Patent ID: 9132920
Filing Date: 2015-09-15
Classification: B64D

Abstract:
1. A turbojet engine nacelle comprising: a front air inlet section, a middle section surrounding a blower of the turbojet engine, and a rear section formed from at least two half-shells connected to one another by means of at least one locking device actuated by a control handle equipped with a secondary locking system comprising a blocking member that, once placed in a blocking position, blocks said control handle in a locking position, said middle section being formed from at least two shrouds that deploy between an operating position and a maintenance position, wherein the blocking member comprises a rod parallel to the control handle and slidably housed within the control handle, the control handle being linearly prolonged by a head of the rod, the blocking member and at least one zone of an internal face of one of the two shrouds abutting one against another in order to prevent the closing of said shroud if the control handle is not located in the locking position and/or if the blocking member is not in the blocking position, and wherein the control handle is displaced by rotation alternately between a stable opening position in which said at least one locking device is open and a stable locking position in which said at least one locking device is closed, passing through an intermediate phase where said at least one locking device is closed.