An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of 36 MPa//m. It has been determined that fracture results at a stress of 238 MPa when the maximum (or critical) internal crack length is 2.13 mm. a) Determine the value of Yona for this same component and alloy at a stress level of 309 MPa when the maximum internal crack length is 1.07 mm. b) Under these circumstances will the component fail?