| CPC B64D 29/06 (2013.01) [B64D 27/402 (2024.01); B64D 27/404 (2024.01)] | 15 Claims |

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1. A propulsion assembly for an aircraft, comprising:
a pylon configured to be fastened beneath a wing of the aircraft,
a turbomachine comprising an engine a fan surrounded by a fan casing and positioned upstream of the engine, the turbomachine having a longitudinal direction X, a transverse direction Y, a vertical direction Z, and a midplane XZ,
a nacelle surrounding the engine and the fan casing and further comprising a load bearer positioned at an upper part of the nacelle and comprising an upstream bearer and a downstream bearer, a nose cowl fixed to a frontal region of the fan casing forward of the load bearer and upstream cowls mounted in an articulated manner on each side of the upstream bearer and downstream cowls mounted in an articulated manner on each side of the downstream bearer,
a forward fan mount fixed between the frontal zone of the fan casing and a frontal zone of the upstream bearer,
a rear pylon mount fixed between the pylon and a rear part of the downstream bearer, and
for each bearer, a positioning assembly comprising a peg secured to a lower spar of the bearer and extending vertically downwards, a shoe secured to the upper part of the fan casing and having an opening in which the peg becomes lodged, the opening being arranged to allow the peg to move only parallel to the longitudinal direction X and the vertical direction Z, and a locking system which locks the peg in the opening, the locking system being arranged to allow the peg to move parallel to the longitudinal direction X and limit the movements of the peg parallel to the vertical direction Z.
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