Abstract: A resilient component for attachment to a rigid temporary reinforcement structure, and a rigid temporary reinforcement structure for attachment to a resilient component are disclosed. The temporary reinforcement structure having one or more datum attachment features for releasably attaching the temporary reinforcement structure to corresponding datum attachment features of the resilient component, where the datum attachment features and the datum features of the resilient component have a common datum, and the temporary reinforcement structure is configured to rigidly support the resilient component during assembly of the resilient component to a structural assembly.

Abstract: An aircraft assembly including: a first aircraft structure, a second aircraft structure, first and second tension bolts arranged to suspend the first aircraft structure below the second aircraft structure, the first and second tension bolts connected to the first aircraft structure such that an end of each of the tension bolts is accessible from respective outer surfaces of the first aircraft structure and first and second fail-safe mechanisms each associated with a respective one of the first and second tension bolts and arranged to suspend the first aircraft structure below the second aircraft structure responsive to failure of the respective tension bolt.

Abstract: A wing for an aircraft, including a main wing, a slat, and a connecting assembly movably connecting the slat to the main wing, the slat being movable between retracted and extended positions. The connecting assembly includes a slat track and a roller bearing. A front section of the slat track is mounted to the slat. A rear section and an intermediate section of the slat track are mounted to the main wing via the roller bearing. The roller bearing includes a guide rail mounted to the main wing and a first roller which is rotatably mounted to the rear section of the slat track. The first roller engages a first engagement surface formed by the guide rail. The roller bearing includes a second roller which is rotatably mounted to the main wing. The second roller engages a second engagement surface formed by the intermediate section of the slat track.

Abstract: A method for assembling an aircraft pylon including a primary structure and at least one internal system positioned at least partially within the primary structure, wherein the assembly method includes a first step of assembling a part of the primary structure so that the interior of the primary structure remains accessible, a step of mounting an internal systems module including at least one support and at least one internal system connected to the support, a second step of assembling the internal systems module and the partially assembled primary structure, a third step of assembling any element of the primary structure not assembled in the first assembly step, and an aircraft pylon assembled by such a method.

Abstract: A resistive skin shell for an acoustic panel or inner wall of an aircraft air intake, comprising an alternation, in a transverse direction, of perforated metal bands and of composite solid bands extending in a longitudinal direction. The perforated metal bands and the composite solid bands form a smooth outer face configured to be in contact with an aerodynamic stream, and a crenelated inner face. The composite solid bands have a thickness greater than the perforated metal bands. Since the perforations are provided in metal bands, which are intrinsically resistant to wear and erosion, the future proofing of the acoustic performance of the resistive skin is guaranteed. Since the composite solid bands, which are thicker, can ensure the mechanical strength of the skin, the thickness of the perforated metal bands can be reduced, allowing perforations with dimensions that are also reduced, having a lower impact on drag.

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: A system for automated management of in-flight restarting of engines of an aircraft includes controllers, each engine of the aircraft being managed by one of the controllers. A controller that detects an engine that has stopped: cuts off the energy supply of the engine and performs a windmill engine start. If at least one other engine has stopped, prioritization of engine restarting includes: collecting information concerning a state of health of each engine; determining from the information collected information representing a probability of restarting each stopped engine; determining a sequential order of restarting the stopped engines as a function of information representing the probability of restarting each stopped engine. Each stopped engine continues to be windmill started until selection of the engine in question in the sequential order of restarting the stopped engines. Thus, the operational status of the aircraft is improved as quickly as possible.

Abstract: A drilling machine and a drilling method including drilling a first bore in a material with a drilling machine by applying a torque to a drilling tool for imparting a rotation at a first rotational speed to the drilling tool, and applying a thrust to the drilling tool for advancing the drilling tool at a first feed speed into the material, wherein a drilling parameter is measured while drilling the first bore, and a second rotational speed and a second feed speed are determined based on the drilling parameter, then drilling a second bore at the second rotational speed and at the second feed speed.

Abstract: An aircraft wing, including a main wing, a leading edge high lift assembly including a high lift body, and an assembly connecting the high lift body to the main wing. The high lift body is movable relative to the main wing between stowed and deployed positions. The connection assembly includes at least one rotation element mounted to the high lift body and rotatably mounted to the main wing. The main wing comprises an upper panel with a leading edge portion and a lower skin panel. The high lift body has a leading and a trailing edge. The high lift body trailing edge moves along the main wing upper skin panel leading edge portion when the high lift body is moved between the stowed and deployed positions. The upper skin panel leading edge portion is elastically deformed when the high lift body is moved from the stowed to the deployed position.

Abstract: A fixture for use in an additive manufacturing and heat treatment process is disclosed. The fixture includes a tool with an upper surface and a lower surface, and an attachment system configured to releasably secure a substrate to the upper surface of the tool. The tool includes a body with an upper face and a lower face, and a reinforcement layer cladding the upper or lower face of the body. The reinforcement layer may be a superalloy.

Abstract: A panel assembly is disclosed having a panel, a beam attached to the panel, and a plurality of stiffeners attached to the panel. Each stiffener includes a respective bridge which crosses over the beam at an intersection from a first side of the beam to a second side of the beam. Each bridge has an outer surface facing away from the panel and an inner surface facing towards the panel. The inner surface of each bridge deviates away from the panel to form a recess at the intersection, and the outer surface of each bridge deviates away from the panel to form a protrusion at the intersection.

Abstract: A pin joint assembly including: a first end lug and a second end lug; a pin hole extending through the first and second end lugs; a first retaining feature and a second retaining feature arrangeable at opposing ends of the pin hole; a headless pin including a pin body for inserting through the pin hole to rotatably couple the first and second end lugs, such that the pin body is retained between the first and second retaining features; a first bushing for positioning between the headless pin and the first end lug, and a second bushing for positioning between the headless pin and the second end lug; wherein the headless pin is isolated from the first and second retaining features.

Abstract: An arrangement comprising an airfoil body, a junction mechanism for attaching the airfoil body to a support element of an aircraft, and a fairing for aerodynamically covering the junction mechanism. The fairing has a cover element covering a trailing end portion of the fairing. The cover element is attached to the trailing edge of the airfoil body by a form fit connection.

Abstract: An aircraft assembly is disclosed having a first structural component and a second structural component. A fastener fastens the first component to the second component. The first structural component includes a body and an insert in the body. The insert has a machined hole through which the fastener extends. The material hardness of the insert is lower than the material hardness of the body.

Abstract: A landing gear system controller for controlling a landing gear system of an aircraft. The controller is configured to receive a request to operate a non-landing gear system element of the aircraft, and to cause operation of at least part of the landing gear system of the aircraft during a take-off or landing procedure on the basis of the request.

Abstract: A drive system for driving a movable flow body having a drive unit, a shaft, a torque sensing device, a no-back friction unit, and an axial bearing. The drive unit is coupled with the shaft to rotate the shaft, the torque sensing device is coupled with at least one of the drive unit and the shaft to detect a torque transferred from the drive unit into the shaft, the no-back friction unit is arranged between the axial bearing and an axial support means of the shaft, such that an axial load of the shaft is supported by the axial bearing, and the no-back friction unit is configured to substantially not counteract a rotation of the shaft in a first direction of rotation of the shaft and to apply a friction-induced additional torque to the shaft in an opposite second direction of rotation.

Abstract: A high-lift device connection assembly (24) for movably connecting a high lift device (16) to a wing (14) of an aircraft (10) wherein a track (30) is movably guided between main rollers (38, 40, 42, 44). In order to provide an enhanced fall back safety feature in case of a failure of a roller the invention proposes a track catcher (92) to be attached to a structure (26) of the wing (14) and configured to bear a load imposed by the track (30) in case of a main roller failure, wherein the track catcher (92) has at least one first hook element (94, 94-1-94-4) engaged within a first recession (72) at a first side of the track (30) and at least one second hook element (96, 96-1-96-4) engaged with a second recession (74) at the second side of the track (30). Further, the invention relates to a wing and an aircraft equipped with such high-lift device connection assembly (24).

Abstract: A method of joining a first workpiece to a second workpiece is disclosed including securing a spark containment cap to the first workpiece, the cap comprising an electrically insulating washer and a cap body defining an air cavity. Once the cap has been secured, a tail of a fastener is inserted into the air cavity through the second workpiece, the first workpiece and the washer. Upon tightening the fastener, the tail of the fastener urges the washer against the first workpiece and the first and second workpiece are thereby clamped between the washer and a head of the fastener so as to form a joint. Advantageously, it has been found that forming a joint in this manner can help to better protect the joint from the effects of electrical arcing.

Abstract: An aircraft brake temperature control system (BTCS) (100) for controlling a temperature of a brake (220) of a landing gear (201) of the aircraft (200). The BTCS (100) includes a controller (110) configured to cause a thermal management system (2000) to regulate the temperature of the brake (220), on the basis of a selection of an objective for regulating the temperature of brake from a plurality of objectives (121), (122) for regulating the temperature of the brake. An aircraft (200) includes the BTCS; and a method (300) controls a temperature of a brake of a landing gear of an aircraft.

Abstract: A fuel system for an aircraft including a fuel tank for storing fuel during operation of the aircraft and a diffuser disposed inside the fuel tank. The diffuser is configured such that it forms part of a flow path configured to connect a fuel source to the inside of the fuel tank. The diffuser includes a wall which at least partially defines an internal space of the diffuser; an opening in the wall, which provides access to the internal space; and a blocking component configured to block the opening.