This invention relates to a mounting system (1) inserted between an aircraft engine and a rigid structure of an attachment strut, the system particularly comprising a thrust resistance device (20). The thrust resistance device (20) comprises two lateral actuators (30) each provided with a rod (34) in which a forward end (34b) is a piston located inside a chamber (38) of a central casing (22) of the engine, the chamber (38) comprising a forward compartment (40) and an aft compartment (42). Moreover, the thrust resistance device (20) comprises a device (32) including a piston (48) fixed to the forward mount (16) and located inside a chamber (50) fixed to the central casing, the chamber (50) comprising a forward compartment (52) and an aft compartment (54), the forward compartment (52) of the chamber (50) being hydraulically connected to the aft compartments (42) of the actuators (30).
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