Some aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of 35MPα√m (31.9 ksi√in). It has been determined that fracture results at a stress of 250MPa (36,250psi) when the maximum (or critical) internal crack length is 2.0 mm (0.08 in.). For this same component and alloy, will fracture occur at a stress level of 325MPa (47,125psi) when the maximum internal crack length is 1.0 mm (0.04 in.)? Why or why not?