Abstract: The present invention relates to a suspension for suspending a turbine engine from the structure of an aircraft, comprising a beam with a first element accepting means of attachment to said structure and a second element accepting means of attachment to the turbine engine. It is one wherein the beam comprises at least a first plate and a second plate, which plates are intended to be positioned transversely with respect to the axis of the engine and joined together by a layer of elastomer, the first plate being secured to the first element and the other plate to the second element. This arrangement allows vibration damping means to be incorporated in between the engine and the structure of the aircraft.