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This specification covers a corrosion-resistant steel in the form of wire
AMS F Corrosion and Heat Resistant Alloys Committee
To provide specifications for lighting and marking of industrial wheeled equipment whenever such equipment is operated or traveling on a highway
OPTC3, Lighting and Sound Committee
This specification covers an aircraft-quality, low-alloy steel in the form of bars and forgings 1.50 inches or less in diameter or least distance between parallel sides (thickness
AMS E Carbon and Low Alloy Steels Committee
This specification covers a corrosion- and heat-resistant steel in the form of seamless tubing
AMS F Corrosion and Heat Resistant Alloys Committee
The following terminology has been generated by the ATA/IATA/SAE Commercial Aircraft Composite Repair Committee (CACRC) and provides terminology for design, fabrication, and repair of composite and bonded metal structures
AMS CACRC Commercial Aircraft Composite Repair Committee
This document has been prepared and issued to provide information and guidance on the application of AQAP 2110 when the Supplier adheres to the provisions of 9100. This document is published as AQAP 2009 Annex F and 9137. It was jointly developed by NATO and industry representatives for use by NATO and industry to facilitate the use and understanding of the relationship between the AQAP 2110 and 9100
G-14 Americas Aerospace Quality Standards Committee (AAQSC)
This SAE practice is intended for the sample preparation of test pieces for automotive wheels and wheel trim. The practice provides a consistent scribing method for use on test panels and or component parts with substrate chemical pretreatment and coating systems. Test specimens can then be subjected to various corrosion tests in order to evaluate performance without significant variations of the degree of exposure of the substrate. The scribing is used to create a break in the coating/finishing as can occur in the field through gravel and other damaging conditions. NOTE— Significant variability is attributed to surface contour, coating hardness/softness, operator reproducibility, and the scribing tool and it’s condition
Wheel Standards Committee
This SAE Aerospace Recommended Practice (ARP) provides guidance for the design of flanges on temperature sensors intended for use in gas turbine engines. Three figures detail the configuration of standard size flange mounts with bolt holes, slotted flanges, and miniaturized flanges for small probes
E-32 Aerospace Propulsion Systems Health Management
This SAE Aerospace Recommended Practice (ARP) defines the nomenclature of temperature measuring devices. General temperature measurement related terms are defined first, followed by nomenclature specifice to temperature measuring devices, particularly thermocouples
E-32 Aerospace Propulsion Systems Health Management
This Aerospace Recommended Practice (ARP) is a general overview of typical airborne engine vibration monitoring (EVM) systems applicable to fixed or rotary wing aircraft applications, with an emphasis on system design considerations. It describes EVM systems currently in use and future trends in EVM development. The broader scope of Health and Usage Monitoring Systems, (HUMS) is covered in SAE documents AS5391, AS5392, AS5393, AS5394, AS5395, AIR4174. This ARP also contains the essential elements of AS8054 which remain relevant and which have not been incorporated into Original Equipment Manufacturers (OEM) specifications
E-32 Aerospace Propulsion Systems Health Management
This specification covers a rust removing compound in the form of a solid, generally powdered, to be dissolved in water, and heated
AMS J Aircraft Maintenance Chemicals and Materials Committee
This SAE Aerospace Recommended Practice covers the recommended requirements for the lighting and characteristics of instruments; information plates and displays, emergency, cautionary, advisory and status displays; circuit breaker and toggle switch positions; and the recommended requirements for the utility lighting system
A-20A Crew Station Lighting
This SAE Aerospace Information Report (AIR) covers the design parameters for various methods of humidification applicable to aircraft, the physiological aspects of low humidities, the possible benefits of controlling cabin humidity, the penalties associated with humidification, and the problems which must be solved for practical aircraft humidification systems. The design information is applicable to commercial and military aircraft. The physiological aspects cover all aircraft environmental control applications
AC-9 Aircraft Environmental Systems Committee
This SAE Aerospace Recommended Practice (ARP) provides the criteria to be applied in order to determine compatibility with each other of an air cargo pallet and air cargo pallet net airworthiness approved under either NAS 3610 [TSO C90c] or AS36100A [TSO pending] performance and testing requirements
AGE-2 Air Cargo
The dedicated aircraft addressed herein is to be an uncompromised all-freighter aircraft developed primarily for use in the civil transport industry. The requirements of thsi document are applicable but not limited to airborne equipment which is subject to the airworthiness directives of FAR part 25 and which is designed to accmmodate unitized cargo in the form of intermodal containers and other compatible unitized load devices. Intermodability in the context of this document encompasses the air-truck-rail-sea modes, and considers uncertificated as well as certificated unit load devices (ULDs). This document covers the fundamental prerequisites for the aircraft cargo compartment and the onboard cargo handling and restraining system. The cargo system and compartment considers primarily 96 in (2.44 m) wide, multiple bottom configuration ULDs. The cargo system and compartment should handle outsize cargo and should consider Civil Reserve Air Fleet (CRAF) requirement compatibility. The
AGE-2 Air Cargo
This SAE Aerospace Recommended Practice (ARP) covers procedures for welding wire verification and conformance to specification composition
AMS B Finishes Processes and Fluids Committee
The scope of this ARP is to provide general requirements for application of electroluminescence to Aerospace Vehicle Crew Station Area instruments and control panels. The design brightness and color recommendations stated in this ARP are intended to apply where a crew station has multiple usage of electroluminescence in both instruments and control panels and when different manufacturers may be involved. These recommendations may also be helpful for the design of individually used displays incorporating electroluminescence, however, this light source has extensive design versatility through variance of manufacturing and operating parameters and the numerous acceptable design recommendations will not be stated herein. Electroluminescence will herein be referred to as EL
A-20A Crew Station Lighting
E-25 General Standards for Aerospace and Propulsion Systems
This document describes a hand-applied, nontank, phosphoric acid anodizing process for surface preparation of aluminum alloys required to achieve optimum bondline durability for structural adhesive bonding
AMS B Finishes Processes and Fluids Committee
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This SAE Aerospace Recommended Practice (ARP) defines the minimum across hexagon corner dimensions for fluid tube fittings and nuts. The ARP covers commonly specified inch and millimeter hexagon sizes
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This Aerospace Recommended Practice describes two performance acceptance test methods to determine the performance acceptability of new production and overhauled air turbine starters. Before a new or overhauled starter is delivered to a customer, the starter is subjected to a performance acceptance test in accordance with an acceptance test procedure. The performance acceptance test is intended to ensure that the customer receives a starter that meets or exceeds minimum starter performance requirements
AE-6 Starting Systems and Auxiliary Power Committee
This document establishes a test procedure for determining the propensity of aircraft turbine engine cleaning and maintenance materials for causing stress-corrosion cracking of titanium alloy parts. The evaluation is conducted on representative titanium alloys by determining the effect of contact with cleaning and maintenance materials on tendency of pre-stressed titanium alloys to crack when subsequently heated to elevated temperatures
AMS J Aircraft Maintenance Chemicals and Materials Committee
The methods and designs presented herein shall not be construed as being the only means of accomplishing these accommodations. This document applies to all transport category aircraft using features required by Department of Transportation Regulations CFR382. Passengers with ambulatory disabilities for whom provisions shall be made on each airplane type and location(s) for their seating are defined in 14CFR382. The goal is to provide cabin service comparable to that available to other travelers without jeopardizing the safety of fellow passengers. This necessitates consideration of physical, neurological and sensory capabilities, and limitations of mobility impaired persons. With proper consideration and design implementation, it will be possible to serve the needs of the majority of the disabled population
S-9B Cabin Interiors and Furnishings Committee
This SAE Aerospace Recommended Practice (ARP) is an application guide for hydraulic power transfer units and describes: The various types Typical design approaches Their operational characteristics and limitations Circuit recommendations Typical applications The scope of this ARP is limited to devices that transfer power between hydraulic systems and do so by means of rotary subassemblies such as hydraulic motors and pumps
A-6C4 Power Sources Committee
This document establishes the requirements for the sequencing of processes relating to parts fabricated from 300M or 4340 modified steel heat treated to, or to be heat treated to, 270,000 psi (1860 MPa) minimum ultimate tensile strength (UTS) and higher
AMS E Carbon and Low Alloy Steels Committee
The requirements of this SAE Aerospace Recommended Practice (ARP) are applicable to ground handling and transport systems equipment which is designated to accommodate main deck unitized cargo in the form of intermodal containers and other compatible unitized load devices. Intermodality in the context of this document concerns primarily air and land modes but does not exclude the marine mode. Equipment with compatibility features for other than main deck cargo is likewise not excluded. It is not the intent of this document to specify equipment design but rather to ensure interface compatibility of the various elements which might make up a total ground handling and transport system developed within a number of different operational schemes. It is the intent of this document to specify minimum ULD handling and restraint features to ensure future interchange capability
AGE-2 Air Cargo
This SAE Aerospace Recommended Practice (ARP) specifies requirements for those portions of the aircraft Unit Load Device ground and terminal handling equipment that will have a direct bearing on the life of the ULD for the purpose of preventing undue wear on the ULD. Past experience has shown that in-service defects in regard to the above equipment cause high ULD cost. Greater control of maintenance is required
AGE-2 Air Cargo
Verification of landing gear design strength is accomplished by dynamic and static test programs. This is essentially a verification of the analytical procedures used to design the gear. An industry survey was recently conducted to determine just what analysis and testing are currently being applied to landing gear. Timing in relation to first flight of new aircraft was also questioned. Opinions were solicited from designers of the following categories and/or types of aircraft: a. military - large land based (bomber); b. mililtary - small land based (fighter); c. military - carrier based (Navy); d. military - helicopter (large); e. military - helicopter (small-attack); f. commercial - large (airliner); g. commercial - small (business); and h. USAF (WPAFB) - recommendations. It is the objective of this AIR to present a summary of these responses. It is hoped that this summary will be useful to designers as a guide and/or check list in establishing criteria for landing gear analysis and
A-5B Gears, Struts and Couplings Committee
The Use Case Trace (UCTRACE) is SAE publication AIR6519 of the Department of Defense Unmanned Control Segment (UCS) Architecture. This document is the SAE publication of the Department of Defense UAS Control Segment (UCS) Architecture: Use Case Trace (UCTRACE) Version 3.4(PR) approved for Distribution A public release 15.S-1859. This information is produced from a script run against the System Use Case Model contained in the UCS Architecture Model AS6518-MODEL.eap configuration item. The System Use Case Model includes, at its lowest level of elaboration, use cases Level 2/3 (L2/L3) that describe specific scenarios of message exchanges between Actors and internal system Participants via ServiceInterfaces. These message exchanges provide a way to create detailed traces that answer the question: “What UCS service interfaces must my components implement to satisfy functional requirements represented by a given Level 2/3 UCS use case?” The AIR6519-UCTRACE spreadsheet contains trace
AS-4UCS Unmanned Systems Control Segment Architecture
This Handbook provides “how to” guidance to industry and government for the reliability Activities and Methods contained in GEIASTD0009 for developing reliable products and systems, successfully demonstrating them during test and evaluation, and sustaining them throughout the system/product life cycle. GEIASTD0009 requires the developers and customer/users working as a team to plan and implement a reliability program that provides systems/products that satisfy the user’s requirements and expectations using a systems engineering approach. The four Objectives of GEIASTD0009 are listed below: Objective 1: Understand customer/user requirements and constraints. The team (developer, customer, and user) includes the Activities necessary to ensure that the user’s requirements and product needs are fully understood and defined, so that a comprehensive design specification and Reliability program plan are generated. Objective 2: Design and redesign for reliability. The developer implements a set
G-41 Reliability
This SAE Aerospace Recommended Practice (ARP) is intended as a guide to aid in the specifying and testing of direct acting three way, two position, single and multiple coil, normally open and normally closed solenoid valves used for the pilot actuation of hydraulic control systems and the control of hydraulic components. The information presented should be useful in standardizing terminology, in specifying requirements and performance parameters, and in defining test methods. The recommendations do not restrict or attempt to define the internal design features of solenoid valves. Standard mechanical, electrical and fluid porting interfaces are recommended to provide commonalty, interchangeability, design flexibility and to be more affordable. In general, this recommended practice is directed toward solenoid valves for use in military and commercial flight control and hydraulic actuation systems. For military aircraft applications, this recommended practice covers solenoid valves for
A-6C5 Components Committee
This SAE Aerospace Recommended Practice (ARP) is applicable to any type of aerospace ground support vehicle, powered or unpowered
AGE-3 Aircraft Ground Support Equipment Committee
AE-7A Generators and Controls Motors and Magnetic Devices
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