Patent ID: 7624945

Claim:
An engine assembly for an aircraft comprising: a turbojet defining an X direction along a longitudinal axis of the turbojet, a Y direction along a transverse axis of the turbojet, and a Z direction along a vertical axis of the turbojet, the X, Y, and Z directions being orthogonal to each other; an engine mount pylon; and a plurality of engine mounts inserted between the engine mount pylon and the turbojet, wherein the plurality of engine mounts comprises a first engine mount, said first engine mount comprising: a first fitting fixed to the engine mount pylon, a second fitting fixed to the turbojet, an intermediate fitting between said first and second fittings, said intermediate fitting being V-shaped with two branches extending in an X-Y plane, wherein said intermediary fitting is assembled onto the first fitting through two swivel pins oriented parallel to each other and along the Z direction of the turbojet, each swivel pin passing through said first fitting and through one of said branches of said intermediary fitting, and each swivel pin defining a ball joint received in an opening of a corresponding branch of said intermediary fitting, a pin oriented along the X direction and fixed to the intermediate fitting, the pin being installed on the second fitting with clearance along the X direction so that said pin slides relative to said second fitting over said clearance along the X direction.