371 materials
AISI 8630 is a nickel-chromium-molybdenum alloy steel (0.28–0.33% C, 0.55–0.75% Ni, 0.40–0.60% Cr, 0.15–0.25% Mo) used primarily in aerospace applications for landing gear, fasteners, and highly stressed structural components requiring high strength and fatigue resistance. The alloy provides yield strengths in the range of 180–280 ksi depending on heat treatment and section size, with good toughness and moderate hardenability suitable for medium-section forgings and bars.
AZ31B-F is a magnesium alloy containing aluminum and zinc in the as-fabricated (annealed) condition, offering moderate strength and good formability for applications in aerospace components, automotive structures, and general engineering where weight reduction is critical. The F temper provides lower strength compared to aged conditions but maintains excellent ductility and machinability, making it suitable for formed and machined parts operating at temperatures up to approximately 150°C.
Clad 7475-T7351 is a high-strength aluminum alloy (7xxx series, zinc-primary) with a thin corrosion-resistant aluminum or aluminum-alloy cladding layer, solution heat-treated, stress-relieved by controlled stretching, and artificially aged to T7351 condition for maximum stress-corrosion cracking (SCC) resistance while maintaining high yield strength (typically 415–435 MPa). This temper is specified for critical aerospace structures, particularly fuselage skins and other damage-tolerant applications where both strength and SCC resistance in marine or humid environments are required.
Clad 7475 aluminum alloy T77511 is a high-strength aluminum-zinc-magnesium-copper alloy with an alclad surface layer, thermomechanically treated to peak aging with controlled stretching, providing excellent fracture toughness and stress-corrosion-cracking resistance for critical aerospace structures. The T77511 temper achieves tensile strengths of 70–80 ksi with superior damage tolerance compared to overaged tempers, making it suitable for highly stressed fuselage and wing components where fatigue and corrosion resistance are essential.
Inconel 718 is a nickel-iron-based superalloy strengthened by γ'' (Ni₃Nb) precipitates, used extensively in jet engines, gas turbines, and high-temperature aerospace applications requiring strength retention to ~650°C. The F condition is the as-fabricated state (annealed after final fabrication without precipitation hardening), providing lower strength but superior ductility and machinability compared to aged conditions, making it suitable for applications requiring post-delivery aging or intermediate machining operations.
PH15-7Mo is a precipitation-hardening martensitic stainless steel containing 15% chromium, 7% molybdenum, and aluminum as a strengthening agent, offering high strength and corrosion resistance for aerospace and fastener applications. The F condition (as-forged) represents the material in its initial forged state prior to heat treatment, providing baseline mechanical properties and serving as a reference condition before applying precipitation-hardening cycles.
Ti-13V-11Cr-3Al in the F (as-fabricated) condition is a metastable beta titanium alloy used in aerospace fasteners and structural components requiring high strength and fatigue resistance; the F temper provides strength in the 1,200–1,400 MPa range without solution treatment, making it suitable for applications where dimensional stability and repeatable mechanical properties are critical.
Ti-15V-3Cr-3Sn-3Al STA is a metastable beta titanium alloy in solution-treated and aged condition, combining high strength (typically 1200-1400 MPa tensile strength) with excellent fracture toughness and damage tolerance for aerospace fasteners and structural components. The STA condition provides optimized strength-toughness balance through controlled precipitation hardening while maintaining good fatigue resistance and low-temperature impact properties required in critical airframe applications.
Ti-6Al-4V in the F (annealed) condition is a two-phase alpha-beta titanium alloy with 6% aluminum and 4% vanadium, used extensively in aerospace applications including aircraft frames, engines, and fasteners. The F temper provides optimal ductility and fracture toughness through stress-relief annealing, sacrificing some strength compared to aged conditions but delivering enhanced damage tolerance and machinability suitable for complex fabrication.