Abstract: A lift apparatus for transporting objects between compartments of an aircraft through an aperture in a floor structure separating the compartments and an aircraft in which such lift apparatus is mounted. The lift apparatus includes a conveyor with a retaining portion to selectively retain and release objects to be transported, a guide to which the conveyor is mounted to be linearly movable along a predetermined path of motion defined by the guide, and a moving mechanism for driving the conveyor to linearly move along the predetermined path of motion. The retaining portion and a closing portion of the conveyor are along the path of motion, and the lift apparatus mounts in an aircraft with the path of motion extending through the aperture. The conveyor is selectively movable along the predetermined path of motion between positions.

Abstract: A pipe installation including conductive first and second pipes installed in a fuel tank; and a fitting which connects the first and second pipes and enables fluid to flow through the pipes via a conduit in the fitting. The fitting is attached to the first or second pipe by a flexible joint which permits relative movement between the fitting and the first or second pipe. The fitting is attached to a structure of the fuel tank. The fitting provides a path of least electrical resistance between the first or second pipe and the structure, and the path of least electrical resistance has a resistance between 50? and 100M?.

Abstract: A method and system for assisting guidance of an aircraft along a runway approach axis. The method includes acquiring a position deviation between a current position of the aircraft and the approach axis, determining an angle between a longitudinal axis of the aircraft and the approach axis, and determining a lateral offset of the trajectory of the aircraft likely to result from a maneuver of alignment of the longitudinal axis of the aircraft with the runway during the landing of the aircraft. A lateral trajectory correction is computed as a function of the lateral trajectory offset. This position deviation is corrected by adding the lateral trajectory correction to it. This position deviation is transmitted to the device for guiding the aircraft.

Abstract: An aircraft having at least one thrust providing jet engine and a fuselage with an integrated pressurized cabin includes an environmental control system having at least one pneumatic air cycle air conditioning unit, a bleed air port in the at least one thrust providing jet engine, a non thrust providing auxiliary supply unit configured to provide electricity and compressed air on ground and during flight, and at least one compressed air line. The at least one compressed air line is coupled with the bleed air port and the auxiliary supply unit. The environmental control system is coupled with the at least one compressed air line. Further, the auxiliary supply unit is dimensioned to exclusively operate the environmental control system by delivering compressed air, and bleed air from the bleed air port is selectively providable to the environmental control system for redundancy.

Abstract: A device and method for moving cargo above a floor inside an aircraft comprises a rigid under-floor. The device comprises a body part for supporting the weight of the cargo, lifting means and for lowering the body part from its lifted position into a retracted position, and a drive unit for moving the body part. The method comprises the steps of providing at least two devices in an aircraft, positioning the devices beneath the cargo, wherein the body parts of the devices are in their retracted positions. The body parts are lifted such that the weight of the cargo is supported by the body parts and the cargo is lifted above the floor. The cargo is then moved to a desired position and lowered into their retracted positions such that the cargo is lowered and the devices are moved away vertically from the cargo.

Abstract: A flight management system for an aircraft and method of securing open world data using such a system. The flight management system includes at least two flight management computers including one computer termed active forming part of an active guidance subsystem configured to supply data for guiding the aircraft. Another computer is termed inactive at the current time. The flight management system includes a validation subsystem that includes the inactive flight management computer and a validation unit connected to the flight management computers. The validation subsystem is independent of the active guidance subsystem and configured to validate open world data and to transmit at least to the active flight management computer data that is validated during the validation.

Abstract: The disclosure herein describes an aircraft assembly tracker system including a user interface configured to display an aircraft part under assembly and overlay one or more zones on the displayed part. The user interface operates on a computing device. The zones represent different panels to be affixed to the aircraft during assembly and their shape displayed on the user interface is identical to the shape of their corresponding panel being affixed to the physical aircraft part. The aircraft assembly tracker system monitors the assembly progress of each zone and automatically alerts aircraft assembly workers when the zone is ready for closure.

Abstract: The runway state determined on the ground by an aircraft and provided to the aircraft on approach does not make it possible to account for possible degradation of the runway occurring since the previous determination of that runway state. Updating of this runway state on the basis of a simple comparison between a desired deceleration and an observed deceleration resulting from a degraded runway is not satisfactory either. The disclosure herein thus provides for obtaining a local stopping distance according to a local runway state characterizing a runway zone on which the aircraft is in movement at the time of the landing, this local stopping distance being estimated based on local measurements made in the aircraft; obtaining a reference stopping distance according to a reference runway state; then comparing these two distances with each other to determine whether the local runway state is more degraded than the reference runway state.

Abstract: A pressure bulkhead for an aircraft comprising a fuselage. The pressure bulkhead comprises an inflatable element, suitable for being filled with air, which in turn comprises a cover which delimits an inner zone. The pressure bulkhead further comprises a seal suitable for providing an airtight seal between the cover and the fuselage of the aircraft.

Abstract: A device for providing reinforcement strand loops for a multi-needle system for mechanically reinforcing a component made of a foamed plastics material, has a profile body, at least two clamps positioned on the periphery and/or end face of the profile body for fixing a reinforcement strand to the profile body, at least one slider which can be moved in parallel with a central longitudinal axis of the profile body to produce a reinforcement strand loop, at least two separators positioned in the periphery and/or end face of the profile body for separating the reinforcement strand loop from the reinforcement strand and a feeder for feeding the reinforcement strand loop. As a result, reinforcement strand loops can be produced with high precision and individually presented to the needles and/or grippers of a multi-needle system.

Abstract: The embodiments relate to a method for additive manufacturing of a component made from a metal matrix composite for a vehicle. In a step of the method, a plurality of elongated filaments is provided. In another step, metallic powder is provided. In a further step, the metal matrix composite component is additively manufactured by melting the metallic powder.

Abstract: A cyclonic separator with an inlet, a fuel outlet, an inner wall comprising a water-permeable material, an outer wall, a cavity between the inner wall and the outer wall, and a water outlet. The cyclonic separator is adapted to discharge water from the water outlet via the cavity and relatively less dense liquid fuel from the fuel outlet. The water-permeable material enables water in the cyclonic separator to flow through the water-permeable material into the cavity, but substantially prevents liquid fuel in the cyclonic separator from doing so.

Abstract: A clip for fastening a pipe to a support, comprising a fixed part, a mobile part, a first joint connecting a first edge of the fixed part and a first end of the mobile part, and a system for holding the mobile part a closed state. The system comprises a lever and a second joint connecting the lever to a second end of the mobile part, and an angled U-shape connected to the second edge of the fixed part, configured to permit the lever and the second joint to pass through the angled U-shape and to permit the lever to be positioned in a folded position against an external face of the mobile part to hold the mobile part in the closed state.

Abstract: In a method for detecting damage to a component of an aircraft, having an unpressurized first area and a pressurized second area, at least one theoretical pressure parameter, characteristic of a theoretical pressure in the unpressurized first area, a theoretical pressure in the pressurized second area or a theoretical pressure difference between the unpressurized first area and the pressurized second area, is determined. At least one actual pressure parameter, characteristic of an actual pressure in the unpressurized first area, an actual pressure in the pressurized second area or an actual pressure difference between the unpressurized first area and the pressurized second area, is recorded. The theoretical pressure parameter is compared with the actual pressure parameter. Damage to a component of the aircraft causing a compression of the unpressurized first area is detected when a difference between the theoretical pressure parameter and the actual pressure parameter exceeds a threshold value.

Abstract: A structural component includes a composite laminate built up of a plurality of layers of carbon fibers, wherein the layers of carbon fibers are oriented in different directions, wherein the carbon fibers are surrounded by a conductive polymer resin, wherein the carbon fibers of at least one of the layers comprise an electrically insulating coating, and wherein at least one of the coated carbon fibers extend through its respective layer to form an electrical connection between ends of the layer spaced apart from one another.

Abstract: Lavatories on-board a vehicle, and in particular to a lavatory unit for use by persons with reduced mobility on-board a vehicle are described. The lavatory unit includes a lavatory housing structure enclosing a lavatory interior space, a door opening in the lavatory housing structure, a toilet assembly inside the lavatory interior space, and a transition seating support for a user. The transition seating support provides a first transfer position and a second transfer position. In the first transfer position, in an open door state the transition seating support is directly accessible for a person sitting in a wheelchair that is located at least partly outside the lavatory unit such that the person can transfer to the transition seating support and vice versa, and in the second transfer position, a person sitting on the transition seating support can transfer to the toilet assembly and vice versa.

Abstract: A seat arrangement includes a first group of seats having first and second passenger seats, a second group of seats having third and fourth passenger seats, a first aisle parallel to a longitudinal axis, and a second aisle parallel to the longitudinal axis. The first passenger seat is situated next to the first aisle with a seat direction parallel thereto, and the fourth passenger seat is situated next to the second aisle with a seat direction parallel thereto. The seat direction of the second passenger seat is angled by at least 2° relative to the seat direction of the first passenger seat. The seat direction of the third passenger seat is angled by at least 2° relative to the seat direction of the fourth passenger seat. The first and second groups are next to each other, and have a longitudinal offset relative to each other along the longitudinal axis.

Abstract: A method for manufacturing an aircraft floor rail includes a step of manufacturing, separately, a first part of the floor rail, comprising at least a first flange, from a corrosion-resistant first material, and a second part of the floor rail, comprising at least a second flange, from a second material having a density that is different from, in particular lower than, that of the first material, and a step of assembling the first and second parts of the floor rail by crimping.

Abstract: A reinforcing arrangement for an opening in an aircraft fuselage structure has a fuselage skin having an inner side, an outer side and a first opening with a first opening contour, and a one-piece reinforcing structure having a thickening section and at least one projecting profile. The first opening contour is surrounded on the inner side of the fuselage skin by an opening edge surface having a thickness corresponding to a thickness of the fuselage skin surrounding the opening edge surface. The thickening section has a bearing surface matched to the opening edge surface and has a receiving section facing away from the bearing surface and surrounding a second opening. The bearing surface is in surface contact with the opening edge surface, and the reinforcing structure is connected to the fuselage skin, with the result that the first opening and the second opening lie one above the other.

Abstract: A vortex generator arrangement for an aircraft comprising a surface section forming a flow surface interacting with a flow surrounding the aircraft in operation, wherein the surface section comprises an opening, a vortex generator movable between a retracted position and an extended position, a retainer for holding the vortex generator in the retracted position, a biasing structure for biasing the vortex generator towards the extended position and a release for releasing the vortex generator from the retainer such that the vortex generator can be moved towards the extended position. Further, a sealing membrane is provided completely sealing the opening when the vortex generator is in the retracted position. The vortex generator is movable through the membrane from the retracted position to the extended position. Furthermore, a flow control system, an aircraft and a method of controlling flow are described and claimed.