Information Reports - SAE Mobilus

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Manufacturers’ Identification of Aerospace Electrical and Electronic Wiring Devices and AccessoriesAIR1351L (Current)7/20/2026
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.
AE-8C2 Terminating Devices and Tooling Committee
EUROCAE/SAE WG80/AE-7AFC Hydrogen Fuel Cells Aircraft Fuel Cell Safety GuidelinesAIR6464 (Current)7/17/2026
This document defines the technical guidelines for the safe integration of Proton Exchange Membrane (PEM) Fuel Cell Systems (FCS), fuel (considered to be liquid and compressed hydrogen storage types only), fuel storage, fuel distribution and appropriate electrical systems into the aircraft. Editorial Note: Today PEM systems and fuel storage represent the most mature FCS technology and currently forms the basis for this standard. Other types of fuel cell systems and fuels (including reforming technologies and electrolyzers), may be covered by a further update to this document.
AE-7F Hydrogen and Fuel Cells
Exposure Levels of UV Radiation in Nondestructive Inspection ProcessesAIR4964A (Current)7/17/2026
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.
AMS K Non Destructive Methods and Processes Committee
Reverse Automatic Emergency Braking (AEB) Testing SummaryJ3339_202607 (Current)7/14/2026
This SAE Information Report provides a broad summary of existing Reverse Automatic Emergency Braking test protocols to help assess whether additional test protocols are needed. Eventually, the task force may develop additional protocols to support testing of Reverse Automatic Emergency Braking systems.
Active Safety and Driver Support Systems Standards Committee
Use Cases for Diagnostic Communication for Plug-in Electric VehiclesJ2836/4_202606 (Current)6/30/2026
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.
Hybrid - EV Committee
Evaluation of Helicopter Turbine Engine Linear Vibration EnvironmentAIR1289A (Current)6/29/2026
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.
S-12 Powered Lift Propulsion Committee
Chemical Oxygen SystemsAIR825/4A (Current)6/29/2026
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.
A-10 Aircraft Oxygen Equipment Committee
Use Cases for Wireless Charging Communication for Plug-in Electric VehiclesJ2836/6_202606 (Current)6/24/2026
This SAE Information Report SAE J2836/6 establishes use cases for communication between plug-in electric vehicles and the EVSE for wireless energy transfer as specified in SAE J2954. It addresses the requirements for communications between the on-board charging system and the wireless EV supply equipment (WEVSE) in support of detection of the WEVSE, the charging process, and monitoring of the charging process. Since the communication to the charging infrastructure and the power grid for smart charging will also be communicated by the WEVSE to the EV over the wireless interface, these requirements are also covered. However, the processes and procedures are expected to be identical to those specified for V2G communications specified in SAE J2836/1. Where relevant, the specification notes interactions that may be required between the vehicle and vehicle operator, but does not formally specify them. Similarly, communications between the on-board charging sub-system and the on-board vehicle electronics is not formally specified in this document. This document will be published as a set of steps. The intent of step 1 was to record as much information on “what we think works” and publish. The intent of step 2 is to provide refinement and missing pieces to step 1, with a an eye to early testing. This version is step 2, with the aim of providing a communication protocol for home chargers.
Hybrid - EV Committee
Automotive Air-Conditioning Service Ports Task Force Field Survey ResultsJ3267_202606 (Current)6/23/2026
The automotive air-conditioning service ports task force conducted a field survey with MACS (Mobile Air Climate Systems Association) in June 2021. The scope of this survey was to determine the types of failures reported primarily at member service shops related to automotive air-conditioning service ports.
ICTMS Supplier Committee
Reduced Effort Brakes and Reduced Effort Vacuum Powered Brake Backup SystemsJ2671_202606 (Current)6/22/2026
This Information Report relates to a special class of automotive adaptive equipment which consists of modifications to the power brake booster systems provided as original equipment of motor vehicles. These modifications are generically called "Reduced Effort Power Brakes" (REPB) The purpose of the modification is to lower the amount of driver effort required to apply the brakes. Retention of reliability, ease of use and maintainability for disabled drivers, passengers, and the general public is of primary concern. Reduced Effort Power Brake modifications should be qualified by the tests referenced in the Recommended Test Procedure. The tests set forth in that procedure should be applied, and failure of a Reduced Effort Power Brake modification to meet those tests should disqualify the modification from the claim of meeting the specifications of this Information Report. Because this is an Information Report, the numerical values for performance measurements presented in this report and in the accompanying Test Procedure, while based upon the best knowledge available at the time, have not been validated by a testing of the Test Procedure.
Adaptive Devices Standards Committee
Active Safety System SensorsJ3088_202606 (Current)6/19/2026
The current document is a part of an effort of the Active Safety Systems Committee, Active Safety Systems Sensors Task Force whose objectives are to: Identify the functionality and performance you could expect from active safety sensors Establish a basic understanding of how sensors work Establish a basic understanding of how sensors can be tested Describe an exemplar set of acceptable requirements and tests associated with each technology Describe the key requirements/functionality for the test targets Describe the unique characteristics of the targets or tests This document will cover items (a) and (b).
Active Safety and Driver Support Systems Standards Committee
Oxygen Cylinder Quality, Serviceability, Maintenance Transfilling, and MarkingAIR1059G (Current)6/15/2026
This document provides guidance concerning the maintenance and serviceability of oxygen cylinders beginning with the quality of oxygen that is required, supplemental oxygen information, handling and cleaning procedures, transfilling, and marking of serviced oxygen assemblies. This document attempts to outline in a logical sequence oxygen quality, serviceability, and maintenance of oxygen cylinders. Content of this document can also be used for refilling oxygen cylinders while installed on aircraft, directly or through an intermediate charging port.
A-10 Aircraft Oxygen Equipment Committee
Side Channel and Fault Injection Attack ResistanceJ3101-4_202606 (Current)6/15/2026
This report provides a survey of side channel and fault injection attacks that have an impact on automotive embedded systems. The focus is on side channel attacks that target cryptographic algorithms and hardware security engines, as well as sensitive data leakage. The report also considers fault injection attacks against typical vehicle components that allow bypassing of security controls to compromise the target system security and outlines some countermeasures to detect and/or prevent them. The report provides a list of security countermeasures that can be considered by manufacturers based on their risk tolerance to such attacks. Additionally, it offers the automotive industry supply chain a common language to facilitate the communication of side channel and fault injection mitigation requirements among the various stakeholders.
Vehicle Electrical System Security Committee
811P2 Commercial Aircraft Information Security, Part 2, Risk Assessment MethodologyARINC811P2 (Current)6/15/2026
The purpose of this standard is to provide airline operators with a structured and practical framework for conducting cybersecurity risk assessments of ground-based systems that interface with or support e-enabled aircraft. By establishing consistent methodologies and practices, the standard aims to ensure that operators can effectively identify, assess, and mitigate cybersecurity risks, thereby safeguarding the safety and airworthiness of their aircraft operations.
Airlines Electronic Engineering Committee
645-2 Secure Software Data LoadingARINC645-2 (Current)6/15/2026
The ARINC 645-2 standard emphasizes comprehensive cybersecurity practices for software data loading in aviation, including digital signatures, access controls, device hardening, and detailed logging to ensure software integrity, authenticity, and system security.
Airlines Electronic Engineering Committee
857 Securing Non-Safety SATCOM CommunicationsARINC857 (Current)6/15/2026
This document provides comprehensive guidance on cybersecurity practices, threat assessment, and security controls for non-safety satellite communication (Satcom) systems onboard commercial aircraft, emphasizing protection of data, system integrity, and privacy.
Airlines Electronic Engineering Committee
ARP4754B Clarification NoticeAIR4757 (Current)6/11/2026
The purpose of this AIR is to provide additional information on some areas of ARP4754B/ED-79B that may need additional clarification in order to be put into practice. This document should be used in conjunction with ARP4754B/ED-79B. The contents are recommendations and should not be construed to be regulatory requirements. This document may be revised with additional information as ARP4754B/ED-79B is put into practice.
S-18 Aircraft and Sys Dev and Safety Assessment Committee
Identification and Assessment of Damage to Composite Aircraft Structures Training DocumentAIR6825 (Current)6/10/2026
Individuals who complete the applicable modules aligned with this training document will be able to define the type of damage, define the extent of damage, determine if further inspection is required, evaluate the damage against published allowable damage limits, and provide accurate documentation of the damage. The intended outcome of the training is increased safety such that no aircraft is released with unknown damage and that the aircraft meets continued airworthiness requirements. The goal is to change the culture from damage discovery to damage reporting while also reducing or eliminating flight delays due to incorrect or insufficient information. Teaching levels have been assigned to the curriculum to define the knowledge, skills, and abilities graduates will need. Minimum hours of instruction have been provided to ensure adequate coverage of all subject matter including lecture and practical exercise. These minimums may be exceeded and may include an increase in the total number of training hours and/or increases in the teaching levels. The modules are intended to be a competency-based training approach. Each curriculum is a subpart of this document. Module 1 is the Composite Awareness curriculum, independent of the application. Module 2 is the Initial Inspection and Damage Mapping curriculum. Module 3 is the Special Inspection Tools curriculum. Module 4 is the Reporting, Recording, and Assessment curriculum. NOTE: While the modules in this document are technically interrelated, each module can be trained independently; modules may be selected as applicable to an operator’s or maintenance organization’s needs. The combination of the modules represents the applicable identification and assessment process for damage to composite aircraft structures (see Figure 1). Module 1 is prerequisite for attendance to the other modules. The contents of Module 1 may also be used for composite awareness training of a broader target audience, including line mechanics.
AMS CACRC Commercial Aircraft Composite Repair Committee
Aircraft Surface Coating Interaction with Aircraft Deicing/Anti-Icing FluidsAIR6232 (Current)6/10/2026
This SAE Aerospace Information Report (AIR) provides descriptions of test methods for determining if an aircraft surface coating of any thickness has adverse effects on aircraft deicing/anti-icing fluids with respect to fluid holdover time performance and aerodynamic performance. Although not the primary mandate of the G-12 Aircraft Ground Deicing Committee, this document also provides descriptions of suggested test methods for evaluating aircraft surface coatings with respect to durability, hardness, weathering, aerodynamic drag, ice adhesion, ice accumulation, contact angle, and thermal conductivity. These additional tests can provide informational data for characterizing the coatings and may be useful to operators when evaluating the coatings.
G-12ADF Aircraft Deicing Fluids
Conducting Measurement Systems Analysis for Rotor Balancing TasksAIR6966 (Current)6/10/2026
This AIR provides a general guideline on how to perform effective measurement systems analysis study (MSA) for rotor balancing tasks. The document also includes applicable data analysis methods and result interpretation.
EG-1A Balancing Committee
Aircraft Fuel System Design GuidelinesAIR7975A (Current)6/9/2026
This document describes the major design drivers and considerations when designing a fuel system for a large commercial aircraft. While not intended as a design manual for individual system components, it does refer out to other SAE specifications where more detail on specific components and subsystems is given. It does include examples of a number of calculations associated with sizing of fuel systems, based on those given in NAVAIR 06-5-504, as well as an appendix summarizing basic fluid mechanical equations that are key for fuel system design. It is acknowledged that most of these calculations would today be performed by modeling tools rather than by hand, but it is considered important for the designer to understand the principles. Some details specific to military aircraft are included, but it is intended that later issues of this document will include appendices that give specific considerations for military aircraft, smaller commercial aircraft, and rotorcraft. Features unique to these types of vehicle are generally not included in this issue.
AE-5A Aerospace Fuel, Inerting and Lubrication Sys Committee
Numerical Modeling Techniques for Jet Engine Test Cell AerodynamicsAIR6355 (Current)6/5/2026
This SAE Aerospace Information Report (AIR) has been written for individuals associated with ground level testing of turbofan and turbojet engines, and particularly for those who might be interested in investigating steady-state performance characteristics of a new test cell design or of proposed modifications to an existing test cell by means of numerical modeling and simulation. It is not the intent of this standard to provide specific test cell design recommendations, which are covered in the reference documentation.
EG-1E Gas Turbine Test Facilities and Equipment
A Guide to Aircraft Power Train MonitoringAIR4174B (Current)5/28/2026
The purpose of this SAE Aerospace Information Report (AIR) is to provide management, designers, and operators with information to assist them to decide what type of power train monitoring they desire. This document is to provide assistance in optimizing system complexity, performance, and cost effectiveness. This document covers all power train elements from the point at which energy in a turbine or electric engine is converted via a gear train to mechanical energy for propulsion purposes. The document covers aircraft engine driven transmission and gearbox components, their interfaces, drivetrain shafting, drive shaft hanger bearings, and associated rotating accessories, propellers, and rotor systems as shown in Figure 1. For guidance on monitoring additional engine components not addressed herein (e.g., main shaft bearings and compressor/turbine rotors), refer to ARP1839. This document addresses rotary and fixed wing applications for rotor, turboprop, turbofan, prop fan, and lift fan drive trains on both commercial and military aircraft. Information is provided to assist in: Defining technology maturity and application risk Cost benefit analysis (value analysis) Selection of system components Selection of technology Managing interface requirements Defining information flow requirements
E-32 Aerospace Propulsion Systems Health Management
Design Considerations for Enclosed Turboshaft Engine Test CellsAIR4989B (Current)5/28/2026
This SAE Aerospace Information Report (AIR) developed by a broad cross section of personnel from the aviation industry and government agencies is offered to provide state-of-the-art information for the use of individuals and organizations designing new or upgraded turboshaft engine test facilities. This document is also applicable to turboprop engines tested with a dynamometer as load absorption device, as they are basically tested as turboshaft engines. For propeller-equipped turbofan testing facilities design considerations, see 2.1.7.
EG-1E Gas Turbine Test Facilities and Equipment
Guide to Engine Lubrication System MonitoringAIR1828D (Current)5/15/2026
This SAE Aerospace Information Report (AIR) provides information and guidance for the selection and use of technologies and methods for lubrication system monitoring of gas turbine aircraft engines. This AIR describes technologies and methods covering oil system performance monitoring, oil debris monitoring, and oil condition monitoring. Both on-aircraft and off-aircraft applications are presented. A higher-level view of lubrication system monitoring as part of an overall engine monitoring system (EMS) is discussed in ARP1587. The scope of this document is limited to those lubrication system monitoring, inspection, and analysis methods and devices that can be considered appropriate for health monitoring and routine maintenance. This AIR is intended to be used as a technical guide. It is not intended to be used as a legal document or standard.
E-32 Aerospace Propulsion Systems Health Management
Constructing a Development Assurance Plan for Integrated SystemsAIR6218A (Current)5/15/2026
This SAE Aerospace Information Report (AIR) supplements ARP4754B/ED-79B by identifying the crucial elements to be considered when constructing the development assurance plans described in Section 3 (Development Assurance Planning) of ARP4754B/ED-79B for integrated systems. Section 4.6.4 of ARP4754B/ED-79B expands the aircraft/system integration and verification activities by emphasizing testing during integration to investigate for unintended behaviors. However, guidelines are needed for planning that are specifically aimed at the aircraft level and at integrating across system functions and boundaries. Until such guidelines are more comprehensively provided, this AIR presents a collection of lessons learned from past certification programs involving integrated systems, and as such it may be considered in conjunction with Sections 3 and 4 of ARP4754B/ED-79B. ARP4761A/ED-135 elaborates the safety activities by adding processes and methods such as the Aircraft or System Functional Hazard Assessment (AFHA/SFHA) and Preliminary Aircraft or System Safety Assessment (PASA/PSSA). These safety activities can contribute to the overall plans for the integration phase of development at the aircraft or system level, including the identification of areas that could lead to cascading failures or unintended behaviors. This AIR is not guidance for system integration technologies.
S-18 Aircraft and Sys Dev and Safety Assessment Committee
Thermoelectric Circuits and the Performance of Several Aircraft Engine ThermocouplesAIR65A (Current)5/7/2026
E-32 Aerospace Propulsion Systems Health Management
Fire Prevention on Forestry MachineryJ1212_202605 (Current)5/7/2026
This document applies to off-road forestry work machines defined in SAE J1116 or ISO 6814.
MTC4, Forestry and Logging Equipment
Concurrent Design of Engines and Specifications of Starting Systems for HelicoptersAIR1296A (Current)4/25/2026
It is recommended that all helicopter engine development programs include an evaluation of engine starting requirements. The evaluation should include starting requirement effects on helicopter weight, cost, and mission effectiveness. The evaluation should be appropriate to the engine stage of development.
S-12 Powered Lift Propulsion Committee
Design and Handling Guide Radio Frequency Absorptive Type Wire and Cables (Filter Line, AS85485)AIR4465B (Current)4/24/2026
This document presents design and application information which will allow optimized utilization of filter line wire and cable purchased to AS85485. Filter line wire is defined and design information is presented. The electrical and mechanical performance characteristics of the wire, along with recommended harnessing methods and techniques, are also presented.
AE-8A Elec Wiring and Fiber Optic Interconnect Sys Install
Requirements for a COTS Assembly Management PlanEIA933D (Current)4/21/2026
This document applies to the development of Plans for integrating and managing COTS assemblies in electronic equipment and Systems for the commercial, military, and space markets, as well as other ADHP markets that wish to use this document. For purposes of this document, COTS assemblies are viewed as electronic assemblies such as printed wiring assemblies, disk drives, servers, printers, laptop computers, etc. There are many ways to categorize COTS assemblies1, including the following spectrum: At one end of the spectrum are COTS assemblies whose design, internal parts2, materials, configuration control, traceability, reliability, and qualification methods are at least partially controlled, or influenced, by ADHP customers (either individually or collectively) or by industry standards. An example at this end of the spectrum is a VME circuit card assembly. At the other end of the spectrum are COTS assemblies whose design, internal parts, materials, configuration control, and qualification methods are not controlled, or controllable, in any way by ADHP customers (either individually or collectively) or by industry standards. An example is a disk drive targeted for an industry other than ADHP use. It is critical for the Plan owner to: (1) review and understand the design, internal parts, materials, configuration control, reliability, and qualification methods of all “as-received” COTS assemblies and their capabilities with respect to their application in the intended System and environment; (2) identify risks; and where necessary (3) take additional action to mitigate the risks associated with the performance and reliability of the COTS assembly in the ADHP system.
APMC Avionics Process Management
Additional Guidance for Metal Powder Feedstock for Additive ManufacturingAIR7359 (Current)4/13/2026
This document is a collection of comments on topics relevant to AMS powder feedstock production and procurement. In some instances, it provides explanation of characteristics not controlled in AMS-AM powder feedstock specifications and the rationale for exclusion (e.g., limitation of applicability or maturity of standardized inspection techniques). In other cases, it provides additional context on the reason for structuring requirements in AMS documents one way instead of other available options.
AMS AM Additive Manufacturing Metals
Artificial Intelligence in Ground Vehicles: Technical, Operational, and Regulatory ChallengesJ3329_202604 (Current)4/12/2026
This SAE Information Report identifies and documents the AI implementation challenges in the following areas: Technical Challenges (see Section 4): Focusing on the technical hurdles to develop AI models from data for complex human-like functions such as recognition, comprehension, and decision-making. Some AI technologies that do not necessarily involve learning from data, such as search algorithms, will not be considered. Operational Challenges (see Section 5): Focusing on the unique difficulties to deploy AI in ground vehicles and supporting infrastructure. These difficulties arise, for example, from issues like cost, environmental concerns, safety, security, etc. Regulatory Challenges (see Section 6): AI-related regulations are rapidly evolving. This section provides an overview of the key AI regulations at the present and some of the challenges to meet them in the ground vehicle domain. Where applicable, this technical report also provides references to AI-related International Standards (IS), Technical Reports (TR), Technical Specifications (TS), and Information Reports (IR) produced by the International Organization for Standardization (ISO), the Institute of Electrical and Electronics Engineers (IEEE), and SAE International (SAE) that address the challenges listed. For brevity, the authors of this report use the general term “Standards” to reference all the above types of documentation referenced. The full list of these standards is included in Section 2. In addition, the authors of this report are restricting the standard’s scope to only published documents and did not include any other type of literature due to space limitations and keeping the report focused. The functional definitions and noted issues and concerns are provided consistent with current industry mobility practices and published peer-reviewed literature. The mitigation examples in this document are not concepts that are necessarily independent of each other. Additionally, some mitigations can conflict with others. For the development of a project, an approach is to use systems engineering to design and implement mitigations, synergizing where possible and performing trade-offs where needed to achieve the system requirements (including applicable regulations and standards).
Artificial Intelligence
Integration and Certification Considerations for Electrified Propulsion AircraftAIR7128 (Current)4/8/2026
This document provides a comprehensive compilation of currently available practices, standards, regulations, and guidance material that have been considered relevant for developing an electrified propulsion system (independently or as part of an aircraft) and that may also help the applicants in the process of building their own certification approach with their Authority. It also covers unique considerations for electrified propulsion development and aircraft integration. It focuses on the particularities introduced by the new technology. This document is not intended to represent a proposed Means of Compliance (MoC) with any particular certification regulation.
E-40 Electrified Propulsion Committee
Arresting Cable Traversing Considerations for Landing GearAIR8619 (Current)4/2/2026
This SAE Aerospace Information Report (AIR) discusses the potential considerations for landing gear that may have to traverse arresting cables. This can be a consideration for civil aircraft and aircraft without arresting hooks that operate into dual use (military and civil) airfields.
A-5B Gears, Struts and Couplings Committee
Terminology and Measurement Methodology for Determining Vehicle Overlap in Offset-Frontal CrashesJ3227_202604 (Current)4/1/2026
This SAE Information Report establishes procedures and terminology for measuring, calculating, and referencing the percent vehicle overlap for a case vehicle in real-world or staged end plane collisions where the end plane of the case vehicle is engaged at one of the two bumper corners but not both. This SAE Information Report may be applied to rear or front plane impacts.
Crash Data Collection and Analysis Standards Committee
Adhesives, Sealants, and Heat Transfer Materials in Battery Systems: A Primer on Materials, Applications, and End-Use Performance RequirementsJ3178_202603 (Current)3/25/2026
This SAE Information Report introduces key concepts and properties of adhesives, sealants, and heat transfer materials (HTMs) and the roles they serve in present-day battery systems applications. The basic chemistry and properties of the three types of materials are summarized along with important health and environmental information. Relevant material dispense methodologies and equipment for material dispensing is reviewed. A series of representative battery applications examples employing adhesives, sealants, and HTMs is also provided with particular attention given to end-use performance.
Battery Pack Assembly Materials Committee
Heavy Vehicle Controls Prioritization and Conflict ResolutionJ3081_202603 (Current)3/25/2026
This document is written to address acceleration and deceleration control issues related to heavy-duty trucks and buses greater than 10000 GVW.
Truck and Bus Brake Systems Committee
Use Cases for Customer Communication for Plug-In Electric VehiclesJ2836/5_202603 (Current)3/18/2026
This SAE Information Report establishes the Use Cases for communications and customer-focused Key Performance Indicators (KPI) between plug-in electric vehicles (PEVs) and their customers. The Use Case Scenarios define the information to be communicated related to customer convenience features for charge on/off control, charge power curtailment, customer preference settings, charging status, electric vehicle supply equipment (EVSE) availability/access, and electricity usage, plus customer information resulting from conflicts to charging preferences. It also addresses the KPI that can provide a uniform set of metrics to quantitively assess the charging experience. This document only provides the Use Cases that define the communications requirements to enable customers to interact with the PEV and the KPI to optimize their experience with charging a PEV. Specifications such as protocols and physical transfer methods for communicating information are not within the scope of this document.
Hybrid - EV Committee
Oil Systems for Helicopter PowerplantsAIR4281A (Current)3/13/2026
Turbine engines installed in helicopters require a highly sophisticated oil system to fulfill two primary tasks: Cooling/oil supply Lubrication of rotating components (bearings, shafts, gears, etc.) While lubrication is an engine internal operation, depending on the engine oil system configuration, cooling and oil supply may require more or less design activity on the aircraft side of the engine/airframe interface for proper engine function. The necessity for engine cooling and oil supply provisions on the airframe can lead to interface problems because the helicopter manufacturer can influence engine related functions due to the design of corresponding oil system components.
S-12 Powered Lift Propulsion Committee
Thesaurus for Fuel System ComponentsAIR1615B (Current)3/12/2026
This document provides a summary of names commonly used throughout the industry for aircraft fuel system components. It is a thesaurus intended to aid those not familiar with the lexicon of the industry.
AE-5A Aerospace Fuel, Inerting and Lubrication Sys Committee
Vehicle Platform Power ManagementJ3311_202603 (Current)3/9/2026
This SAE Information Report is applicable to all types of automotive Electrical/Electronic (E/E) system architectures. It is important to develop a standard approach to commanding differentiable vehicle power policies from a centralized host Electronic Control Unit (ECU) location to applicable and capable ECUs and devices for maximum energy and thermal efficiency while creating and maintaining reuse across the ecosystem. Thus, adoption at a global level will enable efficiencies in product development and validation between all Original Equipment Manufacturers (OEMs) and the supply chain while maximizing reuse of ECUs and devices including respective power policies and capabilities between OEM vehicle systems. The definition of the Central System Power Manager (CSPM), VPPM Agent, Element Descriptor Tables, Element Descriptor Files, reference diagrams, and feature definitions are considered applicable and in scope for definition and standardization under SAE J3311. Software libraries and deployment, power state transition definition, vehicle network, protocol, component E/E topology/structure, electrical implementation schematics, and cybersecurity of transmission and storage of data are considered out of scope for definition and standardization under SAE J3311.
Vehicle Platform Power Management Committee
Assessment of the Inlet/Engine Total Temperature Distortion ProblemAIR5867A (Current)3/4/2026
This report revises ARD50015 document to the AIR format. This report, as was the original, is intended to complement ARP1420C and AIR1419C documents issued by the SAE S-16 Committee on spatial total-pressure distortion. These previous documents addressed only total-pressure distortion and excluded total temperature distortion. The subject of inlet total temperature distortion is addressed in this report with some background and identification of the problem area. The status of past efforts is reviewed, and an attempt is made to define where we are today. Deficiencies, voids, and limitations in knowledge and test techniques for total temperature distortion are identified.
S-16 Turbine Engine Inlet Flow Distortion Committee
Aircraft Tire Chine DesignAIR8776 (Current)3/4/2026
The purpose of this SAE Aerospace Information Report (AIR) is to present a sample of the range of tire chine designs approved for application on aircraft requiring non-standard water spray deflection.
A-5C Aircraft Tires Committee
Use of Models and Tools for Aircraft Systems Development - A Strategy for Development Assurance Aspects with ExamplesAIR6276 (Current)3/1/2026
The increased use of models in the development of complex aircraft and systems provides great opportunities and benefits, but also introduces some additional risks. The purpose of this document is to clarify ways to identify, prioritize, and mitigate risks associated with the use of models and tools in aircraft and system development. This document introduces considerations for the usage of models and tools in aircraft and system development activities that are defined in ARP4754/ED-79 (at latest revision). Throughout this document, a model refers to an abstract representation of a given set of aspects of a system/function/item, and a tool refers to an application or commercial product that is used for aircraft or system development activities such as developing, managing, and executing models, managing requirements validation and implementation verification activities and associated data, and automation of complex development tasks. The characteristics of models and tools and how they are applied differently for system-level development compared to item-level development are discussed. A discussion of several types of potential errors that can arise during the application of models and tools to system development is included as well. This is followed by proposed activities for managing the risks associated with the application of models and tools to system development. These suggestions start by identifying the contribution of models and tools to the decision-making process, and then understanding the impact of potential model and tool errors, leading to a discussion of potential process mitigations and methods for increasing the confidence in the application of models and tools to system development. NOTE: Unless otherwise stated, in the context of this document, the term “risk” is used to mean risks associated with potential errors that can be introduced in model and tool development and usage. System development activities that may employ models and tools include but are not limited to: Developing the system functions, architecture, and design Validating system functions and their requirements under normal and unusual conditions (extreme cases, tolerance stack-ups, failure insertion, etc.), which can help define additional requirements for features to constrain adverse operation Developing test procedures to be used in verifying the implemented system when it becomes available Analyzing the performance of a system against requirements over a range of inputs and conditions or combinations thereof to supplement the system verification Confirming the intended behavior of a system design using a validated model This document applies to models that are used for requirements analysis, design analysis, or to better understand and define requirements. Models that are used as the requirements are not discussed in this document, as in this case the ARP4754/ED-79 (at latest revision) Requirements Capture section and other associated sections provide the pertinent objectives and guidelines. This document does not describe the software or hardware development process or the direct verification of such items. It is assumed that these software or hardware processes, which may involve use of models, are handled by their respective guidance (e.g., DO-178C/ED-12C or DO-254/ED-80). This use of models is not described in this document, despite that it might involve system development processes in combination with software or hardware development processes. There is already a large and growing list of models and tools being applied in the development of complex systems, including computer aided design (CAD) tools for installation analysis, models and tools supporting system safety analysis, architectural models supporting various analyses, and tools used to simulate and analyze system performance or behavior. Two examples are presented to illustrate where models and tools are used to facilitate a set of typical system design decisions. The examples also identify model and tool errors, describe possible mitigation methods used to increase confidence in the use of models and tools in system development, and minimize the effect of errors that may be introduced by using the models and tools. The two examples are: An aircraft-level control law design targeted for software implementation on a digital computer, where a model is used for analysis of the control gains (referred to as the Roll Control System and described in Appendix A) An avionics network architecture where the tool analyzes the interfaces between the elements and identifies issues in the architecture (referred to as the Network Analysis Tool and described in Appendix B) The examples herein are not intended to be an exhaustive treatment of all considerations, but rather to demonstrate a set of principles and techniques that are generally applicable to the use of models and tools in system design. The Roll Control System and the Network Analysis Tool examples show how confidence in the models and tools can be established.
S-18 Aircraft and Sys Dev and Safety Assessment Committee
Analysis of Network V2X-Based Services and Opportunities for StandardizationJ3297_202602 (Current)2/25/2026
This report analyzes the characteristics of mobile network communication and highlights the technical aspects of using mobile networks to implement V2X applications. This report provides a high-level analysis of architecture, protocols, and performance and is intended to support future implementation guidance and standardization for providing V2X services over mobile networks, also referred to as network V2X.
V2X Core Technical Committee
Considerations and Guidelines to Extract Knowledge from Long-Term Archival DataAIR8479 (Current)2/24/2026
The scope of this document is to provide considerations, guidelines, and best practices for extracting knowledge from long-term archival data. The document is intended to cover the data generated across all life cycle stages of an aircraft starting from concept to disposal. This document does not standardize the process, nor does it allow regulatory authorities to recognize the document as an acceptable means of compliance. It is only a guideline document to discover, capture, store, retrieve, process, and consume knowledge.
G-31 Digital Transactions for Aerospace
BOSS - PLUG/PIN, EXPANSION TYPE HOLE PREPARATIONAIR3276A (Current)2/19/2026
E-25 General Standards for Aerospace and Propulsion Systems
Failure Modes for High-Lift Actuation Load PathsAIR7061 (Current)2/17/2026
This SAE Aerospace Information Report provides examples of single failure modes for components used in fixed-wing, high-lift actuation systems’ load paths, as well as the typical hazards posed by those failures at the aircraft level.
A-6B3 Electro-Mechanical Actuation Committee
Airport Electrical Power System HarmonicsAIR5387 (Current)2/17/2026
This SAE Aerospace Information Report (AIR) is intended to cover all airport 50 or 60 Hz electrical systems as well as all electrical utilization equipment that is attached to those systems.
AGE-3 Aircraft Ground Support Equipment Committee
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