Patent ID: 8474751

Claim:
An engine assembly for an aircraft, comprising: a turboprop provided with a propeller and a transmission driving a rotor of said propeller; an attachment mast of the turboprop; an attachment means for attaching the turboprop on said attachment mast, said means comprising a plurality of front engine attachments inserted between said attachment mast and a casing of the turboprop transmission, each front engine attachment comprising an engine vibration insulation system, a support means thereof integrated into the casing of the transmission, as well as a fastening means inserted between said support means and the vibration insulation system, the latter part including: a housing mounted on the support means via a fastening means; a stress transmitting member extending along a first axis parallel to a rotational axis of said propeller, said member comprising an outer end mounted on said attachment mast; and a hollow member integrated in said housing and extending along a second axis orthogonal to and intersecting said first axis, said hollow member housing an inner end of the stress transmitting member, characterized in that for each front attachment, said support means is formed by a plurality of clevises each having a middle plane parallel to a clevis head, integrating one of said first and second axes and orthogonal to the other of said axes.