This procurement specification covers solid rivets and hollow end rivets made from a corrosion and heat resistant steel of the type identified under the Unified Numbering System as UNS S66286 and of 80 ksi single shear strength at room temperature.
This specification covers an aluminum alloy in the form of extruded bars, rods, and profiles 0.250 to 2.000 inches (6.35 to 50.80 mm) in nominal thickness and up to 32 square inches (206 cm2), inclusive, in cross-sectional area (see 8.5).
This specification covers an aluminum alloy in the form of extruded bars, rods, wire, profiles, and tubing, flash-welded rings fabricated from extruded stock, and stock for flash-welded rings (see 8.6).
This specification covers an aluminum alloy in the form of extruded bars, rods, wire, shapes, and tubing 5.000 inches (127.00 mm) and under in nominal diameter or least thickness (wall thickness of tubing) (see 8.5).
This specification covers a corrosion-resistant steel in the form of bars, wire, forgings, extrusions, mechanical tubing, flash-welded rings, and stock for forging, extruding, or flash-welded rings.
The J2012 Digital Annex of Diagnostic Trouble Code Definitions Spreadsheet provides DTC information in an excel format for use in your organization's work processes. The column headings include the same information as contained in the J2012 standard. Information in the excel spreadsheet will be updated several times annually and the spreadsheet includes a column heading denoting which DTCs have been updated in the current version.
This AIR is limited to the requirements of AS50881 and examines these requirements, providing rationale behind them. AS50881 is only applicable to the aircraft EWIS. Pods and other devices that can be attached to an aircraft are considered as part of the aircraft equipment design. Its scope does not include wiring inside of airborne electronic equipment but does apply to wiring externally attached to such equipment. The AS50881 scope does not include attached devices but does include the interface between the pod/equipment and aircraft wiring. Section 3.3.5 addresses components such as antennas and other similar equipment that were once supplied as Government Furnished Aeronautical/Aerospace Equipment (GFAE).
This specification covers a titanium alloy in the form of extruded bars, shapes, and flash-welded rings up through 3.000 inches (76.20 mm), inclusive, in nominal diameter or least distance between parallel sides, and stock for flash-welded rings of any size (see 8.7).
This specification provides requirements for the identification and packaging of sheet, strip, extrusions, and molded parts made of natural rubber, synthetic rubber, reclaimed rubber, and combinations of the above with other materials such as asbestos, cork, and fabrics. AMS2817 covers preferred requirements for identification and packaging of preformed packings.
This SAE Information Report relates to a special class of automotive adaptive equipment which consists of modifications to the power steering system provided as original equipment on personally licensed vehicles. These modifications are generically called “modified effort steering” or “reduced effort power steering.” The purpose of the modification is to alter the amount of driver effort required to steer the vehicle. Retention of reliability, ease of use for physically disabled drivers and maintainability are of primary concern. As an Information Report, the numerical values for performance measurements presented in this report and in the test procedure in the appendices, while based upon the best knowledge available at the time, have not been validated.
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.
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.
This SAE Aerospace Information Report (AIR) provides information and guidance for the selection and use of technologies and methods for lubrication system monitoring of gas turbine aircraft engines. This AIR describes technologies and methods covering oil system performance monitoring, oil debris monitoring, and oil condition monitoring. Both on-aircraft and off-aircraft applications are presented. A higher-level view of lubrication system monitoring as part of an overall engine monitoring system (EMS), is discussed in ARP1587. The scope of this document is limited to those lubrication system monitoring, inspection and analysis methods and devices that can be considered appropriate for health monitoring and routine maintenance. This AIR is intended to be used as a technical guide. It is not intended to be used as a legal document or standard.
This specification covers an aluminum alloy in the form of extruded bars, rods, wire, shapes, and tubing up to 5.000 inches, (127.00 mm), inclusive, in nominal diameter or least thickness (see 8.5).
This specification covers an aluminum alloy in the form of extruded bars, rods, wire, profiles, and tubing 5.000 inches (127.00 mm) and under in nominal diameter or thickness (wall thickness of tubing) and 32 square inches (206 cm2) and under in cross-sectional area (see 8.5).
This SAE Aerospace Information Report (AIR) provides information regarding guidance when utilizing an SHM system for “airworthiness credits”. This document is applicable to civil fixed-wing aerospace airframe structural applications where stakeholders are seeking guidance on the approvals of structural health monitoring (SHM) technologies for aircraft health management applications. While this initial guidance is from the United States’ Federal Aviation Administration (FAA), Technical Innovation Policy Branch, other regulatory agencies may elect to add requirements as needed. Future revisions to this document could include the guidance from other regulatory agencies. This document does not teach how to design an SHM function, how to do a safety or risk analysis, prescribe hardware or software assurance levels, or answer the question “how much mitigation and evidence are enough.”