Airbus Operations (s.a.s.)

Airbus France

Jerome Cassagne

Thomas Deforet

Yvon Martin

Stephane Machado

Anthony Del Blanco

Arnaud Chambreuil

Antoine Cousin

Guillaume Lebas

An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis said assembly comprising a blocking device. The blocking device comprising a screw with a first cylindrical portion which is screwed into an extension of the second sleeve and against which the second end of the articulation spindle can come to press, and a second portion, in the extension of the first portion, with a smaller cross section than said first cylindrical portion, a locking washer which is interposed between the second portion of the screw and the extension of the second sleeve in a locked position, and a longilinear element which passes through the screw and the second sleeve in a locked state.

Assembly comprising an articulation spindle supported by a clevis and immobilized in translation by a blocking device integrating a double anti-rotation system

An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis. The assembly comprises a blocking device which comprises a cylindrical stop housed in an extension of the second sleeve and comprising a front face against which a second end of the articulation spindle can come to bear, and a bolt-and-nut able to adopt a locked state, in which it passes through the stop and the extension so as to immobilize the stop in the extension, and an unlocked state, in which it does not pass through the stop and allows the stop to be removed from the extension.

An assembly with an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis. The assembly comprises a blocking device. The blocking device comprises a nut screwed onto a threaded portion of an extension of the second sleeve and comprising an inner shoulder against which the second end of the articulation spindle can come to bear, a locking washer able to adopt a locked state in which it prevents the nut from rotating with respect to the extension and an unlocked state in which it allows the nut to be unscrewed, and a longilinear element able to adopt a locked state in which it passes through at least the nut so as to prevent it from rotating.

An engine fastener for an aircraft, to secure an engine to a pylon and comprising a fastener body fixed to the pylon and having a cylindrical extension, and a fixing assembly comprising a paddle fixed to the engine and a connection arrangement joined to the paddle and arranged on the cylindrical extension to form a ball-and-socket joint between the cylindrical extension and the paddle. The connection arrangement comprises a ball, formed in one piece, having a central bore in which the cylindrical extension fits, and of which the outer surface is a spherical portion, a fixing element fixing the ball on the cylindrical extension, and two cages, each having an inner surface assuming the form of a spherical portion. The two inner surfaces are arranged opposite one another to house the ball, and for each cage, a joining element joins the cage to the paddle.

Engine fastener for an aircraft

An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis, and a blocking device. The blocking device comprises a nut screwed onto an extension of the second sleeve and comprising an inner shoulder acting as a stop for a second end of the articulation spindle, at least two locking washers engaging with the nut, a tab washer comprising an element immobilizing it in rotation with respect to the second arm of the clevis, and for each locking washer, a blocking element limiting the rotational movement of the locking washer with respect to the tab washer.

The present invention relates to an engine assembly for an aircraft comprising an attachment means, a turboprop on an attachment mast, this means including a plurality of front engine attachments () each having an engine vibration insulation system () including a housing (), a stress transmitting member () extending along a first axis () parallel to an axis of rotation of the propeller and a hollow member () integrated in the housing and extending along a second axis () orthogonal to and intersecting the first axis. According to the invention, a support means for supporting the system () is formed by a plurality of clevises () each having a middle plane parallel to its clevis heads, integrating one of the first and second axes and orthogonal to the other of said axes.

Device for fastening a turboprop, preferably under an aircraft wing

An aircraft engine mounting device attachment arrangement includes a fitting perforated with two orifices, and two ball joints respectively housed in the orifices. The arrangement also includes two anti-rotation systems used to lock the ball joints in their orifices, the system including a main plate traversed by an external ring of the ball joint and including tappets cooperating with notches provided on the ring, the system including a main plate traversed by a main plate of the ball joint and including tappets cooperating with notches provided on the ring. In addition, the plates are connected rigidly to each other.

Aircraft engine mounting device attachment arrangement

This invention relates to a mounting structure () for mounting an engine () under an aircraft wing (), the structure comprising a rigid structure () and means () of fastening this rigid structure under the wing, the mounting means comprising a forward fastener (), an intermediate 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 longitudinal direction (X) of the aircraft. Furthermore, the intermediate fastener comprises a connecting rod capable of transferring forces applied in a direction (Y) transverse to the aircraft, and the aft fastener comprises at least one shackle oriented along a vertical direction (Z) of the aircraft.

Engine mounting structure under an aircraft wing

A structure for mounting a turboprop under an aircraft wing includes a rigid structure and a device for fastening the turboprop on the rigid structure. The rigid structure is composed of a box, and the device for fastening includes at least two lateral connecting rods resisting the engine torque generated by the turboprop, the connecting rods being arranged on each side of the box and each having a forward end connected to a gear box of the turboprop, and an aft end connected to the box.

Structure for mounting a turboprop under an aircraft wing

A mounting structure for mounting a turboprop under an aircraft wing includes a rigid structure provided with an aft underwing box, and at least one forward rigid section. Each forward rigid section has two transverse frames at a spacing from each other. At least one forward rigid section of the rigid structure also includes at least one forward upper box connecting a top part of the two transverse frames of the forward rigid section.

Mounting structure for mounting a turboprop under an aircraft wing

The invention relates to a hanging device () connecting an engine () to a wing () of an aircraft, with the device being made up of a rigid structure () and hanging equipment () interposed between the rigid structure () and the wing (), with the hanging equipment () being made up of a forward attachment () and a rear attachment () made up of at leas one triangular shackle placed in a vertical plane aligned in a transverse direction (Y) of the aircraft. According to the invention, the forward attachment () has, on one side and the other of a vertical plane passing through a longitudinal axis () of the engine (), at least one triangular shackle aligned in the longitudinal direction (X) of the aircraft. Furthermore, the hanging equipment is made up exclusively of forward and rear attachments.

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Toulouse, France

Jerome Cassagne