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This SAE Aerospace Recommended Practice (ARP) recommends a methodology to be used for the design, analysis and test evaluation of modern helicopter gas turbine propulsion system stability and transient response characteristics. This methodology utilizes the computational power of modern digital computers to more thoroughly analyze, simulate and bench-test the helicopter engine/rotor system speed control loop over the flight envelope. This up-front work results in significantly less effort expended during flight test and delivers a more effective system into service. The methodology presented herein is recommended for modern digital electronic propulsion control systems and also for traditional analog and hydromechanical systems.
This SAE Standard establishes a test method and a definition for disclosing the performance of suction/blower fans when applied to self-propelled sweepers that solely use a pneumatic conveyance means for the collection and transfer of “sweepings” into a collection hopper.
This document establishes the requirements for screw-on type reattachable couplings for use in low temperature hose assemblies.
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 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 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 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 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
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 Recommended Practice identifies graphic symbols used in electrical circuit diagrams. The symbols aid troubleshooting electrical systems.
This SAE Recommended Practice defines a recommended practice for implementing a bidirectional, serial communication link among modules containing microcomputers. This document defines those parameters of the serial link that relate primarily to hardware and basic software compatibility such as interface requirements, system protocol, and message format. The actual data to be transmitted by particular modules, which is an important aspect of communications compatibility, is not specified in this document. These and other details of communication link implementation and use should be specified in the separate application documents referenced in Section 2.
This document applies to prognostics of aerospace propulsion systems. Its purpose is to define the meaning of prognostics in this context, explain their potential and limitations, and to provide guidelines for potential approaches for use in existing condition monitoring environments. This document also includes some examples. The current revision does not provide specific guidance on validation and verification, nor does it address implementation aspects such as computational capability or certification.
This SAE Recommended Practice is part of the SAE J2534-2/X_0500 set of documents that extends the SAE J2534-1_0500 API (version 05.00) specification, and defines how to implement UART Echo Byte within the SAE J2534 API framework. This document details only the changes from SAE J2534-1_0500 and items not specifically detailed in this document are assumed to have not changed. An SAE J2534-2/3_0500 interface shall be compliant to the UART Echo Byte feature only when all the required functionality in this SAE Recommended Practice is implemented. Any functionality not required for compliance will be specifically marked as “optional” in this document. This document must be used in conjunction with the SAE J2534-2/BA_0500 and SAE J2534-2/RE_0500 documents.
To define a list of anomalies related to OBD Communications. Misinterpretations of various OBD Communications Standards and Recommended Practices have resulted in OBD “no-communications” situations in the field. This Information Report identifies the most prevalent of these.
This SAE Standard sets forth the procedures to be used in measuring sound levels and determining the time weighted sound level at the operator's station(s) of specified off-road self-propelled work machines. This document applies to the following work machines which have operator stations as specified in SAE J1116: • Crawler Loader • Grader • Log Skidder • Wheel Loader • Crawler Tractor with Dozer • Pipelayer • Dumper • Wheel Tractor with Dozer • Trencher • Tractor Scraper • Backhoe • Sweeper • Roller/Compactor • Hydraulic Excavator • Pad Foot Wheel Compactor with Dozer • Excavator and Wheel Feller-Buncher The instrumentation requirements and specific work cycles for these machines are described. The method used to calculate the time weighted average sound level at the operator station(s) is specified for Leq(5), or optional exchange rates, during continuous operation in a work cycle representing continuous medium to heavy work. The work cycles provide a repeatable reproduceable means
This document covers insulated, flexible air duct assemblies for portable ground support air conditioners and heaters.
Scope is unavailable.
The scope of this document is to: 1 Specify techniques to detect SC parts using electrical testing. 2 Provide various levels of electrical testing that can be used by the User to define test plans for detecting SC parts. 3 Provide minimum requirements for testing laboratories so that User/Requester can determine which test houses have the necessary capabilities. (For example: technical knowledge, equipment, procedures and protocols for performing electrical testing for verification analysis.) Note: User/Requester is defined in AS6171 General Requirements 4 Specify Burn-In and environmental tests. The environmental tests include Temperature Cycling for Active Devices and Thermal Shock for Passive Devices. Seal Tests are described and recommended for hermetic devices. The following terminology is used throughout this document: a Shall = is mandatory; b Should = is recommended; and c Will = is planned (is considered to be part of a standard process). If AS6171/7 is invoked in the contract
This document defines the process steps involved in collecting and processing engine test data for use in understanding engine behavior. It describes the use of an aero-thermal cycle model for reduction and analysis of those data. The analysis process may include the calculation of modifiers to match the model to measured data and prediction of engine performance based on that analysis.
This document establishes common industry practices and recommended screening, qualification, and lot acceptance testing of Plastic Encapsulated Microcircuits (PEMs) for use in space application environments.
This document contains general criteria for the planning, design, and construction of military and commercial ground based aviation fueling facilities that receive, store, distribute, and dispense liquid aviation turbine fuels at airports to both fixed and rotary wing aircraft.
This SAE Recommended Practice is part of the SAE J2534-2/X_0500 set of documents that extends the SAE J2534-1_0500 API (version 05.00) specification, and defines how to implement the Internet Protocol version 4 (IPv4) within the SAE J2534 API framework. This document details only the changes from SAE J2534-1_0500 and items not specifically detailed in this document are assumed to have not changed. An SAE J2534-2/16_0500 interface shall be compliant to the Internet Protocol version 4 (IPv4) feature only when all the required functionality in this SAE Recommended Practice is implemented. Any functionality not required for compliance will be specifically marked as “optional” in this document. This document must be used in conjunction with SAE J2534-2/13_0500 (ethernet), SAE J2534-2/BA_0500, and SAE J2534-2/RE_0500 documents.
This SAE Recommended Practice is part of the SAE J2534-2/X_0500 set of documents that extends the SAE J2534-1_0500 API (version 05.00) specification, and defines how to implement fault-tolerant CAN (FT CAN) within the SAE J2534 API framework. This document details only the changes from SAE J2534-1_0500 and items not specifically detailed in this document are assumed to have not changed. An SAE J2534-2/8_0500 interface shall be compliant to fault-tolerant CAN (FT CAN) feature only when all the required functionality in this SAE Recommended Practice is implemented. Any functionality not required for compliance will be specifically marked as “optional” in this document. This document must be used in conjunction with the SAE J2534-2/BA_0500 and SAE J2534-2/RE_0500 documents.
This SAE Aerospace Standard (AS) defines an industry agreed reference model for load distribution on air cargo unit load device (ULD) bases, to reflect maximum allowable center of gravity (CG) eccentricity and ensure the maximum allowable area load is not exceeded.
This guideline is applicable to existing lead solder production products that will change to lead-free solder processes to meet the ELV Directive 2000/53/EC Annex II, exemption 8B requirements. This guideline is applicable to similar products used by multiple OEM's that have the same manufacturing processes / equipment. The intent is to streamline the supplier’s environmental testing via common qualification to reduce timing, quantities, and costs.
This standard covers all types of manually operated high pressure oxygen, cylinder shut off valves for use in commercial aircraft. It is intended that the valve shall be attached to a pressure cylinder storing oxygen under a nominal pressure of 12.76 MPa (1850 psig) at 21 °C (70 °F). Upon opening the valve, oxygen will be permitted to discharge from the storage cylinder to the valve outlet and to other downstream components of the oxygen system. It shall also be possible to recharge the cylinder through the valve.
This standard describes a requirement for automotive tire traceability. It includes a definition of the RFID tag and the associated tire data set that can be accessed using the RFID tag as an identifier. The standard describes a unique identification and the associated data set for each tire produced by the tire fabricator. This data will either be provided or transmitted at the time of shipment to retailers, wholesalers or original equipment vehicle manufacturers. Tire identification code and data may be used for error proofing, determining the tire specifications or supporting any inquiries that occur for the duration of its automotive life.
Consideration for the damaging effects to aircraft from the failure of wheels and tires should be evaluated. This document discusses the types of problems in-service aircraft have experienced and methodology in place to assist the designers when evaluating threats for new aircraft design. The purpose of this document is to provide a history of in-service problems, provide a historical summary of the design improvements made to wheels and tires during the past 40 years, and to offer methodology which has been used to help designers assess the threat to ensure the functionality of systems and equipment located in and around the landing gear and in wheel wells.
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