| 摘要 |
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 ( 6 a) designed so as to uniquely resist forces applied along a direction (Y) transverse to the turbojet, this engine mount ( 6 a) 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).
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