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This SAE Recommended Practice provides minimum performance requirements and uniform procedures for fatigue testing of wheels intended for normal highway use and temporary use on passenger cars, light trucks, and multipurpose vehicles. For heavy truck wheels and wheels intended to be used as duals, refer to SAE J267. For wheels used on trailers drawn by passenger cars, light trucks, or multipurpose vehicles, refer to SAE J1204. These minimum performance requirements apply only to wheels made of materials included in Tables 1 to 4. The minimum cycles noted in Tables 1 through 4 are to be used on individual test and a sample of tests conducted, with Weibull Statistics using two parameter, median ranks, 50% confidence level, and 90% reliability, typically noted as B10C50.
This SAE Standard provides test procedures for air and air-over-hydraulic disc or drum brakes used for on-highway commercial vehicles over 4536 kg (10000 pounds) GVWR. This recommended practice includes the pass/fail criteria of Federal Motor Vehicle Safety Standard No. TP-121D-01.
This SAE lab test procedure should be used when performing the following specialized weathering tests for wheels; Florida Exposure, QUV, Xenon and Carbon Weatherometer. In addition to these procedures, some additional post-weathering tests may be specified. Please refer to customer specifications for these requirements.
This SAE Recommended Practice is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances. This document establishes additional performance requirements and provides test methods and requirements to evaluate the suitability of materials intended for optical applications in motor vehicles. The tests are intended to determine physical and optical characteristics of the materials only. Performance expectations of finished assemblies, including plastic components, are to be based on tests for lighting devices, as specified in SAE Standards and Recommended Practices for motor vehicle lighting equipment. Glass and materials inclusive to the light source are not in scope for this method.
This specification covers a corrosion- and heat-resistant steel in the form of welding wire.
The purpose of this SAE Aerospace Recommended Practice (ARP) is to provide recommendations which will lead to the standardization of interior door design and operation in all transport aircraft. Interior doors are broadly classified into two main categories which include egress path doors and non-egress path doors. The scope of this ARP does not include crew rest doors, secondary barriers to the flight deck, or doors incorporated in furniture surrounding passenger seats as defined in AS6960.
This specification covers quality assurance sampling and testing procedures used to determine conformance to applicable specification requirements of carbon and low-alloy steel forgings.
These general guidelines and precautions apply to personnel operating directional drilling tracking equipment when used with horizontal directional drilling (HDD) machines as defined in ISO 21467:2023.
This specification covers the engineering requirements for producing a continuous compound zone (white layer) on parts by means of a gaseous, low-temperature, carbon-enriched nitriding process.
This specification covers a high strength, corrosion- and heat-resistant cobalt-nickel-chromium alloy in the form of bars 1-3/4 inches (44.4 mm) and under in nominal diameter.
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 sheet and plate alclad two sides, over 0.187 to 1.000 inch (over 4.750 to 25.40 mm) in nominal thickness, supplied in the -T3/-T351 temper (see 8.5).
This specification covers a corrosion and heat resistant steel in the form of welding wire.
This specification covers a low-carbon steel in the form of sheet and strip coated on both faces with aluminum-silicon alloy by the hot-dip process.
This specification covers an aircraft-quality, low-alloy steel in the form of sheet, strip, and plate.
This specification covers a corrosion-resistant steel in the form of investment castings, solution and precipitation heat treated to 180 ksi (1241 MPa) tensile strength.
This SAE Aerospace Recommended Practice (ARP) discusses design philosophy, system and equipment requirements, environmental conditions, and design considerations for rotorcraft environmental control systems (ECS). The rotorcraft ECS comprises that arrangement of equipment, controls, and indicators which supply and distribute dehumidified conditioned air for ventilation, cooling and heating of the occupied compartments, and cooling of the avionics. The principal features of the system are: a A controlled fresh air supply b A means for cooling (air or vapor cycle units and heat exchangers) c A means for removing excess moisture from the air supply d A means for heating e A temperature control system f A conditioned air distribution system The ARP is applicable to both civil and military rotorcraft where an ECS is specified; however, certain requirements peculiar to military applications—such as nuclear, biological, and chemical (NBC) protection—are not covered. The integration of NBC
This specification covers a corrosion- and heat-resistant steel in the form of seamless or welded and drawn tubing.
This specification covers a titanium alloy in the form of wire for welding filler metal.
This specification covers a corrosion- and heat-resistant nickel alloy in the form of two types of tubing.
This specification covers an aluminum alloy in the form of extruded bars, rods, and profiles (shapes) with a maximum cross-sectional area of 25 square inches (161 cm2), a maximum circle size of 12 inches (305 mm), and a nominal thickness up to 3.250 inches (82.54 mm), inclusive (see 8.6).
This specification covers an acrylonitrile-butadiene (NBR) elastomer that can be used to manufacture product in the form of sheet, strip, tubing, extrusions, and molded shapes. For molded rings, compression seals, O-ring cord, and molded-in-place gaskets for aeronautical and aerospace applications, use the AMS-P-83461 specification or the MIL-PRF-25732 specification.
This specification covers an aluminum alloy in the form of castings (see 8.6).
This specification covers an aluminum alloy in the form of extruded profiles such as angles, channels, tees, zees, I-beams, and H-beams.
This specification covers an aluminum alloy in the form of die forgings up to 6.000 inches (152.40 mm), inclusive, in nominal thickness and forging stock of any size (see 8.6).
This specification establishes a procedure for designating minimum stress-rupture property requirements of castings by means of this AMS number and a series of dash numbers.
This specification covers an aluminum alloy in the form of extruded bars, rods, wire, shapes, and tubing 0.040 to 4.499 inches (1.01 to 114.27 mm), inclusive, in nominal diameter or least thickness and with areas up to 32 square inches (206 cm2), inclusive (see 8.6).
This specification covers an aircraft-quality, low-alloy steel in the form of heat-treated bars and forgings.
This specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
This specification establishes requirements for titanium forgings of any shape or form from which finished parts are to be made (see 2.4.4, 8.3, and 8.6).
This specification covers an aluminum alloy procured in the form of extruded bars, rods, and profiles (shapes) with nominal thickness up to 3.000 inches (76.20 mm), inclusive, and having a cross-sectional area of 26.3 square inches (170 cm2) maximum and circle size of 15.3 inches (389 mm) maximum (see 8.6).
This specification covers a methyl or methyl vinyl silicone rubber material that can be used to manufacture product in the form of sheet, strip, tubing, extrusions, and molded shapes. This specification should not be used for molded rings, compression seals, O-ring cord, and molded in place gaskets for aeronautical and aerospace applications without complete consideration of the end use prior to the selection of this material.
This specification covers a titanium alloy in the form of sheet.
This specification covers a corrosion- and heat-resistant nickel alloy in the form of bars, forgings, flash-welded rings, and stock for forging, flash-welded rings, or heading.
This specification covers a premium aircraft-quality alloy steel in the form of bars and forgings 189 in2 (1219 cm2) and under in cross-sectional area and forging stock of any size.
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 alloy (naval brass) in the form of bars and rods (see 8.5).
This specification covers an aluminum alloy in the form of sheet and plate 0.020 to 0.499 inch (0.50 to 12.50 mm), inclusive, in nominal thickness, clad on two sides (see 8.6).
This specification covers the requirements for electroless nickel with phosphorus deposited on various materials.
This specification covers a corrosion-resistant steel in the form of seamless or welded tubing.
This specification covers a premium-aircraft-quality, low-alloy steel in the form of sheet, strip, and plate.
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