Abstract: A flight management assembly for an aircraft includes at least one flight management system and at least one display device, the flight management system configured to manage at least one flight plan of the aircraft and one long-term reference path of the aircraft. The flight management assembly additionally includes an auxiliary computer, the auxiliary computer being separate from and independent of the flight management system, the auxiliary computer linked to the flight management system and to the display device, the auxiliary computer configured to perform prediction computations to generate at least one short-term path, from at least the long-term reference path received from the flight management system and from current flight parameters of the aircraft and from piloting setpoints of the aircraft.

Abstract: A landing gear assembly (12) includes a primary load bearing strut including a shock absorber having a slider part (15) arranged to slide within a cylinder part (17). A link assembly (50) is attached between the slider part (15) and the cylinder part (17). A bogie (16) supporting wheels is mounted on the strut. The bogie may adopt different pitch angles. A pitch trimmer device (70) is attached to the bogie and to the link assembly, for example thus providing a relatively long moment arm (96) for control of the bogie pitch angle. The arrangement may be such that the pitch trimmer (70) is near mid-stroke as the aircraft achieves the full weight on wheels condition, whereas the pitch trimmer is at a fullest extent for flight case and for retraction. Onset of pitch trimmer closure/movement is used to detect the weight-on-wheels condition.

Abstract: An aircraft tailcone comprising a tailcone fuselage, a turbomachine, for example an APU, housed inside the tailcone, a ram air intake on the tailcone fuselage for the ingestion of ram air towards the interior of the turbomachine compartment, an inlet flap operable reciprocately from an open position in which ingestion of ram air is allowed, and a closed position in which ram air ingestion is prevented. The ram air intake extends annularly along a perimeter of the tailcone fuselage, and the inlet flap is configured such in its closed position that a surface of the inlet flap is substantially flush with the tailcone fuselage.

Abstract: An assembly includes a bag and of a composite panel exhibiting a damaged region to be repaired by polymerization of a repair piece using the bag. The bag includes a sheet intended to be laid over the panel. When the panel and the sheet are laid one atop of the other, the sheet exhibits regions capable of absorbing heat emitted by radiation onto it in a proportion that is dependent on the polymerization temperature needed for that region of the panel that corresponds to it, the radiation being partially absorbed by suitable colouration of the sheet in the region concerned. Determining those regions of the panel in which radiation is less well absorbed than in others means that the heating can be adapted to suit the needs of polymerization in terms of repair and that even polymerization can thus be obtained over the entire damaged region, thereby consolidating the repair.

Abstract: A method for operating a wing (5) including a fixed wing (9), a foldable wing tip portion (11) mounted to the fixed wing (9) pivotally between an extended position 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) in the extended position and/or in the folded position. The method includes controlling the actuation unit (13) to move the foldable wing tip portion (11) either to the extended position or to the folded position until the foldable wing tip portion (11) or the actuation unit (13) contacts a stop element (28), continuing actuation until the actuation unit (13) reaches a stall condition, detecting the stall condition of the actuation unit (13), and locking the arresting unit (15) upon detection of the stall condition.

Abstract: An applicator for application onto and embossing microprofiling of a fluidic medium on a substrate, in particular in the aerospace sector, and a corresponding application device having such an applicator. The applicator has a circumferentially moving die that has an embossing profile, a press for the die and a stabilizing device, in particular a hardening device, for the applied medium. In addition, the applicator has a hollow support body, surrounded by the die at a distance forming a gap, the press being arranged in the gap. The application device has, in addition to the applicator, a handling device for a relative movement between the applicator and a workpiece.

Abstract: A tool for shaping non-cured reinforcement fibers into a substantially T-shaped profile, comprising a web-shaping tool and a forming tool, wherein the forming comprises an inflatable diaphragm.

Abstract: An assembly apparatus for forming an interfay joint during manufacture of an aircraft (10). The assembly apparatus includes an assembly jig (40) to hold a first joint component (26), and an applicator (43) configured to apply an uncured layer of shim to the first joint component. The assembly jig locates, subsequent to the uncured layer of shim being applied, a second joint component (23) in an assembled joint position spaced from the first joint component. As such the uncured layer of shim is compressed between the first and second joint components. A method of forming an interfay joint during manufacture of an aircraft, an interfay joint for an aircraft, an aircraft aerodynamic surface, an aircraft, and a shim layer applicator.

Abstract: An aircraft is disclosed having a wing, the wing having a fixed wing with a wing tip device moveably mounted about a hinge at the tip thereof. The wing tip device is operable between a flight configuration, and a load alleviating configuration for load alleviation during flight. The aircraft includes a restraining assembly operable between a restraining mode in which the wing tip device is held in the flight configuration using a restraining force such as by a brake, and a releasing mode in which the restraining force on the wing tip device is released, such that the wing tip device may adopt the load alleviating configuration.

Abstract: An optical sensor system with two or more optical sensors; two or more receivers; and an optical de-multiplexing system. Each optical sensor includes a fibre grating with a different wavelength characteristic. Each receiver includes a slope filter and a light detector and is associated with a respective one of the optical sensors. The optical de-multiplexing system is arranged to route light from each of the optical sensors to its associated receiver based on a wavelength of the light.

Abstract: A cable routing system is disclosed having dielectric, or insulating, liner which is installed within a cable routing channel, or raceway, to subdivide the channel into at least two secondary channels. This can achieve more efficient use of space and enable more flexible placement of cables within the channels while meeting safety requirements. Installation of cables into the channel can include inserting the cables into the dielectric liner before the installation of the dielectric liner into the cable routing channel. The cable routing system can be used in an aircraft, including within space-constrained areas of the aircraft such as inside a wing.

Abstract: The pylon, intended to support a flying vehicle engine, includes a primary structure formed by at least one longeron and one panel, the panel including at least one end part provided with a notch, the longeron being provided with an end adapted to be positioned in the notch, the panel and the longeron being assembled by welding a part of the end to a part of the notch. A welded primary structure enables minimization of the blanks of parts associated with the longerons and with the panels by avoiding having recourse to the production of edges.

Abstract: A functional unit in a passenger cabin includes a support unit and a passenger seat system. The passenger seat system is formed in two parts and has an upper constructional unit and a lower constructional unit that are each separate components, the upper constructional unit arranged on the support unit and containing at least one backrest, and the lower constructional unit containing a seat frame, at least one seat element and restraint for the passenger on the seat. The seat frame is fastenable to seat rails on the floor of a passenger cabin. For the use position, the upper and lower constructional units are positioned such that a passenger seat is formed. In the use position, personal comfort for the individuals on the seats is not impaired as far as possible, and the division of the seat system into two parts cannot be seen by the user.

Abstract: A panel assembly with a panel and a stringer is disclosed. The stringer has a stringer foot and an upstanding stringer web. The stringer foot has a flange which extends in a widthwise direction between the stringer web and a lateral edge and in a lengthwise direction alongside the stringer web, and a foot run-out which extends between the flange and a tip of the stringer foot. The foot run-out is bonded to the panel at a foot run-out interface. Reinforcement elements, such as tufts, pass through the foot run-out interface. At least some of the reinforcement elements are inclined relative to the foot run-out interface.

Abstract: A method and an apparatus for welding a first object to a second object, wherein the first object is produced from a thermoset and comprises a thermoplastic material outer layer, wherein the second object comprises at least one thermoplastic material outer layer. In addition, a layer of carbon nanotubes is applied to the thermoplastic material outer layer of the first object, and the second object is placed onto the first object. At least some of the thermoplastic material outer layer of the second object lies atop the applied layer of carbon nanotubes. In addition, a potential is applied to the layer of carbon nanotubes, such that an electrical current flows through the carbon nanotubes, wherein the thermoplastic material outer layer of the first object and the thermoplastic material outer layer of the second object are heated and are welded to one another.

Abstract: A device for manipulating a hollow shaft configured to create a pivot link between a first element and a second element. The manipulation device comprises a cylindrical body having a diameter variable by radial contraction or radial expansion of the cylindrical body, a module for controlling the diameter of the cylindrical body configured so that the diameter of the cylindrical body has alternatively at least a first diameter suitable for the cylindrical body to be displaced in the hollow shaft and a second diameter suitable for the cylindrical body to be blocked in the hollow shaft. The cylindrical body comprises an end configured to protrude from the hollow shaft when the cylindrical body is blocked in the hollow shaft. The manipulation device allows the alignment of the orifices due to the end configuration of the cylindrical body.

Abstract: A wing arrangement for an aircraft, comprising a wing having a base section and a tip section pivotably connected to base section such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position. The wing arrangement also comprises a latching arrangement which includes an engagement portion, a latching actuator selectively movable between a first actuator position and a second actuator position, an elastically deformable structure, and a latching element. When the tip section is pivoted from the stowed or deployed position into an engagement position, the elastically deformable structure is initially deformed, and as the tip section pivots further into the deployed or stowed position, the elastic deformation of the elastically deformable structure decreases.

Abstract: A method for the automated testing of electrical cabin loads in a cabin of an aircraft comprises activating at least one electrical cabin load in a predetermined operating mode via a test controller; recording an electric power consumption profile of the at least one electrical cabin load in the activated operating mode via a power controller of an electric power distribution system of the cabin of the aircraft, wherein the power controller regulates electric power consumption of the at least one electrical cabin load within the power distribution system; transmitting the recorded power consumption profile to the test controller; and comparing the recorded power consumption profile with a reference profile for the activated operating mode of the at least one cabin load via the test controller, in order to test the at least one electrical cabin load for operability.

Abstract: A drilling aid system which comprises a body with a first cavity, a shaft mounted to be able to rotate within the first cavity, a slider which has a proximal end mounted to be able to move in translation within the first cavity, where the slider has a second cavity which extends the first cavity, a collar that is able to move in translation on the shaft, a first compression spring having a first stiffness and pressing against the collar and against the proximal end of the slider, and a second compression spring having a second stiffness greater than the first stiffness, and pressing against the collar and against the proximal end of the body. A system of this kind makes it possible to make the user perceive that the end of the drilling operation is nigh and that therefore the force applied to the drill should be reduced.

Abstract: A jet engine including a motor with a fan casing and a nacelle which includes a mobile cowl and a main slider that is mobile in translation between an advanced position and a retracted position in which the mobile cowl and the fan casing define, between them, a window. The nacelle also includes reverser flaps and exterior flaps, each one being mounted articulated on the main slider between a stowed position in which it obstructs the window and a deployed position in which it does not obstruct the window, a secondary slider that is mobile in translation on the main slider between a first position and a second position, a transmission system making each reverser flap and exterior flap pass from the stowed position to the deployed position when the secondary slider passes from the first position to the second position, and a set of actuators that bring about a movement in translation of the main slider and of the secondary slider.