Suppose that a mechanical component on an aircraft is fabricated from an alloy that has a plane-strain fracture toughness of 26 MPa-m1/2. It has been determined that fracture results at a stress of 105 MPa when the maximum (or critical) internal crack length is 9.0 mm. For this same component and alloy, what is the maximum allowable stress level when the critical internal crack length is 5.1 mm?