Patent ID: 8328132

Claim:
An attachment system to attach a turboengine to a pylon of an aircraft, said turboengine comprising a fan casing, a compressor casing disposed adjacent to the fan casing, and a turbine casing disposed adjacent to the compressor casing, said attachment system comprising: first attachment device attached to the pylon and the compressor casing of the turboengine; second attachment device attached to the pylon and the turbine casing of the turboengine; and a third backup attachment device comprising a first portion fixedly attached to the pylon and a second portion fixedly attached to the fan casing of the turboengine, wherein the first and second portions are configured relative to one another so as not to disrupt a predetermined isostatic attachment of the first and second attachment devices to the pylon, wherein, in response to the first attachment device disengaging from the compressor casing or the pylon, or the second attachment device disengaging from the pylon and the turbine casing, the first portion and the second portion engage with each other, and the third backup attachment is separated from the first attachment device and the second attachment device.