Aluminum alloys used in the aircraft industry have to satisfy the requirements of high strength at low density, appropriate resistance to different kinds of corrosion, maximum possible rigidity, good adaptability to manufacturing in the metallurgical and machine-building industries, etc. A new requirement on aircraft materials imposed in the last twenty years is an elevated resistance to crack propagation, because it is impossible so far to completely eliminate cracks in industrial materials. Therefore, aircraft builders have developed the concept of “safe vulnerability to damage,” which permits the presence of cracks in aircraft structures but requires knowledge of the laws of their propagation, The present work is devoted to a direction in the development of aluminum alloys that provides elevated crack resistance parameters.