A large and flat metal alloy plate is to be exposed to reversed tensile-compressive cycles of stress amplitude 150 MPa in a fatigue test. If initially the length of the largest surface crack in this specimen is 0.75 mm and the plane strain fracture toughness is 35 MPam1/2 whereas the values of m and A are 2.5 and 2 x 10-12, respectively (for in MPa and a in m), estimate the fatigue life of this plate. Assume that the parameter Y has a value of 1.75 that is independent of crack length. Fatigue crack propagation rate is given by