A blade outer air seal for a gas turbine engine is provided. The blade outer air seal having: a gas path surface exposed to exhaust gas flow; a first side extending radially outward from the gas path surface; a second side extending radially outward from the gas path surface; and a plurality of film cooling holes disposed on at least one of the gas path surface, the first side and the second side, the film cooling holes disposed at locations described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin.