Results
This SAE Surface Vehicle Technical Information Report, SAE J2836/4, establishes diagnostic use cases between plug-in electric vehicles (PEV) and the electric vehicle supply equipment (EVSE). As PEVs are deployed and include both plug-in hybrid electric (PHEV) and battery electric (BEV) vehicle variations, failures of the charging session between the EVSE and PEV may include diagnostics particular to the vehicle variations. This document describes the general information required for diagnostics and SAE J2847/4 will include the detail messages to provide accurate information to the customer and/or service personnel to identify the source of the issue and assist in resolution. Existing vehicle diagnostics can also be added and included during this charging session regarding issues that have occurred or are imminent to the EVSE or PEV, to assist in resolution of these items.
This SAE Recommended Practice covers the safety alert symbol intended for use on construction and industrial equipment as defined in SAE J1116 and on agricultural tractors and machinery as defined in ASABE S390.
This standard covers oronasal type masks which use a continuous flow oxygen supply. Each such mask comprises a facepiece with valves as required, a mask suspension device, a reservoir, or rebreather bag (when used), a length of tubing for connection to the oxygen supply source, and a means for allowing the crew to determine if oxygen is being delivered to the mask. The assembly shall be capable of being stowed suitably to meet the requirements of its intended use.
This SAE Aerospace Information Report (AIR) provides an orientation regarding the general technology of chemical oxygen generators to aircraft engineers for assistance in determining whether chemical oxygen generators are an appropriate oxygen supply source for hypoxia protection in a given application and as an aid in specifying such generators. Information regarding the details of design and manufacture of chemical oxygen generators is generally beyond the scope of this document.
This SAE Aerospace Information Report (AIR) outlines a recommended procedure for evaluation of the vibration environment to which the gas turbine engine powerplant is subjected in the helicopter installation. This analysis of engine vibration is normally demonstrated on a one-time basis upon initial certification, or after a major modification, of an engine/helicopter configuration. This AIR deals with linear vibration as measured on the basic case structure of the engine and not, for example, torsional vibration in drive shafting or vibration of a component within the engine such as a compressor or turbine airfoil. In summary, this AIR discusses the engine manufacturer’s "Installation Test Code" aspects of engine vibration and proposes an appropriate measurement method.
This SAE Aerospace Recommended Practice (ARP) identifies and defines a method of measuring those factors affecting installed power available for helicopter powerplants. These factors are installation losses, accessory power extraction, and operational effects. Accurate determination of these factors is vital in the calculation of helicopter performance as described in the RFM. It is intended that the methods presented herein prescribe and define each factor as well as an approach to measuring said factor. Only basic installations of turboshaft engines in helicopters are considered. Although the methods described may apply in principle to other configurations that lead to more complex installation losses, such as an inlet particle separator, inlet barrier filter (with or without a bypass system), or infrared suppressor, specialized or individual techniques may be required in these cases for the determination and definition of engine installation losses. Some rotorcraft may use an
The scope of this SAE Aerospace Recommended Practice (ARP) is to establish the procedure for creating titles of aerospace tubing and clamp installation documents generated by SAE Subcommittee G-3E.
This SAE Aerospace Recommended Practice (ARP) defines a means of assessing the credibility of computer models of aircraft seating systems used to simulate dynamic impact conditions set forth in Title 14, Code of Federal Regulations (14 CFR) Parts 23.562, 25.562, 27.562, and 29.562. The ARP is applicable to lumped mass and detailed finite element seat models. This includes specifications and performance criteria for aviation specific virtual anthropomorphic test devices (v-ATDs). This document provides a recommended methodology to evaluate the degree of correlation between a seat model and dynamic impact tests. This ARP also provides best practices for testing and modeling designed to support the implementation of analytical models of aircraft seat systems. Supporting information within this document includes procedures for the quantitative comparison of test and simulation results, as well as test summaries for data generated to support the development of v-ATDs and a sample v-ATD
This SAE Aerospace Standard (AS) covers sealed, self-aligning, anti-friction, rod end ball bearings with application in temperature ranges (1) -65 to 250 °F and (2) -65 to 300 °F with 20% reduction of dynamic load carrying capacity when subjected to operation above 250 °F.
This SAE Aerospace Recommended Practice (ARP) provides recommendations for: The audit process in general A list of specific areas of attention to be audited Maintaining the test facility in such a manner that it meets audit requirements
This procurement specification covers aircraft quality metric spanner nuts for retaining shaft mounted parts. Nuts are made from a corrosion and heat resistant age hardenable iron base alloy of the type identified under the Unified Numbering System as UNS S66286, and silver plated. Thread shear proof strength at room temperature is 450 MPa.
This SAE Aerospace Standard (AS) establishes the characteristics and utilization of 270 V DC electric power at the utilization equipment interface and the constraints of the utilization equipment based on practical experience. These characteristics shall be applicable for both airborne and ground support power systems. This document also defines the related distribution and installation considerations. Utilization equipment designed for a specific application may not deviate from these requirements without the approval of the procuring activity.
This SAE Recommended Practice applies to three-point hitch (Type A) backhoes as defined in SAE J326 when mounted on either an agricultural tractor as defined in ANSI/ASAE S390 or other off-road self-propelled work machine as defined in SAE J1116. This criterion is intended for the manufacturer of the backhoe, whether or not the backhoe is manufactured or marketed by the same company that manufactures or markets the propelling machine.
This standard defines a generic set of electrical interfaces between a host aircraft (“platform”) and an electro-optic/infrared (EO/IR) sensor. This includes connectors, cabling, fiber optics, signals, and power.
This SAE recommended practice defines the system and component functions, measurement metrics, testing methodologies for evaluating the functionality and performance of tire pressure systems, and recommended maintenance practices within the known operating environments. This document is applicable to all axle and all wheel combinations for single unit powered vehicles exceeding 7257 kg (16 000 US lb) gross vehicle weight rating (GVWR), and multi-unit vehicle combinations, up to three (3) towed units, which use an SAE J560 connector for power and/or communication, or equivalent successor connector technology, or which use a suitable capacity wireless solution. Examples of included single chassis vehicles would be – utility and delivery vans, tow trucks, rack trucks, buses, recreational vehicles, fuel trucks, trash trucks, dump trucks, cement trucks, and tractors. Examples of combination vehicles using an SAE J560 or successor connector would be – enclosed van trailers, liquid tanker
To provide general instructions for accomplishing ultrasonic thickness measurements. Measurements can be made from one side of a material when access to the opposite side is restricted.
This SAE Standard defines the method for deriving and verifying the peening intensity exerted onto a part surface during shot peening or other surface enhancement processes.
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.
The purpose of this section is to provide methods and a set of convenient working charts to estimate penalty values in terms of take-off fuel weight for any given airplane mission. The curves are for a range of specific fuel consumption (SFC) and lift/drag ratio (L/D) compatible with the jet engines and supersonic aircraft currently being developed. A typical example showing use of the charts for an air conditioning system is given. Evaluation of the penalty imposed on aircraft performance characteristics by the installation of an air conditioning system is important for two reasons: 1 It provides a common denominator for comparing systems in the preliminary design stage, thus aiding in the choice of system to be used. 2 It aids in pinpointing portions of existing systems where design improvements can be most readily achieved. All factors that influence the flight performance of an aircraft can be expressed in terms of weight, external and momentum drags, and changes in powerplant
This SAE Aerospace Standard (AS) establishes the requirements for fluid fittings that combine both weld fitting end and 24° cone flareless fitting end connections for use in all types of fluid systems.
This document is a companion document to SAE AS4893 “Generic Open Architecture (GOA) Framework Standard” and provides an overview and rationale for SAE AS4893. The GOA Framework establishes an architectural framework to assist in the application of open systems interface standards to the design of specific hardware/software systems. The GOA Framework standard is intended for use by both system designers and system implementers in the development of open systems architectures. It is intended that domain specific guidelines be developed to provide clarification for application of the GOA Framework. The Generic Open Architecture (GOA) Framework was initially developed by the SAE to provide a framework which could be used to classify interfaces needed in airborne avionics systems. At the time of the development of the GOA Framework, development of such a classification was considered crucial to the application of open systems standards to military avionics. However, it was recognized
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