Aluminium alloy 2618A 2618A

spore: profile
id: aluminium-2618a
spore_version: 0.2
family: aluminium-alloys
name: Aluminium alloy 2618A
abbreviation: 2618A
role: high-temperature forged and extruded aerospace alloy, piston and rotating-part alloy
category: metals
type: aluminium
summary: |
  2618A (AlCu2Mg1.5Ni, also written AA 2618A, EN AW-2618A and in older UK use DTD 5014A or BS H16) is a heat-treatable wrought aluminium alloy of the Al-Cu-Mg-Ni family, with about 1.8 to 2.7 % copper, 1.2 to 1.8 % magnesium and 0.8 to 1.4 % nickel. Its T6 temper (solution treated and artificially aged, or T6511 with controlled stretching) has a minimum 0.2 % proof stress of 320 MPa and a minimum tensile strength of 400 MPa for extruded bar under 10 mm thick (Smiths DTD 5014A minima). A supplier datasheet gives a T6 density of 2.76 g/cm³, a melting point of 549 °C and a maximum use temperature of 300 °C. The alloy is the high-temperature cousin of 2024 and 7075 and is widely used for pistons and rotating aircraft parts. Its ancestor R.R.58 (named 2618 in the Wikipedia Hiduminium article) was the main structural material of the Concorde airframe. No flight record for 2618A itself was found in the sources read.
best_for: Forged or extruded rotating parts, pistons and hot structural parts that must keep strength near 200 °C (Smiths datasheet and AircraftMaterials)
weakest_at: Fusion welding (not recommended by the supplier) and atmospheric corrosion resistance, which the supplier rates only fair to medium without protection
identity:
  formula: 'Al-Cu-Mg-Ni alloy, AlCu2Mg1.5Ni (EN AW-2618A family): Cu 1.8 to 2.7, Mg 1.2 to 1.8, Ni 0.8 to 1.4, Fe 0.9 to 1.4, Si 0.15 to 0.25, Mn max 0.25, Zn max 0.15, Ti max 0.20 wt%, Al balance'
  cas: ''
  source: aircraftmaterials-2618a
  where: Chemical Composition Limits table, column Alloy 2618A EAA (Si 0.15 to 0.25, Fe 0.9 to 1.4, Cu 1.8 to 2.7, Mn 0.25 max, Mg 1.2 to 1.8, Ni 0.8 to 1.4, Zn 0.15 max, Ti 0.20 max). The DTD 5014A composition on the Smiths datasheet (Cu 1.8 to 2.7, Mg 1.2 to 1.8, Ni 0.8 to 1.4, Fe 0.9 to 1.4) agrees on the main elements.
  designations:
    - system: UNS
      code: A92618
      source: referansmetal-2618a
      where: Standards list on the 2618A T6 page, row Barra de extrusion (UNS A92618 printed for 2618A T6 bar)
    - system: EN
      code: '3.1924'
      source: referansmetal-2618a
      where: Standards list on the 2618A T6 page, WNR 3.1924
    - system: EN name
      code: EN AW-2618A
      source: smiths-2618a
      where: 'Chemical composition line, General Engineering Euronorm row: EN 573 EN AW-2618A (AlCu2Mg1.5Ni)'
    - system: ISO
      code: AlCu2Mg1.5Ni
      source: referansmetal-2618a
      where: Standards list on the 2618A T6 page, ISO AlCu2Mg1.5Ni
    - system: AA
      code: 2618A
      source: aircraftmaterials-2618a
      where: Page title and composition table, row Alloy 2618A EAA
    - system: ASTM
      code: B221
      note: extruded bar, tube, wire, profile
      source: referansmetal-2618a
      where: Standards list on the 2618A T6 page, ASTM B221 for extrusion bar
    - system: BS
      code: H16
      note: old pre-1980 British specification
      source: smiths-2618a
      where: Specification row Old BS (pre-1980) Specification - H16
    - system: Trade name
      code: Hiduminium 58
      source: aircraftmaterials-2618a
      where: Specifications list, row Hiduminium 58 (the Rolls-Royce R.R. family name; see the Wikipedia Hiduminium article)
tags:
  environments: []
  stresses: []
  applications:
    - structures
    - mechanisms
    - propulsion-and-tanks
properties:
  - benchmark: density
    label: Density, 2618A T6
    value: 2.76
    unit: g/cm³
    scope: material
    conditions:
      temper: T6 (page title ASTM B221 / AlCu2Mg1.5Ni / 2618A / T6)
      form: extruded bar (page title)
      temperature: not stated
    method: Value printed on a supplier datasheet page
    status: ground
    source: referansmetal-2618a
    where: Physical Properties table, row Density
  - benchmark: density
    label: Density, 2618A bar, plate and tube
    value: 2.75
    unit: g/cc
    scope: material
    conditions:
      product: bar, plate and tube (as printed)
      temperature: not stated
    method: Value printed in the product description of a supplier datasheet
    status: ground
    source: smiths-2618a
    where: Product Description paragraph, sentence The alloy has a density of 2.75 g/cc
  - benchmark: melting_point
    label: Melting point, 2618A T6
    value: 549
    unit: °C
    scope: material
    conditions:
      temper: T6 (page title)
      form: not stated
    method: Single value printed on a supplier datasheet page
    status: ground
    source: referansmetal-2618a
    where: Physical Properties table, row Melting Point
  - benchmark: max_service_temp
    label: Maximum use temperature, 2618A
    value: 300
    bound: upper
    unit: °C
    scope: material
    conditions:
      temper: T6 or T6511 (as printed)
      basis: maximum use temperature as printed by the supplier
    method: Value printed in the product description of a supplier datasheet
    status: ground
    source: smiths-2618a
    where: Product Description paragraph, sentence 2618A can be employed to a maximum of 300°C
  - benchmark: cte
    label: Coefficient of thermal expansion, 2618A T6
    value: 21.6
    unit: µm/m°C
    scope: material
    conditions:
      temper: T6 (page title)
      temperature: not stated
    method: Value printed on a supplier datasheet page (printed as µm/m°C)
    status: ground
    source: referansmetal-2618a
    where: Physical Properties table, row Thermal Expansion
  - benchmark: elastic_modulus
    label: Modulus of elasticity, 2618A T6
    value: 71
    unit: GPa
    scope: material
    conditions:
      temper: T6 (page title)
      temperature: not stated
    method: Value printed on a supplier datasheet page
    status: ground
    source: referansmetal-2618a
    where: Physical Properties table, row Modulus of Elasticity
  - benchmark: thermal_conductivity
    label: Thermal conductivity, 2618A T6
    value: 147
    unit: W/m.K
    scope: material
    conditions:
      temper: T6 (page title)
      temperature: not stated
    method: Value printed on a supplier datasheet page
    status: ground
    source: referansmetal-2618a
    where: Physical Properties table, row Thermal Conductivity
  - benchmark: yield_strength
    label: Yield strength, 2618A T6
    value: 350
    unit: MPa
    scope: material
    conditions:
      temper: T6 (page title)
      form: extruded bar (page title)
      measure: not stated
    method: Value printed on a supplier datasheet page
    status: ground
    source: referansmetal-2618a
    where: Mechanical Properties table, row Yield Strength
  - benchmark: ultimate_tensile_strength
    label: Ultimate tensile strength, 2618A T6
    value: 420
    unit: MPa
    scope: material
    conditions:
      temper: T6 (page title)
      form: extruded bar (page title)
    method: Value printed on a supplier datasheet page
    status: ground
    source: referansmetal-2618a
    where: Mechanical Properties table, row Ultimate Strength
  - benchmark: shear_strength
    label: Shear strength, 2618A T6
    value: 260
    unit: MPa
    scope: material
    conditions:
      temper: T6 (page title)
      form: extruded bar (page title)
    method: Value printed on a supplier datasheet page
    status: ground
    source: referansmetal-2618a
    where: Mechanical Properties table, row Shear Strength
  - benchmark: brinell_hardness
    label: Brinell hardness, 2618A T6
    value: 120
    unit: HB
    scope: material
    conditions:
      temper: T6 (page title)
      form: extruded bar (page title)
    method: Value printed on a supplier datasheet page
    status: ground
    source: referansmetal-2618a
    where: Mechanical Properties table, row Hardness
  - benchmark: yield_strength
    label: Minimum 0.2 % proof stress, 2618A T6 bar up to 10 mm
    value: 320
    bound: lower
    unit: MPa
    scope: material
    conditions:
      temper: T6 (minima for T6 condition bar and sections, DTD 5014A)
      thickness: up to and including 10 mm
      basis: minimum specification value
    method: Minimum value printed in the mechanical properties table of a supplier datasheet
    status: ground
    source: smiths-2618a
    where: Mechanical Properties (Minima for T6 Condition Bar/Sections - DTD5014A) table, thickness 10 or less row, 0.2% PS column
  - benchmark: ultimate_tensile_strength
    label: Minimum tensile strength, 2618A T6 bar up to 10 mm
    value: 400
    bound: lower
    unit: MPa
    scope: material
    conditions:
      temper: T6 (minima for T6 condition bar and sections, DTD 5014A)
      thickness: up to and including 10 mm
      basis: minimum specification value
    method: Minimum value printed in the mechanical properties table of a supplier datasheet
    status: ground
    source: smiths-2618a
    where: Mechanical Properties (Minima for T6 Condition Bar/Sections - DTD5014A) table, thickness 10 or less row, UTS column
  - benchmark: elongation
    label: Minimum elongation on 50 mm, 2618A T6 bar up to 10 mm
    value: 5
    bound: lower
    unit: '%'
    scope: material
    conditions:
      temper: T6 (minima for T6 condition bar and sections, DTD 5014A)
      thickness: up to and including 10 mm
      gauge_length: 50 mm
      basis: minimum specification value
    method: Minimum value printed in the mechanical properties table of a supplier datasheet
    status: ground
    source: smiths-2618a
    where: Mechanical Properties (Minima for T6 Condition Bar/Sections - DTD5014A) table, thickness 10 or less row, Elong % on 50 mm column
  - benchmark: yield_strength
    label: Minimum 0.2 % proof stress, 2618A T6 bar 10 to 100 mm
    value: 340
    bound: lower
    unit: MPa
    scope: material
    conditions:
      temper: T6 (minima for T6 condition bar and sections, DTD 5014A)
      thickness: over 10 up to and including 100 mm
      basis: minimum specification value
    method: Minimum value printed in the mechanical properties table of a supplier datasheet
    status: ground
    source: smiths-2618a
    where: Mechanical Properties (Minima for T6 Condition Bar/Sections - DTD5014A) table, thickness 10 to 100 row, 0.2% PS column
  - benchmark: ultimate_tensile_strength
    label: Minimum tensile strength, 2618A T6 bar 10 to 100 mm
    value: 420
    bound: lower
    unit: MPa
    scope: material
    conditions:
      temper: T6 (minima for T6 condition bar and sections, DTD 5014A)
      thickness: over 10 up to and including 100 mm
      basis: minimum specification value
    method: Minimum value printed in the mechanical properties table of a supplier datasheet
    status: ground
    source: smiths-2618a
    where: Mechanical Properties (Minima for T6 Condition Bar/Sections - DTD5014A) table, thickness 10 to 100 row, UTS column
  - benchmark: elongation
    label: Minimum elongation on 50 mm, 2618A T6 bar 10 to 100 mm
    value: 7
    bound: lower
    unit: '%'
    scope: material
    conditions:
      temper: T6 (minima for T6 condition bar and sections, DTD 5014A)
      thickness: over 10 up to and including 100 mm
      gauge_length: 50 mm
      basis: minimum specification value
    method: Minimum value printed in the mechanical properties table of a supplier datasheet
    status: ground
    source: smiths-2618a
    where: Mechanical Properties (Minima for T6 Condition Bar/Sections - DTD5014A) table, thickness 10 to 100 row, Elong % on 50 mm column
corrosion:
  - environment: Atmospheric exposure, general service (supplier rating, no test conditions)
    headline: The supplier rates resistance to atmospheric attack as fair.
    effect: The Smiths datasheet rates 2618A as Fair for resistance to atmospheric attack. No exposure time, rate or test environment is given.
    rating: moderate
    conditions:
      basis: qualitative supplier rating only (printed as Fair; mapped to the nearest enum value)
      test: none stated
    source: smiths-2618a
    where: Corrosion Resistance box, row Resistance to Atmospheric Attack
  - environment: General service (supplier selection rating, Spanish-language page)
    headline: Referans Metal rates the corrosion resistance of 2618A T6 as medium.
    effect: The properties summary for 2618A T6 rates corrosion resistance as Media (medium), with strength rated high, machinability moderate, weldability low, formability good and heat treatment yes. No test environment or exposure time is given.
    rating: moderate
    conditions:
      basis: qualitative supplier rating only
      test: none stated
    source: referansmetal-2618a
    where: Propiedades caracteristicas de 2618A T6 list, row Resistencia a la corrosion
  - environment: Anodising (surface treatment, supplier rating)
    headline: Anodising is rated fair for protection, and it is the usual way to add protection.
    effect: The Smiths datasheet rates anodising as Protective Fair, Hard Fair and Colour Fair, and Bright Unsuitable. The Referans page says that anodising and coatings improve corrosion resistance of 2618A. No corrosion test data is given.
    rating: moderate
    conditions:
      basis: qualitative supplier rating only (printed as Fair; mapped to the nearest enum value)
      test: none stated
    source: smiths-2618a
    where: Surface Treatment box, Anodising row
risks:
  hazards:
    - text: The Hydro safety data sheet for the wrought 2xxx series (revised 2018) lists aluminium at 85 to 97 % with the GHS classes Flam. Sol. 1 H228 and Water-react. 2 H261, plus a combustible dust hazard, and says metallic dusts may ignite or explode. The sheet covers the whole 2xxx family, not 2618A alone, so these classes are a family-level reading.
      ghs:
        - H228
        - H261
      source: hydro-2xxx-sds
      where: Section 3 composition table, row Aluminum; Section 2 text on metallic dust
    - text: The same Hydro sheet lists nickel (up to 2.4 %) with Skin Sens. 1 H317, Carc. 2 H351 (inhalation) and STOT RE 1 H372 (lungs). 2618A contains 0.8 to 1.4 % nickel, so the nickel hazard applies in principle, but the sheet describes the 2xxx family and not 2618A itself.
      ghs:
        - H317
        - H351
        - H372
      source: hydro-2xxx-sds
      where: Section 2.1 classification and Section 3 composition table, row Nickel; hazard statements list
    - text: The same Hydro sheet says that inhaling dusts and fumes can cause metal fume fever, and that small chips, fine turnings and dust from processing may be toxic to aquatic life.
      ghs: []
      source: hydro-2xxx-sds
      where: Section 2.3 Other Hazards
  failure_risks:
    - mode: Poor fusion-weld joints
      trigger: Fusion or gas welding of 2618A parts
      consequence: The Smiths datasheet lists brazing, soldering, oxygen welding and inert-gas welding as Not Recommended. The Referans page rates weldability as low and says mechanical joints are generally preferred. No weld-strength figure was found.
      severity: high
      source: smiths-2618a
      where: Weldability box, rows Brazing and Soldering, Oxygen and Inert Gas; Referans Metal properties summary, row Soldabilidad Baja
    - mode: Strength loss at elevated temperature
      trigger: Service above about 200 °C, up to the 300 °C maximum
      consequence: The Smiths datasheet says the alloy retains its mechanical strength relatively well to around 200 °C and above, with a maximum use of 300 °C. No strength-versus-temperature figure was found in the sources read.
      severity: moderate
      source: smiths-2618a
      where: Product Description paragraph, sentences on maximum 300 °C and strength to around 200 °C
    - mode: Surface corrosion of unprotected parts
      trigger: Long atmospheric exposure without anodising or a coating
      consequence: The supplier rates atmospheric resistance as fair (Smiths) and medium (Referans Metal), and recommends protective finishes. No pit depth, rate or test result for this alloy was found.
      severity: moderate
      source: smiths-2618a
      where: Corrosion Resistance box and Surface Treatment box; Referans Metal properties summary
  side_effects: []
  handling:
    - text: Keep machining dust and fines under control. The Hydro sheet says metallic dusts may ignite or explode and that the product dust may be toxic to aquatic life. It also says to avoid breathing dust or fume.
      source: hydro-2xxx-sds
      where: Section 2.3 text on metallic dust; precautionary statement P260 Do not breathe dust, fume
    - text: Specify T6 or T6511 and the product form before comparing values, because the datasheets give minima for bar and sections and the two tempers differ in how they are made.
      source: smiths-2618a
      where: Product Description paragraph (T6 and T6511 tempers); Mechanical Properties minima table
    - text: Use mechanical joints rather than fusion welding. The Smiths datasheet lists brazing and welding as Not Recommended, and the Referans page rates weldability as low.
      source: referansmetal-2618a
      where: Propiedades caracteristicas list, row Soldabilidad Baja, and the Smiths Weldability box
  mitigations: []
uses:
  - application: mechanisms
    device: Pistons and rotating aircraft parts
    example: AircraftMaterials says 2618A is commonly used for pistons and rotating aircraft parts because it works at higher temperatures, and that it has become very popular for motor racing pistons.
    source: aircraftmaterials-2618a
    where: Introduction paragraph of the Technical Data Sheet
  - application: propulsion-and-tanks
    device: Aircraft engine components
    example: The Referans Metal page lists aircraft engine use in its list of well-known applications for 2618A T6, with aerospace and defence components.
    source: referansmetal-2618a
    where: Algunas aplicaciones bien conocidas para 2618A T6 list, first bullet
  - application: structures
    device: Concorde airframe (grade named 2618 in the source, not 2618A)
    example: The Wikipedia Hiduminium article identifies R.R.58, also known as Aluminium 2618, as the main structural material of the Concorde airframe in the 1960s and 1970s. The article names 2618 and not 2618A, so this is a use of the parent grade.
    source: wiki-hiduminium
    where: In jet engines section, paragraph on R.R.58 and the Concorde airframe
supply:
  - subject: Primary aluminium smelter production, 2025 estimate (world)
    producers:
      - country: China
        share_percent: 60.8
        year: 2025
      - country: India
        share_percent: 5.7
        year: 2025
      - country: Russia
        share_percent: 5.3
        year: 2025
      - country: Canada
        share_percent: 4.5
        year: 2025
      - country: United Arab Emirates
        share_percent: 3.6
        year: 2025
    critical_lists: []
    recycling: 'USGS: in 2025 about 3.6 million tons of aluminum were recovered from purchased scrap in the United States, about 56 % from new scrap and 44 % from old scrap. Old-scrap recovery was equivalent to about 28 % of apparent consumption.'
    substitutes:
      - 'USGS: composites can substitute for aluminum in aircraft fuselages and wings.'
    source: usgs-mcs2026-aluminum
    where: 'World Smelter Production and Capacity table, column 2025e: China 45,000, India 4,200, Russia 3,900, Canada 3,300, United Arab Emirates 2,700, world total (rounded) 74,000 thousand t. Shares are calculated by Space Mushroom from those printed values. Recycling and Substitutes sections.'
documents:
  - title: 'Smiths Metal Centres: 2618A Technical Datasheet (bar and plate, composition, DTD 5014A minima, surface treatment)'
    type: datasheet
    url: https://www.smithmetal.com/pdf/aluminium/2xxx/2618a.pdf
    year: 2023
  - title: 'Referans Metal: ASTM B221 / AlCu2Mg1.5Ni / 2618A / T6 product page (chemical, physical and mechanical tables, standards list)'
    type: datasheet
    url: https://referansmetal.com/alasimli-aluminyum/product/195/uzay-havacilik-savunma/cubuk-lama/astm-b221-alcu2mg1-5ni-2618a-t6?lang=es
  - title: 'AircraftMaterialsUK: Aluminium Alloy 2618A DTD 5014A Technical Data Sheet'
    type: datasheet
    url: https://www.aircraftmaterials.com/data/aluminium/2618a.html
  - title: 'Wikipedia: Hiduminium (R.R. alloys, R.R.58 named as Aluminium 2618 and used in the Concorde airframe)'
    type: database
    url: https://en.wikipedia.org/wiki/Hiduminium
    year: 2026
  - title: 'USGS Mineral Commodity Summaries 2026: Aluminum'
    type: report
    url: https://pubs.usgs.gov/periodicals/mcs2026/mcs2026-aluminum.pdf
    year: 2026
  - title: 'Hydro Extrusion USA: Safety Data Sheet, Wrought Aluminum Products, 2xxx Series Alloys (revision 08/14/2018, issued 09/17/2014)'
    type: sds
    url: https://www.hydro.com/globalassets/01-products--services/extruded-profiles/americas/ena-resources/safety-data-sheets/4-664-2xxx-series.pdf
    year: 2018
gaps:
  - No flight, spacecraft, satellite or launch-vehicle record for the 2618A grade was found. The Concorde airframe use found in the Wikipedia Hiduminium article concerns grade 2618 (R.R.58), not 2618A.
  - No strength-versus-temperature data, creep data or fatigue data for 2618A were found in the sources read. The HAL fatigue study for 2618-T851 returned an HTML page instead of a PDF, and the DTIC report was blocked.
  - No corrosion test data (salt spray, ASTM G34 or G66, exfoliation, stress-corrosion) for 2618A was found. The corrosion entries are supplier ratings only.
  - Ageing times and temperatures for T6 and T6511 are not given in the sources read. The MakeItFrom 2618 T61 values in search snippets were not used, because they are for another grade and temper and the page was not reachable.
  - The electrical figure 37 % IACS on the Referans page sits under an Electrical Resistivity label, and the unit label conflicts, so the value was left out (same treatment as the 2017 profile).
  - The Referans page elongation for T6 bar prints as %6 and cannot be read, so no elongation value for that row was recorded.
  - The Referans page composition under the 2618A heading (Mn 0.00 to 0.25, Ni 0.90 to 1.20, Zn 0.00 to 0.10, Ti 0.04 to 0.10, Fe 0.90 to 1.30, Cu 1.90 to 2.70, Mg 1.30 to 1.80) matches the US 2618 row of the AircraftMaterials table. It was not used for the recipe. The recipe uses the AircraftMaterials 2618A EAA row and agrees with the Smiths DTD 5014A limits on the main elements.
  - Density conflicts slightly between two suppliers (2.75 g/cc on Smiths, 2.76 g/cm³ on Referans). Both are kept with their sources.
  - Machinability is rated Good by Smiths and Moderada (moderate) by Referans Metal. Both ratings are kept as the source prints them; the Referans row is not used in the summary.
  - Shear strength is recorded under the name shear_strength, which is not listed in spores/property-canon.yaml. Brinell hardness is recorded under brinell_hardness, which is also not listed in that file.
  - The hazard classes come from the Hydro SDS for the whole wrought 2xxx family, not a 2618A-specific SDS. Nickel classes are read from the same family sheet.
  - The USGS 2026 aluminum summary does not mention a critical-minerals list, so no critical-list entry is recorded.
  - 'No media entry was added: no image of 2618A was fetched in this run with its licence checked.'
  - The Smiths weldability row is a list of processes marked Not Recommended, with no single weldability rating printed. The failure-risk entry uses those process rows.
story:
  recipe:
    line: 2618A is a wrought Al-Cu-Mg-Ni alloy. Its main alloying elements are copper, magnesium and nickel, with iron and silicon as minor elements (AircraftMaterials composition limits; Smiths DTD 5014A composition). It is made by solution treatment and artificial ageing to T6, or with controlled stretching to T6511 (Smiths). The composition below is the standard range, not a measured value.
    parts:
      - name: Aluminium
        symbol: Al
        share: balance
        role: The matrix of the alloy. Balance of the composition.
      - name: Copper
        symbol: Cu
        share: 1.8 to 2.7 wt%
        role: The main strengthening element with magnesium, forming the age-hardening precipitates of the T6 temper.
      - name: Magnesium
        symbol: Mg
        share: 1.2 to 1.8 wt%
        role: Age-hardening element that works with copper and nickel.
      - name: Nickel
        symbol: Ni
        share: 0.8 to 1.4 wt%
        role: Keeps strength at high temperature, which is why the alloy suits pistons and rotating parts (AircraftMaterials).
      - name: Iron
        symbol: Fe
        share: 0.9 to 1.4 wt%
        role: Minor element printed in the composition limits.
      - name: Silicon
        symbol: Si
        share: 0.15 to 0.25 wt%
        role: Minor element printed in the composition limits.
  risk_groups:
    - title: For people
      level: 1
      verdict: Dust, fume and nickel warnings
      lead: The Hydro safety data sheet for the 2xxx series gives dust, fume and nickel warnings for processing. No health data specific to 2618A were found.
      points:
        - label: Machining dust
          line: Metallic dust can ignite or explode, and dusts and fumes from machining or welding can cause metal fume fever (Hydro SDS, 2xxx series).
        - label: Nickel
          line: The same sheet lists nickel with a skin-sensitiser class (H317) and suspected inhalation carcinogenicity (H351). 2618A contains nickel, so the same care applies to dust and fume.
        - label: Environment
          line: Small chips, fine turnings and processing dust may be toxic to aquatic life, according to the same sheet.
    - title: If it fails
      lead: The failure routes found in the sources are weld joints, loss of strength at high temperature, and surface corrosion.
      points:
        - label: Welds
          line: The Smiths datasheet lists brazing, soldering and welding processes as Not Recommended, and the Referans page rates weldability as low.
        - label: Heat
          line: The Smiths datasheet says the alloy keeps its strength relatively well to around 200 °C and can be used up to 300 °C.
        - label: Corrosion
          line: The supplier rates atmospheric resistance as fair and medium. Protective anodising or coatings are recommended.
    - title: Handling and storage
      points:
        - label: Specify temper
          line: State T6 or T6511 and the product form, because the minima differ between bar and sections and the two tempers are made differently.
        - label: Dust control
          line: Keep machining dust and fines under control, and do not breathe dust or fume, following the Hydro SDS.
  why: 2618A is a high-temperature aerospace alloy. The supplier gives a T6 yield strength of 350 MPa and a tensile strength of 420 MPa, a density of 2.76 g/cm³ and a hardness of 120 HB. It is used for pistons and rotating aircraft parts because it keeps strength at higher temperatures than many aluminium alloys, and its parent grade 2618 was the main structural material of the Concorde airframe.
  uses:
    - where: Pistons and rotating aircraft parts
      line: AircraftMaterials says 2618A is commonly used for pistons and rotating aircraft parts, and it is very popular for motor racing pistons.
    - where: Aircraft engine and defence components
      line: The Referans Metal and Smiths pages list aircraft engine parts, aerospace and defence components, and high-technology applications.
    - where: Concorde airframe (parent grade 2618)
      line: The Wikipedia Hiduminium article says R.R.58, named 2618, was the main structural material of the Concorde airframe. This is the parent grade, not 2618A.
  can_do:
    - label: Carry load at temperature
      value: 350 MPa yield
      benchmark: yield_strength
      line: The supplier gives a T6 yield strength of 350 MPa and a tensile strength of 420 MPa.
    - label: Stay useful when hot
      value: 300 °C maximum
      benchmark: max_service_temp
      line: The Smiths datasheet gives a maximum use temperature of 300 °C.
    - label: Weight
      value: 2.76 g/cm³
      benchmark: density
      line: The Referans Metal page gives a density of 2.76 g/cm³ and Smiths gives 2.75 g/cc.
    - label: Heat
      value: 147 W/m.K
      benchmark: thermal_conductivity
      line: The supplier gives a thermal conductivity of 147 W/m.K for T6.
    - label: Hardness
      value: 120 HB
      benchmark: brinell_hardness
      line: The supplier gives a hardness of 120 HB for T6.
  compare: Compared with the other rows of this site, 2618A is a high-temperature Al-Cu-Mg-Ni alloy whose strength is set by its temper and product form. The sources here give its density, stiffness and thermal figures for this alloy only, and they do not compare it with other grades numerically.
  compare_rows:
    - label: Density
      benchmark: density
    - label: Thermal conductivity
      benchmark: thermal_conductivity
    - label: Modulus of elasticity
      benchmark: elastic_modulus
  handling:
    - Specify T6 or T6511 and the product form, because the minima for bar and sections differ.
    - Keep machining dust and fines under control. Metallic dust can ignite or explode.
    - Use mechanical joints rather than fusion welding. Brazing and welding are Not Recommended on the Smiths datasheet.
  good_for:
    - Forged or extruded rotating parts and pistons that must keep strength at higher temperatures, as printed in the AircraftMaterials and Referans Metal sources.
    - Hot structural parts that run up to about 200 °C, where the supplier says strength is kept relatively well.
    - Engine and defence components with a protective finish such as anodising.
  watch_out:
    - 'Welding: brazing and welding are Not Recommended, and the supplier rates weldability as low.'
    - 'Corrosion: the supplier rates atmospheric resistance fair to medium, so protect bare parts. No test data for this alloy was found.'
    - 'Temper: specify T6 or T6511 before comparing strengths, because the minima differ by thickness.'
    - The sources read here do not confirm any spacecraft or launcher use of the 2618A grade.
  verdict: 2618A is a strong aerospace alloy for hot parts, pistons and rotating components, with a 300 °C maximum use temperature from the supplier. It is hard to weld and only fairly corrosion resistant without a finish, and the sources here do not confirm a flight record for this grade.
sources:
  referansmetal-2618a:
    title: 'Referans Metal: ASTM B221 / AlCu2Mg1.5Ni / 2618A / T6 product page'
    id: UNS A92618, WNR 3.1924, ISO AlCu2Mg1.5Ni, ASTM B221
    url: https://referansmetal.com/alasimli-aluminyum/product/195/uzay-havacilik-savunma/cubuk-lama/astm-b221-alcu2mg1-5ni-2618a-t6?lang=es
    kind: datasheet
    license: Supplier web page (cited, not reproduced)
  smiths-2618a:
    title: 'Smiths Metal Centres: 2618A Technical Datasheet'
    id: EN AW-2618A, DTD 5014A, BS H16
    url: https://www.smithmetal.com/pdf/aluminium/2xxx/2618a.pdf
    year: 2023
    kind: datasheet
    license: Supplier datasheet (cited, not reproduced)
  aircraftmaterials-2618a:
    title: 'AircraftMaterialsUK: Aluminium Alloy 2618A DTD 5014A'
    id: AA 2618A, DTD 5014A, Hiduminium 58
    url: https://www.aircraftmaterials.com/data/aluminium/2618a.html
    kind: datasheet
    license: Supplier web page (cited, not reproduced)
  wiki-hiduminium:
    title: Hiduminium (Wikipedia)
    url: https://en.wikipedia.org/wiki/Hiduminium
    year: 2026
    kind: web
    license: CC BY-SA 4.0 (cited, not reproduced)
  usgs-mcs2026-aluminum:
    title: 'Mineral Commodity Summaries 2026: Aluminum'
    id: USGS MCS 2026
    url: https://pubs.usgs.gov/periodicals/mcs2026/mcs2026-aluminum.pdf
    year: 2026
    kind: report
    license: public domain (USGS)
  hydro-2xxx-sds:
    title: 'Hydro Extrusion USA: Safety Data Sheet, Wrought Aluminum Products, 2xxx Series Alloys (revision 08/14/2018, issued 09/17/2014)'
    url: https://www.hydro.com/globalassets/01-products--services/extruded-profiles/americas/ena-resources/safety-data-sheets/4-664-2xxx-series.pdf
    year: 2018
    kind: datasheet
    license: Manufacturer safety data sheet (cited, not reproduced)
license: CC-BY-4.0
updated: '2026-10-26'
review:
  status: draft
  method: assistant
  checked_values: 17
  unreachable: 2
  caveats: 4
  note: 'Values were read by an AI assistant on 2026-10-26 from the pages named in each entry. Unreachable or blocked: MakeItFrom 2618A pages (search snippet only, not fetched), HAL fatigue paper (returned HTML), DTIC report (blocked). Caveats: the density comes from two suppliers that differ slightly; the minima are DTD 5014A specification values, not typical values; the hazard classes are for the whole 2xxx family; the Concorde airframe use concerns grade 2618, not 2618A.'