Abstract: The invention concerns a process for the production of rolled or extruded products of high strength AlSiMgCu aluminium alloy with good intergranular corrosion resistance, comprising the following steps:casting a plate or billet with the following composition (by weight):Si: 0.7-1.3%Mg: 0.6-1.1%Cu: 0.5-1.1%Mn: 0.3-0.8%Zr: <0.20%Fe: <0.30%Zn: <1%Ag: <1%Cr: <0.25%other elements: <0.05% each and <0.15% in total remainder: aluminium; with: Mg/Si<1homogenising in the range 470.degree. C. to 570.degree. C.;hot working, and optionally cold working;solution heat treating in the range 540.degree. C. to 570.degree. C.;quenching;annealing, comprising at least one temperature plateau in the range 150.degree. C. to 250.degree. C., preferably in the range 165.degree. C. to 220.degree. C., the total period measured as the equivalent time at 175.degree. C. being in the range 30 h to 300 h.

Abstract: The invention relates to an aluminum alloy sheet heat treated by natural aging, quenching and possibly tempering so as to obtain a yield strength greater than 320 MPa, for use in mechanical, naval, aircraft, or spacecraft construction, with a composition (by weight) of:Si: 6.5 to 11%Mg: 0.5 to 1.0%Cu: <0.8%Fe: <0.

Abstract: A high creep resistance aluminum alloy containing, in percent by weight:Cu: 2.0-3.0;Mg: 1.5-2.1;Mn: 0.3-0.7;Fe<0.3;Ni<0.3;Zr<0.15;Ti<0.15;Ag<1.0;Si<0.6;with Si and Ag in amounts such that 0.3<Si+0.4Ag<0.6; other elements <0.05 each and <0.15 total; and balance Al. The alloy has in its wrought state after being treated by natural aging, quenching and aging, a creep strain after 1,000 h at 150.degree. C. under a stress of 250 MPA of less than 0.3% and a fracture time of at least 2,500 h, and can be used for structural parts for aircraft or spacecraft, rotating machine parts, or plastic processing molds.