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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 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 a corrosion- and heat-resistant steel in the form of seamless tubing
AMS F Corrosion and Heat Resistant Alloys 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 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 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 standard specifies the characteristics of the MJ profile metric series of screw threads, altered from ISO 68 M Profile, to include a mandatory controlled radius of 0.18042P to 0.15011P at the root of the external thread and with the minor diameter of both external and internal threads increased to provide a basic thread height of 0.5625H in order to accommodate the external thread maximum root radius. The following detailed requirements are included: a MJ basic profile and design profiles b Standard series of diameter-pitch combinations for nominal thread diameters from 1.6 to 200 mm c Standard thread classes and form tolerances d Formulae for thread dimensions and tolerances e Method of designating MJ threads f Inspection requirement g Tables for selected diameter-pitch combinations for aerospace screws, bolts, nuts, shaft and bearing retaining screw threads, and fluid fittings thread sizes h Tables for MJ screw threads limiting dimensions and tolerances i Symbols for MJ thread
E-25 General Standards for Aerospace and Propulsion Systems
SAE Aerospace Recommended Practice ARP1533 is a procedure for the analysis and evaluation of the measured composition of the exhaust gas from aircraft engines. Measurements of carbon monoxide, carbon dioxide, total hydrocarbon, and the oxides of nitrogen are used to deduce emission indices, fuel-air ratio, combustion efficiency, and exhaust gas thermodynamic properties. The emission indices (EI) are the parameters of critical interest to the engine developers and the atmospheric emissions regulatory agencies because they relate engine performance to environmental impact. While this procedure is intended to guide the analysis and evaluation of the emissions from aircraft gas turbine engines (burning conventional hydrocarbon based liquid fuels), the methodology may be applied to the analysis of the exhaust products of any hydrocarbon/air combustor. Some successful applications include: Aircraft engine combustor development rig tests (aviation jet fueled) Stationary source combustor
E-31G Gaseous Committee
This document includes recommendations of installations of adequate landing and taxiing lighting systems in aircraft of the following categories: a Single engine personal and/or liaison type b Light twin engine c Large multiengine propeller d Large multiengine turbojet e Military high-performance fighter and attack f Helicopter g Electric Vertical Takeoff and Landing (EVTOL) and Urban Air Mobility (UAM
A-20B Exterior Lighting Committee
This AIR provides a detailed example of the aircraft and systems development for a function of a hypothetical S18 aircraft. In order to present a clear picture, an aircraft function was broken down into a single system. A function was chosen which had sufficient complexity to allow use of all the methodologies, yet was simple enough to present a clear picture of the flow through the process. This function/system was analyzed using the methods and tools described in ARP4754A/ED-79A. The aircraft level function is “Decelerate Aircraft On Ground” and the system is the braking system. The interaction of the braking system functions with the aircraft are identified with the relative importance based on implied aircraft interactions and system availabilities at the aircraft level. This example does not include validation and verification of the aircraft level hazards and interactions with the braking system. However, the principles used at the braking system level can be applied at the
S-18 Aircraft and Sys Dev and Safety Assessment Committee
This SAE Aerospace Standard (AS) is intended for use by those involved in the design of aircraft, missile, or space systems, and their support equipment to define the various types of fastener torque
E-25 General Standards for Aerospace and Propulsion Systems
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This document provides a recommended practice for determining decarburization and carburization in heat treated carbon and low-alloy steel parts other than case hardened parts. It is not applicable to raw materials
AMS B Finishes Processes and Fluids Committee
This specification establishes the requirements for self-locking wrenchable nuts with thread sizes 0.7500 thru 1.5000 inches. The nuts are made of corrosion and heat resistant precipitation hardenable iron base alloy of the type identified under the Unified Numbering System as UNS S66286 and of 160,000 psi axial tensile strength at room temperature, with maximum conditioning temperature of parts at 800 °F
E-25 General Standards for Aerospace and Propulsion Systems
This SAE Aerospace Information Report (AIR) is intended to provide guidelines to tightening methods and torque values as applied to electrical connectors, related hardware and switches, relays, circuit breakers, and A-A-59125 type terminal boards. The connectors and associated hardware discussed herein are typically manufactured from aluminum alloy, high-grade engineering thermoplastics, or corrosion-resistant steel, and typically plated with a protective/conductive coating. These guidelines may be used where no rules have been mandated either contractually or otherwise
AE-8C1 Connectors Committee
This Technical Governance is part of the SAE UCS Architecture Library and is primarily concerned with the UCS Architecture Model (AS6518) starting at Revision A and its user extensions. Users of the Model may extend it in accordance with AS6513 to meet the needs of their UCS Products. UCS Products include software components, software configurations and systems that provide or consume UCS services. For further information, refer to AS6513 Revision A or later. Technical Governance is part of the UCS Architecture Framework. This framework governs the UCS views expressed as Packages and Diagrams in the UCS Architecture Model
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Governance of the Unmanned Aircraft System (UAS) Control Segment (UCS) Architecture was transferred from the United States Office of the Secretary of Defense (OSD) to SAE International in April 2015. Consequently, a subset of the UCS Architecture Library Release 3.4(PR) has been published under SAE as the Unmanned Systems (UxS) Control Segment (UCS) Architecture, AS6512. This Version Description Document (VDD) describes the correspondence and differences between the two architecture libraries
AS-4UCS Unmanned Systems Control Segment Architecture
This document defines the requirements for weld fittings and machine weldments using an orbiting welding head suitable for use on cold worked 3AL-2.5V titanium, 21Cr-6Ni-9Mn CRES, and 718 nickel alloy tubing. Fitting standards covered by this specification include non-separable welded elbow, tee, and reducer fittings, and reconnectable 24-degree cone fittings, such as sleeves and unions
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This SAE Aerospace Information Report (AIR) provides methodologies and approaches that have been used to install and integrate full-authority-digital-engine-control (FADEC) systems on transport category aircraft. Although most of the information provided is based on turbofan/turboprop engines installed on large commercial transports, many of the issues raised are equally applicable to corporate, general aviation, regional, and commuter aircraft, and to military installations, particularly when commercial aircraft are employed by military users. The word “engine” is used to designate the aircraft propulsion system. The engine station designations used in this report are shown in Figures 1 to 3. Most of the material concerns an electronic engine control (EEC) with its associated software and its functional integration with the aircraft. However, the report also addresses the physical environment associated with the EEC and its associated wiring and sensors. Since most current transport
E-36 Electronic Engine Controls Committee
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
ARP4761A and its EUROCAE counterpart, ED-135, present guidelines for performing safety assessments of civil aircraft, systems, and equipment. They may be used when addressing compliance with certification requirements (e.g., 14 CFR/CS Parts 23, 25, 27, and 29 and 14 CFR Parts 33, 35, CS-E, and CS-P). ARP4761A/ED-135 may also be used to assist a company in meeting its own internal safety assessment standards. While the safety assessment processes described are primarily associated with civil aircraft, systems, and equipment, these processes may be used in many other applications. The guidelines herein identify a systematic safety assessment process, but other processes may be equally effective. The processes described herein are usually applicable to the new designs or to existing designs that are affected by changes to design or functions. In the case of the implementation of existing design(s) in a derivative application, complementary means such as service experience in a similar
S-18 Aircraft and Sys Dev and Safety Assessment Committee
AS95234 includes reverse bayonet coupling, high current electrical connectors that are watertight and principally used in shipboard, ground vehicles and ground support equipment applications at serve voltages from 200 to 3000 Vrms and temperatures between -55 °C and +125 °C (-67 °F and +257 °F). See 6.1.5 for applications details. For aerospace application connectors, refer to AS50881
AE-8C1 Connectors Committee
この文書は、供給者が9100の規定を遵守する場合の、AQAP-2110の適用に関する情報及びガイダンスを提供するために作成され、発行された。この文書は、AQAP-2110-SRD.2及びIA9137として発行されている。この文書は、NATO及び業界によるAQAP-2110及び9100の関係の理解及び利用を容易にするために、NATO及び業界の代表者が協同で策定した。AQAPは、調達国が対外有償軍事援助(FMS)を調達手段として利用する場合に、必要となる場合がある。 この文書の目的は、調達者及びその9100供給者によるAQAP-2110要求事項の解釈の共通化に寄与することである。 この文書の内容は法的位置づけも契約上の位置づけも有せず、AQAP-2110の要求事項又は9100の要求事項のいずれに対しても取って代わるものでも、追加するものでも、削除するものでもない。 様々な状況が、作業、工程の種類、又は使用される機器、及び関わる要員のスキルのような要因に左右されて存在し得るため、このガイダンスは網羅的なものと見なされることも、また、契約書の要求事項を満たすための特定の手段や方法を義務付けるものと見なされることも望ましくない。ステークホルダーは、これらの要求事項を満たすために、他の手段や方法が使用され得ることを認識すべきである。 このガイダンスの利用者は、AQAP 2110要求事項が、契約書に引用されているとおり、供給者や二次供給者に義務付けられていることに留意することが望ましい
IAQG-1 Standards Committee
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