Engine mount system for a gas turbine engine

A gas turbine engine comprising:

• a propulsor section including a propulsor having a rotor and a plurality of blades;
• a geared architecture including 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 a plurality of 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 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 geared architecture;
• 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, wherein the first engine mount location is axially near the geared architecture relative to the engine axis, the second engine mount location is axially aft of the first turbine relative to the engine axis, the first engine mount location supports a forward engine mount when the engine is mounted, and the second engine mount location supports an aft engine mount when the engine is mounted;
• 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.