Patent ID: 7452429

Claim:
A structural element suitable for aeronautical construction made from at least one extruded product comprising an aluminum alloy of the following composition (by mass): (a) Zn 6.9-7.3% Cu 2.0-2.8% Mg from 1.6 to less than 2.0% wherein Cu/Mg is at least 1.1 (b) at least one element selected from the group consisting of: Zr 0.08-0.20%, Cr 0.05-0.25%, Sc 0.01-0.50% Hf 0.05-0.60% and V 0.02-0.20% (c) Fe+Si<0.20% (d) other elements ≦0.05% each and ≦0.15% total, (e) remainder aluminum, wherein said product possesses at least one of the following sets of properties measured at about 20° C.: (a) a yield stress R p0.2(L) equal to at least 580 MPa and a measured K app(L-T) with W=100 mm equal to at least about 80 MPa√m; (b) a yield stress R p0.2(L) equal to at least 580 MPa and a crack propagation rate da/dn not exceeding about 3×10 −3 mm/cycle for ΔK=27 MPa√m; (c) a yield stress R p0.2(L) equal to at least 580 MPa, an ultimate strength R m(L) equal to at least 600 MPa and a K app(L-T) measured with W=100 mm equal to at least about 80 MPa√m; (d) an ultimate strength Rm(L) equal to at least 600 MPa and a K app(L-T) measured with W=100 mm equal to at least about 80 MPa√m.