Abstract: A controller for a hydraulic braking system for an aircraft is disclosed. The hydraulic braking system includes a first accumulator and a second accumulator, the controller configured to: receive first signals including first pressure data from a first pressure transducer associated with the first accumulator, receive second signals including second pressure data from a second pressure transducer associated with the second accumulator, monitor the received first and second signals to determine whether a predetermined condition has been met, and issue a warning indicating a loss of integrity of the hydraulic braking system in response to a determination that one or more predetermined conditions has been met. A hydraulic braking system for an aircraft and method to determine the integrity of a hydraulic braking system are also disclosed.

Abstract: A method for testing an arresting unit (15) for locking a foldable wing tip portion (11) to a wing (5) that includes a fixed wing (9), a foldable wing tip portion (11), and a folded position, an actuation unit (13) for actuating movement of the foldable wing tip portion (11), and an arresting unit (15) for locking the foldable wing tip portion (11). The method includes: locking the foldable wing tip portion (11) in the extended position by the arresting unit (15), controlling the actuation unit (13) to move the foldable wing tip portion (11) in the direction towards the folded position, such that the foldable wing tip portion (11) urges against the arresting unit (15) with a predefined test load, detecting deformation of the arresting unit (15) during or after application of the test load, and comparing the detected deformation to a predefined threshold deformation.

Abstract: A wing for an aircraft is disclosed having a fixed wing and a foldable wing tip portion mounted to the fixed wing via a hinge rotatable about a hinge axis between an extended position and a folded position. The wing may include an actuation unit with reduced complexity, and may include a ground latch device for latching the foldable wing tip portion in the folded position.

Abstract: An engine attachment configured to link an engine and an aircraft pylon comprising a first end fitting having two mutually parallel wings, a joining piece positioned between the first end fitting wings and linked to the first end fitting by a link system, fixing elements, linking the first end fitting and the pylon, including first and second fixing elements positioned between the first end fitting wings which are inclined by an angle of between 10 and 45° to be able to be put in place and removed in the presence of the joining piece linked to the first end fitting by the link system. The inclined fixing elements absorb lateral loads. The joining piece and the first end fitting are linked by the link system before the engine is fixed to the pylon. The engine is fixed to the pylon by putting the fixing elements in place.

Abstract: A seal is disclosed for a wing for providing an aerodynamic seal between a fixed aerofoil and a movable control surface.

Abstract: A wing tip device for attaching to an aircraft wing comprising a first wing tip device element having a root end and a tip end; a second wing tip device element coupled to the tip end of the first wing tip device element; wherein the second wing tip device element has an inboard portion extending inboard from the tip end of the first wing tip device element and/or an outboard portion extending outboard from the tip end of the first wing tip device element, when viewed in the wing planform direction.

Abstract: An assembly forming an acoustic insulator having a first sheet, a pierced second sheet, and a plurality of first and second structures. Each first structure comprises a first and a second strip, wherein each is shaped to form half of the wall of a cage and wherein, for two successive halves, each strip comprises a facet of a joining wall. Each second structure is made up of a first and a second strip, wherein each is shaped to form half of the wall of a cone, wherein. For each strip, at least one of the wall halves of each cone is pierced. For two successive halves, each strip comprises one facet of the connecting wall. Each cone is located in a cell and each connecting wall is located between the two facets of a joining wall, and, between two adjacent first structures, a second structure is likewise fitted.

Abstract: A production method for an acoustic panel comprising a step of producing a composite structure, a step of providing inserts, wherein each insert comprises a nozzle formed as a hollow cylinder with a through-bore and a cap comprising a base formed as a cylinder and a cover formed as a cone, and wherein the base is accommodated in the bore, a step of positioning the inserts in the composite structure by penetration of the cover into the composite structure so that the bore opens at one side and the other of the composite structure, a step of polymerizing during which the composite structure with the inserts is polymerized, a step of removing the caps, a first step of fixing a honeycomb structure to the polymerized composite structure, and a second step of fixing a rear skin to the honeycomb structure.

Abstract: An assembly for an aircraft, which includes a pylon with a bearing face and a contact face, an engine mount with a bearing face and a contact face bearing against the contact face of the pylon, at least two bolts comprising a threaded stem with a head and a nut bearing against the bearing face of the engine mount, for each head, a bearing washer with a first bearing face and a second bearing face, where the second bearing face of the bearing washer bears against the bearing face of the pylon, and where the head bears against the first bearing face of the bearing washer, a shoe, and, for each bearing washer, a clamp that is secured to the shoe and comprises a first branch and a second branch between which the bearing washer is clamped and is free to rotate.

Abstract: A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.

Abstract: A forward engine attachment system for an engine of an aircraft, the forward engine attachment system including a jet engine pylon including, in the region of the forward part thereof, a front part having an attachment wall, and a forward engine attachment with a connecting rod system on either side of a median plane, wherein each connecting rod system is fixed in articulated manner by at least one first link point to the attachment wall and is designed to be fixed in an articulated manner by at least one second link point to a forward part of the engine. Such a forward engine attachment system thus includes a direct coupling between the jet engine pylon and the engine, allowing the production of an assembly that is less heavy and is easier to produce.

Abstract: A device for a lacquer transfer includes a transfer roller mounted at and rotatable relative to a frame. The roller includes a cylindrical support-body, first ring-element, second ring-element, and a tire including a middle-section forming a circumferential outer contact surface with depressions, the roller configured to roll with the outer contract surface on a work surface of a workpiece for transferring lacquer from the outer contact surface and the depressions to the work surface. The tire includes two annular end-sections attached to a cylindrical outer shell of the support-body resulting in two axially separated and circumferentially extending connections, the tire, connections, and outer shell of the support-body being fluid-tight. The first and second ring-elements are in the first cavity seated on the support-body at a distance in an axial direction of the roller from one another and the middle-section of the tire between the first and second ring-elements is prestrained in the axial direction.

Abstract: A primary structure of a strut for bearing an aircraft power plant including a front part intended to be joined to an aircraft power plant and a rear part intended to be joined to a structure of the aircraft, the front part being formed from a box including an upper longitudinal member, a lower longitudinal member, and lateral panels. A main rib is located at an interface between the front part and the rear part. The rear part is formed from a set of four connecting rods. The first end of each connecting rod is joined to the front part of the primary structure and the second end of each connecting rod is joined to a separate interface for fastening to the structure of the aircraft. This allows a substantial simplification of the primary structure of a strut for bearing an aircraft power plant, which can have advantages in particular in terms of cost, mass, and simplicity of implementation and integration.

Abstract: A fastener for holding together two or more structures. The fastener includes a first bush and a second bush. The first bush includes a hollow shaft having a first end and a second end opposite to the first end. The first end of the first bush has a first radially-extending protrusion. The second bush includes a hollow shaft having a first end and a second end opposite to the first end. The first end of the second bush has a second radially-extending protrusion. The second end of the second bush is configured to connect to the second end of the first bush so as to resist separation of the first and second bushes and so as to define an axial hole through the fastener defined by the shaft of the first bush and the shaft of the second bush.

Abstract: A flap system driving a leading-edge flap between retracted and extended positions comprises a leading-edge flap, an actuator, first, second and third fixed links, first and second connecting links, and an auxiliary link. The first, second and third fixed links are rotatably supported on respective first, second and third structurally fixed points by respective first, second and third support joints. The first fixed link couples with an end of the first connecting link, which is coupled with a first flap joint at another end. The second fixed link rotatably couples with a central region of the first connecting link. The third fixed link rotatably couples with an end of the second connecting link, which is coupled with a second flap joint at another end. The second connecting link couples with the first fixed link through the auxiliary link, each at positions inside of the respective ends.

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 actuation unit (15) for actuating a foldable wing tip portion (9) includes a first housing part (19) including a first attachment device (23) configured for attachment to a fixed wing (5), and a second housing part (21) including a second attachment device (25) configured for attachment to a foldable wing tip portion (9). The second housing part (21) is rotatable about a main axis of rotation (35). The second housing part (21) includes a toothed rack (37) having a concave shape and facing the main axis of rotation (35). A drive pinion (39) is supported at the first housing part (19) and engaging the toothed rack (37) for driving the second housing part (21) rotatingly relative to the first housing part (19). The drive pinion (39) is driven by a coupling arrangement (43) that is configured to be coupled to an output (45) of a motor unit (47).

Abstract: A linking device connecting an aircraft engine and a primary structure of an aircraft pylon, comprising a support connected to the primary structure, a spreader, extending between first and second ends that has a central part connected to the support by a principal link comprising a principal rotation axis, at least one system for limiting the deflection of the spreader comprising an extension secured to the spreader and also upper and lower stops, secured to a fitting secured to the support, between which the extension is positioned.

Abstract: A valve apparatus for an aircraft fluid system is disclosed including a valve housing and a valve member. The valve member is configured to move between a first position in which fluid is able to flow along the fluid flow path, and a second position in which the fluid flow path restricted. A valve member drive means is configured to operate the valve member via an actuator external to the housing. The valve apparatus further includes a sensor configured to monitor a feature in the housing to determine the position of the valve member.

Abstract: An aircraft nacelle including a conduit rigidly connected to an air inlet and a conduit rigidly connected to an engine, a link between the conduit rigidly connected to the air inlet and the conduit rigidly connected to the engine. The link includes a sleeve that receives one end of a first conduit and is rigidly connected to a second conduit, and linking elements that link the sleeve and the first conduit and that are distributed about the entire circumference of the nacelle, each linking element having a threaded stem oriented in a radial direction and being configured to enable tightening from inside the first conduit.