Patent ID: 8529199

Claim:
A turbojet engine nacelle intended for equipping an aircraft, the nacelle comprising: a front air inlet section; a middle section intended for surrounding a blower of the turbojet engine; a rear section formed from at least one first and one second half shell which are mounted movably in rotation on an axis, so as to each be capable of being deployed between an operating position, in which the half shells are close to one another, and a maintenance position, in which the half shells are apart from one another; and at least one locking device comprising at least one locking system, intended to be arranged on a first movable element, and a retaining member, intended to be arranged on a second movable element, the locking system comprising a first hook designed to engage with the retaining member and to support a major part of a locking force, wherein the locking system comprises at least one second hook set back from the first hook so as come into engagement with the retaining member in the event of a fracture of the first hook.