Aluminum-copper-lithium alloy product for fuselage components with improved properties after being held at moderate temperature and processed.

Abstract

The invention relates to a process for manufacturing a T8-grade rolled product with a thickness of 0.8 to 12.7 mm made of an aluminum-based alloy comprising, by weight percentages, 2.05 to 2.25% Cu, 1.25 to 1.45% Li, 0.2 to 0.4% Mg, 0.2 to 0.4% Mn, an amount of Zr less than or equal to 0.03%, an amount of silver less than or equal to 0.1%, 0.01 to 0.05% Ti, an amount of Fe + Si less than or equal to 0.2%, and unavoidable impurities with a content less than or equal to 0.05% by weight each and 0.15% by weight in total, remaining aluminum, wherein, in particular, tempering is carried out at a temperature of 150 °C to 175 °C and such that the equivalent tempering time calculated at 160 °C is between 35 hours and 45h. The laminated products according to the invention exhibit improved thermal stability under prolonged exposure to moderate temperatures, such as 1000h at 85°C or 3000h at 85°C. Abbreviated figure: Figure 2

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