Patent ID: 8517304

Claim:
A device for locking an engine on an aircraft pylon, comprising: two systems that attach the engine to the pylon, located in attachment regions spaced out in a longitudinal direction of the engine and of the aircraft, the attachment regions including a first front region and a second region, the second region placed adjacent to a plane of a center of gravity of the engine and closer to a fan than the first region, wherein a first system of the two systems that attaches to the first region is rigid towards torsional, transverse and vertical forces exerted by the engine, the first region is located at a location of a separation between two compressors of the engine or two turbines depending on whether the fan is at a rear or at a front of the engine respectively, said separation being adjacent to a node of a first engine flexural mode, and a second system of the two systems that attaches to the second region is rigid towards transverse and vertical forces but less rigid than the first system that attaches to the first region, and the device comprises a third system that withstands thrust forces in the longitudinal direction.