Patent ID: 7740200

Claim:
An engine assembly for aircraft comprising: a turbojet including a fan casing; an attachment strut, the attachment strut includes a rigid structure which includes a plurality of cradles arranged in a manner so as to define a portion of a substantially cylindrical surface with a circular cross section; and a plurality of engine mounts interposed between the attachment strut and the turbojet, wherein attachment of the turbojet on the strut is made with the plurality of engine mounts, wherein each of the engine mounts is directly attached to a peripheral annular part of the fan casing of the turbojet, wherein the plurality of cradles includes at least one annular portion shaped cradle substantially centered on a longitudinal axis of the cylindrical surface, the longitudinal axis being parallel to a longitudinal direction of the turbojet, and wherein each of the engine mounts is attached to a forward-most annular portion shaped cradle.