Patent ID: 8851417

Claim:
A connection for connecting an aircraft to a gas turbine engine comprising: a gas turbine engine having an outer casing; a plurality of shackles each mounted to said outer casing through spherical bearings, and at least one shear pin connection for connecting said outer casing to one of said shackles, said shear pin connection including a bolt having a bolt head to be positioned at an inner end of a bearing, said bolt extending outwardly through an inner bore in the bearing to an outer end, a bushing received radially outwardly of said bolt, and between said bolt and an inner periphery of the bearing, a lock member being positioned between an inner end of said bushing and said bolt head, and said lock member being radially expandable, and having a free radially outer dimension that is smaller than an inner dimension of the inner bore, and said lock member being expandable to have an expanded radially outer dimension which is greater than the inner dimension of the inner bore, and a nut to be tightened on said outer end of said bolt, said nut causing said bushing to move relative to said bolt, and cause said lock member to expand radially.