Patent ID: 8979020
Filing Date: 2015-03-17
Classification: B64D

Abstract:
1. A mounting system for mounting a turbofan engine to an aircraft, the turbofan engine having a main rotational axis and an associated transverse axis laterally perpendicular to the main axis, and a nacelle including two annular halves, each half having a hinged end adjacent the pylon and a free end, the system comprising: a pylon; a connection configured for mounting the engine to the pylon and configured to maintain the position of the engine relative to the pylon during operation of the aircraft; at least two hinged connections, each hinged connection being provided between the hinged end of a half and the pylon, the hinges operable to permit closing and opening the halves between open and closed positions; a flexible connection extending between at least one of the hinged connections and the pylon, the flexible connection configured to elastically deform in response to a lateral force exerted on a corresponding half while the halves are in the closed position, the force exceeding a pre-selected threshold, said elastic deformation permitting at least a portion of a corresponding hinged connection to move relative to the engine structure.