This specification covers an aluminum alloy in the form of extruded rods, bars, and profiles (shapes) produced with thickness between 0.040 and 2.500 inches (1.02 to 38.10 mm) in thickness, and having a maximum cross sectional area of 23 in2 (15000 mm2) and a maximum circumscribing circle diameter (circle size) of 16 inches (406 mm) (see 8.4.1).
This specification covers an aluminum alloy in the form of extruded bars, rods, and shapes up to 4.000 inches, incl (101.60 mm, incl) in nominal diameter or least thickness, and having a nominal cross-sectional area up to 20 in2 (129 cm2) (see 8.5).
This specification covers a magnesium alloy in the form of direct chill strand cast round material up to 9.0 inch diameter and rectangular material up to 10 inch by 27.5 inch cross-section (see 8.4) for the purpose of machine from solid applications (see 8.2.1).
The purpose of this recommended practice is to provide the aerospace industry with recommendations concerning minimizing stress-corrosion cracking (SCC) in wrought high-strength aluminum alloy products.
This specification specifies the engineering requirements for heat treatment, by part fabricators (users) or their vendors or subcontractors, of parts (see 8.6.1). It also covers heat treatment by warehouses or distributors converting raw material from one temper to another temper (see 1.3 and 8.5). It covers the following aluminum alloys: 1100, 2014, 2017, 2024, 2098, 2117, 2124, 2195, 2219, 2224, 3003, 5052, 6013, 6061, 6063, 6066, 6951, 7049, 7050, 7075, 7149, 7178, 7249, 7475