Redundant front suspension system for a turboshaft engine

A redundant front suspension system for a turboshaft engine mounted on a pylon of an aircraft comprises a primary suspension device forming the normal front suspension of the engine, and an emergency suspension device which operates in the event of failure of the normal suspension. The primary suspension device comprises a base support which is fixed to the pylon and has a suspension shaft which co-operates with the intermediate casing of the engine. Thrust take-up rods connect the intermediate casing to the base support. The emergency suspension device comprises a first support secured to the pylon and a second support secured to the intermediate casing, each of these two supports having a vertical yoke associated with it. The vertical yokes are interconnected by a connecting rod in a manner which provides a clearance between the rod and at least one of the yokes. The second support carries a vertical pin which is received with clearance in a bore in a horizontal yoke provided on the first support, the vertical pin and the horizontal yoke taking up the longitudinal and transverse forces in the event of a failure of the normal suspension shaft or of a thrust take-up rod. The connecting rod takes up the vertical forces in the event of a failure of the normal suspension shaft.