Structural airframe components, landing gear components, fasteners, and turbine blades.
The standout feature of ASTM A564 materials is their ability to be machined easily in a softer, solution-annealed state (Condition A) and subsequently hardened via low-temperature thermal aging. Because aging temperatures are relatively low (900°F to 1150°F), parts experience minimal distortion and scaling compared to traditional quench-and-temper martensitic steels.
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It offers an excellent combination of high strength, high hardness, and corrosion resistance comparable to 304 stainless steel. Type 631 (17-7 PH) UNS Designation: S17700 Overview: Chromium-nickel-aluminum alloy.
Aged at 1025°F (552°C) for 4 hours, air cool. A balanced condition offering high strength with improved ductility. Purchase and download the digital PDF directly from
There are three typical reasons:
Below is an overview of the typical chemical boundaries for the most common grade, : Weight % (Type 630 / UNS S17400) Carbon (C) Manganese (Mn) Phosphorus (P) 0.040% max Sulfur (S) 0.030% max Silicon (Si) Chromium (Cr) 15.00% – 17.50% Nickel (Ni) 3.00% – 5.00% Copper (Cu) 3.00% – 5.00% Columbium + Tantalum (Nb + Ta) 0.15% – 0.45% Heat Treatment and Aging Conditions Aged at 1025°F (552°C) for 4 hours, air cool
The ASTM A564 standard is regularly updated, with versions like 2013, 2019a, and 2025 appearing in searches.