Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Airbus France

Technofan

Olivier Pautis

Jérôme Colmagro

Jonathan Blanc

Michael Berjot

Wolfgang Brochard

Paolo Messina

Germain Gueneau

Lionel Czapla

Laurent Lafont

Thomas Robiglio

Pierre-Antoine Combes

Rohan Nanda

William Tulloch

Adeline Soulie

Frédéric Ridray

Pascal Chaumel

Frédéric Piard

Eric Bouchet

Olivier Dubois

Pat Broomfield

Francis Dazet

Stéphane Combes

Jean-Michel Rogero

Olivier Barbara

Pascal Gougeon

Laurent Tizac

Cédric Poupon

David Ewens

Paul-Adrien Taveau

Marc De Nicola

Laurent Agostini

Thomas Firmignac

Pascal Martinez

Jean-Baptiste Vignes

Jean Michel Rogero

Umberto Gastaldi

Nicolas Sentenac

Laurent Frenot

An assembly comprising a wing with a lower surface panel and an upper surface panel and an engine pylon comprising a primary structure fixed to the wing with a fixing base. The fixing base comprises fourth fixing yokes while the primary structure bears fourth fittings, the fourth fixing yokes being secured to the fourth fittings with fourth rods.

Assembly for an aircraft comprising a wing and an engine pylon for coupling a propulsion system to said wing

An aircraft having a fixed structure, an engine pylon, and a cowling system, a slider bearing a rear cowl and able to move in translation from an advanced position to a retracted position, a displacement system having, on either side of a median plane of the engine pylon, a guide as one with the fixed structure, a sliding element as one with the slider and sliding along each guide disposed on the same side, and a support as one with the fixed structure and having a blade parallel to the translation direction and on which a surface parallel to the translation direction of the slider rests. The presence of the mobile cowl ensures, inter alia, easy access to the inside of the engine pylon and to the systems that are housed therein.

Aircraft having an engine pylon with a mobile cowl

An assembly including a wing with a pressure-side panel and a suction-side panel through which two bores pass, an engine pylon including a blade with three bores and two fastening lugs, each of which has a sixth bore, two first shackles fastened between the blade and the suction-side panel, two second shackles fastened between the blade and the suction-side panel and two fittings, which are fastened beneath the pressure-side panel and each have a female clevis for housing a fastening lug therein.

An engine pylon for an aircraft and comprising an inverted U-shaped upper spar with two lateral walls, a U-shaped lower spar with two lateral walls, where the free ends of the lateral walls of the spars are adjacent, an arrangement to the free end of a lateral wall of one spar to the free end of the lateral wall of the other spar, and ribs between the spars where each has a top end fixed to the lateral walls of the upper spar and a bottom end fixed to the lower spar. Such an engine pylon thus offers a reduced number of component parts and a single row of fixings per side, enabling a saving in weight and in assembly time.

Engine pylon for coupling a jet engine to a wing of an aircraft

An aircraft comprising a fastening element and an engine pylon with two rear covers. Each cover includes a movable lower cover mounted articulated on a rear portion in which in the closed position, the two movable lower covers are moved together and in which in the open position, they are tilted and moved apart from each other. For each movable lower cover, a hinge system, and at least one locking system locks the two movable lower covers together in the closed position and locks each movable lower cover to the fastening element in the open position. The presence of the movable lower covers provides, inter alia, easy access to the inside of the engine pylon, and the locking system locks the movable lower covers.

Aircraft comprising an engine pylon with a movable cover assembly and a specific locking system

An assembly for a nacelle, which includes a fixed cowl, a movable cowl that is movable between a closed position and an open position, and including an upper edge and a lower edge and, between the two edges, a reinforcing rib. The fixed cowl includes, an upper reinforcing rib and a lower reinforcing rib, a hinge including a fixed part attached to the upper reinforcing rib of the fixed cowl, a movable part attached to the reinforcing rib of the movable cowl, and at least two locks, each one including a first part secured to the lower reinforcing rib and a second part secured to the reinforcing rib of the movable cowl. An assembly of this kind serves to provide access to the inside of the nacelle while ensuring that the cowls remain sufficiently rigid.

Assembly for a nacelle of an aircraft engine, said assembly comprising a fixed cowl and a cowl mounted so as to be able to move on the fixed cowl

A shackle for fastening an aircraft engine including a ball joint with a pin including a ring including a first bore and a sleeve assembled in the first bore and having a second bore configured to receive the pin and the diameter of which progressively increases to have a flared inner surface at each of its ends, the fastening shackle being arranged such that a spherical outer surface of the ring bears an anti-friction coating produced on a region extending beyond the contact region with the body of the shackle, this first region being bordered by rims forming a projection around the coating, and/or the second bore bears an anti-friction coating on a region extending beyond its contact region with the pin, this region being bordered by rims forming a projection around this anti-friction coating, at the ends of the flared inner surface.

Shackle for fastening an aircraft engine comprising a pair of encapsulated anti-friction coatings, and aircraft comprising such a shackle

An engine pylon of an aircraft having a rear portion, two rear cowls around the rear portion, each rear cowl having an upper fixed cowl and a lower movable cowl mounted articulated on the rear portion, wherein in the closed position the two lower movable cowls are moved close to one another, such that their lower edges are contiguous, wherein in the open position the two lower movable cowls are tilted such that their lower edges are moved away from one another, for each lower movable cowl, a hinge system fixed between the lower movable cowl and the rear portion, and at least one locking system which locks the two lower movable cowls to one another in the closed position. The presence of the lower movable cowls ensures, among other things, easy access to the interior of the engine pylon.

Aircraft engine pylon having a movable assembly of cowls

An engine mounting pylon for suspending a turbofan beneath an aircraft wing, including a primary structure, a fastening device for fastening to the turbofan, and a fastening device for fastening to the wing. The engine mounting pylon furthermore comprises multiple rigid braces that mechanically connect the primary structure to the wing of the aircraft, a first brace-attachment device that mechanically connects a first end of each brace to the wing, and a second brace-attachment device that mechanically connects a second end of each brace to the primary structure. This braced-pylon architecture makes it possible to reduce the dimensions of the primary structure and the various elements that constitute the first and second attachment devices.

Braced-pylon architecture for mounting an engine to an aircraft

An engine pylon has a primary structure fastened between an engine and an aircraft wing and a cowling system having a front set of fixed cowls, a rear cowl, a displacement system having a first structure as one with the rear cowl and having a first slide mechanism, and a second structure fastened to a fixed structure of the wing and having second slide mechanism. The slide mechanisms cooperate so as to realize a sliding connection and to move the rear cowl in translation from an advanced position to a retracted position. An immobilizing system locks the rear cowl in the advanced position.

Aircraft engine pylon having a mobile cowl

An assembly having a pylon with an upper spar and two lateral scoops, a wing with a skin and a front spar, port-side/starboard-side front/rear brackets, each with a recess for a nut. The front spar has front/intermediate/rear pleats. Each front bracket is positioned against the front pleat and the intermediate pleat. Each rear bracket is positioned against the intermediate pleat and the skin. For each recess, the associated bracket has an open bore passing through it that opens into the recess. For each recess, the assembly has a fastening bolt having the nut and a screw of which the threaded shank passes through coaxial bores in the front pleat, in the skin, in the upper spar and in the associated lateral scoop, and the open bore, and is screwed into the nut, and of which the head bears against the lateral scoop.

Assembly for an aircraft, the assembly comprising a mast and a wing

An assembly including a connecting device, connecting first and second parts, including first and second links positioned on respective opposite sides of the first and second parts and an interleaved stiffener, positioned between the first and second links, having a first contact face oriented toward the first link and a second contact face oriented toward the second link, parallel to the first face, the first and second contact faces being separated by a distance equal to that separating the first and second links. This interleaved stiffener makes it possible to limit the risks of bending of the links when they are loaded in compression.

Assembly including two links and an interleaved stiffener, aircraft engine attachment including at least one such assembly

An assembly having a pylon with an upper spar and four lateral scoops, a wing with a skin, longitudinal spars and fittings, and, for each lateral scoop, two fastening assemblies, wherein the skin and the fitting each have a first bore and wherein the upper spar and the lateral scoop each have a second bore, wherein each fastening assembly has a screw passing through the first and the second bores, a nut, two eccentric rings, threaded onto one another and onto the screw, and a system for stopping the eccentric rings rotating. The assembly makes it possible to dispense with the use of the spigots while also ensuring the reaction of the shear forces contained in the XY plane by the bolts on account of the reduced tolerances between the various bores, the external and internal surfaces of the eccentric rings and the plain zones of the screws.

Assembly for an aircraft, the assembly having a pylon and a wing

An assembly for an aircraft that has a wing and an engine pylon having a primary structure with right-side and left-side panels, an upper and a lower spar and a rear rib, two sets of upper or lower shackles, one set fastening the right-side panel to the wing, and a second set fastening the left-side panel to the wing, a fastening element secured to the rear rib or to the lower spar, a rear rod connecting the fastening element to the wing, a transverse shackle connecting the upper spar to the wing, a line connecting two centers of the transverse shackle being oriented transversely relative to a longitudinal axis of the engine pylon, and a reinforcing panel, at each joint between a right-side or left-side panel and an upper or lower shackle, which is fastened along a height against the panel and to which the shackle is also fastened.

Assembly for an aircraft having a wing and an engine pylon for coupling a jet engine to said wing

A junction of a pylon with an aircraft wing, the pylon including a primary structure extending from front to rear along a longitudinal axis and in the form of a box with a rear face and an upper spar forming an upper face of the box, a longitudinal median plane separating the primary structure into two parts, left and right, the junction comprising a rear attachment system for attaching the pylon to the wing, this system being arranged at the rear of the primary structure, the rear attachment system including a shoe attached beneath the wing, the shoe being connected, via at least one articulated connecting rod, to a fitting attached to the rear face of the pylon by an articulation whose articulation pin, termed the horizontal articulation pin, is perpendicular to the longitudinal median plane, and the shoe being connected to the upper spar via a force reacting system.

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Merville, France

Olivier Pautis