Abstract: A rear attachment suspension or device of a turbo engine to an aircraft pylon includes an upper brace fitted with a pylon fastening device and hinged by second ball joint connections, first and second rocker bars transversal to the longitudinal axis of the engine on both sides of the axis of the engine and a third rocker bar disposed there between. The rocker bars are linked to the engine by first ball joint connections. The first and second rocker bars each include a third stand-by link and the upper brace is formed of a beam fixed rigidly to the pylon. The rocker bars are designed to ensure their interchangeability, thereby reducing the risks of error during assembly.

Abstract: A jet engine suspension includes a master component for attachment, fixed to an aircraft pylon. In the event of breakage of the master component and in the situation where the fixing screws are no longer able to transmit force, a peg is provided which resists transmitted loads such that the master component collapses until an upper shoulder rests on the pylon and supports the master component. The peg is free of dynamic stress in normal service and there is absolutely no risk of it cracking in fatigue.