The yield strength for 7075-T6 is 525-MPa and for 300-Grade maraging steel it is 2100-MPa. The fracture toughness values are 28 and 66-MPa (m)1/2, respectively. Both of these materials find applications in the aircraft industry. The aluminum alloy is used for airframe applications, while the maraging steel has been used for landing gear and for the main shafts in jet turbine engines. The flaw size resolution limit of the NDE equipment for any cracks is 1.4-mm. If these components are inspected and then put into service at one-half of their respective material’s yield strength, are the critical flaw sizes for both materials subject to detection? Assume KI = σ (πa)1/2 Y, where Y=1.0