Patent ID: 6959553

Claim:
A gas turbine engine assembly comprising: a gas turbine engine comprising a longitudinal axis; and a thrust link having a longitudinal axis substantially aligned with respect to said engine longitudinal axis, said thrust link comprising at least a portion of an engine mount for said gas turbine engine and comprising a first connector, a second connector, and a span section extending therebetween, said first connector comprising a first side, a second side, and an opening extending therebetween and defined by an inner surface, said inner surface comprising a plurality of threads extending radially outward into said connector opening such that said threads are axially spaced substantially constant along said inner surface, said plurality of threads comprises a first thread portion positioned proximate said first side and initially engaging a threaded apparatus coupled to said first connector, said plurality of threads comprising a cutback, wherein said cutback extends through said first thread portion, said first connector coupled to said turbine engine, said cutback configured to facilitate reducing stresses induced into said plurality of threads.