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Concepts For Manufacturing a Seat Backrest Structure Dominated by an Extruded Magnesium Alloy

  • Technical Paper
  • 2021-01-0277
To be published on 2021-04-06 by SAE International in United States
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Cast Magnesium Subframe Development – Bolt Load Retention

  • Technical Paper
  • 2021-01-0274
To be published on 2021-04-06 by SAE International in United States
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Joining magnesium die casting using self-piercing riveting (SPR) with a rivet receiver layer

  • Technical Paper
  • 2021-01-0275
To be published on 2021-04-06 by SAE International in United States
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Aluminum Alloy, Extrusions 5.6Zn - 2.5Mg - 1.6Cu - 0.23Cr (7075-O) Annealed

  • Aerospace Material Specification
  • AMS4476A
  • Current
Published 2021-02-11 by SAE International in United States
This content contains downloadable datasets
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Aluminum Alloy, Sheet 3.5Cu - 1.1Li - 0.50Mg - 0.40Ag - 0.12Zr (2098-T8) Solution Heat Treated, Cold Worked, and Artificially Aged

  • Aerospace Material Specification
  • AMS4457A
  • Current
Published 2021-01-26 by SAE International in United States
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Aluminum Alloy, Extruded Rod, Bar, and Profiles (7055-T76511) 8.0Zn - 2.3Cu - 2.0Mg - 0.16Zr Solution Heat Treated, Stress-Relieved, and Overaged

  • Aerospace Material Specification
  • AMS4336C
  • Current
Published 2020-12-10 by SAE International in United States
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Aluminum Alloy, Extrusions 1.0Mg - 0.60Si - 0.28Cu - 0.20Cr (6061-T4) Solution Heat Treated and Naturally Aged

  • Aerospace Material Specification
  • AMS4161J
  • Current
Published 2020-12-03 by SAE International in United States
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Aluminum Alloy, Plate (2297-T87) 2.8Cu - 1.5Li - 0.30Mn - 0.12Zr Solution Heat Treated, Stretched, and Artificially Aged

  • Aerospace Material Specification
  • AMS4330D
  • Current
Published 2020-11-30 by SAE International in United States
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TEST PROCEDURES FOR EVALUATING BOLT-LOAD RETENTION OF MAGNESIUM ALLOYS

  • Ground Vehicle Standard
  • USCAR35-1
  • Current
Published 2020-11-19 by SAE International in United States
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Aluminum Alloy, Seamless Drawn Tubing 1.0Mg - 0.60Si - 0.28Cu - 0.20Cr (6061-T4) Solution Heat Treated and Naturally Aged

  • Aerospace Material Specification
  • AMS4480A
  • Current
Published 2020-11-19 by SAE International in United States
This content contains downloadable datasets
Annotation ability available