Patent ID: 8668441

Claim:
A nacelle for a bypass turbofan comprising a front air-intake section, a mid-section designed to surround a fan of the turbofan and a rear section having means for coupling to a mast designed to be connected to a fixed structure of an aircraft, said rear section comprising a structural framework onto which is mounted at least one aerodynamic and acoustic smoothing panel, wherein said acoustic panel is not fixed and is attached to the structural framework by floating or elastic attachment means, so as to allow the acoustic panel to deform in a substantially centrifugal radial direction relative to the turbofan in the presence of over pressurized air in an engine compartment, wherein said floating or elastic attachment means comprise a nut facing a hole passing through the structural framework, and designed to receive and retain a shank of a screw mounted in a reinforcing bush housed in a hole passing through the acoustic panel, wherein said nut comprises a base attached to the structural framework and having a housing in which the nut itself is mounted so as to move in translation on an axis of said hole passing through the structural framework, the elastic attachment means comprising a return spring being provided in this housing in order to return the nut itself to a rest position at a distance from the structural framework.