AMS 5525 - A286 Stainless Steel Sheet, Strip & Plate (Solution Heat Treated)
What is AMS 5525?
AMS 5525 is the SAE International aerospace material specification for A286 (UNS S66286), an austenitic iron-nickel-chromium precipitation-hardenable superalloy, supplied in the form of sheet, strip, and plate in the solution heat treated condition.
Heat treatment per AMS 5525 consists of solution annealing at a minimum of 1800°F (982°C) for one hour minimum, followed by oil or water quench.
In the solution heat treated condition, A286 per AMS 5525 achieves a minimum tensile strength of 130 ksi (896 MPa) and a minimum yield strength of 85 ksi (586 MPa), with exceptional ductility and weldability.
A286 is one of the original iron-based superalloys and retains its strength and oxidation resistance up to 1,300°F (704°C), making AMS 5525 a preferred specification for high-temperature aerospace sheet metal fabrication.
AMS 5525 Available Forms and Stocked Sizes
AMS 5525 covers three distinct flat product forms with specific thickness ranges:
Thickness: up to and including 0.1874 inches (4.76 mm)
Thickness: up to and including 0.1249 inches (3.17 mm)
Width: up to 24 inches (610 mm)
Thickness: 0.1875 inches (4.76 mm) and above
Fighter Jet Metals stocks and supplies AMS 5525 A286 sheet, strip, and plate in standard and custom-cut sizes with same-day quote response. Plate saw cutting, shearing, and laser cutting services are available in-house.
Applications of AMS 5525
Aerospace & Defense Applications
- Jet engine combustion liners, flame tubes, and transition ducts
- Afterburner components and tail pipes
- Turbine housings, exhaust casings, and heat shields
- High-temperature structural sheet metal components
- Aircraft engine fuel nozzle supports and brackets
- Military engine components requiring form-and-weld fabrication
- Sheet metal airframe parts in high-heat zones
Industrial Gas Turbine Applications
- Combustion hardware (liners, caps, swirlers)
- Transition pieces between combustor and turbine
- First-stage turbine shroud segments
- High-temperature duct assemblies
Cryogenic Applications
- Liquid nitrogen and liquid oxygen handling equipment
- Cryogenic storage vessel internals
- Piping and manifolds for liquefied natural gas (LNG) systems
- Tank structures requiring non-magnetic, high-strength material at −196°C
Oil & Gas Applications
- Downhole components in high-temperature, corrosive environments
- Sour gas service equipment (NACE MR0175 / ISO 15156 compliance)
- High-pressure, high-temperature (HPHT) wellhead hardware
Chemical Composition - AMS 5525
The following chemical composition limits apply to A286 (UNS S66286) per AMS 5525:
| Element | Symbol | Minimum % | Maximum % |
|---|---|---|---|
| Nickel | Ni | 24.0 | 27.0 |
| Chromium | Cr | 13.5 | 16.0 |
| Molybdenum | Mo | 1.00 | 1.50 |
| Titanium | Ti | 1.90 | 2.35 |
| Boron | B | 0.003 | 0.010 |
| Vanadium | V | 0.10 | 0.50 |
| Aluminum | Al | - | 0.35 |
| Carbon | C | - | 0.08 |
| Manganese | Mn | - | 2.00 |
| Silicon | Si | - | 1.00 |
| Phosphorus | P | - | 0.025 |
| Sulfur | S | - | 0.025 |
| Iron | Fe | Balance | - |
Nickel and chromium provide the austenitic structure, corrosion resistance, and oxidation resistance up to 1,300°F. Molybdenum adds solid-solution strengthening and pitting resistance.
Titanium and aluminum are the precipitation hardening elements – they combine with nickel to form the gamma-prime (γ’) strengthening phase when aged.
Boron segregates to grain boundaries and significantly improves creep rupture life and elevated-temperature ductility.
Mechanical Properties - AMS 5525
Minimum mechanical properties required by AMS 5525 for A286 sheet, strip, and plate in the solution heat treated condition:
| Property | Imperial | Metric |
|---|---|---|
| Tensile Strength (min) | 130,000 psi (130 ksi) | 896 MPa |
| Yield Strength, 0.2% offset (min) | 85,000 psi (85 ksi) | 586 MPa |
| Elongation in 2 in. (min) | 25% | 25% |
Elevated Temperature Properties - AMS 5525
A286 per AMS 5525 retains useful strength and oxidation resistance at temperatures that would degrade conventional stainless steels.
Typical properties at elevated temperature (after solution treatment + aging):
| Temperature | Tensile Strength (typical) | Yield Strength (typical) | Elongation (typical) |
|---|---|---|---|
| Room Temp (70°F / 21°C) | 147 ksi (1014 MPa) | 120 ksi (827 MPa) | 20% |
| 800°F (427°C) | 130 ksi (896 MPa) | 108 ksi (745 MPa) | 17% |
| 1000°F (538°C) | 122 ksi (841 MPa) | 100 ksi (689 MPa) | 16% |
| 1200°F (649°C) | 110 ksi (758 MPa) | 92 ksi (634 MPa) | 14% |
| 1300°F (704°C) | 90 ksi (621 MPa) | 75 ksi (517 MPa) | 12% |
Physical Properties - AMS 5525
| Property | Value (Imperial) | Value (Metric) |
|---|---|---|
| Density | 0.286 lb/in³ | 7.92 g/cm³ |
| Weight vs. Carbon Steel | ~100% (approximately equal density) | ~100% |
| Melting Range | 2500°F–2560°F | 1371°C–1404°C |
| Modulus of Elasticity | 29.1 × 10⁶ psi | 201 GPa |
| Thermal Conductivity | 8.6 BTU/(hr·ft·°F) | 14.9 W/(m·K) |
| Coefficient of Thermal Expansion | 9.4 × 10⁻⁶ /°F | 16.9 × 10⁻⁶ /°C |
| Specific Heat | 0.099 BTU/(lb·°F) | 414 J/(kg·K) |
| Max Service Temperature (Continuous) | 1,300°F | 704°C |
| Oxidation Resistance to | 1,500°F | 816°C |
| Cryogenic Service Capability | Down to −320°F | Down to −196°C |
AMS 5525 vs AMS 5858 - Key Differences
Both AMS 5525 and AMS 5858 cover A286 in flat product forms (sheet, strip, plate) in the solution heat treated condition.
Engineers and buyers frequently need to choose between these two specifications.
| Feature | AMS 5525 | AMS 5858 |
|---|---|---|
| Alloy | A286 (UNS S66286) | A286 (UNS S66286) |
| Product Forms | Sheet, Strip, Plate | Sheet, Strip, Plate |
| Condition | Solution Heat Treated | Solution Heat Treated (Unaged) |
| Emphasis | General-purpose A286 flat products | Weldability - no aging prior to fabrication |
| Specification Status | Original / older revision | More recent revision; preferred for weld fabrication |
| Tensile Strength Min | 130 ksi (896 MPa) | 130 ksi (896 MPa) |
| Yield Strength Min | 85 ksi (586 MPa) | 85 ksi (586 MPa) |
| Elongation Min | 25% | 25% |
| When to Use | General procurement; OEM called out AMS 5525 | Weld-critical applications; when drawing calls for unaged condition |
For most applications, AMS 5525 and AMS 5858 supply the same material in the same condition.
When your drawing or OEM specification calls for one or the other, use what is called out.
When you have a choice, AMS 5858 is the preferred specification for components that will be welded.
AMS 5525 Machining Guidelines
A286 is more difficult to machine than standard austenitic stainless steels (304/316) and behaves similarly to nickel-based superalloys.
The alloy work-hardens rapidly and has poor thermal conductivity, which concentrates heat at the cutting edge.
- Cutting speeds: Low (30–60 SFM for carbide tooling) – significantly lower than 304 stainless steel
- Feeds: Heavy chip loads preferred over high speeds; light feeds accelerate work hardening without cutting
- Tooling: Sharp, positive-rake carbide inserts; cobalt HSS for drilling and tapping; avoid dull tooling entirely
- Coolant: Heavy-duty sulfo-chlorinated cutting fluid or flood coolant required; never machine A286 dry
- Work hardening: A286 work hardens very rapidly at the cut surface – maintain constant feed and never allow the tool to dwell or rub
- Chatter: Rigid workholding and short tool overhangs are critical; chatter accelerates tool wear and surface damage
- Comparison: Machining A286 is similar in difficulty to Inconel 718 – more challenging than 304 SS, easier than Waspaloy
AMS 5525 Weldability
The solution heat treated (unaged) condition per AMS 5525 is the correct starting material for welding.
A286 that has already been precipitation hardened (aged) is susceptible to hot cracking during welding and should not be welded without re-annealing first.
- GTAW (TIG): Primary process for A286; argon or argon-helium shielding required
- GMAW (MIG): Higher deposition rate; suitable for heavier sections
- PAW (Plasma Arc): Used for precision aerospace weld joints
- Electron Beam (EBW): Vacuum process for critical joints where contamination is a concern
- Filler metal: Use matching A286 filler wire (UNS S66286); AWS ER320LR is an alternative for some applications
- Pre-heat: Not typically required for A286 sheet in the solution-treated condition
- Interpass temperature: Keep below 300°F (149°C) to prevent sensitization
- Post-weld heat treatment: For service above 900°F (482°C), a post-weld solution anneal (1800°F / 982°C) followed by aging is recommended to fully restore properties in the heat-affected zone
- Key advantage of AMS 5525 condition: Because the material is NOT aged prior to delivery, welding risk is minimized and post-weld aging can be performed after all fabrication is complete
Why AMS 5525 - Not Stainless Steel, Not Nickel Alloy
A286 occupies a unique position in the aerospace materials ecosystem.
Different distributors categorize it under stainless steel, nickel alloys, or superalloys – and all three are partially correct:
- It is iron-based (balance iron) – like a stainless steel
- It has 24–27% nickel – like a nickel superalloy in composition
- It strengthens through precipitation hardening (γ’) a mechanism characteristic of nickel superalloys (Inconel 718, Waspaloy)
- It costs less than nickel superalloys – iron-base content makes A286 significantly more affordable than Inconel 718 or Waspaloy while offering competitive high-temperature strength up to 1,300°F (704°C)
When to choose A286 per AMS 5525 over alternatives:
When application temperature exceeds 900°F (482°C) or when higher strength is needed
When cost is a constraint and service temperature is below 1,200°F (649°C)
When sheet/plate form is needed (Waspaloy is primarily used in disk/forgings applications)
When service temperature exceeds 750°F (400°C) – titanium loses significant strength above this range, while A286 continues to perform to 1,300°F
AMS 5525 Cross-Reference Specifications
SHEET & PLATE
Both cover the same flat product forms in the same condition. See the AMS 5525 vs. AMS 5858 comparison section below.
BARS & FORGINGS
Bar, wire, forgings, tubing, and rings in various heat treat conditions. Different product forms – not interchangeable with AMS 5525
General Electric Specifications
Certified to GE Aviation standards for jet engine hardware.
ROLLS ROYCE SPECIFICATIONS
Certified to Rolls-Royce standards for turbine and high-temperature parts.
PRATT & WHITNEY SPECIFICATIONS
Certified to Pratt & Whitney standards for fracture-critical rotating engine components.
SAFRAN SPECIFICATIONS
Certified to Safran / CFM International standards for engine hardware.
Trade Names and Equivalent Designations
A286 per AMS 5525 is known by several designations across different standards systems:
| Designation | System | Notes |
|---|---|---|
| A286 | Common name | Most widely used international notation |
| A-286 | Alternate hyphenation | Common in older drawings and military documents |
| Alloy A-286 | Commercial name | Historical designation from Special Metals / Inco |
| UNS S66286 | UNS (Unified Numbering System) | Standard material identifier in North America |
| AISI 660 | AISI designation | American Iron and Steel Institute |
| W.Nr. 1.4980 | Werkstoffnummer (DIN/EN) | European material number |
| X5NiCrTi26-15 | DIN/EN compositional name | European designation |
| Fe-26Ni-15Cr | Compositional shorthand | Approximate composition description |
| AMS 5525 | Full SAE designation | For sheet/strip/plate procurement |
Why Source AMS 5525 from Fighter Jet Metals?
Fighter Jet Metals supplies A286 sheet, strip, and plate to AMS 5525 with full mill certifications, heat-lot traceability, and AS9100D quality system compliance.
All material is supplied with certified mill test reports (CMTR) traceable to origin heat/lot, signed certificate of conformance, and documentation suitable for aerospace first-article and production use.
In-house processing available for AMS 5525 plate and sheet:
Plate saw cutting (thickness and length/width cuts)
Shearing (sheet and thin plate)
Laser cutting
Custom blanks and near-net shapes
Certified Material for Critical Service
Materials supplied in 6Al-4V titanium must meet strict aerospace certification and traceability requirements. Fighter Jet Metals supports sourcing across a wide range of AMS, MIL, and OEM specifications, ensuring compliance with industry standards.
All material is supplied with full mill certifications, complete heat-lot traceability, and detailed documentation. This ensures reliability and suitability for safety-critical aerospace, defense, and high-performance engineering applications.