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This AIR provides information about the specific requirements for missile hydraulic pumps and their associated power sources.
This specification covers an aluminum-lithium alloy in the form of extruded profiles with a maximum cross-sectional area of 19 square inches (123 cm2) and a maximum circle size of 11 inches (279 mm) from 0.040 to 0.499 inch (1.00 to 12.50 mm) in thickness (see 8.6).
This specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
This specification covers a copper-beryllium alloy in the form of bars, rods, shapes, and forgings (see 8.5).
This document applies to the development of Plans for integrating and managing COTS assemblies in electronic equipment and Systems for the commercial, military, and space markets, as well as other ADHP markets that wish to use this document. For purposes of this document, COTS assemblies are viewed as electronic assemblies such as printed wiring assemblies, disk drives, servers, printers, laptop computers, etc. There are many ways to categorize COTS assemblies1, including the following spectrum: At one end of the spectrum are COTS assemblies whose design, internal parts2, materials, configuration control, traceability, reliability, and qualification methods are at least partially controlled, or influenced, by ADHP customers (either individually or collectively) or by industry standards. An example at this end of the spectrum is a VME circuit card assembly. At the other end of the spectrum are COTS assemblies whose design, internal parts, materials, configuration control, and
This specification covers an aluminum alloy in the form of sheet and plate with a thickness of 0.125 to 0.499 inch (3.20 to 12.67 mm), inclusive (see 8.5).
This SAE Recommended Practice was developed primarily for passenger car and truck applications but may be used in marine, industrial, and similar applications. It addresses nonmetallic caps and both metallic and nonmetallic filler necks.
This specification covers an aluminum alloy in the form of hand forgings 8 inches (203 mm) and under in nominal thickness and of forging stock (see 8.6).
To establish the acceptance criteria for discontinuities as revealed by magnetic particle or liquid penetrant examination of aircraft utility parts as in 1.2.
This SAE Recommended Practice provides a method for determining the Effective Projected Luminous Lens Area (EPLLA) of a lamp function using design analysis. This standard was created to clarify and address how to determine EPLLA with traditional and new technologies.
This procedure describes a method of measuring the resistance to wet color transfer of materials such as textiles, leather, and composites.
This document describes an inspection procedure for detecting, by use of a radiographic opaque tracer and fluoroscopy or radiography methods, flaws which have been produced as the result of cutting, machining, or drilling operations in composite or laminate structures.
This specification covers a premium aircraft-quality, corrosion-resistant steel in the form of bars, wire, forgings, flash-welded rings, and extrusions up to 12 inches (305 mm) in nominal diameter or least distance between parallel sides (thickness) in the solution heat-treated condition (see 8.4) and stock of any size for forging, flash-welded rings, or extrusions.
This document establishes the minimum curriculum requirements for training, practical assessments, and certifying composite structure repair personnel and metalbond repair personnel. It establishes criteria for the certification of personnel requiring appropriate knowledge of the technical principles underlying the composite structural repairs and/or metalbond they perform. Persons certified under this document may be eligible for licensing/certification/qualification by an appropriate authority, in addition to this industry-accepted technician certification. Teaching levels have been assigned to the curriculum to define the knowledge, skills, and abilities graduates will need to make repairs to composite or metalbond structure. Minimum hours of instruction have been provided to ensure adequate coverage of all subject matter, including lecture and laboratory. These minimums may be exceeded and may include an increase in the total number of training hours and/or increase in the teaching
This specification covers a corrosion- and heat-resistant steel in the form of bars, forgings, and forging stock.
This specification covers a titanium alloy in the form of bars, wire, flash-welded rings 3.00 inches (76.2 mm) and under in nominal diameter or least distance between parallel sides and 16 square inches (103 cm2) and under in cross-sectional area, and stock of any size for flash-welded rings (see 8.6).
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 the requirements for electrodeposited hard chromium plate.
This specification covers absorbent fabric materials supplied either as dry cloth or presaturated cloth for solvent cleaning process applications.
This SAE Aerospace Standard (AS) covers components of rotary flap assemblies to be used with portable equipment for peening of metal parts. The flap assemblies consist of a flap attached to a mandrel and shall be of the following sizes:
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 an aluminum alloy in the form of sheet and plate, alclad both sides, supplied in the -T361 temper.
This specification covers a premium aircraft-quality alloy steel in the form of bars, forgings, and forging stock.
This specification covers a corrosion- and heat-resistant steel in the form of welding wire.
This specification covers a corrosion-resistant steel product in the solution and precipitation heat-treated (H1050) condition, 12 inches (305 mm) and under in nominal diameter, thickness, or, for hexagons, least distance between parallel sides.
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 in the solution and precipitation heat-treated (H1150) condition.
This specification covers a titanium alloy in the form of prealloyed powder.
This specification covers a beryllium aluminum alloy in the form of investment castings.
This specification covers a corrosion-resistant steel product 12 inches (305 mm) and under in nominal diameter, thickness or, for hexagons, least distance between parallel sides, and having a maximum cross-sectional area of 144 in2 (930 cm2) in the solution and precipitation heat treated (H900A) condition.
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