Abstract: Assembly including an aircraft turbine engine and a pylon for mounting the turbine engine to an element of the aircraft. The pylon includes members for suspending the turbine engine, the members being connected to the turbine engine in at least one plane which is perpendicular to the axis and which is located upstream of the combustion chamber of the turbine engine, such that the turbomachine is cantilevered to the pylon, The assembly further includes at least one damper which connects the turbomachine to the pylon and which is located in a plane perpendicular to the axis located downstream of the combustion chamber, the damper being configured to limit the relative movements between the turbine engine and the pylon without transmitting force.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.