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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 premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
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 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).
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 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 sheet and plate with a thickness of 0.125 to 0.499 inch (3.20 to 12.67 mm), inclusive (see 8.5).
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 test procedures, performance requirements, and guidelines for cleaners intended for use on motor vehicles.
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.
This specification covers one type of brass in the form of forgings and forging stock.
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 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 absorbent fabric materials supplied either as dry cloth or presaturated cloth for solvent cleaning process applications.
This specification covers piston rings fabricated from cast iron.
This SAE Aerospace Standard (AS) provides a standardized test procedure that can be used to evaluate material capability in a dynamic sealing application. This procedure will be utilized by applicable elastomer material specifications which are used for production of O-rings and other seals. This specification is applicable to the dynamic testing requirements for aerospace elastomer parts utilizing materials conforming to AMS7XXX series specifications, user specifications, or print on a Purchase Order (PO) that calls out this document for aerospace applications. This procedure is intended for testing NBR. Other elastomers may have different requirements which will require a separate procedure.
This specification covers a corrosion- and heat-resistant nickel alloy in the form of investment castings.
The intent of this document is to develop a recommended practice for PEV chargers, whether onboard or off-board the vehicle, that will enable equipment manufacturers, vehicle manufacturers, electric utilities, and others to make reasonable design decisions regarding power quality. The three main purposes are as follows: 1 To identify those parameters of a PEV battery charger that must be controlled in order to preserve the quality of the AC service. 2 To identify those characteristics of the AC service that may significantly impact the performance of the charger. 3 To identify values for power quality, susceptibility, and power control parameters that are based on current U.S. and international standards. These values should be technically feasible and cost effective to implement into PEV battery chargers. SAE J2894/2 will describe the test methods for the parameters/requirements in this document.
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