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