An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of . it has been determined that fracture results at a stress of 250 mpa when the maximum (or critical) internal crack length is 2.0 mm. (a) determine the value of for this same component and alloy at a stress level of 325 mpa when the maximum internal crack length is 1.0 mm. (b) under these circumstances will the component fail?