Abstract: The present invention relates, on the one hand, to a nacelle (1) for a double flow turboreactor (2) comprising a front air intake section (5), a median section (6) intended for surrounding a fan (3) of the turboreactor and a rear section (7), said rear section having an internal structure (7b) intended for serving as a housing to a rear portion of the turboreactor, characterized in that the internal structure possesses attachment means suitable for enabling the nacelle to be fastened to a pylon (12) intended to be connected to a fixed structure (13) of an aeroplane on at least one portion of said internal structure, and on the other hand, to a propellant assembly and to an aircraft provided with such a nacelle.

Abstract: The present invention relates, on the one hand, to a nacelle (1) for a double flow turboreactor (2) comprising a front air intake section (5), a median section (6) intended for surrounding a fan (3) of the turboreactor and a rear section (7), said rear section having an internal structure (7b) intended for serving as a housing to a rear portion of the turboreactor, characterised in that the internal structure possesses attachment means suitable for enabling the nacelle to be fastened to a pylon (12) intended to be connected to a fixed structure (13) of an aeroplane on at least one portion of said internal structure, and on the other hand, to a propellant assembly and to an aircraft provided with such a nacelle.