AMS 5536 - Hastelloy X Nickel Alloy Sheet, Coil & Plate (Solution Annealed)
AMS 5536 is the SAE International aerospace material specification for Hastelloy X (UNS N06002), a nickel-chromium-iron-molybdenum superalloy, supplied in the form of sheet, coil, and plate in the solution annealed condition.
Hastelloy X is one of the most widely used nickel-base superalloys for high-temperature applications, combining solid-solution strengthening, exceptional oxidation resistance, and outstanding fabricability.
In the solution annealed condition per AMS 5536, Hastelloy X achieves a minimum tensile strength of 100 ksi (690 MPa) and a minimum yield strength of 45 ksi (310 MPa) with a minimum elongation of 35%. The alloy retains useful strength and oxidation resistance at temperatures up to 2200°F (1204°C), making AMS 5536 the primary specification for Hastelloy X flat-rolled products used in gas turbine combustion hardware, aircraft afterburner components, and industrial furnace applications.
AMS 5536 Available Forms and Stocked Sizes
AMS 5536 covers Hastelloy X in flat-rolled forms:
Thickness: up to and including 0.1874 inches (4.76 mm)
Thickness: 0.1875 inches (4.76 mm) and above
Fighter Jet Metals stocks and supplies AMS 5536 Hastelloy X sheet, coil, 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 5536
Aerospace & Gas Turbine Applications
- Gas turbine combustion cans and combustion liners
- Transition ducts between combustor and turbine
- Flame holders and flame tubes
- Afterburner components and augmentor hardware
- Turbine exhaust casings and heat shields
- Aircraft engine fuel nozzle bodies and supports
- Military engine sheet metal fabrications requiring high-temperature capability
Industrial Furnace & Heat Treating Applications
- Industrial furnace rolls, trays, fixtures, and muffles
- Retorts and radiant tubes for atmosphere furnaces
- Heat treating baskets and work support fixtures
- Kiln furniture and high-temperature process components
- Furnace liners and radiation shields
Chemical & Petrochemical Processing
- Reactor components in high-temperature chemical processes
- Catalyst support grids and screens
- High-temperature piping and ducting for corrosive gas service
- Pressure vessels for sour gas and sulfurous environments
- Heat exchanger components requiring combined heat and corrosion resistance
Chemical Composition - AMS 5536
The following chemical composition limits apply to Hastelloy X (UNS N06002) per AMS 5536:
| Element | Symbol | Minimum % | Maximum % |
|---|---|---|---|
| Nickel | Ni | Balance | - |
| Chromium | Cr | 20.5 | 23.0 |
| Iron | Fe | 17.0 | 20.0 |
| Molybdenum | Mo | 8.0 | 10.0 |
| Boron | B | - | 0.010 |
| Cobalt | Co | 0.50 | 2.50 |
| Tungsten | W | 0.20 | 1.00 |
| Carbon | C | 0.05 | 0.15 |
| Manganese | Mn | - | 1.00 |
| Silicon | Si | - | 1.00 |
| Phosphorus | P | - | 0.040 |
| Sulfur | S | - | 0.030 |
Chromium provides oxidation resistance and forms a protective Cr₂O₃ scale at high temperatures.
Molybdenum provides solid-solution strengthening, which is the primary hardening mechanism in Hastelloy X – unlike precipitation-hardenable superalloys (Inconel 718, A286), Hastelloy X does not age harden.
Iron content (17–20%) makes Hastelloy X a nickel-iron-chromium-molybdenum alloy rather than a pure nickel-base alloy, which contributes to its relatively lower cost compared to Inconel 625 or Waspaloy.
Cobalt and Tungsten provide additional solid-solution strengthening at elevated temperatures.
The controlled carbon range (0.05–0.15%) promotes carbide formation at grain boundaries, which improves creep resistance.
Mechanical Properties - AMS 5536
Minimum mechanical properties required by AMS 5536 for Hastelloy X sheet, coil, and plate in the solution annealed condition:
| Property | Imperial | Metric |
|---|---|---|
| Tensile Strength (min) | 100,000 psi (100 ksi) | 690 MPa |
| Yield Strength, 0.2% offset (min) | 45,000 psi (45 ksi) | 310 MPa |
| Elongation in 2 in. (min) | 35% | 35% |
Elevated Temperature Properties - AMS 5536
Hastelloy X per AMS 5536 retains useful strength at temperatures that far exceed the capability of conventional stainless steels and most other nickel alloys. Typical properties at elevated temperature (solution annealed condition):
| Temperature | Tensile Strength (typical) | Yield Strength (typical) | Elongation (typical) |
|---|---|---|---|
| Room Temp (70°F / 21°C) | 114 ksi (786 MPa) | 52 ksi (359 MPa) | 43% |
| 1000°F (538°C) | 89 ksi (614 MPa) | 38 ksi (262 MPa) | 37% |
| 1200°F (649°C) | 76 ksi (524 MPa) | 34 ksi (234 MPa) | 35% |
| 1500°F (816°C) | 52 ksi (359 MPa) | 28 ksi (193 MPa) | 33% |
| 1800°F (982°C) | 24 ksi (165 MPa) | 16 ksi (110 MPa) | 46% |
| 2000°F (1093°C) | 12 ksi (83 MPa) | 9 ksi (62 MPa) | 58% |
Physical Properties - AMS 5536
| Property | Value (Imperial) | Value (Metric) |
|---|---|---|
| Density | 0.297 lb/in³ | 8.22 g/cm³ |
| Melting Range | 2300°F–2470°F | 1260°C–1355°C |
| Modulus of Elasticity | 28.0 × 10⁶ psi | 193 GPa |
| Thermal Conductivity | 6.1 BTU/(hr·ft·°F) | 10.6 W/(m·K) |
| Thermal Conductivity (1800°F) | 12.0 BTU/(hr·ft·°F) | 20.8 W/(m·K) |
| Coefficient of Thermal Expansion | 8.4 × 10⁻⁶ /°F | 15.1 × 10⁻⁶ /°C |
| Specific Heat | 0.098 BTU/(lb·°F) | 410 J/(kg·K) |
| Max Service Temperature (Oxidizing) | 2200°F | 1204°C |
| Max Service Temperature (Reducing/Carburizing) | 1800°F | 982°C |
AMS 5536 vs AMS 5754 - Key Differences
Both AMS 5536 and AMS 5754 cover Hastelloy X (UNS N06002) in the solution annealed condition, but for entirely different product forms.
| Feature | AMS 5536 | AMS 5754 |
|---|---|---|
| Alloy | Hastelloy X (UNS N06002) | Hastelloy X (UNS N06002) |
| Product Forms | Sheet, Coil, Plate | Bar, Forgings, Rings |
| Condition | Solution Annealed | Solution Annealed |
| Tensile Strength Min | 100 ksi (690 MPa) | 100 ksi (690 MPa) |
| Yield Strength Min | 45 ksi (310 MPa) | 45 ksi (310 MPa) |
| Elongation Min | 35% | 35% |
| When to Use | Sheet metal fabrication, formed parts, weld assemblies | Machined components, shafts, flanges, structural forgings |
AMS 5536 and AMS 5754 specify the same alloy in the same condition with the same minimum mechanical properties.
The choice is driven entirely by product form required by the engineering drawing.
If the drawing calls for sheet or plate – use AMS 5536. If it calls for bar or forgings – use AMS 5754.
AMS 5536 Machining Guidelines
Hastelloy X is more difficult to machine than austenitic stainless steels but is considered one of the more machinable nickel superalloys compared to Inconel 718 or Waspaloy.
- Cutting speeds: Low to moderate (40–80 SFM for carbide tooling) – faster than Inconel 718, slower than 304 stainless
- Feeds: Moderate chip loads; avoid rubbing – Hastelloy X work hardens, though less aggressively than A286
- Tooling: Sharp, positive-rake carbide inserts; coated carbide (TiAlN) preferred for longer tool life
- Coolant: Flood coolant required – sulfo-chlorinated cutting fluid or water-soluble coolant; never machine dry
- Work hardening: Hastelloy X work hardens moderately – maintain consistent feed and avoid dwell
- Comparison: Easier to machine than Inconel 718 or Waspaloy; more difficult than 304/316 stainless steel; similar to Hastelloy C276
AMS 5536 Weldability
Hastelloy X per AMS 5536 has excellent weldability – one of the key reasons it is preferred over many other nickel superalloys for sheet metal fabrication.
The alloy does not require pre-weld heat treatment and is highly resistant to strain-age cracking during welding.
- GTAW (TIG): Primary process; argon or argon-helium shielding required
- GMAW (MIG): Suitable for heavier sections; higher deposition rate
- PAW (Plasma Arc): Used for precision aerospace joints
- Electron Beam (EBW): Vacuum process for critical aerospace joints
- Resistance welding: Spot and seam welding applicable for thin sheet assemblies
- Filler metal: ERNiCrMo-2 (Hastelloy X matching filler) preferred; ERNiCrMo-3 (Inconel 625 filler) is an acceptable alternative for most applications
- Pre-heat: Not required – Hastelloy X does not require pre-heat under normal conditions
- Interpass temperature: Keep below 200°F (93°C) to minimize distortion
- Post-weld heat treatment: Solution anneal at 2150°F (1177°C) – not always required, but recommended for applications subject to stress-corrosion or severe service
- Key weldability advantage: Unlike precipitation-hardenable alloys (A286, Inconel 718), Hastelloy X is not susceptible to strain-age cracking during welding. This makes it the preferred choice for complex, multi-weld assemblies such as combustion liners and transition ducts
Why AMS 5536 Hastelloy X - The High-Temperature Sheet Metal Standard
Hastelloy X occupies a unique position in the aerospace and industrial materials ecosystem as the go-to alloy for high-temperature sheet metal fabrication.
When application temperature exceeds the capability of stainless steels but cost and fabricability must be balanced:
Hastelloy X is required when service temperature exceeds approximately 1400°F (760°C) – stainless steels oxidize and lose strength well below Hastelloy X’s operating range
Hastelloy X operates 900°F higher – use A286 up to 1300°F (704°C), Hastelloy X up to 2200°F (1204°C)
Hastelloy X is easier to form, weld, and fabricate into complex sheet-metal shapes; Waspaloy is used primarily in disk/forgings with higher strength requirements
Hastelloy X is preferred for high-temperature oxidizing environments; Inconel 625 is preferred for aqueous corrosion and lower-temperature elevated-service
Hastelloy X has better oxidation resistance at very high temperatures (above 1800°F); Inconel 718 has higher room-temperature and moderate-temperature strength but loses advantage above 1400°F
AMS 5536 Cross-Reference Specifications
AMS 5536 - Related SAE AMS Specification
The companion SAE AMS specification for Hastelloy X in long-product forms. Different product forms – not interchangeable with AMS 5536.
General Electric Specifications
Certified to GE Aviation standards for jet engine combustion and high-temperature hardware.
Rolls-Royce Specifications
Certified to Rolls-Royce standards for turbine and high-temperature engine hardware.
Snecma / Safran Specifications
Certified to Snecma / Safran standards for aircraft engines and high-temperature structural parts.
Other Specifications
Product Design Specification for Hastelloy X sheet and plate used in aerospace and high-temperature industrial applications.
Trade Names and Equivalent Designations
Hastelloy X per AMS 5536 is known by several designations across different standards systems:
| Designation | System | Notes |
|---|---|---|
| Hastelloy X | Trade name | Original designation by Haynes International |
| Alloy X | Common name | Generic designation used in non-branded references |
| UNS N06002 | UNS (Unified Numbering System) | Standard material identifier in North America |
| W.Nr. 2.4665 | Werkstoffnummer (DIN/EN) | European material number |
| NiCr22Fe18Mo | DIN/EN compositional name | European designation |
| AMS 5536 | Full SAE designation | For sheet, coil, plate procurement |
| AMS 5754 | Full SAE designation | For bar, forgings, rings |
Why Source AMS 5536 from Fighter Jet Metals
Fighter Jet Metals supplies Hastelloy X sheet, coil, and plate to AMS 5536 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 5536 sheet and plate
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.