Abstract: A suspension for suspending of a turbine engine from the structure of an aircraft using a beam with an attachment device which attaches to the structure and at least one link rod articulated via one end to a journal secured to the beam and via the other to a fitting secured to the turbine engine is disclosed. This suspension is one wherein the journal is mounted on the beam via a flexible coupling formed of two preloaded laminated, elastomer and metal, cylinders.

Abstract: A suspension for suspending a turbine engine from the structure of an aircraft is disclosed. The suspension includes a beam with a first element including a first attachment unit which attaches the beam to the structure and a second element including a second attachment unit which attaches to the beam to the turbine engine. The beam further includes a first plate and a second plate. The plates are positioned transversely 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 second plate to the second element. This arrangement allows vibration damping between the engine and the structure of the aircraft.

Abstract: The present invention relates to the suspending of a turbine engine from the structure of an aircraft using a beam with means of attachment to said structure and at least one link rod articulated via one end to a journal secured to the beam and via the other to a fitting secured to the turbine engine. This suspension is one wherein the journal is mounted on the beam via a flexible coupling formed of two preloaded laminated, elastomer and metal, cylinders.