This AS provides the minimum performance requirements for the following types of inflatable emergency evacuation devices (hereinafter referred to as device[s]): 1 Type I - Inflatable Slide: A device suitable for assisting occupants in descending from a floor-level airplane exit or from an airplane wing to the ground. A Type I off-wing slide is a device that does not include a ramp. 2 Type II - Inflatable Slide/Raft: A device suitable for assisting occupants in descending from a floor-level airplane exit or an airplane wing to the ground that is also designed to be used as a life raft. A Type II off-wing slide/raft is a device that does not include a ramp. 3 Type III - Inflatable Exit Ramp: A device suitable for assisting occupants in descending from certain overwing exits to an airplane wing. 4 Type IV - Inflatable Ramp/Slide: A device suitable for assisting occupants from an overwing exit or airplane wing to the ground. It is a combination ramp and wing-to-ground device. 5 Type VS-9A Safety Equipment and Survival Systems Committee
This specification establishes the requirements for flake or granular cetyl alcohol, solvents for dissolving the cetyl alcohol, preparation and application requirements for use of cetyl alcohol as an installation lubricant on mechanical fasteners, such as pins, bolts, nuts, washers, threaded or nonthreaded fastening devices, and inspection criteria for coated partsE-25 General Standards for Aerospace and Propulsion Systems
This specification covers a magnesium alloy in the form of sheet and plate from 0.016 to 3.000 inches (0.41 to 76.20 mm), inclusive, in thickness (see 8.5AMS D Nonferrous Alloys Committee
This specification covers a magnesium alloy in the form of extruded bars, rods, wire, tubing, and profiles up to 40 square inches (258 cm2) in cross-sectional area (solids) and up to 8.5 inches (216 mm) OD by 1.188 inches (30.18 mm) wall thickness (tubing) (see 8.5AMS D Nonferrous Alloys Committee
This specification covers a corrosion-resistant steel in the form of bars, wire, forgings, and forging stockAMS F Corrosion and Heat Resistant Alloys Committee
This specification covers unalloyed copper in the form of sheet, strip, and plate at least 0.015 inch (0.38 mm) in nominal thicknessAMS D Nonferrous Alloys Committee
This SAE Aerospace Information Report (AIR) describes the Architecture Framework for Unmanned Systems (AFUS). AFUS comprises a Conceptual View, a Capabilities View, and an Interoperability View. The Conceptual View provides definitions and background for key terms and concepts used in the unmanned systems domain. The Capabilities View uses terms and concepts from the Conceptual View to describe capabilities of unmanned systems and of other entities in the unmanned systems domain. The Interoperability View provides guidance on how to design and develop systems in a way that supports interoperabilityAS-4JAUS Joint Architecture for Unmanned Systems Committee
This SAE Standard establishes minimum requirements for lighting and marking earthmoving work machinery as defined in SAE J1116. It may be used as guidance for other types of machinery. Earthmoving work machines are normally operated off-highway. Therefore, this SAE document is not intended to be used as a basis for regulations by those having authority over on-highway motor vehiclesOPTC3, Lighting and Sound Committee
This SAE Standard was developed to provide a method for indicating the direction of engine rotation and numbering of engine cylinders. The document is intended for use in designing new engines to eliminate the differences which presently exist in industryEngine Power Test Code Committee
This SAE Standard establishes practices to: a Manage risk and ensure security of a cyber-physical system (CPS) throughout its life cycle by utilizing systems engineering principles; b Assess the impact of cyber-physical systems security (CPSS) objectives and requirements; c Assess the security risks to CPS technical effectiveness and functions, and address weaknesses and vulnerabilities; d Address various domains of consideration (see 3.1) that take into account operating conditions of the system, command and control, configuration management (refer to SAE EIA649), etc., that could negatively impact CPSS or CPS-designed purpose; e Perform design validation and verification to assess security and risk of the CPSG-32 Cyber Physical Systems Security Committee
This SAE Aerospace Information Report (AIR) focuses on opportunities, challenges, and requirements in use of blockchain for Unmanned Aircraft Systems (UAS) operating at and below 400 feet above ground level (AGL) for commercial use. UAS stakeholders like original equipment manufacturers (OEMs), suppliers, operators, owners, regulators, and maintenance repair and overhaul (MRO) providers face many challenges in certification, airspace management, operations, supply chain, and maintenance. Blockchain—defined as a distributed ledger technology that includes enterprise blockchain—can help address some of these challenges. Blockchain technology is evolving and also poses certain concerns in adoption. This AIR provides information on the current UAS challenges and how these challenges can be addressed by deploying blockchain technology along with identified areas of concern when using this technology. The scope of this AIR includes elicitation of key requirements for blockchain in UAS acrossG-31 Digital Transactions for Aerospace
The present Aerospace Recommended Practice specifies for airplane operator and tow vehicle manufacturers the basic testing requirements for towbarless tow vehicles to be used on the nose gear of conventional tricycle type landing gears of commercial civil transport aircraft with maximum ramp weight between 8600 kg (19 000 lb) and 50 000 kg (110 000 lb), commonly designated as “regional aircraft”. Its purpose is to achieve testing results, or equivalent computer modeling, demonstrating that the loads induced by the tow vehicle will not exceed the design loads of the airplane’s nose landing gear and associated structure, reduce the certified safe life limit of the nose landing gear, or otherwise compromise the airplane’s structural integrity and airworthiness certificationAGE-3 Aircraft Ground Support Equipment Committee
This drawing specifies parts ESC74-08, ESC74-10, ESC74-12, ESC74-14, ESC74-16, ESC74-18, ESC74-20, ESC74-22, ESC74-24, and ESC74-28. To view suppliers qualified to manufacture this part, visit https://ts200.sae-itc.orgEngine and Airframe Technical Standards Committee (TSC)
This technical specification document describes tests that certain parts may be required to meet. For example, this tech spec applies to ESC30. To view suppliers qualified against this standard, visit https://ts200.sae-itc.orgEngine and Airframe Technical Standards Committee (TSC)
This SAE Aerospace Information Report (AIR) provides an overview of EB technology as it applies to the aerospace fiber optic industry. Applicable personnel include: Managers Engineers Technicians Logisticians Trainers/Instructors Third Party Maintenance Agencies Quality AssuranceAS-3 Fiber Optics and Applied Photonics Committee
This drawing specifies parts ESC62-10 and ESC62-12. To view suppliers qualified to manufacture this part, visit https://ts200.sae-itc.orgEngine and Airframe Technical Standards Committee (TSC)
This standards gives the dimensional requirements for insert arrangements used in MIL-C-5015, MIL-C-22992 (Classes C, J, and R), and MIL-C-83723 (Series II) electrical connectorsAE-8C1 Connectors Committee
This SAE Recommended Practice was prepared to provide engineers, designers, and manufacturers of motor vehicles with a set of minimum performance requirements in order to assess the suitability of silicone and other low water tolerant type brake fluids (LWTFs) for use in motor vehicle brake systems. These fluids are designed for use in braking systems fitted with rubber cups and seals made from styrene-butadiene rubber (SBR), or a terpolymer of ethylene, propylene, and a diene (EPDM). In the development of the recommended requirements and test procedures contained herein, it is concluded that the LWTFs must be functionally compatible with braking systems designed for SAE J1703 and SAE J1704 fluids. To utilize LWTFs to the fullest advantage, they should not be mixed with other brake fluids. Inadvertent mixtures of LWTFs with fluids meeting SAE J1703 are not known to have any adverse effects on performance, but not all combinations have been tested. Vehicle manufacturer’s recommendationsBrake Fluids Standards Committee
This brief User Guide recaps the content of the AS6518B UCS Architectural Model. The purpose of the UCS Architecture Model is to provide the authoritative source for other models and products within the UCS Architecture as shown in the AS6512B UCS Architecture: Architecture DescriptionAS-4UCS Unmanned Systems Control Segment Architecture
This specification establishes process controls for the repeatable production of aerospace parts by Laser Powder Bed Fusion (L-PBF). It is intended to be used for aerospace parts manufactured using Additive Manufacturing (AM) metal alloys, but usage is not limited to such applicationsAMS AM Additive Manufacturing Metals
Today's sophisticated aircraft are required to effectively perform a variety of missions. With the advent of micro-miniaturization in electronics and advanced digital computers, a new generation of avionics equipment and systems can be utilized to increase the capabilities of the aircraft. As the quantity and variety of equipment and functions increases, the problems of inter-connecting these equipments with wires presents a constraint on size, weight, signal conditioning, reliability, maintainability and electromagnetic control. Conventional wiring has resulted in large bundles of wires and many connectors which adds excessive weight and reduces the space available for the pilot and other vital elements. This limitation can be relieved significantly by the application of well proven multiplexing techniquesAS-1A Avionic Networks Committee
This SAE Recommended Practice defines the information contained in the header and data fields of non-diagnostic messages for automotive serial communications based on SAE J1850 Class B networks. This document describes and specifies the header fields, data fields, field sizes, scaling, representations, and data positions used within messages. The general structure of a SAE J1850 message frame without in-frame response is shown in Figure 1. The structure of a SAE J1850 message with in-frame response is shown in Figure 2. Figures 1 and 2 also show the scope of frame fields defined by this document for non-diagnostic messages. Refer to SAE J1979 for specifications of emissions related diagnostic message header and data fields. Refer to SAE J2190 for the definition of other diagnostic data fields. The description of the network interface hardware, basic protocol definition, the electrical specifications, and the CRC byte are given in SAE J1850. SAE J1850 defines two and only two formats ofVehicle Architecture For Data Communications Standards
This SAE Recommended Practice defines the information contained in the header and data fields of non-diagnostic messages for automotive serial communications based on SAE J1850 Class B networks. This document describes and specifies the header fields, data fields, field sizes, scaling, representations, and data positions used within messages. The general structure of a SAE J1850 message frame without in-frame response is shown in Figure 1. The structure of a SAE J1850 message with in-frame response is shown in Figure 2. Figures 1 and 2 also show the scope of frame fields defined by this document for non-diagnostic messages. Refer to SAE J1979 for specifications of emissions related diagnostic message header and data fields. Refer to SAE J2190 for the definition of other diagnostic data fields. The description of the network interface hardware, basic protocol definition, electrical specifications, and the CRC byte is given in SAE J1850. SAE J1850 defines two and only two formats ofVehicle Architecture For Data Communications Standards
This document recommends display criteria for instrumentation on the flight deck of transport aircraft, taking account of human factors that affect engineering designS-7 Flight Deck Handling Qualities Stds for Trans Aircraft
The intent of this SAE Aerospace Information Report (AIR) is to inform the aerospace industry about various systems available to monitor the inflation pressure and/or temperature of an aircraft tire. The tire pressure monitoring system (TPMS), with cockpit display, is the most widely used of all aircraft tire monitoring systems, and is detailed in this document more than other systemsA-5C Aircraft Tires Committee
NOTE— SAE J2366-7LX—ITS Data Bus Application Message Layer Lexicon is now combined (as an appendix) with SAE J2366-7 to provide for a quicker revision process in the future. This SAE Surface Vehicle Recommended Practice defines an Application Message Layer, which may be used as part of a complete protocol stack with the other protocol layers in the SAE J2366 family. The Application Message Layer provides application message support for devices that are interconnected via a bus or network. Design of the messages and headers has stressed flexibility, expandability, economy (in terms of octets on the bus), and reusability. The Application Message Layer is independent of the underlying network used, and may be used on any network. Sections of this document make specific reference to the use of SAE J2366-7 with other layers of the SAE J2366 family of protocols, and may not apply when SAE J2366-7 is used with other networks. In addition, this document defines an audio arbitration scheme thatITS Council
This AIR discusses the use and application of EMC antennas and antenna factors. The relationships between antenna gain, antenna factor, power density (W/m2), and field strength (V/m) are discussed. Some examples of their use are given. Illustrations of commercially available EMC antennas commonly used in performing EMI measurements are included. In addition to the illustrations, the antenna factors, frequency ranges, typical uses (applications), and the manufacturers of these antennas are also listedAE-4 Electromagnetic Compatibility (EMC) Committee
This SAE Aerospace Recommended Practice (ARP) describes the recommended performance levels for equipment located on the aircraft exterior which produces radiant energy which will provide desired information when viewed with NVIS goggles. These performance intensities, normally stated in candelas for visible light, are modified to consider the goggle spectral response range. Where necessary, location of the equipment on the airplane is specified. The spectral emission characteristics may or may not include visible light. Whether or not visible energy is emitted, this document will refer to these items of equipment as "lightsA-20B Exterior Lighting Committee
This SAE Recommended Practice covers the recommended testing techniques for the determination of electric field immunity of an automotive electronic device. This technique uses a strip line{sup}1 from 10 kHz to 200 MHz and is limited to exposing the harnesses (and/or devices) which have a maximum height of equal to or less than 1/3 the strip line height. When J1113-23 was released in 1995, a note was included in the scope regarding the expected life of the document which stated: "This method is being replaced by the Tri-plate Line (SAE J1113-25) which is considered to be a superior method. It will be retained for historical purposes for a period of five years where upon it will be considered to be withdrawn." The committee decided in August 2001 to ballot this document for cancellationElectromagnetic Compatibility (EMC) Standards
This SAE Aerospace Information Report (AIR) has been prepared to provide information regarding options for optical control of fluid power actuation devices. It is not intended to establish standards for optical fluid power control, but rather is intended to provide a baseline or foundation from which standards can be developed. It presents and discusses approaches for command and communication with the actuation device via electro-optic means. The development of standards will require industry wide participation and cooperation to ensure interface commonality, reliability, and early reduction to practice. To facilitate such participation, this document provides potential users of the technology a balanced consensus on its present state of development, the prospects for demonstration of production readiness, and a discussion of problem areas within this technology. The intent is to inform the user/designer of the options available for interfacing photonics (optics) to hydraulic powerA-6A3 Flight Control and Vehicle Management Systems Cmt