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This specification covers two types of refined hydrocarbon compounds in the form of liquids. This specification only covers newly manufactured materials.
This specification covers an aluminum alloy in the form of sand, permanent mold, composite mold, and investment castings (see 8.6).
This specification covers an aluminum alloy in the form of permanent mold castings (see 8.6).
This specification covers a cobalt alloy in the form of sheet and plate up to 1 inch (25 mm) in nominal thickness or round bars up to 3-1/2 inches (89 mm) in nominal diameter.
This specification covers a titanium alloy in the form of pre-alloyed powder.
This AIR by the G-11AT (Automation and Tools) subcommittee, examines the failure mode, effects and criticality analysis (FMECA) requirements and procedures as performed on current and earlier vintage engineering programs. The subcommittee has focused on these procedures in relation to the concurrent engineering (CE) environment to determine where it may be beneficial, to both FMECA analysts and users, to automate some or all of the FMECA processes. Its purpose is to inform the reader about FMECAs and how the FMECA process could be automated in a concurrent engineering environment. There is no intent on the part of the authors that the material presented should become requirements or specifications imposed as part of any future contract. The report is structured to include the following subjects: a A FMECA overview b The current FMECA process c FMECA in the concurrent engineering environment d FMECA automation e The benefits of automation
This specification covers procedures and requirements for peening of metal parts with portable, bonded-shot, rotary flap assemblies in accordance with AS2592. The principles of rotary flap peening are similar to conventional shot peening, except conversion of arc height values using the magnetic test strip holder is required for intensity determination.
This specification covers a corrosion-resistant steel in the form of bars, wire, forgings, and forging stock.
This specification covers a corrosion and heat resistant nickel alloy in the form of sheet and strip.
This specification covers a titanium alloy in the form of sheet, strip, and plate up through 4.000 inches (101.60 mm) inclusive in thickness (see 8.6).
This specification covers a high strength, corrosion- and heat-resistant cobalt-nickel-chromium alloy in the form of bars 1-3/4 inch (44 mm) nominal diameter thickness or for hexagons least distance between parallel sides (see 8.3).
This SAE Standard covers complete general and dimensional specifications for the various types of tube fittings intended for general application in the automotive, appliance, and allied fields. See SAE J1131 for the performance requirements of reusable (push to connect) fittings intended for use in automotive air brake systems. Flare type fittings shall be as specified in Figures 1 to 4 and Tables 3 to 5. NOTE—For sizes 3/16 to 3/8 and 1/2 to 3/4 the flare type fittings depicted in Figures 1A to 3C are identical with the corresponding refrigeration tube fittings specified in SAE J513. Special size combination fittings 3/16 to 3/8 and 1/2 to 3/4 shall be as specified in SAE J513. Inverted flared type fittings shall be as specified in Figures 5 to 11 and Tables 3, 6, 7, 8, and 9. Gages and gaging procedures pertaining to inverted flared tube fittings are given in Appendix A. NOTE—The seat dimensions specified in Table 6 are predicated on practical threading limitations in steel fittings
This specification covers a carbon steel in the form of sheet, strip, and plate.
This specification covers a premium aircraft-quality, low-alloy steel in the form of sheet, strip, and plate.
This specification covers non-silicone synthetic rubber sealing compounds supplied as a two-component system that cures at room temperature.
This SAE Information Report is provided as an advisory guide. Individual application discretion is recommended. The content has been presented as accurately as possible, but responsibility for its application lies with the user. The document covers a number of the variables in the torque-tension relationship: friction, materials, temperature, humidity, fastener and mating part finishes, surfaces, and the kind of tightening tools or equipment used. Also described in this document is the torque management required to achieve satisfactory fastened joint tightening. This guide is limited in application to clearance fit threads, such as the common 6g/6H class of fit. Other thread types including interference fit, mechanical locking, prevailing torque, or forms other than ISO-metric may apply to some aspects of this standard but are not specifically covered. The procedures described in this document are based on general factors for the determination of the torque-tension relationship for the
This specification covers an aluminum alloy in the form of extruded profiles with a maximum cross-sectional area of 25 in2 (160.29 cm2) and nominal thicknesses from 0.250 to 2.500 inch, inclusive (6.3 to 63.50 mm, inclusive) (see 8.7).
This specification covers a corrosion-resistant steel in the form of sheet, strip, and plate.
This document contains information that can be used by the air transportation industry to evaluate the design of airplane interior stairways with respect to the safety of passengers and crew in normal operating conditions and emergency evacuations.
The intended upper bound of this specification is that the particle size distribution (PSD) of powders supplied shall be <60 mesh (250 μm) and that no powder (0.0 wt%) greater than 40 mesh (425 μm) is allowed.
This document is the Architecture Description (AD) for the SAE Unmanned Systems (UxS) Control Segment (UCS) Architecture Library Revision B or, simply, the UCS Architecture. The architecture is expressed by a library of publications as referenced herein. The other SAE publications in the UCS Architecture Library Revision B are AS6513B and AS6518B. The library also includes the government-owned Autonomous Ground Vehicle Reference Architecture (AGVRA) Data Model Framework Version 3.1A.
This specification covers a premium aircraft-quality, high-strength, low-alloy steel in the form of bars, forgings, mechanical tubing, flash welded rings, and stock for forging or flash welded rings.
This specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, flash welded rings, and stock for forging or flash welded rings.
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
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