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Browse AllThis 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 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 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 hand forgings 8 inches (203 mm) and under in nominal thickness and of forging stock (see 8.6).
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 specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
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.
Three levels of fan structural analysis are included in this practice: a Initial structural integrity. b In-vehicle testing. c Durability (laboratory) test methods. The initial structural integrity section describes analytical and test methods used to predict potential resonance and, therefore, possible fatigue accumulation. The in-vehicle (or machine) section enumerates the general procedure used to conduct a fan strain gage test. Various considerations that may affect the outcome of strain gage data have been described for the user of this procedure to adapt/discard depending on the particular application. The durability test methods section describes the detailed test procedures for a laboratory environment that may be used depending on type of fan, equipment availability, and end objective. The second and third levels build upon information derived from the previous level. Engineering judgment is required as to the applicability of each level to a different vehicle environment or a