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Titanium Alloy, Bars, Wire, and Rings, 5Al - 2.5Sn, Annealed, 110 ksi (758 MPa) Yield Strength

AMS G Titanium and Refractory Metals Committee
  • Aerospace Material Specification
  • AMS4926P
  • Current
Published 2019-06-20 by SAE International in United States

This specification covers a titanium alloy in the form of bars, wire, flash welded rings 4.000 inches (101.60 mm) and under in nominal diameter or least distance between parallel sides and 16 in2 (103 cm2) and under in cross-sectional area, and stock of any size for flash welded rings.

 
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Heat Treatment of Carbon and Low-Alloy Steel Parts, Minimum Tensile Strength Below 220 ksi (1517 MPa)

AMS E Carbon and Low Alloy Steels Committee
  • Aerospace Material Specification
  • AMS2759/1G
  • Current
Published 2019-06-17 by SAE International in United States

This specification, in conjunction with the general requirements for steel heat treatment covered in AMS2759, establishes the requirements for heat treatment of carbon and low-alloy steel parts to minimum ultimate tensile strengths below 220 ksi (1517 MPa). Parts are defined in AMS2759. Due to limited hardenability in these materials, there are size limits in this specification.

 
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Aluminum Alloy Extrusions, 4.4Cu - 1.5Mg - 0.60Mn (2024-T3), Solution Heat Treated and Cold Worked

AMS D Nonferrous Alloys Committee
  • Aerospace Material Specification
  • AMS4152N
  • Current
Published 2019-06-17 by SAE International in United States

This specification covers an aluminum alloy in the form of extruded bars, rods, wire, shapes, and tubing produced with cross sectional area of 32 in2 (206 cm2) maximum.

 
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Training and Approval of Heat-Treating Personnel

AMS B Finishes Processes and Fluids Committee
  • Aerospace Standard
  • ARP1962B
  • Current
Published 2019-06-11 by SAE International in United States

This SAE Aerospace Recommended Practice (ARP) describes training and approval of personnel performing certain heat-treating and associated operations that could have a material impact on the properties of materials being heat treated. It also recommends that only approved personnel perform or monitor the functions listed in Table 1.

 
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Titanium Alloy Bars, Forgings, and Rings, 6Al - 4V Extra Low Interstitial (ELI), Duplex Annealed, Fracture Toughness

AMS G Titanium and Refractory Metals Committee
  • Aerospace Material Specification
  • AMS4931F
  • Current
Published 2019-06-11 by SAE International in United States

This specification covers a titanium alloy in the form of bars 6.000 inches (152.40 mm) and under in nominal diameter or least distance between parallel sides, forgings and flash welded rings 6.000 inches (152.40 mm) and under in thickness, and stock for forging and stock for flash welded rings of any size.

 
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A Refined In-Flight Icing Model and its Numerical Implementation

FH Joanneum GmbH-Wolfgang Hassler
Published 2019-06-10 by SAE International in United States
A refined in-flight icing model is proposed whose primary focus lies on an improved prediction of the runback dynamics. The most significant capabilities/properties of the model are:Incorporation of surface tension and wetting effects in the runback modelFully transient treatment of the ice accretion/depletion process and the runback flowTreatment of unsteady heat transfer in the runback layer, the accreted ice layer and the underlying substrate as well as phase transitions solid/liquid in the ice layerStrict mass- and enthalpy-conservative growth/depletion of the ice layer (this is achieved by a specially designed mesh deformation algorithm)An essential part of the paper is devoted to the treatment of surface tension and wetting effects: These effects result from disjoining pressure contributions to the pressure terms in the runback continuity equation, i.e., these effects are inherent properties of the simulated runback dynamics. In particular, phenomena such as film rupture, bead formation and bead coalescence naturally appear in the computed runback flow, and also contact angle hysteresis effects can be simulated with the current wetting model. Besides the treatment of wetting effects the…
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Titanium Alloy Sheet, Strip, and Plate, 6Al - 2Sn - 4Zr - 2Mo - 0.08Si, Duplex Annealed

AMS G Titanium and Refractory Metals Committee
  • Aerospace Material Specification
  • AMS4919J
  • Current
Published 2019-06-10 by SAE International in United States

This specification covers a titanium alloy in the form of sheet, strip, and plate 0.025 to 3.000 inches (0.64 to 76.20 mm), inclusive, in nominal thickness.

 
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Cleaner for Exterior Aircraft Surfaces Thickened or Gel-Type, Water-Base

AMS J Aircraft Maintenance Chemicals and Materials Committee
  • Aerospace Material Specification
  • AMS1523B
  • Current
Published 2019-06-03 by SAE International in United States
This specification covers a thickened, water-base, type cleaner in the form of a gel.
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Titanium Alloy, Extrusions and Flash Welded Rings, 6Al - 4V, Solution Heat Treated and Aged

AMS G Titanium and Refractory Metals Committee
  • Aerospace Material Specification
  • AMS4934H
  • Current
Published 2019-06-03 by SAE International in United States

This specification covers a titanium alloy in the form of extruded bars, and shapes, flash welded rings up through 3.000 inches (76.20 mm) inclusive, in nominal diameter or least distance between parallel sides, and stock for flash welded rings of any size.

 
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Heat Treatment of Steel Raw Materials

AMS E Carbon and Low Alloy Steels Committee
  • Aerospace Material Specification
  • AMSH6875B
  • Current
Published 2019-05-29 by SAE International in United States
This specification covers the requirements for heat-treatment of four classes of steel (See 1.2) and the requirements for furnace equipment, test procedures and information for heat-treating procedures, heat-treating temperatures and material (See 6.3) test procedures. This specification is applicable only to the heat treatment of raw material (See 6.3.1); it does not cover the requirements for the heat treatment of steel parts (See 3.4 and 6.3.2). This specification also describes procedures that, when followed, will produce the desired properties and material qualities within the limitations of the respective alloys tabulated in Tables 1A, 1B, 1C and 1D. Alloys other than those specifically covered herein may be heat treated using all applicable requirements of this specification.
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