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This AIR provides information about the specific requirements for missile hydraulic pumps and their associated power sources.
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 specification covers a magnesium alloy in the form of investment castings (see 8.6).
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 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.
This specification covers a copper-zinc alloy (brass) in the form of sheet, strip, and plate (see 8.6).
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 specification establishes the requirements for an expanded polytetrafluoroethylene (ePTFE) in the form of sealing tape, gaskets, or sheets requiring no mixing or curing.
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 heat-treatable, corrosion-resistant steel in the form of bars, wire, forgings, mechanical tubing, and stock for forging or heading.
This specification covers the requirements for electrodeposited cadmium on metal parts.
This specification covers one type of copper-beryllium alloy in the form of sheet, strip, and plate (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 a corrosion-resistant steel in the form of investment castings homogenized and solution and precipitation heat treated to 130 ksi (895 MPa) tensile strength.
This specification covers a magnesium alloy in the form of extruded bars, rods, wire, tubing, and profiles.
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, 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 (see 8.6).
This specification covers the requirements for a manganese phosphate coating on ferrous alloys.
This specification covers the requirements for producing brazed joints in parts made of steels, iron alloys, nickel alloys, and cobalt alloys by use of nickel alloy filler metal.
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.
This specification covers a titanium alloy in the form of bars up through 4.000 inches (101.60 mm) in nominal diameter or least distance between parallel sides, inclusive, and stock for forging of any size (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 the requirements for silver deposited on metal parts with a copper strike between the basis metal and the silver deposit.
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 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 SAE Aerospace Recommended Practice (ARP) contains guidance to assist users by providing a method to install an AS6224/2 repair sleeve.
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