The invention relates to an engine assembly for an aircraft comprising a
turbojet, a engine mount pylon, and a plurality of engine mounts inserted
between the engine mount pylon and the turbojet. According to the
invention, the plurality of engine mounts comprises a engine mount (6a)
designed so as to uniquely resist forces applied along a direction (Y)
transverse to the turbojet, this engine mount (6a) comprising an
intermediate fitting (46) assembled onto a first fitting (40) fixed to
the pylon through two swivel axes (48) oriented parallel along a vertical
direction (Z), and a pin (56) oriented along a longitudinal direction (X)
and fixed to the intermediate fitting, the pin being installed on a
second fitting (58) fixed to the turbojet, with clearance along the
longitudinal direction (X).