Information Reports - SAE Mobilus
This document is offered to provide state-of-the-art information about design factors that must be considered in the design of new or significantly modified engine test cells used to test propeller equipped turboprop engines in either QEC or bare engine configurations. The report does not address design considerations for test cells designed to test turboprop engines with dynamometer type load absorption devices because they are essentially tested as turboshaft engines. Design considerations for those test cells are presented in AIR4989, Reference 2.1.
This SAE Aerospace Information Report presents a glossary of terms commonly used in the ground delivery of fuel to an aircraft and pertinent terms relating to the aircraft being refueled.
This AIR provides information about the specific requirements for missile hydraulic pumps and their associated power sources.
This SAE Aerospace Information Report (AIR) provides a general description of methods for hardness testing of O-rings including factors which affect precision and comparison of results with those obtained in standard tests.
This Information Report describes eddy current testing, flux leakage testing, ultrasonic testing, and magnetic particle testing of steel tubing. The purpose of these testing methods is to expose flaws in the tube material or weld zone, such as discontinuities, seams, cracks, holes, voids, and other imperfections characteristic to the specific construction of the tubing. When agreed upon between the producer and purchaser, nondestructive testing is used in lieu of destructive hydrostatic pressure proof testing. Aircraft and Aerospace applications were not considered during the preparation of this document.
The purpose of this SAE Information Report is to define common industry terminology and nomenclature relative to thermal flow control valves and to describe common thermal flow control valve applications in automotive, highway truck, mobile construction equipment, and industrial applications. This document is primarily directed at internal combustion engine or electric powered applications and the downstream systems to which power is provided, such as transmissions, hydraulics, air compression, etc. The information contained herein does not constitute an SAE Standard.
This document is reissued for application to helicopters. It is primarily intended to apply to the engine or engines, but it shall also apply to fire protection of lines, tanks, combustion heaters, and auxiliary powerplants (APU). Post-crash fire protection is also discussed.
This document is reissued for application to helicopters.
Waste heat recovery (WHR) systems are used in vehicles and machines powered by internal combustion (IC) engines to capture unused and therefore wasted heat and utilize it. This reduces fuel consumption and emissions by improving efficiency. This information report is a survey of the waste heat recovery methods that include the use of heat exchangers.
This SAE Information Report has been prepared at the request of the SAE Road Vehicle Aerodynamics Forum Committee (RVAC), incorporating material from earlier revisions of the document first prepared by the Standards Committee on Cooling Flow Measurement (CFM). Although a great deal is already known about engine cooling, recent concern with fuel conservation has resulted in generally smaller air intakes whose shape and location are dictated primarily by low vehicle drag/high forward speed requirements. The new vehicle intake configurations make it more difficult to achieve adequate cooling under all conditions. They cause cooling flow velocity profiles to become distorted and underhood temperatures to be excessively high. Such problems make it necessary to achieve much better accuracy in measuring cooling flows. As the following descriptions show, each company or institution concerned with this problem has invested a lot of time and as a result gained considerable experience in
The previous revision of AIR5784 summarizes some of the available literature on cabin air study, engine oil composition, decomposition, and toxicity testing. This revision of AIR5784 includes literature and information on stakeholder involvement, selected air sampling studies, oil composition, and oil degradation, published from 2000 to 2023. The entire contents of the reviewed literature are not necessarily endorsed by either SAE or the members of the study group who produced it. This is not a comprehensive review but is intended to enable E-34 and other technical organizations to participate in informed discussions on the topic. Also, the review is intended to indicate where additional work may be necessary to properly gauge the potential role that turbine lubricants (and OPs) play in cabin air quality. The toxicology of oil fumes and their individual constituents is beyond the scope of this document and outside the remit of this committee.
It is expected that Level 4 and 5 automated driving systems-dedicated vehicles (ADS-DVs) will eventually enable persons to travel at will who are otherwise unable to obtain a driver’s license for a conventional vehicle, namely, persons with certain visual, cognitive, and/or physical impairments. This information report focuses on these disabilities but also provides guidance for those with other disabilities. This report is limited to fleet-operated, on-demand, shared mobility scenarios, as this is widely considered to be the first way people will be able to interact with ADS-DVs. To be more specific, this report does not address fixed-route transit services or private vehicle ownership. Similarly, this report is focused on motor vehicles (refer to SAE J3016), not scooters, golf carts, etc. Lastly, this report does not address the design of chair lifts, ramps, or securements for persons who use wheeled mobility devices (WHMD) (e.g., wheelchair, electric cart, etc.), as these matters
This SAE Aerospace Information Report (AIR) defines the areas where incompatibility may exist between the selected wire and the electrical connector in which it is terminated and how to design for compatibility. Refer to ARP914 for a glossary of connection terms.
This SAE Aerospace Information Report (AIR) provides general guidance for design considerations and qualification in endurance, strength, and fatigue of landing gear using composite components as principle structural elements. The information discussed herein includes the development and evaluation of design data considering the potential for imbedded manufacturing defects, manufacturing process variations, the component operating environment, potential damage threats in service, rework and overhaul, and inspection processes. This AIR mainly discusses the use of thick composites for landing gear structural components. Considerations and recommendations provided in this AIR may therefore differ greatly from considerations and recommendations found in widely accepted composite design references such as CMH-17 and Advisory Circulars such as AC 20-107B.
This document is reissued for application to helicopters.
This SAE Information Report is provided as an advisory guide and is not intended to be made a procurement requirement. Individual application discretion is recommended. The content has been presented as accurately as possible, but responsibility for its application lies with the user. The document covers a number of the variables in the torque-tension relationship: friction, materials, temperature, humidity, fastener and mating part finishes, surfaces, and the kind of tightening tools or equipment used. With an understanding of the variables to be considered, several methods to determine and tighten fasteners using the torque-tension relationship are identified. This guide is limited in application to fasteners with ISO-metric or UN series threads. Other thread types, such as self-tapping or thread forming, may apply to some aspects of this standard but are not specifically covered. The procedures described in this document are based on general factors for the determination of the
Terminology within this document is limited to the dynamics and handling characteristics of single track, two-wheeled vehicles.
This SAE Aerospace Information Report (AIR) is limited to the subject of compatibility of wiring as part of aircraft Electrical Wiring and Interconnect Systems (EWIS) installed in and around aircraft fuel tanks.
This SAE Aerospace Information Report (AIR) includes general information about the various types and styles of flexible tanks and the tank-mounted fittings that adapt the tank to the surrounding structure and fluid-system plumbing. Recommendations are given relative to the dimensional layout of the tank when these recommendations serve to avoid tank fabrication problems and tank/structure interface problems. As a part of these recommendations, critical dimensions of plumbing adapter fittings are discussed and recommendations made. Tank manufacturing tolerances are given. Recommendations are made relative to cavity design and preparation to facilitate a reliable installation. The special installation requirements of nonself-sealing, self-sealing, and crash-resistant tanks are discussed. This document is not intended to replace the information or requirements of the military and commercial procurement specifications listed in Section 2. No attempt has been made, except in a very general
This document establishes the minimum curriculum requirements for training, practical assessments, and certifying composite structure repair personnel and metalbond repair personnel. It establishes criteria for the certification of personnel requiring appropriate knowledge of the technical principles underlying the composite structural repairs and/or metalbond they perform. Persons certified under this document may be eligible for licensing/certification/qualification by an appropriate authority, in addition to this industry-accepted technician certification. Teaching levels have been assigned to the curriculum to define the knowledge, skills, and abilities graduates will need to make repairs to composite or metalbond structure. Minimum hours of instruction have been provided to ensure adequate coverage of all subject matter, including lecture and laboratory. These minimums may be exceeded and may include an increase in the total number of training hours and/or increase in the teaching
This report lists documents that aid and govern the design of aircraft and missile fuel systems. The report lists the military and industry specifications and standards and the most notable design handbooks that are commonly used in fuel system design. Note that only the principle fuel specifications for the U.S. and Europe (Military Specifications, ASTM, and Def Stan) have been included within this report. The specifications and standards section has been divided into two parts: a master list arranged numerically of all industry and military specifications and standards, and a component list that provides a functional breakdown and a cross-reference of these documents. It is intended that this report be a supplement to specifications ARP8615, MIL-F-17874, and JSSG 2009. Revisions and amendments which are correct for the specifications and standards are not listed. The fuel system design handbooks are listed for fuels and for system and component design.
Current regulations (e.g., Title 14 of the United States Code of Federal Regulations, or 14 CFR) define design requirements for oxygen system provisions for protection of crewmembers and passengers following emergency events such as in-flight decompression. This aerospace information report (AIR) addresses the operational oxygen system requirements for a decompression incident that may occur at any point during a long-range flight, with an emphasis for a decompression at the equal time point (ETP). This AIR identifies fuel and oxygen management contingencies and presents possible solutions for the efficient, safe, and optimum fuel/oxygen flight continuation. Oxygen management is a critical concern for all aircraft, ranging from single-engine types operating above 10000 feet to complex, high-performance aircraft equipped with supplemental oxygen systems. Proper planning ensures compliance with regulations and supports pilot and passenger safety at higher altitudes. This document
This SAE Recommended Practice defines the minimum performance specifications for sensors used within anthropomorphic test devices (ATDs) when performing impact tests per SAE J211. It is intended that any agency proposing to conduct tests in accordance with SAE J211 shall be able to demonstrate that the transducers they use would meet the performance requirements specified in this document.
This SAE Information Report applies to structural integrity, performance, drivability, and serviceability of personally licensed vehicles not exceeding 10000 pounds GVWR such as sedans, crossovers, SUVs, MPVs, light trucks, and van-type vehicles that are powered by gas and alternative fuel such as electric, plug-in hybrid, or hybrid technologies. It provides engineering direction to vehicle modifiers in a manner that does not limit innovation, and it specifies procedures for preparing vehicles to enhance safety during vehicle modifications. It further provides guidance and recommendations for the minimum acceptable design requirements and performance criteria on general and specific structural modifications, thereby allowing consumers and third-party payers the ability to obtain and purchase equipment that meets or exceeds the performance and safety of the OEM production vehicle.
This document applies to the development of Plans for integrating and managing electronic components in equipment for the military and commercial aerospace markets, as well as other ADHP markets that wish to use this document. Examples of electronic components described in this document include resistors, capacitors, diodes, integrated circuits, hybrids, application specific integrated circuits, wound components, and relays. It is critical for the Plan owner to review and understand the design, materials, configuration control, and qualification methods of all “as-received” electronic components and their capabilities with respect to the application; and to identify risks and, where necessary, take additional action to mitigate the risks. The technical requirements are in Section 3 of this standard and the administrative requirements are in Section 4.
The document provides clarity related to multiple temperature coolant circuits used with on-highway and off-highway, gasoline, and light-duty to heavy-duty diesel engine cooling systems, or hybrid vehicle systems. These multiple temperature systems include engine jacket coolant plus at least one lower temperature system. Out of scope are the low temperature systems used in electric vehicles. This subject is covered in SAE J3073. Note that some content in SAE J3073 is likely to be of interest for hybrid vehicles. Out of scope are the terms and definitions of thermal flow control valves used in either low-temperature or high-temperature coolant circuits. This subject is covered in SAE J3142.
This SAE Aerospace Information Report (AIR) discusses the nature of landing gear stability, describes many common landing gear stability problems, and suggests approaches and methods for solving or avoiding them.
This SAE Aerospace Information Report (AIR) discusses the sources of copper in aviation jet fuels, the impact of copper on thermal stability of jet fuels and the resultant impact on aircraft turbine engine performance, and potential methods for measurement of copper contamination and reduction of the catalytic activity of copper contamination in jet fuels. This document is an information report and does not provide recommendations or stipulate limits for copper concentrations in jet fuels.
This SAE Information Report establishes Use Cases for communication between plug-in electric vehicles (PEVs) and the electric power grid, for energy transfer and other applications.
This SAE Aerospace Information Report (AIR) is intended as a guide toward standardization of descriptions and specifications of fluid contamination products.
This Handbook is intended to accompany or incorporate AS5643, AS5643/1, AS5657, AS5706, and ARD5708. In addition, full understanding of this Handbook also requires knowledge of IEEE-1394-1995, IEEE-1394a, and IEEE-1394b standards. This Handbook contains detailed explanations and architecture analysis on AS5643, bus timing and scheduling considerations, system redundancy design considerations, suggestions on AS5643-based system configurations, cable selection guidance, and lessons learned on failure modes.
This document outlines the functional and design requirements for baggage/cargo tow tractors used for airline services.
This Aerospace Information Report (AIR) will examine considerations relative to the use of mechanical switches on aircraft landing gear, and present "lessons learned" during the period that these devices have been used.
The scope of the test method is to provide stakeholders including fluid manufacturers, airport operators, brake manufacturers, aircraft constructors, aircraft operators and airworthiness authorities with a relative assessment of the effect of deicing chemicals on carbon oxidation. This simple test is only designed to assess the relative effects of runway deicing chemicals by measuring mass change of contaminated and bare carbon samples tested under the same conditions. It is not possible to set a general acceptance threshold oxidation limit based on this test method because carbon brake stack oxidation is a function of heat sink design and the operating environment.
This document describes machine-to-machine (M2M)1 communication to enable cooperation between two or more traffic participants or CDA devices hosted or controlled by said traffic participants. The cooperation supports or enables performance of the dynamic driving task (DDT) for a subject vehicle equipped with an engaged driving automation system feature and a CDA device. Other participants may include other vehicles with driving automation feature(s) engaged, shared road users (e.g., drivers of conventional vehicles or pedestrians or cyclists carrying compatible personal devices), or compatible road operator devices (e.g., those used by personnel who maintain or operate traffic signals or work zones). Cooperative driving automation (CDA) aims to improve the safety and flow of traffic and/or facilitate road operations by supporting the safer and more efficient movement of multiple vehicles in proximity to one another. This is accomplished, for example, by sharing information that can be
This document covers the general physical, electrical, functional, and performance requirements for adapters connected to standards conforming conductive power transfer via handheld conductive coupler capable of transferring either DC or single-phase power using two current-carrying contacts. The focus is on defining the process to evaluate the suitability of adapters for NACS couplers. This edition only covers adapters used between SAE J3400 and SAE J1772.
This SAE Aerospace Information Report (AIR) describes a method for assessing size dependent particle losses in a sampling and measurement system of specified geometry utilizing the non-volatile Particulate Matter (nvPM) mass and number concentrations measured at the end of the sampling system.1 The penetration functions of the sampling and measurement system may be determined either by measurement or by analytic computational methods. Loss mechanisms including thermophoretic (which has a very weak size dependence) and size dependent losses are considered in this method2 along with the uncertainties due to both measurement error and the assumptions of the method. The results of this system loss assessment allow development of estimated correction factors for nvPM mass and number concentrations to account for the system losses facilitating estimation of the nvPM mass and number at the engine exhaust nozzle exit plane. As the particle losses are size dependent, the magnitude of correction
This section presents methods and examples of computing the steady-state heating and cooling loads of aircraft compartments. In a steady-state process the flows of heat throughout the system are stabilized and thus do not change with time. In an aircraft compartment, several elements compose the steady-state air conditioning load. Transfer of heat occurs between these sources and sinks by the combined processes of convection, radiation, and conduction in the following manner: 1 Convection between the boundary layer and the outer airplane skin. 2 Radiation between the external skin and the external environment. 3 Solar radiation through transparent areas directly on flight personnel and equipment and on the cabin interior surfaces. 4 Conduction through the cabin walls and structural members. 5 Convection between the interior cabin surface and the cabin air. 6 Convection between cabin air and flight personnel or equipment. 7 Convection and radiation from internal sources of heat such as
Common or obvious surface imperfections are normally visible to the naked eye before or after fabrication or processing. Illustrations and definitions of these imperfections are contained in this SAE Information Report. The identifying names are those commonly used throughout the steel industry. The imperfections identified include the major and most often encountered imperfections known to exist at this time. These imperfections are variable in appearance and severity. Extreme conditions have been selected in some instances in order to obtain suitable photographs. Photographs are courtesy of the American Iron and Steel Institute, Kaiser Aluminum, U.S. Steel, Nucor Steel, Samuel Steel, Steel Dynamics, Worthington Steel, and companies no longer in existence: LTV Steel, National Steel, and The Budd Company.
The scope of this report is to capture fundamental principles of selecting a wire size for an aerospace application using the method prescribed in AS50881 and additional calculations, not found in AS50881, to ensure the wire selection will adequately perform in the specific physical and environmental conditions. This report covers wire selection and sizing as part of the electrical wire interconnection systems (EWIS) used in aerospace vehicles. Aerospace vehicles include manned and unmanned airplanes, helicopters, lighter-than-air vehicles, missiles, and external pods. This document does not apply to wiring inside of airborne electronic equipment but shall apply to wiring externally attached to such equipment. Wire selection must consider physical and environmental factors to size wires such that they have sufficient mechanical strength, do not exceed allowable voltage drop levels, are protected by materials or circuit protection devices, and meet circuit current carrying requirements
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