Patent ID: 8333343

Claim:
A turbojet nacelle designed to be fitted to an aircraft, the nacelle comprising: a forward air-intake section; a mid-section designed to surround a fan of the turbojet; and an aft section formed from at least a first half-shell and a second half-shell mounted so as to be able to rotate on an axis so that each of the half-shells can deploy between a working position in which the half-shells are brought closer to one another and a maintenance position in which the half-shells are separated from one another, the mid-section and aft section being connected to one another by a frame that is fixed relative to the turbojet, the first and second half-shells being fitted with positioning means interacting in the working position with matching positioning means arranged on the fixed frame, wherein the first half-shell at least is fitted with immobilization means interacting, in the maintenance position, with matching immobilization means placed on the fixed frame, in order to prevent the translation of the first half-shell on its axis and in the working position, the immobilization means on the half-shell is completely disengaged from the matching immobilization means on the fixed frame.