Methods and apparatus for mounting a gas turbine engine

An apparatus for mounting a gas turbine engine to a pylon, the gas turbine engine including an upstream section and a downstream section, the gas turbine engine defining a roll axis, a yaw axis, and a pitch axis, the apparatus comprising:

• a first mount to couple the upstream section of the gas turbine engine to the pylon;
• and
• 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 and the thrust linkage, and
• wherein the downstream section is cantilevered from the upstream section.

A gas turbine engine configured to be coupled to a pylon, the gas turbine engine defining a roll axis, a yaw axis, and a pitch axis, the gas turbine engine comprising:

• a first thrust linkage to couple the gas turbine engine to a first attachment point on the pylon;
• a second thrust linkage to couple the gas turbine engine to a second attachment point on the pylon, the second thrust linkage displaced along a first axis from the first thrust linkage, the first thrust linkage and the second thrust linkage to react a first moment generated during operation of the gas turbine engine, wherein the first attachment point and the second attachment point are separated by a vertical displacement, and the first moment is a moment about the pitch axis of the gas turbine engine;
• and
• a third thrust linkage to couple the gas turbine engine to a third attachment point on the pylon, the third thrust linkage displaced from the first thrust linkage along a second axis, the second axis perpendicular to the first axis, the third thrust linkage and the first thrust linkage to react a second moment, the second moment applied in a direction perpendicular to the first moment, wherein the second moment is applied about the yaw axis of the gas turbine engine, wherein the third and second attachment points are separated by the vertical displacement, and wherein the second thrust linkage is laterally between the first thrust linkage and the second thrust linkage at a same location along an axial direction defined by the gas turbine engine.