Abstract: The invention relates to a method for mounting an engine (1) on an aircraft strut (3) comprising engine suspension members (31) integral with the strut, the engine being integral with a suspension cradle (6) whereby it is suspended from the strut, the method comprising a step of hoisting the engine in a vertical direction as far as the strut then a step of approaching the strut by a movement of the engine in another direction, characterised in that an intermediate part (7) is fixed to the strut beforehand, by attaching it to said suspension members (31), said intermediate part (7) having an interface intended to cooperate with a complementary interface provided on the cradle (6), in such a way as to position the cradle relative to the intermediate part at the end of the approach movement to the strut. The invention also relates to the system for implementing the method.

Abstract: The invention relates to a method for mounting an engine (1) on an aircraft strut (3) comprising engine suspension members (31) integral with the strut, the engine being integral with a suspension cradle (6) whereby it is suspended from the strut, the method comprising a step of hoisting the engine in a vertical direction as far as the strut then a step of approaching the strut by a movement of the engine in another direction, characterised in that an intermediate part (7) is fixed to the strut beforehand, by attaching it to said suspension members (31), said intermediate part (7) having an interface intended to cooperate with a complementary interface provided on the cradle (6), in such a way as to position the cradle relative to the intermediate part at the end of the approach movement to the strut. The invention also relates to the system for implementing the method.

Abstract: The invention provides a suspension structure for suspending a turboprop (10) having two unducted propellers on a structural element of an aircraft, the suspension structure comprising a cradle (18) for fastening to a structural element of the aircraft and having two lateral beams (22) connected to a main beam (20) extending parallel to a longitudinal axis (14) of the turboprop so as to form a V-shaped cradle structure, the cradle being fastened to the turboprop via two angle members (24) connecting each free end of the lateral beams of the cradle to the turboprop, via an axial link (28) connecting one end of the main beam of the cradle of the turboprop, and via at least one transverse link (30) situated in a plane extending transversely relative to the longitudinal axis of the turboprop and connecting the cradle to the turboprop.

Abstract: The invention provides a suspension structure for suspending a turboprop (10) having two unducted propellers on a structural element of an aircraft, the suspension structure comprising a cradle (18) for fastening to a structural element of the aircraft and having two lateral beams (22) connected to a main beam (20) extending parallel to a longitudinal axis (14) of the turboprop so as to form a V-shaped cradle structure, the cradle being fastened to the turboprop via two angle members (24) connecting each free end of the lateral beams of the cradle to the turboprop, via an axial link (28) connecting one end of the main beam of the cradle of the turboprop, and via at least one transverse link (30) situated in a plane extending transversely relative to the longitudinal axis of the turboprop and connecting the cradle to the turboprop.