Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Pierre-Antoine Combes

Michael Berjot

Marc De Nicola

Olivier Pautis

Paul Morrell

Oliver Marks

Paul-Adrien Taveau

Guillaume De Almeida

Ryan Holland

Russell Older

Germain Gueneau

Jean-Baptiste Vignes

An assembly comprising a longitudinal member of an aircraft wing, where the longitudinal member has a contact wall which is penetrated by first bores, each passing through the contact wall parallel to a longitudinal direction, an engine pylon which is arranged at the end of the longitudinal member in the longitudinal direction and having an upper longitudinal member which, for each first bore, is penetrated by a second bore which is aligned with the first bore, and a nut and a screw for each pair of a first bore and a second bore, which are aligned, where the screw is screwed into the nut successively via the first bore and the second bore, sandwiching the upper longitudinal member and the contact wall.

Assembly of a longitudinal member of a wing and an engine pylon which are horizontally aligned relative to one another

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

A propulsion assembly for an aircraft, having a turbomachine, a pylon, and a device for reacting thrust forces having a main fitting, a spreader pivoting on the main fitting and having an opening, two rods articulated to the turbomachine and to the spreader, a secondary fitting fastened beneath the pylon and having a secondary female clevis constituted of two secondary arms passed through by holes of oblong shape and aligned along a secondary axis (R), wherein the spreader is housed in the secondary female clevis of the secondary fitting, wherein the opening is coaxial with the secondary axis (R), and a backup connection pin inserted with a tight fit into the opening and with clearance into the holes. Also an aircraft with such a propulsion assembly.

Aircraft propulsion assembly having a device for reacting thrust forces

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 has a structure for fastening an aircraft engine beneath a wing and has two lateral faces. The structure has a tunnel laterally passing through it, between and through the lateral faces, and the engine pylon has a spreader housed in the tunnel and fastened in an articulated manner to each lateral face. A first end of the spreader has a first bore. A second end of the spreader has two second bores each forming a connection point with the engine. A rod is fastened in an articulated manner to the first bore and has two third bores each forming a connection point with the engine. Such an engine pylon has the ability to attach the engine, with reduced vertical bulk and with less drag.

Engine pylon for fastening an aircraft engine

A hinge assemblyfor an aircraft component comprises first and second hinge plates, each hinge plate including a plurality of fingersto. The fingers of the first and second hinge plates are interleaved. A seal assemblytois provided between at least some of the fingers. The provision of a hinge including interposed fingers allows for a hinge assembly having a complex aerodynamic profile to be made, while the sealing function is performed by the seals filling the gaps between the fingers.

Aircraft hinge assembly

A hinge assemblyfor an aircraft component including first and second hinge plates, having an aerodynamic surface. A first seal assemblytois provided and arranged to seal between the aerodynamic surfaces of the hinge plates. A second seal assemblytois arranged to seal between the undersides of the hinge plates in order to reduce pressure leakage between voids under the hinge. The provision of two seal assemblies, each having a dedicated function, addresses the competing demands made on the sealing arrangement of an aircraft hinge assembly in use.

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Toulouse, France

Pierre-Antoine Combes