Abstract: The present invention is directed to highly controlled alloy composition relationship of a high purity Al—Mg—Cu alloy within the 2000 series aluminum alloys as defined by the Aluminum Association, wherein significant improvements are revealed in fracture toughness through plane strain, fracture toughness through plane stress, fatigue life, and fatigue crack growth resistance.

Abstract: The present invention is directed to highly controlled alloy composition relationship of a high purity Al—Mg—Cu alloy within the 2000 series aluminum alloys as defined by the Aluminum Association, wherein significant improvements are revealed in fracture toughness through plane strain, fracture toughness through plane stress, fatigue life, and fatigue crack growth resistance.

Abstract: An aluminum-copper-zinc alloy having ancillary additions of lithium. The alloy composition includes from about 5 to 13 wt % zinc and from about 0.01 to 1.0 wt % lithium.

Abstract: A substantially unrecrystallized extrusion comprising about 3.6 to about 4.2 wt. % copper, about 1.0 to about 1.6 wt. % magnesium, about 0.3 to about 0.8 wt. % manganese, about 0.05 to about 0.25% zirconium, the balance substantially aluminum, incidental elements and impurities. The extrusion has a longitudinal yield strength of at least about 50 ksi and a longitudinal tensile ultimate strength of at least about 70 ksi. On a preferred basis, the extrusions of this invention include very low levels of both iron and silicon, typically on the order of less than 0.1 wt. % each, and more preferably about 0.05 wt. % or less iron and about 0.03 wt. % or less silicon.

Abstract: A substantially unrecrystallized extrusion comprising about 3.6 to about 4.2 wt. % copper, about 1.0 to about 1.6 wt. % magnesium, about 0.3 to about 0.8 wt. % manganese, about 0.05 to about 0.25% zirconium, the balance substantially aluminum, incidental elements and impurities. The extrusion has a longitudinal yield strength of at least about 50 ksi and a longitudinal tensile ultimate strength of at least about 70 ksi. On a preferred basis, the extrusions of this invention include very low levels of both iron and silicon, typically on the order of less than 0.1 wt. % each, and more preferably about 0.05 wt. % or less iron and about 0.03 wt. % or less silicon.

Abstract: Rolled plate products up to 6 inches thick or more and other products in an aluminum alloy consisting essentially of about 5.2 to 6.8% zinc, 1.7 to 2.4% copper, 1.6 to 2% magnesium, 0.03 to 0.3% zirconium, balance substantially aluminum and incidental elements and impurities, are useful in making structural members for commercial airplanes especially by machining or shaping such members from the plate. Such members include lower wing skins and wing spars and other members. The plate is made by operations comprising homogenization, hot rolling, solution heat treatment, stretching and artificial aging. Alternatively, the plate is shaped after stretching, which may include machining, and is then artificially aged.

Abstract: There is claimed a lower wing structure for a commercial jet aircraft which includes a substantially unrecrystallized rolled plate member made from an aluminum alloy consisting essentially of about 3.6 to 4.0 wt. % copper, about 1.0 to 1.6 wt. % magnesium, about 0.3 to 0.7 wt. % manganese, about 0.05 to 0.25 wt. % zirconium, the balance aluminum and incidental elements and impurities. On a preferred basis, the alloy products of this invention include very low levels of both iron and silicon, typically on the order of less than 0.1 wt. % each, and more preferably about 0.05 wt. % or less iron and about 0.03 wt. % or less silicon. This alloy composition may be rolled to form lower wing skin plates and extruded or rolled to form wing box stringers therefrom.

Abstract: There is claimed a lower wing structure for a commercial jet aircraft which includes a substantially unrecrystallized rolled plate member made from an aluminum alloy consisting essentially of about 3.6 to 4.0 wt. % copper, about 1.0 to 1.6 wt. % magnesium, about 0.3 to 0.7 wt. % manganese, about 0.05 to 0.25 wt. % zirconium, the balance aluminum and incidental elements and impurities. On a preferred basis, the alloy products of this invention include very low levels of both iron and silicon, typically on the order of less than 0.1 wt. % each, and more preferably about 0.05 wt. % or less iron and about 0.03 wt. % or less silicon. This alloy composition may be rolled to form lower wing skin plates and extruded or rolled to form wing box stringers therefrom.