Engine mount system for a gas turbine engine

A gas turbine engine comprising:

• a propulsor section including a rotor and a plurality of blades;
• an epicyclic gear train having a gear reduction ratio of greater than 2.5:1;
• a compressor section including a first compressor and a second compressor axially aft of the first compressor relative to an engine axis, the first compressor including three stages, and the second compressor including a greater number of stages than the first compressor;
• a turbine section including a first turbine and a second turbine, the first turbine including two stages, the second turbine including a greater number of stages than the first turbine but including a lesser number of stages than the second compressor, and the second turbine having a pressure ratio greater than 5:1 and driving the rotor through the gear train;
• and
• a static structure comprising a plurality of cases distributed along the engine axis, wherein the plurality of cases includes a first case and a second case positioned aft of the first case relative to the engine axis, the first case includes a first engine mount location, the second case includes a second engine mount location that reacts an engine thrust in operation, wherein the first engine mount location is axially near the gear train relative to the engine axis, and each of the first engine mount location and second engine mount location supporting an engine mount when the engine is mounted;
• and
• wherein the static structure supports a bearing system, and wherein the first turbine, the second turbine and the rotor are rotatably supported by the bearing system.