| 摘要 |
<p>The invention relates to an aircraft engine unit comprising a turboshaft engine, a pylon and a plurality of engine mounts which are disposed between the pylon and the turboshaft engine. According to the invention, the plurality of engine mounts comprises one mount (6a) which is designed simply to take up the stresses exerted along a transverse axis (Y) of the turboshaft engine. The aforementioned mount (6a) comprises: an intermediate fitting (46) which is assembled to a first fitting (40) which is solidly connected to the pylon by means of two swivel shafts (48) which are disposed parallel to one another along a vertical axis (Z), and a slug (56) which is disposed along a longitudinal axis (X) and which is solidly connected to the intermediate fitting. Said slug is mounted to a second fitting (58) with play along axis X, said second fitting being connected to the turboshaft engine.</p> |
