Abstract: An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.

Abstract: The method for fitting a sheath on a cable harness includes a series of steps including determining the length of sheath to be used, mounting the sheath on a mounting tool of tubular shape, inserting the cable harness into the mounting tool, removing the mounting tool and arranging the sheath around the cable harness, fitting a sheath stop at one of the ends of the sheath, the sheath stop fastening the end of the sheath to the cable harness stretching the sheath over the cable harness so as to extend it and tension it, and fitting a sheath stop at the other one of the ends of the sheath.

Abstract: A brake temperature sensing system for an aircraft including a sensor apparatus and an interrogation apparatus. The sensor apparatus includes a temperature sensor for attachment to a brake disc of an aircraft brake, and a relay for attachment to the brake. The temperature sensor is configured to wirelessly transmit a measurement signal containing information relating to a temperature of the brake disc, responsive to receiving a wireless interrogation signal. The relay is configured to receive an interrogation signal from the interrogation apparatus; wirelessly transmit the interrogation signal to the temperature sensor; receive the wireless measurement signal from the temperature sensor; and transmit the received measurement signal. The interrogation apparatus comprises a controller configured to generate an interrogation signal; and a transceiver configured to transmit the generated interrogation signal to the sensor apparatus; and receive the measurement signal transmitted by the sensor apparatus.

Abstract: A method for repairing a structure comprising at least one zone to be heated and which comprises the steps of inflating a frame to form a framework, attaching panels removably to the frame to form an enclosure referred to as a heating enclosure, positioning the enclosure over the zone, heating the interior space of the enclosure using a heating device.

Abstract: The invention relates to a braiding bobbin for a braiding device. The braiding bobbin includes a cylindrical braiding spool, from which a previously wound, multilayer ribbon can be unwound, wherein a first layer of the ribbon consists of a pre-impregnated fiber film, and a second layer of the ribbon consists of a protective film. In addition, the braiding bobbin includes a bracket to which the braiding spool is frontally and rotatably fastened. Additionally provided for the braiding bobbin is a cylindrical additional spool for winding the protective film of the unwound ribbon and a deflection element. The deflection element is fastened to the bracket, wherein the deflection element is secured spaced apart in the radial direction R to the braiding spool and designed for deflecting the protective film from the braiding spool to the additional spool.

Abstract: An insulation component to be attached to a fuselage structure of an aircraft. The insulation component extends in a planar manner, and at least one peripheral recess, running transversely to the at least one longitudinal recess, is formed in a first surface of the insulation component configured to receive a respective associated peripheral support of the fuselage structure.

Abstract: A cabin monument for an aircraft. The cabin monument has a framework with a base frame and a frame structure connected to the base frame, and side walls fastened to the frame structure. By fastening the side walls to the structural struts of the frame structure, a mechanical load acting on the cabin monument is distributed between the framework and the side walls.

Abstract: A vehicle cabin seat rail system includes a seat rail having a top side having a plurality of raster openings and mechanically couplable with a cabin floor, a plurality of holding devices positionable on the top side, each being selectively engageable with at least one first raster opening or at least one second raster opening for arresting the holding device and configured for holding an object on the seat rail, and a plurality of marking devices couplable with the seat rail, and configured for optically or mechanically indicating approaching of a first position on the seat rail corresponding to the first raster opening of a respective holding device and of a second position of the same holding device corresponding to the second raster opening, in relation to another object arrested on the seat rail, to prevent an arresting of the holding device on the seat rail on other positions.

Abstract: To reduce the overall mass of an engine assembly for aircraft, this assembly comprises a part of the fuselage of an aircraft, a turbomachine comprising an unfaired propeller, together with an annular row of unfaired after-guide vanes located aft of the propeller and rotationally fixed in relation to a longitudinal axis of the turbomachine, and a mounting pylon. At least part of the leading edge of the pylon is incorporated within the annular row between two after-guide vanes.

Abstract: An aircraft bipolar high-voltage network includes a DC voltage converter comprising two unipolar input connections, two bipolar output connections and a reference potential connection, and at least one unipolar device having two electrical connections which are each coupled to one of the two unipolar input connections. The DC voltage converter has a first DC voltage converter module coupled to a first of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a first of the bipolar output connections via a module output connection, and a second DC voltage converter module coupled to a second of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a second of the bipolar output connections via a module output connection.

Abstract: The present application relates to a fuel flow system. In particular, the application relates to a fuel flow system for an aircraft. The fuel flow system has a fuel conduit having a fuel inflow and a fuel outflow along which a fuel/water mix is configured to flow from the fuel inflow to the fuel outflow. The fuel conduit is fluidly communicable with a fuel tank. A peripheral conduit surrounds at least part of the fuel conduit. A water-permeable member is disposed between the fuel conduit and the peripheral conduit. The water-permeable member enables water from the fuel/water mix to flow through the water-permeable member from the fuel conduit into the peripheral conduit, but at least substantially prevents liquid fuel from the fuel/water mix from doing so.

Abstract: An aircraft comprises a landing gear assembly on a part of which is mounted a motor for driving a wheel of the landing gear assembly, for example to enable the aircraft to perform taxiing manoeuvres. The motor is a liquid-cooled motor and the liquid that is used to cool the motor is hydraulic fluid, preferably hydraulic fluid taken from a hydraulic system that already exists on the aircraft to supply other consumers of hydraulic fluid pressure on the aircraft. The hydraulic fluid thus has other utility (i.e. other than cooling the motor) on the aircraft and therefore has a significant volume (and therefore a significant heat capacity). There may be a need to convert from high pressure hydraulic fluid to a lower pressure supply.

Abstract: A method for producing a connecting device for connecting films with conductor tracks includes the steps of laying a first film with conductor tracks onto a forming die, applying a first lower shell of a plastic material onto a first end portion of the forming die, producing a cut-out and shifting the first film so that the cut-out lies completely on the first lower shell, applying upper conductor tracks of a conductive material onto the first lower shell so that the upper conductor tracks overlap with the conductor tracks of the first film, and applying a first upper shell of a plastic material onto the first lower shell so that the first film, the first lower shell and the first upper shell connect together by substance bonding to form a first connector. In this way, an integral connector can be provided on each film.

Abstract: A monitoring device comprising a monitoring pattern signal generating module, a calibration pattern signal generating module, a mixer module for mixing an input signal with the monitoring pattern signal and the calibration pattern signals, a recognition module configured to recognize the monitoring pattern signal, at least one calculation module for calculating at least one offset error and at least one gain error, a transmission module for transmitting a signal of proper operation or of faulty operation to a user device depending on whether the monitoring pattern signal is recognized or not recognized by the recognition module and a transmission module for transmitting a signal representative of the offset error and a signal representative of the gain error.

Abstract: A method of measuring a height of a fuel in an aircraft fuel tank (21)b including illuminating the fuel in the aircraft fuel tank and detecting reflected light from the fuel. Optical coherence tomography is used to determine the height of a surface of fuel in the fuel tank. An apparatus (30) is used to measure a height of a surface of fuel in an aircraft fuel tank, and an aircraft fuel tank system with a fuel tank and an apparatus for measuring a height of a surface of fuel in the aircraft fuel tank.

Abstract: A turbofan comprising a fan casing and a nacelle comprising a cowl translatable between an advanced position and a pushed-back position in which the mobile cowl and the fan casing define a window therebetween. The nacelle also comprises reverser flaps, each reverser flap being mounted in a linked manner on the mobile assembly between a closed position in which it obstructs the window and an open position in which it does not obstruct the window. The nacelle also has an impelling mechanism comprising a lever arm rotatable on the mobile assembly and having a roller, a connecting rod mounted rotatably between the reverser flap and the lever arm, and a channel receiving the roller, the channel having a front part parallel with the translation direction and a rear part extending after the front part and oriented inward as it progresses from the front toward the rear.

Abstract: Devices for protecting aircraft against bad weather. A device for protecting a wing of an aircraft including a load-bearing structure for a protective wall for the wing, the load-bearing structure having a supporting frame having at least two uprights linked by at least one cross member, at least one upright, at the end of the frame having a linking attachment arrangement permitting at least rotation about an axis perpendicular to the surface, the other uprights, each having one foot with an arrangement configured to facilitate the movement of the frame over the surface on which the frame rests. The protection device enables immediate, rapid and easy positioning requiring very few operators.

Abstract: The control device of a communication system of an aircraft having a predefined number of communication channels comprises a processing unit and one or more sets of buttons each associated with a communication channel. The number of sets of buttons is less than the predefined number of communication channels of the communication system. The device comprises a set of call buttons comprising at least one transmission button, and a display area on a display screen, this display area being associated with the set of call buttons. The processing unit is configured to display an indication in the display area associated with the set of call buttons when the communication system receives a call on a channel with which no set of buttons is associated and to select this channel for transmission following an action of a user on the transmission button of the set of call buttons.

Abstract: A wing (5) having a base section (5) and a tip section (13), the base section (7) having a first end portion (9) and a second end portion (11), the tip section (13) having a third end portion (15) and a fourth end portion (17), wherein the second end portion (11) and the third end portion (15) are coupled so that the tip section (13) is pivotable with respect to the base section (7) about a pivot axis (19, 19?), and an actuating arrangement having an actuator (21) which is coupled to the base section (7) and the tip section (13) and which is operable to effect a pivotal movement of the tip section (13) relative to the base section (7) between a stowed position and a deployed position.

Abstract: A device measures a flight parameter of an aircraft which has a radome. Systems measure the deformation of a wall of the radome due to forces exerted by the air on the radome. A computer computes the flight parameter from deformation measurements obtained by the systems. The systems have an optical fiber carried by the radome provided with Bragg gratings. Each fiber has a plurality of Bragg gratings distributed over a length of the fiber so as to distribute the Bragg gratings over the radome when the fiber is installed.