Airbus Operations (s.a.s.)

Airbus France

Airbus Operations Gmbh

Jérôme Cassagne

Lionel Czapla

Jean Geliot

Thomas Deforet

Benoit Orteu

Frédéric Vinches

Rémi Amargier

Kotaro Fukasaku

Yvon Martin

Anthony Del Blanco

Arnaud Chambreuil

Didier Rovatti

Michael Belin

Miren Egana-Abarrategui

Jean Pierre Couffignal

Stéphane Machado

A propulsion assembly for an aircraft, having a T-shaped chassis with a horizontal structure and a vertical structure, a gearbox fastened to a front of the chassis, and a propulsion system having the following propulsion elements: an electric motor driving the components of the gearbox, a fuel cell, a tank and a cooling system, wherein the propulsion elements are fastened beneath the horizontal structure and against the vertical structure by fastening means.

Propeller propulsion system with T-shaped chassis

A rear engine attachment includes a beam attached to the reactor strut, a rudder mounted by a pivot connection on the beam about a main rotational axis, and two thrust rods each exhibiting a first end attached to the rudder and a second end attached to a front section of an engine, the two thrust rods and the rudder attached to the beam together defining a primary thrust path between the engine and the reactor strut to bear the engine thrust. For each thrust rod, the rear engine attachment exhibits a waiting fail-safe system activated in the event of a failure of the primary thrust path. The rear engine attachment includes, for each thrust rod, a break detector integral with the rudder which is provided to come into contact with the beam in the event of a failure of the primary thrust path. The attachment allows a quick inspection to be made to determine whether there has been a failure of the primary thrust path.

Rear attachment of an aircraft engine comprising break detectors

A fire seals system positioned in a corner of a region of attachment between a rear engine mount and a pylon and comprising a metal shoe comprising a fitting comprising two first vanes forming an L fixed in the corner and a lower second vane between the lower edges of the two first vanes and an upper second vane between the upper edges of the two first vanes, and a flexible tongue having a fixed upstream end and a free downstream end in which an intermediate part of the tongue is arranged between the lower second vane and the upper second vane, and a longilinear seal attached to a thrust reverser cowl with one end of the longilinear seal bearing against the tongue. Such a fire seals system makes it possible to limit the spread of flames and to absorb movements of the nacelle.

Metal fire seals system for aircraft engine mount

This invention relates to a structure () for mounting an engine () under an aircraft wing (), comprising a rigid structure () and means () of mounting this rigid structure under the wing, the mounting means () comprising a forward fastener () and an aft fastener (). According to the invention, the forward fastener has at least one triangular shackle on each side of a vertical plane passing through a longitudinal axis () of the engine, placed in a vertical plane oriented along a direction inclined with respect to a longitudinal direction (X) and a transverse direction (Y) of the aircraft, and located in a horizontal plane defined by these directions (X) and (Y). Furthermore, the aft fastener comprises at least one shackle oriented along a vertical direction (Z) of the aircraft.

Engine mounting structure under an aircraft wing

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Toulouse, France

Jérôme Cassagne