| 摘要 |
This aircraft propulsion assembly comprises a nacelle (1) and a turbojet engine, said nacelle comprising an intermediate part (7) and said turbojet engine comprising a fan casing (19) located inside said intermediate part (7), said intermediate part (7) comprising two fan casing half-covers (17b) each able to move about substantially longitudinal axes situated at the upper part of said nacelle, between a closed position in which they cover said casing (19) and an open position in which they allow the periphery of this casing (19) to be accessed, the propulsion assembly being characterized in that said covers (17b) are articulated at least in part directly to said propulsion assembly. |
