Abstract: An aircraft wing, including a main wing and a trailing edge high lift assembly movably arranged at a main wing trailing edge, the high lift assembly including a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between retracted and extended positions. In the extended position, a gap is present between a main wing lower rear panel and a flap leading-edge section. In the retracted position, the gap is closed or minimized. The flap is movable between an extended position, a first retracted position, and a second retracted position where the flap is moved beyond the first retracted position in a forward direction, and the wing comprises a gap closing device configured to close or minimize the gap in both the first and second retracted positions of the flap, and to open the gap in the flap extended position.

Abstract: A fastening system for an aircraft to fasten at least one tank to contain liquid hydrogen, allowing easy access to the tank. The fastening system includes a longitudinal box, upper formers fastened to the upper end of the longitudinal box and lower formers fastened to the lower end of the longitudinal box, at least two upper formers including two fastening devices to each connect a fastening point of the tank to an upper former, at least one lower former including two second fastening devices to each connect a second fastening point of the tank to the lower former. The fastening system allows an operator to access the tanks that are capable of being fastened by the fastening system.

Abstract: A actuator arrangement is disclosed in which the high-lift device support that supports and guides movement of a high-lift device, such as a flap, is in axial alignment with a control actuator assembly that controls one or more control surfaces. This allows a single support fairing to be sufficient for covering both the track member and the control actuator assembly and allowing for reduced drag and weight.

Abstract: A mounting member configured to support a cabin component to be mounted to a mounting rail. The rail mounting arrangement comprises a disengagement locking mechanism that prevents a removal of the mounting member along a transversal direction of the mounting rail, while still allowing movement along the longitudinal direction. The rail mounting arrangement includes a securing mechanism that is configured to secure the mounting member at the desired location along the mounting rail.

Abstract: Two components of an aircraft structure are joined by providing a threaded opening in one of them and supporting an alignment insert in that opening. The alignment insert is used to guide drilling of the second component such that a hole is produced which is aligned with the threaded opening, for instance using an alignment projection which physically guides a drill. The alignment insert may then be removed. A fastener is then inserted through that hole and into the threaded opening, then tightened to form the completed joint.

Abstract: An aircraft wing section assembly is disclosed having a structural spine, a movement mechanism including a support rod 1 extending through the structural spine, a first lever, for connection to and for moving a first moveable control surface, pivotally mounted to the support rod, a second similar lever for connection to and for moving a second moveable control surface, and a connection mechanism for connecting the first and second levers such that pivotal movement of the first lever causes pivotal movement of the second lever, and an actuation mechanism for actuating pivotal movement of the first lever, such that, in use, when the actuation mechanism actuates pivotal movement of the first lever, the second lever also pivotally moves, thus causing movement of both the first and second moveable control surfaces. Also disclosed is an aircraft wing assembly, an aircraft and a method of operating an aircraft.

Abstract: A method for operating a water supply system for an aircraft, as well as a corresponding water supply system operating in accordance with the method and an aircraft having such water supply system. The method includes two operation sequences of a pump and a valve, each sequence including a time delay between operation of the pump and operation of the valve.

Abstract: A cradle for supporting an aircraft landing gear assembly is disclosed including a chassis for transporting the cradle and an arm movable between a stowed position and an elevated position with respect to the chassis. The arm has a set of clamps for securing the landing gear assembly to the cradle. In this way the landing gear assembly is held securely in the stowed position for storage and transport, and held securely in the elevated position for installation to an aircraft, such that damage to the landing gear assembly during transportation and installation is minimised.

Abstract: A method for assembling aircraft panels by welding improves the flexibility thereof. Panels are butted together along longitudinal joining lines and fixed to one another via their longitudinal edges by welding without the longitudinal ends of their welded edges being connected to one another. Longitudinal hoops are fixed to partially cover the concave surface of the panels at least partially at the ends. The absence of welding at the ends introduces the desired flexibility. The disclosure also covers the fuselage portions formed by assembling panels according to this method and the aircraft including such portions.

Abstract: A device for latching a door of an oxygen mask container in an aircraft cabin includes a door for an oxygen mask container having an inner side, outer side and hinge, a first latching device attached to the inner side, and a second latching device movable relative to the first latching device to selectively engage or disengage the second latching device. A retaining element is attachable to a structural part inside the oxygen mask container. A test control device on the inner side of the door includes a movable hook element and can move the hook element to a first or second position. The hook element can engage the retaining element in the first position to restrict an opening degree of the door. The hook element is placed in the second position such that when the door is opened, the hook element is moved past the retaining element.

Abstract: A lightning strike protection layer for an aircraft is disclosed having a first portion and a second portion, the first portion includes a first fibre reinforced polymer composite layer and a first electrically conductive metal layer and the second portion includes a second fibre reinforced polymer composite layer and a second electrically conductive metal layer, and the first and second portions are joined at a butt joint, with the first and second fibre reinforced polymer composite layers abutting and the first and second electrically conductive metal layers abutting; and a butt-strap extending across the butt joint, the butt-strap comprising a third electrically conductive metal layer electrically connected to the first and second electrically conductive metal layers.

Abstract: A rib mounting assembly for an aircraft is disclosed including a rib post and a seal member. The rib post has a rib post foot to mount with a longitudinal spar and a rib post web upstanding from the rib post foot. The seal member has a seal body and a mounting flange. The mounting flange is mounted with the rib post foot and the seal body extends from an end of the rib post.

Abstract: A method for manufacturing at least a portion of a box structure obtained from an outer skin and a plurality of sections each having a joining face in contact with the outer skin. The method comprises a step of positioning the sections on a mold, a step of obtaining a flat fiber preform having a thickness substantially equal to the outer skin, a step of placing a central portion of the fiber preform on the sections positioned on a first face of the mold and a step of forming a lateral extension of the fiber preform to press the fiber preform against a forming surface. A central wingbox obtained by the method is provided and a forming tool for carrying out the method.

Abstract: A stiffener is disclosed including a core and a shell which surrounds the core. The shell is formed from a fibre material, and the core includes first and second battens arranged side by side, and a foam spacer between the battens. The stiffener extends in a lengthwise direction, and the battens and the foam spacer have respective lengths which extend in the lengthwise direction of the stiffener. The core is assembled with the spacer between the battens, then surrounded with the shell. The stiffener may be a stringer for an aircraft wing.

Abstract: An acoustic treatment panel includes at least one acoustically resistive layer, a reflective layer and at least one cellular structure interposed between the acoustically resistive layer and the reflective layer. The cellular structure includes cylindrical and identical main tubes which are closed at one end by the acoustically resistive layer and at the other end by the reflective layer, spacer zones between the main tubes, the spacer zones being sealed relative to one another, cutouts made at an end of certain main tubes, in contact with the reflective layer, and/or secondary tubes positioned in the main tubes and/or in the spacer zones, the cutouts and/or the secondary tubes being configured to generate acoustic cells of different dimensions from identical main tubes.

Abstract: A method of landing an aircraft in which the aircraft receives information from a second aircraft via a direct aircraft-to-aircraft communication from the second aircraft to the aircraft; determines a landing plan of the aircraft based on the information; and lands the aircraft based on the landing plan. The use of a direct aircraft-to-aircraft communication (i.e. a communication from the second aircraft to the first aircraft which does not travel via an intermediary such as a land station, air traffic controller or satellite) makes the method reliable because such a communication is inherently secure and difficult to hack.

Abstract: A method of determining a status of a tyre monitoring device that includes a power supply. The method includes determining a value indicative of consumption of the power supply, determining a status of the tyre monitoring device based on the value indicative of consumption of the power supply, and providing an indication based on the determined status.

Abstract: A wing for an aircraft includes a leading edge as a first chordwise edge, a trailing edge as a second chordwise edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create wing box with the upper skin and the lower skin, and at least one of a fluid line, an electrical line, and a mechanical power transfer device attached inside or reaching into the wing box at least partially.

Abstract: A computer-implemented method of predicting tire pressure of a tire of an aircraft, the method including obtaining first data indicative of an inflation pressure of the tire, obtaining second data indicative of a brake temperature of a brake associated with an aircraft wheel to which the tire is mounted, obtaining third data indicative of a gas temperature of the tire, and obtaining fourth data indicative of one or more predicted operational conditions of the aircraft during a future time period. The method includes determining, based at least in part on the first, second, third and fourth data, predicted tire pressure characteristics of the tire during the future time period.

Abstract: A spark containment cap for enclosing an end of a fastener protruding from a structure, the enclosed body having a base and a cover portion, the cover portion extending from the base, the base providing an adhering surface for adhering the spark containment cap to a structure, and the base and the cover portion together forming a cavity within the enclosed body inside which the end of a fastener can be enclosed.