Turboshaft engine attached to a pylon of the fuselage of an aircraft by a failsafe suspension system

A turboshaft engine attached to a pylon of a fuselage of an aircraft by a suspension system comprising:

• a front suspension system provided at a front suspension plane perpendicular to a longitudinal axis of the turboshaft engine and located at an intermediate turboshaft engine casing, the front suspension system connecting the turboshaft engine casing to the pylon;
• a rear suspension system provided at a rear suspension plane perpendicular to the longitudinal axis of the turboshaft engine and located at an exhaust casing of the turboshaft engine, the rear suspension system connecting the exhaust casing to the pylon;
• and
• a failsafe intermediate suspension system provided at a failsafe intermediate suspension plane perpendicular to the longitudinal axis of the turboshaft engine and located between the front and rear suspension planes, the intermediate suspension plane being closer to the rear suspension plane than the front suspension plane, the intermediate suspension system comprising at least one connecting rod with a first end connected to a first fastening provided on an outer fan duct of the turboshaft engine and a second end connected to a second fastening provided on the pylon so as to present a center distance between a center of the first end and a center of the second end in an axial direction of the connecting rod,
• wherein the connecting rod is movable within a predetermined clearance in the axial direction when the rear suspension system of the rear plane is operating and the connecting rod is in a standby position so that the center distance can vary,
• wherein a flexible element made of a flexible material is provided in the connecting rod so as to introduce the predetermined clearance by an elastically deformable nature of the flexible element so that the center distance can vary when the rear suspension system is operating and the connecting rod is in the standby position, and
• wherein the connecting rod can be disassembled and includes at least first and second distinct parts that are respectively articulated at the turboshaft engine and at the pylon and are connected together in an axially adjustable manner via a single outer threaded ring surrounding facing ends of the first and second distinct parts of the rod.