Abstract: A combined composite and metal hybrid component and a method of forming said component, are disclosed, the component comprising a substantially sheet-like or web-like body portion, made of a composite material, at least one stiffening member made of a metal and at least one made of a composite material, and curing the component in a vacuum bag, such that the metal stiffening member is formed against the composite stiffening member and the metal stiffening member remains a part of the hybrid composite component.

Abstract: A rotational joint (101) that rotatably couples a wing tip device (4) to a fixed wing (3), and includes an outer race (8) and an inner race (9), a rotational drive member (70) and the race that is rotationally fixed relative to the wing tip device (4) each being provided with a coupling section (110, 111, 114), the coupling sections coupled to each other by a coupling member (119), that is received in a bore (112, 113) in one of the coupling sections, such that rotation of the drive member (70) rotates the race that is rotationally fixed relative to the wing tip device, to rotate the wing tip device (4) from one configuration to the other, wherein the coupling member (119) is mounted in the bore such that it is movable radially within the bore.

Abstract: A virtual window device, particularly for use in an airplane, includes a bezel, or a frame, with a display arranged within the bezel, or within the frame; a distance sensor unit configured to produce at least one first distance signal indicating a first distance to an object; a first camera unit configured to capture a live video of a real scene; and a computing unit configured to select, based at least on the at least one first distance signal, a section of the live video of the real scene captured by the first camera unit; wherein the computing unit is further configured to control the display to display the selected section.

Abstract: A cable harness test system includes a cable tester that has a microcomputer and a multiplicity of first test point connections for connecting first ends of a multiplicity of electrical lines of a cable harness and is designed to feed line test signals into the multiplicity of electrical lines of the cable harness at the first test point connections, and also a multiplicity of interface simulation devices that each have a multiplicity of second test point connections for connecting second ends of the multiplicity of electrical lines of the cable harness and are each designed to return line test signals received from the cable tester at the second test point connections to the cable tester by the multiplicity of electrical lines of the cable harness.

Abstract: A fiber composite component having a first and a second fiber composite element each bent along a transverse axis opf the fiber composite component to have, respectively, in succession, a first and second base flange, a first and second web section, a first and second top flange and a first and second stiffening web. Respectively, the first and second base flanges are parallel to the first and second top flanges, the first and second web sections are angled with respect to each of the first and second base flanges and the first and second top flanges, the first and second stiffening webs are at right angles with respect to the first and second top flanges, and the first stiffening web and the second stiffening web are congruent with respect to one another, and are connected to one another, along a longitudinal axis of the fiber composite component.

Abstract: An adapter system for a check valve which comprises a housing open at the bottom and a lateral wall pierced by a hole, and a flap fitted inside the housing and movable between a shut-off position in which the flap shuts off the hole and a free position in which the flap does not shut off the hole. A plug is provided for being inserted into the hole through an end face and a stop is provided for being placed against the lateral wall of the housing opposite the lateral wall pierced by the hole and comprising an attachment device provided for attaching the stop to the housing and provided so that the plug comes to rest against the stop. Such an adapter system may be installed without it being necessary to dismantle the housing.

Abstract: An ice-protection system for an aerodynamic structure for an aircraft comprising: an outer skin defined by a leading edge point and a trailing edge point that are interconnected by an upper skin and a lower skin, an internal chamber defined within the outer skin configured to be in fluid communication with the atmosphere external to the outer skin via an inlet and an outlet, and at least one air heater provided within the chamber in proximity to the inlet, wherein during use, a pressure differential exists between the inlet and the outlet that causes external air to flow through the chamber from the inlet to the outlet, and wherein the heater is configured to heat the air passing through the inlet such that the temperature of the air in the chamber is sufficiently increased so as to prevent ice accretion on the outer skin.

Abstract: An aircraft ceiling liner element comprises a load-bearing carrier platform, configured to form a part of an aircraft ceiling liner, and a mounting mounted on the carrier platform, connectable to a primary structure of the aircraft. An electrical connection mounted on the carrier platform is connectable to an electrical supply network of the aircraft. Furthermore, the aircraft ceiling liner element comprises a mechanical interface mounted on the carrier platform, configured to attach various interchangeable modular units detachably and in a load-transferring manner to the carrier platform, and an electrical interface mounted on the carrier platform, which interface is configured to create an electrical connection between the modular unit and the carrier platform.

Abstract: A simple device for accurately measuring real-time air flows along a wall, and relating to a measuring device including an optical sensor configured to measure an illuminance distribution on a free surface of the optical sensor. A mobile member movably is mounted on the light sensor by partially covering its free surface, the mobile member being adapted to be freely directed by a local air flow pattern, thus, modulating the illuminance distribution on the free surface so as a current illuminance distribution measurement by the optical sensor indicates the current direction of the mobile member representing the current air flow pattern.

Abstract: A casing for connecting electrical lines printed on a foil to a voltage supply. The casing comprises a space, terminal pads and a block. The casing has an opening between a first wall of the space and a first outer side of the casing. The terminal pads are at least partially arranged on a second outer side of the casing. The block is configured to move between a first position and a second position, both within the space. The block is configured to press the foil against a second wall of the space when the block is in the first position. The block is configured to establish an electrical connection between the electrical lines printed on the foil and the terminal pads when the block is in the first position. The space is configured to receive the foil through the opening when the block is in the second position.

Abstract: A control apparatus 300 for controlling a steering system 301 of an aircraft landing gear, the aircraft landing gear being configurable in a stowed configuration and a deployed configuration. The steering system 301 includes a wheel arrangement 202 including one or more wheels. The control apparatus 300 is arranged to perform a control process which includes: receiving one or more signals from one or more sensors 302a, 302b indicating a position of the wheel arrangement 202 when the landing gear is in the stowed configuration; determining whether a predetermined condition is satisfied in relation to the position of the wheel arrangement 202; and, in response to determining that the predetermined condition is satisfied, performing an adjustment process to control the steering system 301 to adjust the position of the wheel arrangement 202.

Abstract: A trolley handling device for guiding a trolley into and out of a trolley stowage, comprising a trolley holder adapted to interact with and secure the trolley against displacement relative to the trolley holder in at least a first direction, and a guiding device comprising a first guiding element attached to the trolley holder and a second guiding element adapted to be provided on a structural part arranged near the stowage. The first and second guiding elements are configured to engage with each other and to guide the trolley between a first position, in which the trolley is essentially arranged inside of the stowage, and a second position, in which the trolley is at least partially arranged outside the stowage. The trolley, in its second position, is arranged offset relative to its first position in the first direction and in a second direction perpendicular to the first direction.

Abstract: An aircraft windshield that improves pilot and co-pilot's perception of the outside world. The windshield includes a transparent panel held inside a structure of the aircraft, in which the upper part and the lower part are bridged so that the loads applied to the panel are (at least partially) diverted. Due to part of the loads applied on the panel being diverted, it is possible to provide a larger window panel than currently available that offers better visibility to the outside.

Abstract: An aircraft air conditioning system includes an ambient air line which is configured have ambient air flow therethrough and is connected to a mixer of the aircraft air conditioning system to supply ambient air to the mixer, and a refrigerating machine which includes a refrigerant circuit configured to have a refrigerant flow therethrough, the refrigerant circuit being thermally coupled to the ambient air line to transfer heat, from the ambient air flowing through the ambient air line, to the refrigerant circulating in the refrigerant circuit, before the ambient air is supplied into the mixer. A control device is configured to control the ambient air flow through the ambient air line such that the ambient air is selectively conducted through different sections of the ambient air line or different bypass lines running parallel to the sections of the ambient air line.

Abstract: An arrangement for selectively arresting a serving trolley in a cabin includes a walling extending perpendicularly to a cabin floor. The walling has a height at least equal to the height of a serving trolley. The arrangement has an upper arresting unit positioned at an upper fastening section of the walling and a lower arresting unit positioned at a lower fastening section of the walling. The upper arresting unit has a first engagement element and a second engagement element, wherein at least one of the engagement elements is movable relative to the other engagement element. The upper arresting unit releasably engages two distanced recesses at an upper end of the serving trolley by way of the engagement elements. The lower arresting unit includes at least one third engagement element and is designed for engaging a bottom side component of the serving trolley by way of the third engagement element.

Abstract: An aircraft wing comprises a fixed wing, and a wing tip device at the tip thereof. The wing tip device is configurable between (i) a flight configuration for use during flight, and (ii) a ground configuration for use during ground based operations. In the ground configuration with span of the wing is reduced. The wing further comprises a locking mechanism including a locking pin with a longitudinal axis, the locking pin associated with one of the fixed wing and the wing tip device, and a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin. The bush is located within a bush housing arranged to allow relative movement of the bush in the direction of the longitudinal axis of the locking pin when the locking pin is received within the bush.

Abstract: A tooling device for producing a planar structural component for an aircraft has a moulding tool part with a contour surface for receiving a planar semi-finished product, a heating device for heating the semi-finished product, a film produced from an elastically deformable material and a clamping system with a first clamping device arranged on a first longitudinal side of the contour surface, and a second clamping device arranged on a second longitudinal side of the contour surface located opposite the first longitudinal side. The film is couplable to the clamping devices by the edge regions thereof and, when it is coupled to the clamping devices, covers the contour surface of the moulding tool part. The film is elastically deformable relative to the contour surface by the first and/or the second clamping device to press the semi-finished product in a planar manner against the contour surface for deforming purposes.

Abstract: An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.

Abstract: A screen support configured to attach a screen to a seat equipped with a rear enclosure and including an attachment system configured to clamp the rods of a headrest of the seat, a support system including a limb connected to the attachment system and at least one support runner connected to the limb and configured to bear against the rear enclosure, and an engagement system configured to permit the temporary attachment of a screen and connected to the third limb.

Abstract: In order to reduce congestion of attachments between an aircraft engine and its attachments, an engine assembly is provided, the primary structure of the device of which includes a structural cover surrounding the engine and connected on a central box, the cover including an outer skin interiorly delimiting a secondary flow. A group of main mounts is provided as a group of secondary mounts laid out at the rear of the group of main mounts, the group of main mounts including a plurality of bolts distributed around the longitudinal axis of the engine and ensuring the attachment of a front end of the cover to the hub of the intermediate case, and a group of secondary mounts including a plurality of secondary mounts distributed around the axis and ensuring attachment of a rear portion of the engine to a rear end of the cover.