Patent ID: 8801376

Claim:
A fabricated engine case of a gas turbine engine, comprising: an annular outer case, an annular inner case disposed co-axially within the outer case and a plurality of circumferentially spaced struts radially extending between the outer and inner cases, the struts being affixed to the respective outer and inner cases; and a mount apparatus affixed to the outer case for mounting the engine to an aircraft, the mount apparatus including a mount base having opposed first and second sides, the first side providing an engine mounting surface and the second side being substantially radially spaced apart from a circumferential skin of the outer case to define a gap between the mount base and the skin, the mount base being supported on respective front and rear ends of the outer case, the apparatus further including a load bearing member extending radially through the gap between the second side of the mount base and the circumferential skin of the outer case, the load bearing member connecting the mount base to one of the struts.