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This document is intended to establish a procedure to certify AD fallback test driver skill levels as an endorsement to SAE J3300 foundational level certification. The SAE J3300/3 endorsement can be used by the individual driver to qualify their skills as a test driver of vehicles with automated driving features. The SAE J3300/3 endorsement levels may also be used by test facilities or other organizations when seeking test or professional drivers with these skills. This document provides directions for obtaining the endorsement, including associated AD fallback test driving skill examination requirements, through SAE J3300-certified Examiners (refer to SAE J3300 for definition). Endorsement registration and associated records are administered through Probitas Authentication®. Probitas Authentication® is the current Independent Program Administrator for the SAE J3300 series. This document is a supplement to SAE J3300, providing information specific to the AD fallback test driver skill
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 Almen strip holder is required for intensity determination.
This SAE Aerospace Information Report (AIR) covers the general requirements for, and the listing of, manufacturers’ identification markings, names, symbols or trademarks, and CAGE codes that appear on electrical and electronic wiring devices and accessories as required by individual product specifications. Supplier markings from previous submitted listings are maintained for component traceability.
This specification covers a corrosion- and heat-resistant steel in the form of bars, forgings, and forging stock.
This procedure measures the resistance to radiant heat flow of insulating materials in sleeve, tubing, or tape (collectively referred to as “sleeve”) form. The sleeve’s effectiveness (SE) is determined by measuring the difference in surface temperature of a flat black, single-diameter ceramic cylinder with and without the standard diameter sleeve at the specified temperature, position, and distance from the radiant heat source.
This specification covers the requirements for thermal spray coatings applied using the high velocity oxygen fuel (HVOF) combustion process. This specification is not intended to be used for duplex coatings, i.e., the application of the coating over a previously applied coating.
The purpose of this SAE Aerospace Recommended Practice (ARP) is to provide the sample selection and endurance time test procedures for SAE Type II, III, and IV aircraft deicing/anti-icing fluids, required for the generation of endurance time data of acceptable quality for review by the SAE G-12 Holdover Time Committee. The related standard ARP5718 provides the process by which endurance time data is converted to holdover times for publication by regulators and subsequent use by aircraft operators.
This method is intended to evaluate the thermal and oxidative stability of synthetic, ester-based aviation lubricants under defined conditions of time and temperature. This method is applicable to lubricants meeting the compositional and performance requirements of AS5780.
Long wave ultraviolet or UV-A irradiation (between 320 and 400 nm) is used for fluorescent inspections in magnetic particle and liquid penetrant examinations. UV-A irradiation is obtained from either LED, fluorescent, or high intensity discharge lamps that are stationary or portable. Commercially available UV-A lamps possess a large variation in intensity output that may introduce a legitimate concern for possible health hazards. This document reviews the nature of UV-A irradiation emitted by lamps and acceptable UV dosage limits adopted by the American Conference of Governmental Industrial Hygienists (ACGIH®) and European Union and recommendation of proper practices when working with UV-A irradiation.
This specification covers the installation of aircraft interior lighting for military aircraft.
This SAE Recommended Practice identifies and defines requirements relating to the safe integration of the fuel cell system, the hydrogen fuel storage and handling systems (as defined and specified in SAE J2579) and high voltage electrical systems into the overall Fuel Cell Vehicle. The document may also be applied to hydrogen vehicles with internal combustion engines. This document relates to the overall design, construction, operation and maintenance of fuel cell vehicles.
This document covers evaluation techniques for determining the power consumption characteristics of engine driven hydraulic pumps used on heavy-duty trucks and buses. The testing technique outlined in this SAE Recommended Practice was developed as part of an overall program for testing and evaluating fuel consumption of heavy-duty trucks and buses. The technique outlined in this document provides a description of the test to be run to determine power consumption of these engine driven components, the type of equipment and facilities which are generally required to perform these tests are discussed in SAE J745. It is recommended that the specific operating conditions suggested throughout the test be carefully reviewed on the basis of actual data obtained on the specific vehicle operation.
This specification covers a style 7781 glass cloth impregnated with a heat-curable polyester resin system, the resin being processed to a “B” stage condition, and furnished in the form of continuous rolls.
MIL-STD-1553 establishes requirements for digital command/response time division multiplexing (TDM) techniques on military vehicles, especially aircraft. The existing MIL-STD-1553 network operates at a bit rate of 1 Mbps and is limited by the protocol to a maximum data payload capacity of approximately 700 kilobits per second. The limited capacity of MIL-STD-1553 buses coupled with emerging data rich applications for avionics platforms plus the expense involved with changing or adding wires to thousands of aircraft in the fleet has driven the need for expanding the data carrying capacity of the existing MIL-STD-1553 infrastructure.
This specification covers a magnesium alloy in the form of sand castings.
This specification covers an aluminum alloy powder metallurgy product in the form of round extrusions up to 3.5 inches (89 mm) in diameter and rectangular and other solid extrusions up to 10 square inches (64.5 cm2) in cross-sectional area. The maximum extrusion length is 100 inches (2.5 m).
This specification covers a single-component, heat-reactive, thermosetting aromatic system which thermally cures to form a polyimide polymer structure.
This SAE Standard covers the mechanical and physical requirements for Compacted Graphite Iron (CGI) castings used in automotive and allied industries. Requirements in this document include: a Tensile Strength b Yield Strength c Elongation d Graphite Morphology
The following system of symbols is recommended for use in technical papers and engineering reports dealing with hydrodynamic drives.
See Table 1.
The following schematic diagrams reflect various methods of illustrating automotive transmission arrangements. These have been developed to facilitate a clear understanding of the functional interrelations of the gearing, clutches, hydrodynamic drive unit, and other transmission components. Two variations of transmission diagrams are used: in neutral (clutches not applied) and in gear. For illustrative purposes, some typical transmissions are shown.
This AIR is limited to the requirements of AS50881 and examines these requirements, providing rationale behind them. AS50881 is only applicable to the aircraft EWIS. Pods and other devices that can be attached to an aircraft are considered as part of the aircraft equipment design. Its scope does not include wiring inside of airborne electronic equipment but does apply to wiring externally attached to such equipment. The AS50881 scope does not include attached devices but does include the interface between the pod/equipment and aircraft wiring. Section 3.3.5 addresses components such as antennas and other similar equipment that were once supplied as Government Furnished Aeronautical/Aerospace Equipment (GFAE).
This SAE Aerospace Standard (AS) sets forth criteria for the selection and verification processes to be followed in providing tires that will be suitable for intended use on civil aircraft. This document encompasses new and requalified radial and bias aircraft tires.
This specification presents requirements for thin-walled (inside diameter greater than four times the wall thickness and outside diameter 1/4 inch and larger) corrosion-resistant steel tubing in approximately the 1/8 hard condition, of special quality, suitable for use in high-pressure hydraulic systems.
The purpose of this document is to establish air-conditioning design guidelines that will apply to most systems rather than the specific design of any particular system. Operating conditions and characteristics of the equipment will determine the design of any successful system; since these characteristics and conditions vary greatly from one application to another, the designer shall determine the goals expected to be reached under the conditions encountered. To determine the capacity of such items as blowers, condenser fans, condenser coils, evaporator coils, filters, compressors, etc., will require the adherence to several guidelines, some of which are outlined in the following paragraphs.
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