an aircraft fluid system is disclosed in which the pipe support block is arranged to support a pipe on a structural member, such as a bracket. The pipe support has a first part and a second part which together form a collar. The collar has a pipe receiving bore and is configured to support a fluid pipe on the structural member. First and second fastener holes extend through both the first part and the second part. The first and second fastener holes are each arranged to receive a fastener to fasten the first and second parts to each other and to the structural member.

Abstract: A bypass turbofan with a nacelle delimiting a stream and including a cowl mobile in translation between an advanced position in which a window is open between the stream and the exterior, transmission systems, each of which includes at least one arm mobile in rotation between retracted and deployed positions across the stream, in which each transmission system is mobile in translation between advanced and retracted positions, for each arm, a flexible veil fastened to the arm and alternately occupying a folded or unfolded position, and, for each transmission system, an actuator configured to move the mobile cowl, the transmission system and each arm.

Abstract: A mount for a double-walled vessel includes a first support to support the mount against an outer wall of the double-walled vessel, a second support to support the mount against an inner wall of the double-walled vessel, and a flexible member connecting the first support and the second support. The first support and can be arranged at a first end of the flexible member and the second support can be arranged at a second end of the flexible member opposite to the first end. Further described are a vessel including at least one such mount as well as a vehicle including such vessel.

Abstract: An aircraft system for an aircraft, the aircraft system including a controller configured, during a take-off procedure, to receive a first signal indicative of a climb rate of the aircraft and, when the controller determines, on the basis of the first signal, that the climb rate of the aircraft is positive, cause a retraction alert to be issued to a flight crew of the aircraft, the retraction alert indicative that a landing gear of the aircraft is retractable.

Abstract: A connection assembly between two portions of a supply line for a cryogenic fluid, the assembly including a male nozzle arranged to be at least partially inserted into a female nozzle together forming a tight mechanical link, over a distance of a few centimeters, a thermal insulation chamber for each of the two line portions and an additional thermal insulation chamber to thermally insulate the connection zone of the two line portions, and an expansion chamber for the cryogenic fluid that is configured to be linked to a cryogenic fluid sensor, arranged about the connection zone of the two line portions. This enables two cryogenic fluid line portions to be connected without requiring one portion to be inserted into the other portion over a significant length, thereby enhancing mechanical flexibility and obviating the need for significant free space about the connection assembly to assemble and disassemble the assembly.

Abstract: A spark containment cap forms a sealed cavity around an end of a fastener protruding from a structure. The cap has a cap body defining an air cavity enclosing the end of the fastener. The cap body includes an annular base (210) terminating at a base rim (211) surrounding an opening into the air cavity. An annular skirt of the cap provides an annular sealing volume extending around the base rim to receive an annular bead of a curable sealing material around the opening into the cavity to provide a seal between the cap body and the structure to seal a volume of gas within the cavity. The cap body includes a cap upper to receive the end of the fastener. The cap upper (220) is positionable so that an axis of the cap upper is offset from an axis of the annular skirt (230).

Abstract: A spark containment cap for forming a sealed cavity around an end of a fastener protruding from a structure is disclosed having a cap body with an annular base terminating at a rim which surrounds an opening into an air cavity arranged to enclose the end of the fastener. An annular sealing volume extends around the rim arranged to receive an annular bead of a curable sealing material around the opening into the cavity to provide a seal between the cap body and the structure to seal a volume of gas within the cavity. An engaging feature is configured to engage with the end of the fastener to prevent rotation of the fastener relative to the cap when the end of the fastener is received by the cap. A fastening system, a joint, an aircraft and a method of securing a fastener and a spark containment cap to a structure are also disclosed.

Abstract: A flexible pillar for a variable geometry flight control surface including upper skin and lower skins includes an elongate shape elastic element having an and at least a first end and a second end. The flexible pillar can be disposed between the upper skin and the lower skin so the elastic element can be fixed to the upper skin at the first end of the flexible pillar and fixed to the lower skin at the second end of the flexible pillar. The flexible pillar has a rigidity along the longitudinal axis of the flexible pillar that is greater than a rigidity of the flexible pillar in shear along a transverse axis of the flexible pillar, the flexible pillar making it possible to obtain a support having a longitudinal direction and able to transmit forces between its ends without, or with little, deformation longitudinally and to be easily deformed in a transverse direction.

Abstract: Restricting commands for a tire monitoring device including controlling entry into a configuration mode and restricting operation based on detection of an abnormal command pattern. The method includes, at a tire monitoring device: receiving a configuration request from a first device for the tire monitoring device to operate in a configuration mode, the configuration request provided using a first wireless communication protocol; responsive to receipt of the configuration request, initiating communication using a second wireless communication protocol; establishing successful communication using the second wireless protocol; and entering the configuration mode responsive to establishing successful communication using the second wireless communication protocol.

Abstract: An induction heated tool system for receiving and heating polymer-fiber components from a starting temperature to a target temperature includes a tool part having a receiving cutout, the tool part formed from a thermally dimensionally stable material so it has a coefficient of thermal longitudinal expansion less than 10×10?6 K?1, or less than 5×10?6 K?1, or less than 4×10?6 K?1 in the plane of the largest dimension of the receiving cutout, at temperatures between the starting and target temperatures. A receiving cutout for receiving a polymer-fiber component is in the tool part, the receiving cutout delimited by a receiving surface portion so a polymer-fiber component received in the receiving cutout can lie against the receiving surface portion. A susceptor element includes a ferromagnetic material with a first Curie temperature. The susceptor element is on a surface portion of the tool part outside the receiving cutout and the receiving surface portion.