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Lubricant Application, Solid Film, Heat Cured, Corrosion Inhibiting

E-25 General Standards for Aerospace and Propulsion Systems
  • Aerospace Standard
  • AS5528D
  • Current
Published 2020-03-10 by SAE International in United States
This SAE Aerospace Standard (AS) establishes the surface pretreatment, temperature, and baking time required to cure AS5272 lubricant when it is applied over the surfaces of manufactured parts of various metals.
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Aluminum Alloy, Hand Forgings and Rolled Rings 6.3Cu - 0.30Mn - 0.18Zr - 0.10V - 0.06Ti (2219-T852/T851) Solution Heat Treated, Mechanically Stress Relieved, and Precipitation Heat Treated

AMS D Nonferrous Alloys Committee
  • Aerospace Material Specification
  • AMS4144G
  • Current
Published 2020-02-18 by SAE International in United States
This specification covers an aluminum alloy in the form of hand forgings 17 inches (432 mm) and under in nominal thickness, and rolled rings up to 6 inches, incl (152 mm, incl) in nominal thickness at the time of heat treatment (see 8.5).
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Aluminum Alloy, Extruded Rod, Bar and Profiles (7055-T74511) 8.0Zn - 2.3Cu - 2.0Mg - 0.16Zr Solution Heat Treated, Stress-Relieved, and Overaged

AMS D Nonferrous Alloys Committee
  • Aerospace Material Specification
  • AMS4324B
  • Current
Published 2020-02-10 by SAE International in United States
This specification covers an aluminum alloy in the form of extruded bars, rods, and profiles (shapes) produced with a cross sectional area of 24 square inches (155 square centimeters) maximum and a circumscribing circle (see 8.3) diameter (circle size) of 10.5 inches (267 mm) maximum, with a nominal thickness up to 3.000 inch (76.20 mm), inclusive (see 8.6).
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Aluminum Alloy, Plate (7065-T7451) 7.7Zn - 2.1Cu - 1.65Mg - 0.10Zr Solution Heat Treated, Stress-Relieved, and Overaged

AMS D Nonferrous Alloys Committee
  • Aerospace Material Specification
  • AMS4361A
  • Current
Published 2020-01-30 by SAE International in United States
This specification covers an aluminum alloy in the form of plate.
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Aluminum Alloy, Plate (7065-T7651) 7.7Zn - 2.1Cu - 1.65Mg - 0.10Zr Solution Heat Treated, Stress-Relieved, and Overaged

AMS D Nonferrous Alloys Committee
  • Aerospace Material Specification
  • AMS4351A
  • Current
Published 2020-01-30 by SAE International in United States
This specification covers an aluminum alloy in the form of plate.
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Aluminum Alloy, Alclad Sheet 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (Alclad 7050-T76) Solution Heat Treated and Overaged

AMS D Nonferrous Alloys Committee
  • Aerospace Material Specification
  • AMS4243C
  • Current
Published 2020-01-13 by SAE International in United States
This specification covers an aluminum alloy in the form of alclad sheet 0.040 to 0.187 inch (1.02 to 4.75 mm) inclusive in nominal thickness (see 8.6).
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Magnesium Alloys in Aircraft Seats - Developments in Magnesium Alloy Flammability Testing

Aircraft SEAT Committee
  • Aerospace Standard
  • AIR6160A
  • Current
Published 2020-01-09 by SAE International in United States
This document provides informational background, rationale and a technical case to allow consideration of the removal of the magnesium alloy restriction in aircraft seat construction as contained in AS8049B. The foundation of this argument is flammability characterization work performed by the FAA at the William J. Hughes Technical Center (FAATC), Fire Safety Branch in Atlantic City, New Jersey, USA. The rationale and detailed testing results are presented along with flammability reports that have concluded that the use of specific types of magnesium alloys in aircraft seat construction does not increase the hazard level potential in the passenger cabin in a post-crash fire scenario. Further, the FAA has developed a lab scale test method, reference DOT/FAA/TC-13/52, to be used as a certification test, or method of compliance (MOC) to allow acceptability of the use of magnesium in the governing TSO-C127 and TSO-C39C. Other flammability studies are also cited in the AIR document to substantiate the FAA findings.
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Aluminum Alloy, Plate 6.2Zn - 1.8Cu - 2.4Mg - 0.13Zr (7010-T7651) Solution Heat Treated, Stress Relieved, and Precipitation Heat Treated

AMS D Nonferrous Alloys Committee
  • Aerospace Material Specification
  • AMS4204D
  • Current
Published 2019-12-27 by SAE International in United States
This specification covers an aluminum alloy in the form of plate 0.250 to 5.500 inch (6.35 to 139.70 mm), inclusive in nominal thickness (see 8.5).
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Aluminum Alloy, Plate (7160-T7451) 7.0Zn – 2.2Cu – 1.5Mg - 0.10Zr Solution Heat Treated, Stress Relieved, and Overaged

AMS D Nonferrous Alloys Committee
  • Aerospace Material Specification
  • AMS4432
  • Current
Published 2019-12-19 by SAE International in United States
This specification covers an aluminum alloy in the form of plate 1.000 to 6.000 inch (25.40 to 152.40 mm), inclusive, in nominal thickness (see 8.4).
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Aluminum Alloy, Alclad Sheet 4.4Cu - 1.5Mg - 0.60Mn (Alclad 2024-O) Annealed, Fine Grain

AMS D Nonferrous Alloys Committee
  • Aerospace Material Specification
  • AMS4274B
  • Current
Published 2019-12-17 by SAE International in United States
This specification covers an aluminum alloy in the form of sheet 0.009 to 0.126 inch (0.23 to 3.20 mm) inclusive, in nominal thickness, alclad.
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