Standards - SAE Mobilus

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Items (49,068)
This SAE Recommended Practice establishes for passenger cars, light trucks, and multipurpose vehicles with GVW of 4500 kg (10000 pounds) or less: a Minimum performance standards for windshield wiper systems. b Test procedures that can be conducted on uniform test equipment by commercially available laboratory facilities. c Uniform terminology of windshield wiper system characteristics and phenomena consistent with those found in guides for the use of engineering layout studies to evaluate system performance. d Guides for the design and location of components of the systems for function, servicing of the system, etc. The test procedures and minimum performance standards outlined in this document are based on currently available engineering data. It is the intent that all portions of the document will be periodically reviewed and revised as additional data regarding windshield wiping system performance are developed
Wiper Standards Committee
This SAE Standard establishes the requirements for lubricating oils containing ashless dispersant additives to be used in four-stroke cycle, reciprocating piston aircraft engines. This document covers the same lubricating oil requirements as the former military specification MIL-L-22851. Users should consult their airframe or engine manufacturer’s manuals for the latest listing of acceptable lubricants. Compliance with this specification must be accomplished in accordance with the Performance Review Institute (PRI) product qualification process as described in the documents referenced in 2.1.3. Requests for submittal information may be made to the PRI at the address shown in 2.1.3, referencing this specification. Products qualified to this specification are listed on a Qualified Products List (QPL) managed by the PRI. Approval and/or certification for use of a specific piston engine oil in aero applications is the responsibility of the individual equipment builders and/or governmental
E-38 Aviation Piston Engine Fuels and Lubricants
This specification covers an aluminum alloy in the form of plate 4.001 to 10.000 inches (101.60 to 254.00 mm), inclusive, in nominal thickness
AMS D Nonferrous Alloys Committee
This SAE Recommended Practice establishes mechanical property ranges for low-carbon automotive hot-rolled sheet, cold-rolled sheet, and metallic-coated sheet steels. It also contains information that explains the different nomenclature used with these steels
Metals Technical Committee
This specification covers a corrosion- and heat-resistant steel in the form of bars, wire, mechanical tubing, forgings, and forging stock
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers an age-hardenable nitriding grade of aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock
AMS E Carbon and Low Alloy Steels Committee
This SAE Recommended Practice defines the system and component functions, measurement metrics, and testing methodologies for evaluating the functionality and performance of tire pressure systems for use on trailers under 26000 pounds GVWR within the known operating environments. This document is applicable to all towed trailers under 26000 pounds GVWR. Examples of towed trailers are recreational vehicle travel trailers and fifth wheels, utility trailers, cargo trailers, livestock trailers, flatbed trailers, boat trailers, and snowmobile trailers. These trailers can be equipped with one, two, or three axles with each axle supporting either two or four tires. These systems are recommended to address all tires in service as originally installed on a trailer by the OEM. This recommended practice can also be applied to external TPMS that also cover tow vehicles and trailers simultaneously. This document will focus on tire pressure systems of the monitoring type
Trailer Committee
This specification covers a discontinuously reinforced aluminum alloy (DRA) made by mechanical alloying 2124A aluminum powder and silicon carbide particulate (SiC). It is produced in the form of extruded bar, rod, wire, and shapes with cross section inclusive of 1-inch (25.4-mm) diameter or less (see 8.7
AMS D Nonferrous Alloys Committee
This SAE Recommended Practice applies to motor vehicle Forward Illumination Devices which incorporate limited adaptive beam pattern capabilities. This document is to be used in conjunction with other forward lighting standards and/or recommended practices which define the base beam procedures, requirements, and guidelines
Road Illumination Devices Standards Committee
This standard covers design requirements, performance requirements, and methods of procurement for tools and associated accessories used to cut aerospace vehicle electrical wire and cable. Aerospace vehicle electrical wire has stranded conductors with protective plating and specialized insulation. Poor quality wire cutting can compromise the performance of wiring
AE-8C2 Terminating Devices and Tooling Committee
This specification covers a corrosion- and heat-resistant steel in the form of bars, wire, forgings, mechanical tubing, flash-welded rings, and stock for forging or flash-welded rings
AMS F Corrosion and Heat Resistant Alloys Committee
This document establishes an industry standard checklist for the auditing of the methods and procedures used in aircraft deicing and anti-icing on the ground to support conformance with the industry global standards, AS6285, AS6286 and AS6332. The checklist covers the use of SAE AMS1424 and SAE AMS1428 qualified fluids (Types I, II, III, and IV) and non-fluid methods
G-12T Training and Quality Programs Committee
This document proposes a method to demonstrate compliance to engine certification rules requiring tolerance of the control system to single failures leading to Loss of Power Control (LOPC) or Loss of Thrust Control (LOTC) for electric or hybrid engines. At issue 1, the document was developed to address only fully electric engine configurations targeting single engine CS/part 23 level 1 and 2 aircraft applications. The methodology proposed herein is based on an alternative definition of Loss of Power Control (LOPC) proposed by EASA, the FAA, TCCA, and ANAC in a joint Decision Document. It is therefore only applicable to projects which elect to implement this authority-proposed alternative definition. Other approaches for the demonstration of compliance of electric engines to control system single fault tolerance requirements, including approaches based on legacy practices applicable to piston engines, remain possible. They are, however, outside of the scope of this document. Future
E-40 Electrified Propulsion Committee
This SAE Recommended Practice describes the test procedures for conducting free-motion headform testing of heavy truck cab interior surfaces and components. A description of the test setup, instrumentation, impact configuration, target locations, and data reduction is included
Truck Crashworthiness Committee
This SAE Standard describes alternator physical, performance, and application requirements for heavy-duty electrical charging systems for off-road work machines, including those defined in SAE J1116
CTTC C2, Electrical Components and Systems
This specification covers a discontinuously reinforced aluminum alloy (DRA) made by mechanical alloying 2124A aluminum powder and silicon carbide (SiC) particulate. It is produced in the form of extruded bar, rod, wire, and shapes with cross section inclusive of 1-inch (25.4-mm) diameter or less (see 8.7
AMS D Nonferrous Alloys Committee
This specification covers a titanium alloy in the form of bars up through 1.000 inch (25.40 mm) in diameter or least distance between parallel sides, inclusive, forgings of thickness up through 1.000 inch (25.40 mm), inclusive, high-strength fastener stock up through 1.250 inch (31.75 mm), inclusive, and stock for forging of any size (see 8.7
AMS G Titanium and Refractory Metals Committee
This specification provides processing and acceptance requirements for electrical discharge machining (EDM) when applied to the manufacturing of parts
AMS B Finishes Processes and Fluids Committee
The purpose of this SAE Aerospace Information Report (AIR) is to provide rotorcraft and engine designers with a better understanding of turboshaft engine idle power characteristics and objectives to be considered in the design and integration process. For the purpose of this document, idle is the lowest suitable steady-state power setting, most commonly corresponding to a gas generator speed setting or range. In general, a lower engine idle setting is desired by the airframer to reduce noise, fuel consumption, and main rotor downwash when on the ground and to reduce the size requirement of a rotor brake system. In contrast, the engine manufacturer generally prefers a higher engine idle setting, as operation further away from the engine design speed involves more challenges in operability and mechanical design. A variety of rotorcraft and engine factors are described for consideration. Some typical engine power and torque trends are presented for illustrative purposes. The information
S-12 Powered Lift Propulsion Committee
This equipment specification covers requirements for airfield liquid anti-icing/deicing equipment for airfield snow removal purposes. The unit shall include a combination of a carrier vehicle, liquid product tank, and dispensing system. This vehicle as a unit shall be an integrated chemical dispensing deicing/anti-icing application system. Primary application is for the liquid chemical application for cleaning of ice and snow from airfield operational areas such as runways, taxiways, and ramp aprons. The term “carrier vehicle” represents the various self-propelled prime movers that provide the motive power necessary to move snow and ice control equipment during winter operations. The airport operator may require this specified piece of equipment in order to maintain the airfield during large and small snow events. When necessary, the airfield liquid anti-icing/deicing chemical applicator (ALAD) shall be a central and critical element in the winter pavement maintenance fleet in the
G-15 Airport Snow and Ice Control Equipment Committee
This SAE Aerospace Recommended Practice (ARP) provides an overview of the various types of polytetrafluoroethylene (PTFE) backup rings for hydraulic and pneumatic fluid power applications, including their advantages and disadvantages
A-6C2 Seals Committee
This SAE Recommended Practice establishes the test procedure, environment, instrumentation, and data analyses for comparing interior sound level of passenger cars, multipurpose vehicles, and light trucks having gross vehicle weight rating (GVWR) of 4540 kg (10 000 lb) or less. The test procedure is characterized by having fixed initial conditions (specified initial vehicle speed and gear selection at the starting point on the test site) to obtain vehicle interior sound measurement during road load operation over various road surfaces at specified constant speeds. The measurement data so derived is useful for vehicle engineering development and analysis
Light Vehicle Exterior Sound Level Standards Committee
This specification covers the requirements for electrodeposited bronze plate and its subsequent removal
AMS B Finishes Processes and Fluids Committee
This document provides guidance for ECS design for UA primarily by reference to existing applicable SAE AC-9 documents with indication of how they would apply and how they may need to be adapted for UA. This document provides guidance related to environmental control for onboard equipment, cargo, animals, and passengers. This document cannot provide detail design guidance for all potential types of UA. Limited information is available for ECS requirements for UA that may carry passengers, but it should be expected that the same comfort and safety standards would be applied to UA as prescribed in current civil aviation authority rules and military specifications. Additional requirements unique to UA can be expected for totally autonomous UA operation with no provision for flight or ground crew monitoring and intervention in the event of ECS failures or malfunctions. This document does not pertain to the related ground stations that may be controlling the UA
AC-9 Aircraft Environmental Systems Committee
This SAE Aerospace Information Report (AIR) provides additional information and the rationale used for certain elements of AS6413. This AIR is provided to assist persons performing the tests described in AS6413 with an understanding of certain aspects of the test apparatus and the test criteria, such as the volume of the test chamber, cell heating rate, and the pass/fail criteria. It will be updated concurrently with AS6413 to explain changes, provide rationales, and cover future cell/battery technologies as they arise
G-27 Lithium Battery Packaging Performance
This SAE Aerospace Standard (AS) specifies the testing requirements, including test equipment, to demonstrate a package of lithium-ion (UN3480) cylindrical cells of a format of 21700 or smaller intended for air transport contains the potential hazardous effects to the aircraft resulting from the failure of a cell within the package. The test described in this standard is intended to force a cylindrical lithium-ion cell into thermal runaway using thermal energy applied to the exterior of a cell. It is understood that, in the future, technology may be developed that will prevent cells from going into thermal runaway by this standard’s test protocol. The scope of this standard may be expanded as more technology and information become available
G-27 Lithium Battery Packaging Performance
This specification covers virgin, unfilled polytetrafluoroethylene (PTFE) in the form of sheet manufactured by compression molding and sintering
AMS P Polymeric Materials Committee
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
AMS D Nonferrous Alloys Committee
Wire and cable products progress through a series of handling or operational steps from the time they leave the manufacturer, and until a finished harness or assembly is ready for installation on a vehicle. Throughout these many steps, environmental or processing conditions may be present which can generate damage detrimental to the wire or cable and/or its intended application
AE-8A Elec Wiring and Fiber Optic Interconnect Sys Install
It is the purpose of this document to present design recommendations that will provide a basis for satisfactory and safe electrical installations in transport aircraft. This document is not intended to be a complete electrical installation design handbook. However, the requirements for safety extend so thoroughly throughout the electric systems that few areas of the installation are untouched by the document. It is recognized that individual circumstances may alter the details of any design. It is, therefore, important that this document not be considered mandatory but be used as a guide to good electrical application and installation design. Transport aircraft electric systems have rapidly increased in importance over a number of years until they are now used for many functions necessary to the successful operation of the aircraft. An ever increasing number of these functions are critical to the safety of the aircraft and its occupants. The greatly increased power available in
AE-8A Elec Wiring and Fiber Optic Interconnect Sys Install
The purpose of this document is to serve as a resource to aerospace designers who are planning to utilize Wavelength Division Multiplexed (WDM) interconnects and components. Many WDM commercial systems exist and they incorporate a number of existing, commercially supported, standards that define the critical parameters to guide the development of these systems. These standards ensure interoperability between the elements within these systems. The commercial industry is motivated to utilize these standards to minimize the amount of tailored development. However, since some of the aerospace parameters are not satisfied by the commercial devices, this document will also try to extend the commercial parameters to those that are necessary for aerospace systems. The document provides cross-references to existing or emerging optical component and subsystem standards. These parameter definitions, test methods, and procedures typically apply to telecommunications application and in some cases
AS-3 Fiber Optics and Applied Photonics Committee
This ARP specifies the recommended methods of marking electrical wiring and harnesses to aid in the positioning/routing of electrical wiring, harnesses and cable assemblies
AE-8A Elec Wiring and Fiber Optic Interconnect Sys Install
This specification covers two types of virgin, unfilled polytetrafluoroethylene (PTFE) in the form of molded rods, tubes, and shapes. This specification does not apply to product over 12 inches (305 mm) in length, rods under 0.750 inch (19.05 mm) in diameter, and tubes having wall thickness under 0.500 inch (12.70 mm
AMS P Polymeric Materials Committee
ARP6366 defines a comprehensive and widely-accepted set of specification guidelines to be considered by those seeking to use or design fiber optic sensors for aerospace applications. Some of the most common applications for fiber optic sensing within aerospace include inertial guidance and navigation (gyros) and structural monitoring (temperature, strain, and vibration sensing). Common sensor infrastructure elements include: transmitting and receiving opto-electronics (e.g., sources and receivers); multiplexing and demultiplexing optics; optical cabling; and signal processing (both hardware and firmware/software
AS-3 Fiber Optics and Applied Photonics Committee
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