Patent ID: 8783614

Claim:
A nacelle of a turbojet engine, intended to be fitted to an aircraft, comprising: an air intake front section, a middle section intended to surround a fan of the turbojet engine, and a rear section formed of at least a first and a second half-shell mounted such that they are able to rotate about an axis so that each can be deployed between a work position in which the half-shells are close together and a maintenance position in which the half-shells are distanced from one another, the first half-shell comprising: a first follower element in a region situated some distance from an axis of rotation, the first follower element being designed to bear against a first guide element that is fixed with respect to the turbojet engine as the first half-shell rotates to a first phase of separation of the maintenance position; and a second follower element, angularly offset from the first follower element with respect to the axis of rotation of the first half-shell, the second follower element designed to bear against a second guide element that is fixed as the first half-shell rotates to a second phase of separation of the maintenance position, wherein the first follower element and the second follower progressively bear against the first and second guide elements during movement into the maintenance position and do not bear against the first and second guide elements in the work position.