Abstract: A device and method for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces.

Abstract: Device for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces. Set of fuselage sections assembled by means of a device of the type described above. Method of assembling two fuselage sections by means of a device of the type described above.

Abstract: A propulsion system for an aircraft, including a dual-flow turbojet and a mounting structure for mounting this turbojet on the wing surface or on the fuselage of an aircraft. The mounting structure includes an aft aerodynamic fairing including a thermal protection floor to protect the mounting structure from the heat of a primary airstream channelled by an exhaust nozzle of the turbojet, as well as an air inlet provided in a longitudinal aerodynamic wall washed by a secondary airstream of the turbojet and delimiting together with an other similar wall a cavity isolated from the secondary airstream for extracting a cooling airstream from the secondary airstream, and air circulation means fed by the air inlet and having at least one outlet aperture emerging in a space between the thermal protection floor and the exhaust nozzle.

Abstract: The invention relates to a device for the detection of defects in a recess, comprising a longitudinal hollow body (107), a movement conversion means (109) housed in said body (107) and installed free to move along the longitudinal direction, and at least one sensor (11) coupled to said body (107) and to said conversion means (109) such that longitudinal translation of the conversion means will move said sensor (11) in transverse translation between a retracted position and an extended position.

Abstract: A device for repairing defects in an internal layer of a structure, for example, an aircraft. The device includes a cylindrical body which rotates around its axial direction, a movement conversion device housed in the cylindrical body and assembled such that it is able to move in the axial direction, a configuration device able to cause the displacement of the conversion device by an axial traveling motion, and a cutting element coupled to the cylindrical body and to the conversion device such that the cutting element is able to be made to rotate by the cylindrical body and to be made to move with a radial displacement by the conversion device between a folded position and a deployed position through an opening defined in the cylindrical body in order to machine the internal layer with a cut which depends on the axial displacement of the conversion device.

Abstract: A method for transmitting data, between an on-board segment on board an aircraft and on the ground, via a plurality of access networks. The on-board segment transmits to the ground information providing the association between the access networks and the corresponding IP addresses of the aircraft via these different networks. This information is used by a segment on the ground to make up and update a look-up table between identifiers of the access network and IP addresses of the aircraft. For transmitting a packet on the uplink, the recipient IP address is selected from IP addresses appearing in the look-up table.

Abstract: A device for mounting an aircraft engine, including a rigid structure, an engine attachment including a connecting plate superposed to an associated connecting plate of said rigid structure, and means for mutually tightening said plates comprising at least one wedge-effect tightening block and corresponding bearing surfaces of said plates which are conformed so that, when each tightening block is applied against said bearing surfaces along a direction parallel to the plane of the contact surface between both of these plates, this block exerts by a wedge-effect a force for tightening these plates against each other along a direction perpendicular to said plane.

Abstract: A wing box rib (13), joining an aircraft wing (3) to the wing box and to the rest of the structure, extends advantageously over an adjacent part of the fuselage (2), having in particular an upper line (14) situated above a junction line (15) of the wing upper surface panel (3). The connection is simplified, as is the structure of the aircraft and its manufacture, a lightening is possible, and the transmission of stresses takes place in a more favourable manner.

Abstract: The invention relates to an aircraft engine attachment pylon, comprising a box formed by the assembly of a first spar (18), a second spar (20) and two lateral panels (22), the pylon also comprising an aft engine attachment (8) fitted with an aft attachment body (54), and also provided with two lateral fittings (26) associated with the two lateral panels (22) to which they are fixed and from which they project laterally outside the caisson, each fitting (26) forming a plane attachment interface (36) with the attachment body (54) through which bolts pass (56). According to the invention, each interface (36) is in the shape of a straight segment inclined at 45° from the vertical direction (Z) as seen in section on any transverse plane of the pylon passing through it.

Abstract: A stairway used for gaining access from a theoretically horizontal lower level to a theoretically horizontal higher level, and including a succession of intermediate steps between these two levels. A subassembly of intermediate steps corresponding to the steps closest to the lower level is mobile between a first deployed position at which the lower intermediate steps are in the extension of other intermediate steps, and a raised position at which the lower intermediate steps are in a substantially vertical position.

Abstract: An engine mounting structure for an engine aircraft including a rigid structure forming a caisson, together with an engine mounting system mounted on the structure, and a rear engine attachment, including an attachment strut to which is connected at least one shackle, to be connected to the engine. The engine mounting system includes a system for transmitting thrust efforts generated by the engine, including two lateral connecting rods connected to a spreader beam mounted in articulated fashion relative to the caisson. The attachment strut constitutes the spreader beam, wherein the body is mounted in articulated fashion relative to the caisson using an articulated shaft system.

Abstract: An engine unit for an aircraft including a turboprop engine and its device for mounting on to a wing surface. The device includes a rigid structure and a mechanism for fastening the turboprop engine on to this structure. The fastening mechanism includes six mutually independent hydraulic systems, each one exclusively dedicated to the transfer, to the rigid structure, of forces exerted respectively according to one of the six degrees of freedom of movement. Each hydraulic system includes at least one hydraulic jack with a piston attached to one of the two elements, i.e. either the turboprop engine or the rigid structure, together with a cylinder housing the piston and attached to the other of the two elements.

Abstract: An aircraft engine assembly including a turbojet, a turbojet attachment pylon, and a nacelle mounted on the attachment pylon and surrounding the turbojet. The nacelle includes at least one mobile nacelle portion forming a single piece envelope all around a section of the turbojet, this mobile nacelle portion being mounted free to slide on the attachment pylon so that it can be moved from the forward position in the aft direction, and vice versa.

Abstract: A propeller for an aircraft turbine engine comprising a plurality of vanes as well as a hub having a plurality of accommodating ports receiving the bases of said vanes, each vane base being rotatably mounted in its associated accommodating port. The propeller also has at least one vane retaining ring structure in the radial direction outwardly from the hub, being cladded around the latter.

Abstract: The invention relates to a method and a device for checking a communication system (3) comprising a plurality of modules (7) adapted to be installed in an aircraft under development (5), said checking device including: means (11) for building an identification and synchronization database (17) for said communication system (3), said database contractually defining interfaces between said plurality of modules from change notes relative to an initial technical definition, means (11) for defining, in said database (17), signals configured to be exchanged between said plurality of modules (7) via a plurality of connections (3) interconnecting said interfaces, said signals being defined to be synchronized with each other as well as with the physical materialization of said connections, and means (11) for checking, before an evaluation of a maturation test of the communication system (3), an interface consistency for all of said signals of said database (17).

Abstract: The invention relates to a process and an on-board system for evaluating flight strategies aboard an aircraft, linked with a flight plan (13) of the aircraft, including: calculation means (5) for determining relations between the flight parameters including parameters of time, of fuel quantity, of altitude and of speed, interface means (9) for providing at least one envelope of values (25a-25d) representative of a domain of definition of a plurality of flight strategies, interface means (9) for providing at least one determined strategy defined by determined values assumed by the flight parameters at a reference point, interface means (9) to allow the selection and setting of the value of a first parameter among said flight parameters, generating and supplying another envelope of values allowing exploration of another plurality of possible strategies, and interface means (9) to allow the selection and setting of the value of a second parameter, generating and supplying another determined strategy.

Abstract: A securing mast for securing an engine to the wing of an aircraft, wherein the device includes two fasteners, a first eng of each fastener being secured to the engine and the second end of each fastener being secured to the wing, wherein the fasteners include hinged junction means capable of modifying the geometry of the aforementioned fasteners in order to modify a distance between the engine and the wing.

Abstract: The invention relates to a flight control system for an aircraft comprising control surfaces (111, 211, 331, 431, 541, 121-225), and actuators associated with said control surfaces to control flight functions of roll, yaw, pitching and aerodynamic braking of the aircraft. All of the actuators (111a1-211a2, 121a-225a) associated with the control surfaces controlling at least one of said flight functions are electromechanical actuators. A part of said control surfaces associated with the electromechanical actuators are divided control surfaces (111, 211, 331, 431, 541), each of said divided control surfaces being composed of at least two independent surfaces (113, 114, . . .

Abstract: An aircraft cockpit that includes comfort and/or security adjustable equipment in which the adjustments are controlled by an adjustment management system so that, by the unique selection of a position desired by the pilot from at least two positions, the adjustment of each of the aforementioned members is modified from a current value to a predetermined value characteristic of the selected position and depending on the pilot. The data characteristic of the members adjustments controlled by the adjustment management system and depending on the pilot are stored in a mobile medium and read by a means for recognizing the aforementioned management system. The adjustments controlled by the adjustment management system can relate to piloting seats, piloting rudder bars, piloting armrests, individual aeration systems and individual lighting systems.

Abstract: The invention relates to a pylon (14) for attaching a turbo-shaft aircraft engine designed to be laterally offset on a rear part of the aircraft structure, where the pylon possesses an aerodynamic profile which includes a leading edge (16), as well as a first hot air distribution channel (30) passing along the leading edge in order to provide anti-icing, where this engine attachment pylon includes moreover a second hot air channel (36) belonging to a system for supplying pressurised air to the aircraft. According to the invention the second channel (36) is housed inside the first channel (30).