An aircraft propulsion system comprising: a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis; a nacelle surrounding said core engine; at least one free power turbine (50, 52) driven to rotate by exhaust gases exiting said turbine section; at least one rotor module driven to rotate by said at least one free power turbine; and first and second pylons (64, 66) extending away from said nacelle and operable to mount said core engine to an aircraft, wherein said first and second pylons are spaced from one another on opposite sides of at least one plane containing said centerline axis and mirror one another across said at least one plane; and wherein each of said first and second pylons further include an aft beam extending between first and second ends (86, 88), said first end is mounted to said core engine at a first position along said centerline axis proximate to a composite center of gravity of said core engine, said nacelle, said at least one free power turbine, and said at least one rotor module; and wherein each of said first and second pylons further include a fore beam extending between first and second ends, said first end is mounted to said core engine at a second position along said centerline axis spaced closer to said intake than said first position; and a thrust beam extending between first and second ends wherein said first end is mounted to said core engine at said first position, wherein said respective first ends of said aft beam and said thrust beam are proximate to one another and said respective second ends of said fore beam and said thrust beam are proximate to one another. a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis; a nacelle surrounding said core engine; at least one free power turbine (50, 52) driven to rotate by exhaust gases exiting said turbine section; at least one rotor module driven to rotate by said at least one free power turbine; and first and second pylons (64, 66) extending away from said nacelle and operable to mount said core engine to an aircraft, wherein said first and second pylons are spaced from one another on opposite sides of at least one plane containing said centerline axis and mirror one another across said at least one plane; and wherein each of said first and second pylons further include an aft beam extending between first and second ends (86, 88), said first end is mounted to said core engine at a first position along said centerline axis proximate to a composite center of gravity of said core engine, said nacelle, said at least one free power turbine, and said at least one rotor module; and wherein each of said first and second pylons further include a fore beam extending between first and second ends, said first end is mounted to said core engine at a second position along said centerline axis spaced closer to said intake than said first position; and a thrust beam extending between first and second ends wherein said first end is mounted to said core engine at said first position, wherein said respective first ends of said aft beam and said thrust beam are proximate to one another and said respective second ends of said fore beam and said thrust beam are proximate to one another.