Abstract: A method of synthetic visualization of a scene viewed from an aircraft and synthetic vision system. The system includes a processing unit for generating a synthetic image of a scene ahead of the aircraft, a unit for displaying on a visualization screen a background image corresponding to this synthetic image and symbols for piloting the aircraft, and a monitoring device including a unit for generating at least two virtual control elements, representations of the control elements integrated into the synthetic image, a unit for detecting on the synthetic image the representations and their position, and a unit for verifying whether these positions are consistent with position of a line of zero pitch and/or of a line of zero roll of the aircraft, the display being carried out only in case of consistency between these positions, that is to say the absence of any problem of orientation of the synthetic image.

Abstract: An aircraft passenger cabin area comprises a main aisle extending substantially parallel to a longitudinal axis of the aircraft passenger cabin area, a restricted area, wherein a non-encroachable safety area is defined in the region of the restricted area, a transverse aisle connecting the main aisle to the restricted area and at least one passenger seat comprising a rigid carrier structure, a backrest and a seat element and arranged in the passenger cabin area adjacent to the transverse aisle such that the seat element faces the transverse aisle. The seat element is displaceable, relative to the backrest and carrier structure, in a direction substantially perpendicular to a longitudinal axis of the transverse aisle between a usable position and an out-of-use position. In its usable position, the seat element, protrudes into the safety area, but, in its out-of-use position, the seat element clears the safety area.

Abstract: A passenger seat arrangement for installation in an aircraft comprises a seat unit with a backrest element and a seat element. The seat arrangement also comprises a supporting frame carrying the seat unit and comprising at least one seat mounting, which has a first backrest holder, to which the backrest element can be releasably fixed in a load-transferring manner in a first position on the seat mounting, and a second backrest holder, to which the backrest element can be releasably fixed in a load-transferring manner in a second position on the seat mounting. When the passenger seat arrangement is installed in the aircraft, the backrest element is pivoted in relation to a longitudinal axis of the aircraft in a state in which it is fixed to the first backrest holder relative to a state in which it is fixed to the second backrest holder.

Abstract: An engine attachment system comprising an engine pylon with a top wall, a bottom wall and two lateral walls, and a front engine attachment with a beam which bears two connecting rods for fixing the engine. The engine attachment system also comprises an intermediate piece with a bottom wall and four lateral walls, wherein the beam is fixed against an outer face of the bottom wall, wherein the intermediate piece is fitted at a front-end face of the engine pylon in such a way that an inner face of the bottom wall comes against the front-end face of the engine pylon, and in such a way that the lateral walls of the intermediate piece are superposed with the walls of the engine pylon. In such an engine attachment system, the front engine attachment is thus located on the front-end face of the engine pylon, allowing a space saving.

Abstract: An electrical link (8) between a DC high-voltage power source (2) and a user apparatus (5) including: an electrical conductor (4) surrounded by an insulating cover (4a), and an electrical protection device (3) that includes a conductive sleeve (7) arranged around the insulating cover (4a), a current generator (10) connected to a current injection point (30) of the conductive sleeve (7), a circuit breaker (9) arranged on the conductor and configured to cut off a current transiting through the conductor (4), and a detection module (11) connected to a current tap-off point (31) of the conductive sleeve (7) and to the circuit breaker (9) and configured to detect a current leak out of the conductor (4) and command the circuit breaker (9).

Abstract: The invention relates to a fastening unit (100) for movably fastening an aircraft component (300) to a support structure (400) of an aircraft (500). The fastening unit (100) has a connection element (5) having a hole (5a). The fastening unit (100) also has a first support arm (1) having a first end (1a) for connecting to the support structure (400) of the aircraft (500) and having a second end (1b) for connecting to the connection element (5). The fastening unit (100) also has a second support arm (2) having a first end in (2a) for connecting to the support structure (400) of the aircraft (500) and having a second end (2b) for connecting to the connection element (5).

Abstract: A safety open and closing system for an overpressure door on fuselage of an aircraft. Wherein the safety opening and closing system allows safe access through the overpressure door to the compartment. The safety open and closing system including an assembly of a hollow beam, a blocking bar in the hollow beam, a spring biasing the blocking bar with respect to the hollow beam and a lever at the end of the blocking beam which pivots between a position A that allows closure of the overpressure door and a position B preventing closure of the door.

Abstract: An airfoil comprising a main wing and a high-lift body. The high-lift body defines a concave recess. The airfoil further comprises a sealing device having two sealing elements arranged in the concave recess. The sealing elements are plate-shaped and abut sectionally on the high-lift body and have side faces extending perpendicularly to the common rotational axis. When the high-lift body is moved between a retracted position and a deployed position, the sealing elements rotate relative to the main wing and relative to each other, such that an overlap between the sealing elements is smaller when the high-lift body is in the deployed position than when the high-lift body is in the retracted position.

Abstract: A landing gear system for an aircraft includes a retractable landing gear assembly, a hydraulic actuator for actuating movement part, for example a bogie of the landing gear assembly, and an accumulator associated with the actuator. The accumulator comprises a volume of pressurised gas separated from hydraulic fluid by a separator piston. Travel of the separator piston beyond a certain position is indicative of a fault. The accumulator includes a snubbing device that acts to slow movement of the separator piston beyond that position. A monitoring system measures the time taken for the movement of the landing gear part effected by the hydraulic actuator. If the measured time is longer than a threshold time, that is indicative of a possible fault in the accumulator, that might, without the snubbing, remain undetected and/or hidden from view.

Abstract: Disclosed is a landing gear bogie pitch trimmer, comprising a hydraulic actuator for adjusting a pitch of a landing gear bogie, in use, a fluid interface for receiving, from an aircraft hydraulic system external to the landing gear bogie pitch trimmer, hydraulic fluid for use in actuating the hydraulic actuator, and a flow control valve for controlling flow of the hydraulic fluid through the fluid interface in use. Also disclosed is a system, a landing gear controller, a method, and an aircraft.

Abstract: A color based heating system is disclosed. A film for repair of aircraft components of fiber reinforced plastic has color changing properties that can include being temperature-dependent. The color changing properties can be reversible. A system for heating a repair site of a component of fiber reinforced plastic includes the film, a camera and a heating plate. The heating plate can have individually controllable heating zones. A controller can use local color signals of the camera for locally controlling local heating zones of the heating plate. The controller can assign local color signals of the camera to temperatures.

Abstract: An aircraft comprises a fuselage, at least a first electrical generator and a second electrical generator, a set of electrical equipment items distributed in the fuselage and an electrical power distribution network comprising a switching system and a set of buses. The buses comprise at least a first bus and a second bus extending, at least partly, in a longitudinal direction of the fuselage and following segregated paths in the fuselage. In a normal mode of operation, the switching system links the first electrical generator to the first bus and the second electrical generator to the second bus. Each bus comprises connection points at different locations distributed along its length and each of the electrical equipment items is linked to a connection point of a bus via a local electrical power supply link.

Abstract: In a manufacturing method for a component, a clamping force is applied perpendicular to a surface of a first portion of a semifinished product containing reinforcing fibers via opposing first clamping surfaces of a first clamping tool. A clamping force is applied perpendicular to a surface of a second portion of the semifinished product via mutually opposing first clamping surfaces of a second clamping tool, spaced a first distance from the first clamping tool. A shaping device deforms a third portion of the semifinished product lying between the first and the second portions to form a first subportion and an opposite second subportion. The first distance is reduced to a second distance. A clamping force is applied perpendicular to the surfaces of the first and second subportions via a second clamping surface of the first clamping tool and an opposite second clamping surface of the second clamping tool.

Abstract: A laminated glazing includes a first and a second glass sheet that are bonded by a first interlayer adhesive layer, a peripheral zone of the laminated glazing being covered by a stepped metal element, a window press that is rigidly connected to the structure for mounting the laminated glazing making contact with the laminated glazing, so as to hold the laminated glazing secure to its mounting structure, an electrical conductor linking the stepped metal element and the structure for mounting the laminated glazing by way of the window press.

Abstract: A folding wing having a wing tip device (3) rotatable between flight and ground configurations, about an Euler axis of rotation (11). The wing tip device (3) and a fixed wing (1) are separated along an oblique cut plane (13) passing through the upper and lower surfaces of the folding wing. A rotational joint (15) for coupling the wing tip device (3) to the fixed wing (1) during rotation between the ground and flight configurations. The rotational joint includes a follower (17a) and a guide (17b), one which being fixed relative to the wing tip device and the other being fixed relative to the fixed wing. The follower and guide interlock such as by interlocking rings. The follower is received in the guide such that during rotation between the ground and flight configurations the follower moves along the arcuate path defined by the guide.

Abstract: A leading edge skin panel for an aerodynamic structure of an aircraft. The skin panel includes attachment components for attaching the leading edge skin panel to the structure. A primary attachment component is configured to substantially prevent spanwise relative movement between the leading edge skin panel and the structure. The remaining attachment component are configured to permit a predetermined amount of spanwise relative movement between the leading edge skin panel and the structure.

Abstract: An aircraft air conditioning system comprising an air conditioning unit adapted and configured to be supplied with compressed process air and to generate cold fresh air, a mixer adapted and configured to mix the cold fresh air from the air conditioning unit with recirculation air recirculated from an aircraft region to be air conditioned, an air outlet adapted and configured to direct mixed air from the mixer into the aircraft region, a first sensor adapted and configured to detect an actual temperature in the aircraft region, a second sensor adapted and configured to detect a temperature of the mixed air directed into the aircraft region, and a control unit adapted and configured to control an operation of the air conditioning unit in dependence on a difference between the temperature of the mixed air directed into the aircraft region and the actual temperature in the aircraft region.

Abstract: An aircraft door hinge assembly, comprising a door with an outer skin and a frame provided with at least one lug; a fuselage frame provided with at least one clevis configured to be pivotally attached to the lug with a hinge pin so that the door is pivotable relative to the fuselage door frame about a hinge line; a rotatable filler pivotally mounted, at a proximal end, within a gap provided by the clevis; and, a fixed filler having a proximal end fixedly attached to an outermost surface of the lug adjacent to the hinge line, and having a distal end configured to overlap the distal end of the rotatable filler, such that the fixed filler limits rotation of the rotatable filler.

Abstract: A lifting surface comprising a movable discontinuity located in the surface of the lifting surface. The movable discontinuity is movable between an active position in which the movable discontinuity acts as vortex generator, and a passive position in which the movable discontinuity is integrated into the surface of the lifting surface without acting as vortex generator. The lifting surface may be in an elevator, the elevator being rotatable around a hinge line with respect to the rest of the lifting surface. A bar is rigidly joined to the elevator. The bar, the elevator and the movable discontinuity are configured such that when the elevator rotates with respect to the rest of the lifting surface, the bar moves the movable discontinuity that departs from the surface of the lifting surface, acting as a vortex generator.

Abstract: An arrangement in a cabin of a vehicle has a plurality of cabin monuments, placeable in rows, of which the lateral surfaces are in laminar contact, said cabin monuments having a front side and a rear side and a wall surface of the aircraft fuselage, at least sections of which face toward the cabin of the vehicle and are not aligned parallel with a lengthwise axis of the cabin. The cabin monuments are arranged in rows parallel to the lengthwise axis of the cabin, so that the front sides and the rear sides are each aligned parallel to the lengthwise axis of the cabin. The rear sides of at least two cabin monuments, each of which include storage space for cabin trolleys, are positioned with an offset relative to each other in a direction transverse to the lengthwise axis of the cabin.