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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 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 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 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 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 SAE Recommended Practice is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances. This document provides standardized laboratory tests, test methods and equipment, and requirements for lighting devices covered by SAE Recommended Practices and Standards. It is intended for devices used on vehicles less than 2032 mm in width. Tests for vehicles larger than 2032 mm in overall width are covered in SAE J2139. Device specific tests and requirements can be found in applicable SAE technical reports
Test Methods and Equipment Stds Committee
SAE J3072 establishes requirements for a grid support inverter system function that is integrated into a plug-in electric vehicle (PEV), which connects in parallel with an electric power system (EPS) by way of conductively coupled, electric vehicle supply equipment (EVSE). This standard also defines the communication between the PEV and the EVSE required for the PEV onboard inverter function to be configured and authorized by the EVSE for discharging at a site. The requirements herein are intended to be used in conjunction with IEEE 1547-2018 and IEEE 1547.1-2020 or later versions
Hybrid - EV Committee
This standard specifies the communications hardware and software requirements for fueling hydrogen surface vehicles (HSV), such as fuel cell vehicles, but may also be used where appropriate with heavy-duty vehicles (e.g., buses) and industrial trucks (e.g., forklifts) with compressed hydrogen storage. It contains a description of the communications hardware and communications protocol that may be used to refuel the HSV. The intent of this standard is to enable harmonized development and implementation of the hydrogen fueling interfaces. This standard is intended to be used in conjunction with the hydrogen fueling protocols in SAE J2601 and nozzles and receptacles conforming with SAE J2600
Fuel Cell Standards Committee
This specification covers a corrosion- and heat-resistant nickel alloy in the form of bars, forgings, flash-welded rings 10.0 inches (254 mm) and under in nominal diameter or distance between parallel sides, and stock of any size for forging, flash-welded rings, or heading
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers a corrosion- and heat-resistant, work-strengthened, and aged cobalt-nickel-chromium alloy in the form of bars 2 inches (50 mm) and under in nominal diameter
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers an aluminum alloy in the form of sheet 0.040 to 0.249 inches (1.02 to 6.32 mm), inclusive, in nominal thickness (see 8.5
AMS D Nonferrous Alloys Committee
This specification covers a corrosion- and heat-resistant nickel alloy in the form of sheet, strip, and foil 0.1874 inch (4.76 mm) and under in nominal thickness
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers procedures for marking bare wire for welding to provide positive identification of cut lengths, regardless of length, and of spools, and to ensure that the wire is clean and free from foreign materials and corrosion
AMS B Finishes Processes and Fluids Committee
This specification covers established manufacturing tolerances applicable to aluminum alloy drawn tubing ordered to inch/pound dimensions. These tolerances apply to all conditions, unless otherwise noted. The term "excl" applies only to the higher figure of the specified range
AMS D Nonferrous Alloys Committee
This specification covers a plasticized, polyether-type, urethane (EU) resin and hardener which, when mixed and cured, produces elastomeric polyurethane products
AMS P Polymeric Materials Committee
This specification has been declared "CANCELLED" by the Aerospace Materials Division, SAE, as of November 1995, and has been superseded by AMS 6440
AMS E Carbon and Low Alloy Steels Committee
This specification covers accelerated curing synthetic rubber compounds with corrosion inhibitors and low adhesive strength supplied as a two-component system
AMS G9 Aerospace Sealing Committee
This specification covers an aluminum alloy in the form of sheet
AMS D Nonferrous Alloys Committee
This specification covers one grade of glass-fiber-filled polytetrafluoroethylene (PTFE) in the form of molded billets
AMS P Polymeric Materials Committee
This specification covers a pearlitic malleable iron in the form of castings
AMS E Carbon and Low Alloy Steels Committee
This document is intended to supplement the SAE J1939 documents by offering the SAE J1939 information in a form that can be sorted and search for easier use
Truck Bus Control and Communications Network Committee
The purpose of this SAE Aerospace Information Report (AIR) is to provide guidance for aircraft engine and propeller systems (hereafter referred to as propulsion systems) certification for cybersecurity. Compliance for cybersecurity requires that the engine control, propeller control, monitoring system, and all auxiliary equipment systems and networks associated with the propulsion system (such as nacelle systems, overspeed governors, and thrust reversers) be protected from intentional unauthorized electronic interactions (IUEI) that may result in an adverse effect on the safety of the propulsion system or the airplane. This involves identification of security risks, their mitigation, verification of protections, and their maintenance in service. This document is intended to serve as suitable guidance for propulsion system manufacturers and applicants for propulsion system type certification. It is also intended to provide guidance for subsequent propulsion system integration into
E-36 Electronic Engine Controls Committee
This document provides general and specific design guidance for the development of software data loading equipment for all types of aircraft. The primary purpose of data load is to upload loadable software parts to airborne computers. A secondary function of data load is downloading data from airborne computers. Software data load functionality generally falls into the following categories: Portable Data Loader (PDL) for loading equipment on the ground or carried onto aircraft to perform onboard loading. Airborne Data Loader (ADL) for installation on aircraft to perform onboard loading. Data Load Function (DLF) is software that performs the data loading. This document defines data loaders designed to load avionics equipment over a high-speed interface using an Ethernet network protocol. This document defines media interfaces and protocol requirements specific to all data load functions, whether portable or airborne. This document also describes the desired capabilities of data loading
Airlines Electronic Engineering CommitteeAvionics Maintenance CommitteeFlight Simulator Engineering and Maintenance Committee
This AIR discusses the DC resistivity property of EMI gaskets
AE-4 Electromagnetic Compatibility (EMC) Committee
This specification has been "SUPERSEDED" by the Aerospace Materials Division, SAE, as of July, 1991
AMS CE Elastomers Committee
This Aerospace Standard covers two types of compensated altimeters which indicate, by visual means, the pressure altitude compensated for the static pressure system errors of the aircraft
A-4 Aircraft Instruments Committee
This specification covers the requirements for electrodeposited chromium plating
AMS B Finishes Processes and Fluids Committee
This Aerospace Information Report (AIR) will examine considerations relative to the use of mechanical switches on aircraft landing gear, and present "lessons learned" during the period that these devices have been used
A-5B Gears, Struts and Couplings Committee
This specification covers a corrosion-resistant steel in the form of two types of aircraft tubing
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers a silicone (VMQ) elastomer, reinforced with glass cloth, in the form of sheet
AMS CE Elastomers Committee
This specification has been "CANCELLED" by the Aerospace Materials Division, SAE, as of October 1996
AMS P Polymeric Materials Committee
This specification covers a titanium alloy in the form of round bar and wire, 0.625 inch (15.88 mm) and under in nominal diameter or thickness
AMS G Titanium and Refractory Metals Committee
This specification covers a magnesium alloy in the form of die forgings 3 inches (76 mm) and under in nominal thickness at time of heat treatment, hand forgings 6 inches (152 mm) and under in nominal thickness, and forging stock of any size (see 8.5
AMS D Nonferrous Alloys Committee
This SAE Standard specifies processes for the cleaning of metal surfaces to remove any extraneous or undesirable material or deposits at any stage of manufacture, storage or service and for the preparation of these surfaces for further treatment. Any necessary stress-relieving treatments are also included. This Standard does not override special preparatory procedures specified in individual Defence Standards, Defence Specifications, DTD Process Specifications, DG Ships Specifications and Naval Defence Standards. It also does not cover cleaning operations associated with the maintenance of internal combustion engines, the preliminary removal of heavy deposits of oil, grease, or dirt accumulated during operational service, preparations for welding and the cleaning of electrical contacts
AMS B Finishes Processes and Fluids Committee
This specification covers a precision cold rolled corrosion and heat resistant nickel alloy in the form of sheet and strip over 0.005 up to 0.015, inclusive, inch in nominal thickness and foil up to 0.005 inch, inclusive, in nominal thickness (see 8.5
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers a titanium alloy in the form of bars up through 4.000 inches (101.60 mm) in nominal diameter or least distance between parallel sides, inclusive, forgings of thickness up through 4.000 inches (101.60 mm), inclusive, and stock for forging of any size (see 8.6
AMS G Titanium and Refractory Metals Committee
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