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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
BOLT, MACHINE - DOUBLE HEXAGON EXTENDED WASHER HEAD, PD SHANK, CUP WASHER LOCKED, CRES, UNS S66286, 130 KSI MIN, .2500-28 UNJF-3AAS9677C (Current)7/17/2026
E-25 General Standards for Aerospace and Propulsion Systems
Procedure for Thermal Aging Test for Polyol Ester Gas Turbine Engine LubricantsARP6299A (Current)7/17/2026
This method is intended to evaluate the thermal and oxidative stability of synthetic, ester-based aviation lubricants under defined conditions of time and temperature. This method is applicable to lubricants meeting the compositional and performance requirements of AS5780.
E-34 Propulsion Lubricants Committee
J1979-DA, Digital Annex of E/E Diagnostic Test ModesJ1979DA_202607 (Current)7/16/2026
The SAE J1979 document set includes the communication between the vehicle's On-Board Diagnostic (OBD) systems and test equipment implemented across vehicles within the scope of regulated emissions and propulsion related OBD. The SAE J1979 Digital Annex supplements the J1979 base documents primarily by maintaining a global registry of regulated emissions and propulsion related data identifiers.
Vehicle E E System Diagnostic Standards Committee
Lighting, Aircraft Interior, Installation ofAS18276B (Current)7/16/2026
This specification covers the installation of aircraft interior lighting for military aircraft.
A-20C Interior Lighting
Manganese Alloy, Brazing Filler Metal 66Mn - 16Ni - 16Co - 0.80B 1770 to 1875 °F (966 to 1024 °C) Solidus-Liquidus RangeAMS4780J (Current)7/15/2026
This specification covers a manganese alloy in the form of powder, preforms, and a viscous mixture (paste) of the powder in a suitable binder.
AMS F Corrosion and Heat Resistant Alloys Committee
Hard Anodic Coating of Magnesium Alloys Alkaline Type, High VoltageAMS2467B (Current)7/15/2026
This specification establishes the procedures used to produce a hard anodic coating on magnesium alloys and the properties of the coating.
AMS B Finishes Processes and Fluids Committee
Steel, Corrosion-Resistant, Sheet, Strip, and Plate, 9.0Mn - 20Cr - 6.5Ni - 0.28N (21-6-9LC), Solution Heat TreatedAMS5595J (Current)7/15/2026
This specification covers a corrosion-resistant steel in the form of sheet, strip, and plate.
AMS F Corrosion and Heat Resistant Alloys Committee
Starter Battery Identification and ClassificationJ2981_202607 (Current)7/15/2026
This document provides recommendations to identify battery group sizes and dimensions for 6 V, 8 V, 12 V, and 24 V lead acid batteries.
Starter Battery Standards Committee
Physical Layer, 250 kbit/s, Twisted Shielded PairJ1939-11_202607 (Current)7/15/2026
This document defines a physical layer having a robust immunity to EMI and physical properties suitable for harsh environments. This document is suitable for CAN interfaces applying CAN HS (high-speed) transceivers as specified in ISO 11898-2. These SAE Recommended Practices are intended for light- and heavy-duty vehicles on- or off-road, as well as appropriate stationary applications which use vehicle derived components (e.g., generator sets). Vehicles of interest include, but are not limited to, on- and off-highway trucks and their trailers, construction equipment, and agricultural equipment and implements.
Truck and Bus Control and Communications Network Committee
Leaded Phosphor Bronze Strip, 88.5Cu - 4.0Sn - 4.0Pb - 3.0Zn - 0.26P, Cold Rolled, Half Hard (H02)AMS4520N (Current)6/8/2026
This specification covers a copper alloy in the form of strip (see 8.6).
AMS D Nonferrous Alloys Committee
709A-1 Precision Airborne Distance Measuring Equipment (DME/P)ARINC709A-1 (Current)8/17/1994
This standard provides general and specific design guidance for the development of a DME/P, which provides slant range distance from an aircraft to a selected DME ground facility. For landing purposes, the DME/P complements the angle MLS/ILS with precise range data.
Airlines Electronic Engineering Committee
717-15 Flight Data Acquisition and Recording SystemARINC717-15 (Current)6/6/2011
This document provides design guidance for the development and installation of a Digital Expandable Flight Data Acquisition and Recording System (DEFDARS) primarily intended for airline use. As such, this guidance will include specific requirements necessary to accommodate mandatory flight data recording and other flight data acquisition needs plus the requirements to ensure customer controlled interchangeability of equipment in a standard aircraft installation. The system capability was expanded to accommodate a data bus speed of 1024 words per second.
Airlines Electronic Engineering Committee
818-3 Avionics Digital Video Bus (ADVB) High Data RateARINC818-3 (Current)12/16/2019
ARINC 818 defines the digital video interface standard intended for use in all types of flight deck displays. This document represents the aviation version of ANSI Fibre Channel Audio Video (FC-AV) defined by ANSI INCITS 356-2002. Supplement 3 Supports the latest digital video rates of 12 Gbps and higher using 64B/66B encoding and 28 Gbps using 256B/257B encoding.
Airlines Electronic Engineering Committee
628 Part 4B - Cabin Equipment Interfaces (CEI), Part 4B, Cabin Management and Entertainment System - Cabin Distribution System (CDS) - Star WiringARINC628P4B (Current)6/18/1999
Cabin equipment interfaces Part 4B is similar to description provided for Part 4A. The significant difference is that Part 4B specifies a CDS using a star wiring topology. Standardized wiring, connectors and installation requirements for a passenger seat network, overhead video network, and cabin management equipment network are included. Electrical and fiber optic networks are covered.
Airlines Electronic Engineering Committee
628 Part 6 Cabin Equipment Interfaces (CEI) Part 6 Fiber Optic Cable Assembly General SpecificationARINC628P6 (Current)2/28/2002
ARINC Specification 628, Cabin Equipment Interfaces (CEI) Part 6 Fiber Optic Cable Assembly General Specification, defines the minimum acceptable provisions for connectorized fiber optic cable assemblies used in permanently installed airframe wire bundles that are part of ARINC 628 supported systems. The intent is for the cable assembly supplier to use this specification as a guideline to provide the prospective IFE contractor with cable assemblies that have adequate quality and performance for the intended application. These assemblies are suitable for cabin systems applications only. Applicable guidelines not found in this specification may be found in Section 9 of ARINC Specification 628 Part 4A.
Airlines Electronic Engineering Committee
653P5-1 Avionics Application Software Standard Interface, Part 5, Core Software Recommended CapabilitiesARINC653P5-1 (Current)8/7/2019
Part 5 defines additional ARINC 653 core software capabilities to ease integration on a variety of Integrated Modular Avionics (IMA) hardware platforms by allowing platform suppliers to extend and customize it for use with their unique hardware platform. Supplement 1 expands the guidance provided on resource profiling and execution profiling pertinent to the use of multicore processors in avionics.
Airlines Electronic Engineering Committee
VHF DIGITAL LINK (VDL) MODE 2 IMPLEMENTATION PROVISIONSARINC631-7 (Current)7/10/2017
This document describes the functions to be performed by airborne and ground components of the VDLM2 to successfully transfer messages from VHF ground networks to avionics systems on aircraft and vice versa where the data are encoded in a code and byte independent format. The compatibility of VDLM2 with OSI is established by defining a set of services and protocols that are in accordance with the OSI basic reference model. The compatibility with the ATN protocols is achieved by defining a set of interfaces between the VDLM2 subnetwork protocol specification and the Mobile Subnetwork Dependent Convergence Function (MSNDCF). The SNDCF is defined in the ICAO ATN SARPs.
Airlines Electronic Engineering Committee
666 - Electronic Distribution of SoftwareARINC666 (Current)5/1/2002
This document describes a secure internet facility for sending all types of aviation software using the world wide web (www). Software suppliers may use this document as a starting point for the construction of a secure web server utility. It provides sufficient flexibility and is compatible with numerous software distribution models. The file management structure is consistent with other ARINC standards for loadable software, and references ARINC 665 and ARINC 667 in particular.
Airlines Electronic Engineering Committee, Avionics Maintenance Committee
Flight Management Computer SystemARP1570 (Current)12/16/2002
The purpose of this document is to describe the recommendations of SAE Committee S-7 for a Flight Management Computer System (FMCS) capable of providing the functions and displays listed below to permit completion of a desired flight plan in an energy efficient and/or cost effective manner while meeting the requirements of Air Traffic Control. The recommendations of this document apply to transport aircraft and describe the operational objectives of the FMCS and related controls and displays.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Airplane Air Conditioning Engineering Data: ThermodynamicsAIR25 (Current)5/1/1990
AC-9 Aircraft Environmental Systems Committee
Aerospace Series Quality Management System Assessment for Maintenance Organizations (Based on ISO 9001:2000)AS9111A (Current)11/19/2012
G-14 Americas Aerospace Quality Standards Committee (AAQSC)
RESOLUTION OF INSERVICE ANOMALIES THROUGH ASAPPARINC640 (Current)9/30/1997
Defines a generalized process by which anomalies in aircraft systems can be detected. This process is intended to improve timely isolation and resolution of those anomalies. The objective is to reduce costs to the airlines, airframe manufacturers and aircraft systems suppliers by removing anomalous behavior from aircraft systems in a timely manner.
Avionics Maintenance Committee
664P1-2 Aircraft Data Network, Part 1, Systems Concepts and OverviewARINC664P1-2 (Current)6/20/2019
The purpose of this document is to provide an overview of data networking standards recommended for use in commercial aircraft installations. These standards provide a means to adapt commercially defined networking standards to an aircraft environment. It refers to devices such as bridges, switches, routers and hubs and their use in an aircraft environment. This equipment, when installed in a network topology, can optimize data transfer and overall avionics performance.
Airlines Electronic Engineering Committee
429P3-19 Mark 33 Digital Information Transfer System (DITS) - Part 3 - File Data Transfer TechniquesARINC429P3-19 (Current)6/25/2009
This standard defines the air transport industry's standards for the transfer of digital data between avionics system elements. Part 3 defines the data link layer protocol standards.
Airlines Electronic Engineering Committee
653P3Bc1 Avionics Application Software Standard Interface, Part 3B, Conformity Test Specifications for ARINC 653 Extended ServicesARINC653P3BC1 (Current)7/18/2019
ARINC 653, Part 3B is the Compliance Test Specification for ARINC 653 Extended Services presently defined in ARINC 653 Part 2. The document specifies a set of stimuli and the expected responses. Future work on the ARINC 653 document set includes an effort to define Operating System services for multi-core processor environments. The Compliance Test Specification is expected to be updated in step with ARINC 653, Part 2.
Airlines Electronic Engineering Committee
HANDLE - PROPELLER SHAFT WRENCHAS353A (Current)12/5/2012
AGE-2 Air Cargo
626-3 Standard ATLAS Language for Modular TestARINC626-3 (Current)1/1/1995
This standard defines an airline-recommended subset of the Abbreviated Test Language for All Systems (ATLAS)intended to be used in conjunction with test systems that are compliant with ARINC 608A. ATLAS is a standard abbreviated English language used in preparation and documentation of test procedures that can be implemented with automatic or semiautomatic test equipment.
Airlines Electronic Engineering Committee, Avionics Maintenance Committee
591 Quick Access Recorder for AIDS System (QAR)ARINC591 (Current)7/1/1972
This standard provides design guidance for development and installation of a QAR, whose basic functions are to store digital data supplied at the output of an ARINC 573 FDAU or other similar acquisition unit and provide an easy access to this stored data for systematic ground processing for performance monitoring, maintenance monitoring or other purposes.
Airlines Electronic Engineering Committee
Environmental Conditions Applicable to Transport Aircraft Electrical EquipmentAIR31 (Current)12/16/2002
AE-7P Protective and Control Devices
Thermophysical Properties of the Natural Environment, Gases, Liquids, and SolidsAIR1168/9A (Current)7/25/2011
This AIR is arranged in the following four sections: 2A - Properties of the Natural Environment 2B - Properties of Gases 2C - Properties of Liquids 2D - Properties of Solids A summary of each section is given below.
AC-9 Aircraft Environmental Systems Committee
Aluminum Alloy, Clad Two Sides Sheet, 0.6Mg - 0.35Si - 0.28Cu (No. 24 Brazing Sheet), As FabricatedAMS4460C (Current)4/30/2026
This specification covers an aluminum alloy in the form of sheet, clad on two sides.
AMS D Nonferrous Alloys Committee
Aluminum Alloy Castings, 7.0Si - 0.58Mg - 0.15Ti (E357.0-T6), Solution and Precipitation Heat TreatedAMS4288A (Current)6/15/2026
This specification covers an aluminum alloy in the form of castings (see 8.10).
AMS D Nonferrous Alloys Committee
COUPLING, MALE, 6 INCH AIR DUCTAS7365/5A (Current)6/23/2026
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
Inspection, Ultrasonic, of Thin Materials 0.50 Inch (12.7 mm) and Under in Cross-Sectional ThicknessAMS2632C (Current)6/2/2022
This specification covers the procedure for ultrasonic inspection of flat, contoured, round, and hollow cylindrical products having a cross-sectional thickness of 0.02 to 0.50 inch (0.5 to 12.7 mm). This specification does not apply to inspection of composite materials.
AMS K Non Destructive Methods and Processes Committee
Aluminum Alloy, 7011 Alclad 7178 Plate and SheetAMSQQA250/28C (Current)2/14/2014
This specification covers the specific requirements for 7178 aluminum alloy, 7011 alclad, plate and sheet; the general requirements are covered in AMS-QQ-A-250. The plate and sheet covered by this specification shall be an integral composite product consisting of a heat-treatable 7178 aluminum alloy core with thin layers of a 7011 aluminum alloy anodic to the core and of approximately equal thickness, bonded to both surfaces.
AMS D Nonferrous Alloys Committee
Rod Ends and Clevis PinsJ493_201302 (Current)2/25/2013
Fasteners Committee
CUSHION, LOOP CLAMP, MULTIPLE, 2-TUBE, AMS3303AS9393A (Current)10/13/2022
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
RING, LOCK, SERRATEDAS51990C (Current)2/10/2020
E-25 General Standards for Aerospace and Propulsion Systems
Minimum Design and Performance of Airplane Galley In-Flight Carts, Containers, and Associated ComponentsAS8056A (Current)10/16/2025
This SAE Aerospace Standard (AS) establishes minimum design and performance requirements for carts, containers, and associated components intended for installation in galleys and other areas of transport category airplanes. The requirements include establishing installation criteria for use by compartment designers and installers of the equipment.
S-9B Cabin Interiors and Furnishings Committee
Forward Collision Warning and Automatic Emergency Braking Test Procedure and Minimum Performance Requirements - Truck and BusJ3029_202301 (Current)1/17/2023
This SAE Recommended Practice (RP) establishes uniform powered vehicle-level test procedure for forward collision warning (FCW) and automatic emergency braking (AEB) used in trucks and buses greater than 10000 pounds (4535 kg) GVWR equipped with pneumatic brake systems for detecting, warning, and avoiding potential collisions. This RP does not apply to electric powered vehicles, trailers, dollies, etc., and does not intend to exclude any particular system or sensor technology. These FCW/AEB systems utilize various methodologies to identify, track, and communicate data/information to the operator and vehicle systems to warn, intervene, and/or mitigate in the momentary longitudinal control of the vehicle. This specification will test the functionality of the FCW/AEB (e.g., ability to detect objects in front of the vehicle), its ability to indicate FCW/AEB engagement and disengagement, the ability of the FCW/AEB to notify the human machine interface (HMI) or vehicle control system that an
Truck and Bus Automation Safety Committee
CONNECTOR RECEPTACLE, BAYONET COUPLING, IN LINEAS95234/1A (Current)11/6/2023
AE-8C1 Connectors Committee
Landing Gear System Development PlanARP1598D (Current)4/24/2025
A-5 Aerospace Landing Gear Systems Committee
Event Data RecorderJ1698_202303 (Current)3/1/2023
This SAE Recommended Practice describes common definitions and operational elements of Event Data Recorders. The SAE J1698 series of documents consists of the following: SAE J1698-1 - Event Data Recorder - Output Data Definition: Provides common data output formats and definitions for a variety of data elements that may be useful for analyzing vehicle crash and crash-like events that meet specified trigger criteria. SAE J1698-2 - Event Data Recorder - Retrieval Tool Protocol: Utilizes existing industry standards to identify a common physical interface and define the protocols necessary to retrieve records stored by light duty vehicle Event Data Recorders (EDRs). SAE J1698-3 - Event Data Recorder - Compliance Assessment: Defines procedures that may be used to validate that relevant EDR output records conform with the reporting requirements specified in Part 563, Table 1 during the course of FMVSS-208, FMVSS-214, and other applicable vehicle level crash testing.
Event Data Recorder Committee
MALE FERRULE, THREADLESS-FLEXIBLE, FIXED CAVITY, CURRENT CARRYING, SELF BONDING, BUTT WELDEDAS5837 (Current)1/9/2013
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
Sealed Trailer Tow ConnectorJ3008_202307 (Current)7/19/2023
This SAE Standard provides the auxiliary requirements for automotive or RV, additional 12 position, sealed Trailer Tow Connector Plug and Receptacle. The information included within this specification is intended to cover the test methods, design, and performance requirements of optional features for additional power, clean ground for electronic functions, video, data communication, and supplementary electric brake control.
Connector Systems Standards Committee
Motor Vehicle Driver and Passenger Head PositionJ1052_202307 (Current)7/19/2023
This SAE Standard describes head position contours and procedures for locating the contours in a vehicle. Head position contours are useful in establishing accommodation requirements for head space and are required for several measures defined in SAE J1100. Separate contours are defined depending on occupant seat location and the desired percentage (95 and 99) of occupant accommodation. This document is primarily focused on application to Class A vehicles (see SAE J1100), which include most personal-use vehicles (passenger cars, sport utility vehicles, pick-up trucks). A procedure for use in Class B vehicles can be found in Appendix B.
Human Accom and Design Devices Stds Comm
A Guide to Landing Gear System IntegrationAIR5451A (Current)9/8/2022
The landing gear system is a major and safety critical airframe system that needs to be integrated efficiently to meet the overall aircraft program goals of minimizing the penalties of weight, cost, dispatch reliability and maintenance. As the landing gear system business develops and large-scale teaming arrangements and acquisitions become increasingly common, it may be desirable in some instances to procure an Integrated Landing Gear System. This document provides guidelines and useful references for developing an integrated landing gear system for an aircraft. The document structure is divided into four sections: Landing Gear System Configuration Requirements (Section 3) Landing Gear System Functional Requirements (Section 4) Landing Gear System Integrity Requirements (Section 5) Landing Gear System Program Requirements (Section 6) The landing gear system encompasses all landing gear structural and subsystem elements. Structural elements include shock struts, truck beams, torsion
A-5 Aerospace Landing Gear Systems Committee
CONNECTORS, ELECTRICAL, RECTANGULAR, RECEPTACLE, CRIMP CONTACTS, (SINGLE INSERT, TYPE IV, CLASS 1, (−65 °C TO +125 °C), SERIES 2, SHELL DESIGNATOR A, FLOAT MOUNTING)AS81659/68B (Current)1/26/2022
AE-8C1 Connectors Committee
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