Search
Advanced Search
of the following are true
(
)

Results

Items (219,613)
Aircraft Pressures and Temperatures – Resource DocumentAIR8471 (Current)
This SAE AIR covers Forced Air technology including: reference material, equipment, safety, operation, and methodology. It is intended to provide pressure and temperature (temps pages 26 & 31) information and minimum safety guidelines regarding use of equipment to remove frozen contaminants related to: i) Forced air ii) Forced air/fluid iii) Deicing fluid
G-12M Methods Committee
Aircraft Skin Pressures and TemperaturesAIR8469 (Current)
This information report covers all known aircraft with respect to deicing operations, especially with regard to OEM pressure and temperature limitations on the airframe. It provides data for airlines/operators on compliance with OEM limits and confirms that OEM limits are not exceeded during deicing operations.
G-12M Methods Committee
Missile Hydraulic Pumps and Their Power SourcesAIR560D (Current)
This AIR provides information about the specific requirements for missile hydraulic pumps and their associated power sources.
A-6C4 Power Sources 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
BOLT, MACHINE - DOUBLE HEXAGON EXTENDED WASHER HEAD, CLOSE TOLERANCE SHANK, AMS4967 (UNS R56400), 160 KSI, .2500-28 UNJF-3AAS3148C (Current)6/15/2026
SCOPE IS UNAVAILABLE
E-25 General Standards for Aerospace and Propulsion Systems
FITTING ASSEMBLY, REDUCER RING LOCKED PORT CONNECTION TO BEAM SEAL, 5000 PSI /8/AS4383F (Current)6/15/2026
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
Control Measures for Laser Safety in the Navigable AirspaceARP5572B (Current)6/15/2026
This SAE Aerospace Recommended Practice (ARP) provides information and guidance for the control of hazardous laser exposure in the navigable airspace. This ARP does not address techniques that pilots can apply to mitigate laser illuminations during a critical phase of flight. Such mitigation strategies are described in ARP6378.
G-10T Laser Safety Hazards Committee
Guide for Conducting an HIRF and Lightning Safety Assessment (HLSA)ARP8482 (Current)6/15/2026
Highly integrated electrical and electronic systems that perform functions within an aircraft may have potential failure conditions during and after exposure to the High-Intensity Radiated Fields (HIRF) or lightning environments. It is therefore necessary to conduct an HIRF and Lightning Safety Assessment (HLSA) that can identify potential failure conditions resulting from exposure to the aircraft HIRF and lightning environments. The failure conditions, failure conditions classifications, and independence principles identified by Aircraft Functional Hazard Assessment (AFHA), Preliminary Aircraft Safety Assessment (PASA), System Functional Hazard Assessment (SFHA), and Preliminary System Safety Assessment (PSSA), and lessons learned from previous experience, are used to identify proposed requirements during the development process. Ultimately, these requirements will result in a design capable of demonstrating that exposure to the HIRF and lightning environments will not result in
AE-4 Electromagnetic Compatibility (EMC) Committee
645-2 Secure Software Data LoadingARINC645-2 (Current)6/15/2026
The document explains why stronger cybersecurity is now essential in aircraft software distribution, especially for portable and airborne data loaders. As aircraft systems have become more interconnected, older loading methods - developed before modern security threats - are no longer sufficient. Software and data must be protected both while being transported and while stored, ensuring they are not altered, intercepted, or spoofed and that they come from a trusted source. It highlights that, historically, software was often moved through unsecured methods without protections such as digital signatures or certificate authentication, leaving the distribution chain vulnerable to tampering. Portable and airborne data loaders were identified as weak points in this process because they could receive and store software without verifying its integrity or authenticity. To address this, security standards such as ARINC 835 and ARINC 827 were introduced to harden these systems and protect the
Airlines Electronic Engineering Committee
702A-6 Advanced Flight Management Computer SystemARINC702A-6 (Current)6/15/2026
The Advanced FMCS provides expanded functions beyond that defined in ARINC 702 to support the anticipated requirements for operation in the CNS/ATM operating environment. GNSS and RNP based navigation, air-to-ground data link for communications and surveillance, and the associated crew interface control/display definitions are included. The NextGen/SESAR concepts and their relative effects on the FMS are addressed in this document. The functional requirements also apply to a Flight Management Function (FMF) in an Integrated Modular Avionics (IMA) architecture with software partitions.
Airlines Electronic Engineering Committee
BOLT, MACHINE - DOUBLE HEXAGON EXTENDED WASHER HEAD, CLOSE TOLERANCE SHANK, AMS4967 (UNS R56400), 1600 KSI, .3125-24 UNJF-3AAS3149C (Current)6/15/2026
E-25 General Standards for Aerospace and Propulsion Systems
FITTING, PORT PLUG AND BLEEDERAS5169E (Current)6/15/2026
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
BEARING, BALL, AIRFRAME, ANTIFRICTION, EXTERNAL SELF-ALIGNING, EXTRA LIGHT DUTY CORROSION-RESISTANT NITROGEN STEEL (CREN)AS27648/1A (Current)6/15/2026
ACBG Rolling Element Bearing 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
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
Hydraulic Filter Elements - Method for Evaluating Dynamic Efficiency with Cyclic FlowARP4205A (Current)6/15/2026
This SAE Aerospace Recommended Practice (ARP) describes a method for evaluating the performance of filter elements designed for aerospace hydraulic systems. The performance is measured and reported in terms of filtration ratios and stabilized contamination levels while testing with cyclic flow.
A-6C1 Fluids and Contamination Control Committee
NUT, SELF-LOCKING, PLATE, SIDE BY SIDE, REDUCED RIVET SPACING, LOW HEIGHT, UNS S66286, CLASS: 125 KSI/800 °FAS3482E (Current)6/12/2026
E-25 General Standards for Aerospace and Propulsion Systems
Delegated Product Release VerificationAS9117A (Current)6/12/2026
This standard specifies requirements for DPRV to establish common product/service requirements for use at all levels of the supply chain. This standard shall apply when an organization elects to delegate product release verification by contractual flow down to their supplier (reference 9100 and 9110 standards) to perform product acceptance on their behalf. The delegating organization shall use this standard as the baseline for establishing a DPRV process, although they may include additional contract requirements to meet their specific needs.
SAE Committee
NUT, SELF-LOCKING, EXTENDED DOUBLE HEXAGON, REDUCED FLANGE, DRY FILM LUBE, UNS S66286, CLASS: 160 KSI/800 °FAS3486E (Current)6/12/2026
E-25 General Standards for Aerospace and Propulsion Systems
NUT, SELF-LOCKING, SHANK, UNS S66286 SILVER PLATE ON THREAD ONLY, UNJ THREADAS3534B (Current)6/12/2026
E-25 General Standards for Aerospace and Propulsion Systems
BOLT, TEE HEAD - AMS5662, CHAMFERED, .3750-24 UNJF-3A (STRESS RUPTURE RESISTANT)AS3412C (Current)6/12/2026
E-25 General Standards for Aerospace and Propulsion Systems
Direct Delivery Authorization Guidance for Aerospace CompaniesAS9107 (Current)6/12/2026
Limited to the commercial aerospace industry where a request is made for a PO to have Direct Delivery Authorization (DDA), which includes an Appropriate Arrangement (AA) between the PO and the Design Organization (DO). In this process, the DO is responsible for ensuring the continuous updating of approved design data to the PO, whilst the PO is responsible for assurance that the manufactured article conforms to approved design data. The PO is responsible to provide airworthiness release documentation.
SAE Committee
Gland Design Criteria and Dimensions for Dynamic Radial O-Ring Seal Applications Specifically for Engine and Engine Control Systems Operating at 1500 psi MaxARP1233B (Current)6/12/2026
This document recommends standard gland design criteria and dimensions for dynamic radial O-ring seal applications specifically for engine and engine control systems operating at pressures up to a maximum of 1500 psi (10342.14 kPa) and provides recommendations for modifying these glands in special applications. There are no provisions in this document for anti-extrusion devices. NOTE: The criteria set forth here are similar to but not identical with those in MIL-G-5514 and AS4716. This document is not intended to replace MIL-G-5514 or AS4716 for hydraulic applications.
A-6C2 Seals Committee
NUT, SELF LOCKING, HEXAGON, REGULAR HEIGHT, UNS S66286, CLASS: 125 KSI/800 °FAS3483C (Current)6/12/2026
E-25 General Standards for Aerospace and Propulsion Systems
NUT, SELF-LOCKING, PLATE, ONE LUG, REDUCED RIVET SPACING, LOW HEIGHT, UNS S66286, CLASS: 125 KSI/800 °FAS3480E (Current)6/12/2026
E-25 General Standards for Aerospace and Propulsion Systems
NUT, SELF-LOCKING, PLATE, TWO LUG, LOW HEIGHT, UNS S66286, CLASS: 125 KSI/800 °FAS3478E (Current)6/12/2026
E-25 General Standards for Aerospace and Propulsion Systems
FITTING, TEE, PIPE, INTERNAL THREADAS4857B (Current)6/11/2026
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
UNION, SHORT FLARELESS TUBE FITTING, INTERNALLY SWAGEDAS5531A (Current)6/11/2026
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
COUPLING, MALE, 12 INCH AIR DUCTAS7365/3A (Current)6/11/2026
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
UNION, FLARELESS TUBE FITTING, INTERNALLY SWAGEDAS5530A (Current)6/11/2026
SCOPE IS UNAVAILABLE.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
COUPLING, FEMALE, 12 INCH AIR DUCTAS7365/2A (Current)6/11/2026
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
BAND, FEMALE COUPLING, 12 INCH AIR DUCTAS7365/6A (Current)6/11/2026
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
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
Tape, Nylon, LoopAMS3784B (Current)10/1/1995
This specification has been "CANCELLED" by the Aerospace Materials Division, SAE, as of October 1995.
AMS P Polymeric Materials Committee
TAPE, NYLON, LOOPAMS3784A (Current)1/1/1993
AMS P Polymeric Materials Committee
EPOXY RESIN, TETRAGLYCIDYL METHYLENEDIANILINE 14,000 TO 18,000 Centipoise ViscosityAMS3702A (Current)1/1/1993
AMS P Polymeric Materials Committee
CURING AGING, SOLID AROMATIC AMINE, 4,4’ - DIAMINODIPHENYL SULFONEAMS3099A (Current)10/1/1992
AMS P Polymeric Materials Committee
BOLT, MACHINE - DOUBLE HEXAGON EXTENDED WASHER HEAD, DRILLED, PD SHANK, UNS S66286, SILVER PLATED, .3750-24 UNJF-3AAS9577C (Current)6/8/2026
E-25 General Standards for Aerospace and Propulsion Systems
ALLOY SHEET AND STRIP, CORROSION AND HEAT RESISTANT 15Cr - 45Ni - 4W - 4Mo - 3Ti - 1Al Consumable Electrode Vacuum MeltedAMS5509 (Current)7/1/1981
AMS F Corrosion and Heat Resistant Alloys Committee
Alloy, Sheet, Strip, and Plate, 15cr 45ni 4w 4mo 3ti 1al Consumable Electrode Vacuum MeltedAMS5509A (Current)1/1/1992
This specification has been "CANCELLED" by the Aerospace Materials Division, SAE as of April, 1991.
AMS F Corrosion and Heat Resistant Alloys Committee
Low Speed Thorax Impact Test Procedure for the HIII 50th Male DummyJ2779_202206 (Current)6/29/2022
Dummy Testing and Equipment Committee
Automatic Transmissions - Schematic DiagramsJ647_202512 (Current)12/1/2025
The following schematic diagrams reflect various methods of illustrating automotive transmission arrangements. These have been developed to facilitate a clear understanding of the functional interrelations of the gearing, clutches, hydrodynamic drive unit, and other transmission components. Two variations of transmission diagrams are used: in neutral (clutches not applied) and in gear. For illustrative purposes, some typical transmissions are shown.
Automatic Transmission and Transaxle Committee
Software Supportability Program StandardJA1004_201205 (Current)5/6/2012
This SAE Standard defines the basic structural elements, and guidance on compilation and management, for a software supportability program. Software supportability considerations include initial design influence and through-life support embracing the operational use, post-delivery modification, and logistics management of software. This document requires that the processes of design, development, selection, and production of software include software supportability considerations, as relevant to particular project needs.
G-41 Reliability
Bolts and Screws-Steel Corrosion and Heat Resistant, Upset Headed, Heat Treated, Roll Threaded Solution and Precipitation Treated (Ams 5731)AMS7477D (Current)10/1/1993
AMS F Corrosion and Heat Resistant Alloys Committee
Guidelines for Testing and Support of Aerospace, Fiber Optic, Inter-Connect SystemsARP5061A (Current)8/16/2018
ARP5061A provides guidelines for optical performance testing of short haul fiber optic inter-connection systems used in aerospace vehicles. The focus of this document is to introduce the proper testing tools and establish common pre- and post-installation test methods and troubleshooting methodologies.
AS-3 Fiber Optics and Applied Photonics Committee
Quality Management Systems - Requirements for Aviation, Space, and Defense OrganizationsAS9100D (Current)9/20/2016
This standard includes ISO 9001:20152 quality management system requirements and specifies additional aviation, space, and defense industry requirements, definitions, and notes. It is emphasized that the requirements specified in this standard are complementary (not alternative) to customer and applicable statutory and regulatory requirements. If there is a conflict between the requirements of this standard and customer or applicable statutory or regulatory requirements, the latter shall take precedence. This International Standard specifies requirements for a quality management system when an organization: a needs to demonstrate its ability to consistently provide products and services that meet customer and applicable statutory and regulatory requirements, and b aims to enhance customer satisfaction through the effective application of the system, including processes for improvement of the system and the assurance of conformity to customer and applicable statutory and regulatory
G-14 Americas Aerospace Quality Standards Committee (AAQSC)
BLADE OR VANE - DIMENSIONING OF TURBINE ENGINE AIRFOILARP265 (Current)5/1/1996
E-25 General Standards for Aerospace and Propulsion Systems
J1979-DA, Digital Annex of E/E Diagnostic Test ModesJ1979DA_202508 (Current)5/27/2026
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
Epoxy Resin, Tetraglycidyl Methylenedianiline, 14,000 to 18,000 Centipoise ViscosityAMS3702B (Current)10/1/1995
This specification has been "CANCELLED" by the Aerospace Materials Division, SAE, as of October 1995.
AMS P17 Polymer Matrix Composites Committee
Curing Agent, Solid Aromatic Amine, 4, 4-Diaminodiphenyl SulfoneAMS3099B (Current)10/1/1995
This specification has been "CANCELLED" by the Aerospace Materials Division, SAE, as of October 1995.
AMS P Polymeric Materials Committee
Items per page:
1 – 50 of 219613