(Solved): An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughn ...

An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of $35\mathrm{MPa}\sqrt{\mathrm{m}}$. It has been determined that fracture results at a stress of $269\mathrm{MPa}$ when the maximum (or critical) internal crack length is $2.85\mathrm{mm}$. a) Determine the value of $Y?\sqrt{?a}$ for this same component and alloy at a stress level of $349\mathrm{MPa}$ when the maximum internal crack length is $1.43\mathrm{mm}$. $\mathrm{MPa}\sqrt{\mathrm{m}}$ b) Under these circumstances will the component fail?