Patent ID: 8480025

Claim:
A rear part of an aircraft comprising: a fuselage defining an internal space of the aircraft; at least two engines; an engine support structure, traversing the fuselage in an area of first and second openings made in the fuselage, and distributed on either side of a vertical median plane of the aircraft, wherein the support structure includes first and second opposite ends, each of the first and second opposite ends of the support structure protruding externally from the fuselage, respectively on either side of the vertical median plane, and supporting one of the engines; and fastening means connecting the support structure to the fuselage; wherein the fastening means includes two effort transmission connecting rods positioned, as seen from a front view of the rear part of an aircraft, on either side of the vertical median plane, wherein each connecting rod includes a first end mounted on the support structure in rotary fashion along an axis of rotation parallel to the longitudinal direction of the aircraft, and a second end mounted on the fuselage, at a distance from the first and second openings, in a rotary fashion along an axis of rotation parallel to the longitudinal direction of the aircraft, wherein the rear part of an aircraft is configured so as to allow, by rotation of the connecting rods around the axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second openings of the fuselage.