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This AIR provides information about the specific requirements for missile hydraulic pumps and their associated power sources.
This specification covers a magnesium alloy in the form of investment castings (see 8.6).
This specification covers an aluminum alloy in the form of rolled or forged rings up to 6 inches (152 mm), inclusive, in thickness (see 3.3.1.1.1) and an OD to wall thickness ratio of 10 or greater (see 8.5).
This specification covers a nitriding grade of premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock. AMS6496 and AMS6497 cover UNS K23280 with other quality levels.
This specification covers a magnesium alloy in the form of investment castings (see 8.6).
This SAE Aerospace Recommended Practice (ARP) provides the user with standardized guidelines for the measurement of effective intensity of short pulse width strobe anticollision lights for aircraft in the laboratory, in maintenance facilities, and in the field. A common source of traceability for calibration of the measurement systems, compensation for known causes of variation in light output such as the use of colored lenses, and recommendations which minimize sources of errors and uncertainties are included in this document. Estimates of uncertainty and error sources for each class of measurement are discussed.
This SAE Recommend Practice establishes for passenger cars, light trucks, and multipurpose vehicles with GVW of 4500 kg (10000 pounds) or less, as defined by the EPA, and M1 category vehicles, as defined by the European Commission:
This procedure describes a method of measuring the resistance to wet color transfer of materials such as textiles, leather, and composites.
This specification covers a copper-zinc alloy (brass) in the form of sheet, strip, and plate (see 8.6).
This specification covers an aluminum alloy in the form of sheet from 0.063 to 0.249 inch (1.60 to 6.30 mm) in nominal thickness (see 8.6).
This specification covers a low-alloy steel in the form of sheet, strip, and plate 4.00 inches (101.6 mm) and under in thickness.
The purpose of this SAE Recommended Practice is to establish a uniform laboratory procedure for securing and reporting the friction and wear characteristics of brake linings. The performance data obtained can be used for in-plant quality control by brake lining manufacturers and for the quality assessment of incoming shipments by the purchasers of brake linings.
This SAE Standard was developed to provide a method for indicating the direction of engine rotation and numbering of engine cylinders. The document is intended for use in designing new engines to eliminate the differences which presently exist in industry.
This specification covers an aluminum alloy in the form of plate 1.000 to 6.000 inches (25.40 to 152.40 mm), inclusive, in nominal thickness (see 8.5).
This specification establishes the requirements for an expanded polytetrafluoroethylene (ePTFE) in the form of sealing tape, gaskets, or sheets requiring no mixing or curing.
AMS4269C has been declared “STABILIZED” by SAE AMS Committee D Nonferrous Alloys and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability of technical requirements. Newer technology may exist.
This specification covers a corrosion-resistant steel product 8 inches (203 mm) and under in nominal diameter, thickness or for hexagons, least distance between parallel sides, and having a maximum cross-sectional area of 64 square inches (413 cm2) in the solution and precipitation heat treated (H925) condition.
This specification covers a corrosion-resistant steel product in the solution and precipitation heat-treated (H950) condition, 12 inches (305 mm) and under in nominal diameter, thickness, or, for hexagons, least distance between parallel sides.
This specification covers a fluorosilicone (FVMQ) rubber in the form of molded rings.
This specification covers a corrosion- and heat-resistant steel in the form of bars, forgings, and forging stock.
This specification covers piston rings fabricated from cast iron.
This specification covers a corrosion- and heat-resistant nickel alloy in the form of investment castings.
This specification covers an aluminum alloy in the form of castings (see 8.6).
This specification covers an aluminum alloy in the form of sheet and plate, alclad both sides, supplied in the -T361 temper.
This specification covers an aluminum alloy in the form of die castings.
This specification covers a magnesium alloy in the form of investment castings (see 8.6).
This specification covers a magnesium alloy in the form of extruded bars, rods, wire, tubing, and profiles.
This specification covers an aluminum alloy in the form of castings (see 8.6).
This specification covers a magnesium alloy in the form of plate 0.250 to 6.000 inches (6.35 to 152.40 mm), inclusive, in nominal thickness (see 8.5).
This specification covers an aluminum alloy in the form of die castings.
This detail specification, along with AMS6562, establishes the requirements for continuous E-glass fabric impregnated with a medium temperature, out-of-autoclave, oven-vacuum-bag cure modified B-staged epoxy resin. The prepreg is produced using a one side coated (one side tacky) hot-melt process.
This specification covers a corrosion-resistant steel in the form of investment castings homogenized, solution, and precipitation heat treated to 150 ksi (1034 MPa) minimum tensile strength.
This specification covers two tempers of aluminum alloy in the form of bars, rods, and wire up to 8.000 inches (203.2 mm) in nominal thickness (see 8.6).
This specification covers a corrosion-resistant steel in the form of investment castings homogenized and solution and precipitation heat treated to 180 ksi (1241 MPa) tensile strength.
This specification establishes the requirements for anodic coatings on aluminum alloys.
This specification covers a titanium alloy in the form of sheet, strip, and plate through 4.000 inches (101.6 mm) nominal thickness.
This specification covers a nitriding grade of aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock. AMS6497 and AMS6498 cover UNS K23280 having other quality levels.
The intent of this specification is for the procurement of carbon fiber and fiberglass epoxy prepreg products with 350 °F (177 °C) cure for aerospace applications; therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the production quality assurance section (4.3) of this base specification, AMS6891.
This specification covers tantalum in the form of sheet, strip, plate, and foil up through 0.1875 inch (4.75 mm), inclusive (see 8.7).
The purpose of this SAE Aerospace Recommended Practice (ARP) is to provide the aerospace industry with recommendations concerning the minimization of stress corrosion cracking in wrought heat-treatable carbon and low-alloy steels and in austenitic, precipitation hardenable, and martensitic corrosion-resistant steels and alloys. The detailed recommendations are based on laboratory and field experience and reflect those design practices and fabrication procedures which should avoid in-service stress corrosion cracking.
This specification covers a titanium alloy in the form of bars, wire, forgings, flash-welded rings 4.000 inches (101.60 mm) and under in nominal diameter or least distance between parallel sides, and stock of any size for forging or flash-welded rings (see 8.6).
This specification covers corrosion-resistant steel bars, wire, shapes, and forgings.
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