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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 specification covers environment resistant, heat-shrinkable solder type shield terminations. They may be used on data-bus, RF, and shielded cables in applications. Operating temperature of each product are as indicated on detail specifications.
This specification covers design requirements, performance requirements, and methods of procurement for tools and associated accessories used to strip aerospace vehicle electrical wire and cable. Aerospace vehicle electrical wire has stranded conductors with protective plating and specialized insulation. Poor quality wire strippers or mismatched blades can compromise the performance of wiring.
The AS6224 specification covers environment resistant, permanent insulation repair sleeves for repairing different types of insulation damages of wire or cable jackets in installed applications. The repair sleeve is intended to repair damaged primary wire or cable jacket covers where the shielding and wire conductors are not damaged.
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