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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 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
This document has been declared "CANCELLED" as of June 2017. By this action, this document will remain listed in the Numerical Section of the Aerospace Standards Index. Cancelled specifications are available from SAE
Nadcap Management Council
This document has been declared "CANCELLED" as of June 2017. By this action, this document will remain listed in the Numerical Section of the Aerospace Standards Index. Cancelled specifications are available from SAE
Nadcap Management Council
ARP1834 provides general guidance for the selection, approach to, and performance of various kinds of F/FA of digital systems and equipment. Its prime objective is to present several industry-acceptable, cost-effective methods for identifying, analyzing, and documenting digital-equipment failure modes and their effects. The analysis techniques and considerations presented here are directed to digital-equipment hardware faults and failures exclusively. ARP1834 is not intended as an exhaustive treatment of the enormously complex process involved in the analytical failure evaluation of complete digital systems, nor as a universally applicable, definitive listing of the necessary and sufficient steps and actions for such evaluation. ARP4761 provides updated methods and processes for use on civil aircraft safety assessment. When analyzing these types of systems, ARP4761 should be used in lieu of this ARP. ARP1834 addresses the following areas of consideration in the preparation and
S-18 Aircraft and Sys Dev and Safety Assessment Committee
This SAE Aerospace Standard (MA) establishes the diameter-pitch combinations of ISO metric 60° screw threads recommended for use in the aerospace industry for metric module shaft or bearing retaining screw threads
E-25 General Standards for Aerospace and Propulsion Systems
No Scope available
Engine and Airframe Technical Standards Committee (TSC)
This SAE Aerospace Standard (AS) establishes uniform requirements and procedures for the fire testing of flexible hose assemblies and rigid tube assemblies (including coiled tubes) to be used in aircraft or aerospace vehicle fluid systems. These procedures may also be followed for fire tests on other piping components as specified by the customer. It also refers to standard fire test equipment to be used in conducting "referee" fire tests
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This document has been declared "CANCELLED" as of June 2017. By this action, this document will remain listed in the Numerical Section of the Aerospace Standards Index. Cancelled specifications are available from SAE
Nadcap Management Council
E-25 General Standards for Aerospace and Propulsion Systems
This SAE Aerospace Standard (AS) establishes requirements applicable to metal stock that is ordered and produced in accordance with an Aerospace Material Specification (AMS). Topics include producer requirements, distributor requirements, size and grain orientation nomenclature, and purchaser ordering information to distributors. Requirements of this document have been developed to address titanium and titanium alloys, aluminum and aluminum alloys, carbon and alloy steels, and corrosion and heat-resistant alloys
AMS G Titanium and Refractory Metals Committee
This procurement specification covers aircraft quality bolts and screws made from a low alloy, heat resistant steel of the type identified under the Unified Numbering System as UNS K14675. The following specification designations and their properties are covered
E-25 General Standards for Aerospace and Propulsion Systems
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
The Generic Open Architecture (GOA) Framework family of documents is organized into sets. This is the introductory document for those sets. The GOA family of documents is intended to support the development of affordable systems through the use of open systems concepts. The GOA family of documents is intended to provide input for the systems engineering process. The documents are applicable to the analysis of existing architectures as well as the development of new system architectures using open systems concepts. The domain specific documents catalog appropriate interface standards and, along with the domain independent documents, define a technical architecture for an associated specific domain. In other words, they provide the “rules and regulations” (i.e., the “building codes”) to be used during the systems engineering process when developing a system architecture for use in that domain. Each domain specific set of documents includes recommended interface standards, rationale for
AS-2 Embedded Computing Systems Committee
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
Electrolytically deposited chrome plate is the current standard surface treatment for landing gear component interface surfaces that require good wear resistance and corrosion protection. Chrome plated components are typically plagued by a slight debit in fatigue performance, detrimental mud cracking surface pattern, susceptibility to scoring, wear, and seal leakage. In addition, recent changes in environmental compliance standards place further restrictions on the use of electrolytically deposited chromium. Some commercial applications have already eliminated the use of chrome plate on current and future products. As a result, a substitute for electrolytically deposited chrome plate has been sought for several years. High Velocity Oxygenated Fuel (HVOF) thermal spray coatings have been developed to the point where they are being implemented as an alternative to hard chrome plate on high strength low alloy steels for external surfaces on landing gear applications. Some of the
A-5 Aerospace Landing Gear Systems Committee
The purpose of this recommended practice is to establish a general form which may be used as a guide in the preparation of detail specifications. This recommended practice shall not be used for procurement or be referred to in the detail specification
A-6C5 Components Committee
This specification covers one type of 5,000-pound capacity aircraft cargo tie down. The tie down is designated CGU-1/B and is furnished in a minimum length of 240 inches
AGE-2 Air Cargo
This specification prescribes general requirements for marking of aircraft ground support equipment and other vehicles (i.e., runway sweepers, firetrucks, refuelers, etc.), used on or near the flight line area with retro-reflective materials
AGE-3 Aircraft Ground Support Equipment Committee
This document defines cables that are used to provide electrical power for U.S. Department of Defense avionics support and test equipment
AGE-3 Aircraft Ground Support Equipment Committee
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