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This specification covers two types of refined hydrocarbon compounds in the form of liquids. This specification only covers newly manufactured materials.
This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
This specification covers a titanium alloy in the form of bars, wire, flash-welded rings 3.00 inches (76.2 mm) and under in nominal diameter or least distance between parallel sides and 16 square inches (103 cm2) and under in cross-sectional area, and stock of any size for flash-welded rings (see 8.6).
This specification covers an aluminum alloy in the form of permanent mold castings (see 8.6).
This specification covers an aluminum alloy in the form of sand, permanent mold, composite mold, and investment castings (see 8.6).
This specification covers a titanium alloy in the form of sheet, strip, and plate up through 4.000 inches (101.60 mm), inclusive (see 8.6).
This specification covers a cast tin bronze in the form of sealing rings (see 8.5).
This specification covers the requirements for electrodeposited zinc-nickel on metal parts, including fasteners and other standard parts.
This recommended practice covers the attachment of bonded anti-noise brake pad shims only. Mechanically attached shims (those without bonding) are not covered by this procedure.
This specification covers a tantalum alloy in the form of sheet, strip, and plate from 0.010 through 0.250 inch (0.25 through 6.35 mm), inclusive (see 8.5).
This SAE Aerospace Information Report (AIR) describes a method for assessing size dependent particle losses in a sampling and measurement system of specified geometry utilizing the non-volatile Particulate Matter (nvPM) mass and number concentrations measured at the end of the sampling system.1 The penetration functions of the sampling and measurement system may be determined either by measurement or by analytic computational methods. Loss mechanisms including thermophoretic (which has a very weak size dependence) and size dependent losses are considered in this method2 along with the uncertainties due to both measurement error and the assumptions of the method. The results of this system loss assessment allow development of estimated correction factors for nvPM mass and number concentrations to account for the system losses facilitating estimation of the nvPM mass and number at the engine exhaust nozzle exit plane. As the particle losses are size dependent, the magnitude of correction
This specification covers an aluminum alloy in the form of plate 4.001 to 7.000 inches (101.62 to 177.80 mm), inclusive, in nominal thickness (see 8.5).
This SAE Aerospace Recommended Practice (ARP) provides methods and guidelines for isolating dissimilar repair patch materials from carbon fiber reinforced plastic (herein also referred to as carbon composite) structure during a repair operation.
This specification covers a titanium alloy in the form of seamless tubing (see 8.7).
This SAE Aerospace Standard (AS) covers the general requirements for the design, manufacture, and test of 28 VDC, 270 VDC, and 115 VAC solid-state power controllers (SSPCs) for use in electrical power systems. SSPCs conforming to this standard are intended for use in controlling the making and breaking of power circuits for electrically operated equipment and devices, and for providing overload and short-circuit protection. Applications that require SSPCs to have a high level of performance in some areas or may be exposed to harsher electrical or environmental conditions are designated as CLASS A. Applications that utilize SSPCs in moderate level of performance or are exposed to a controlled environment are designated as CLASS C. Applicability of both MIL-STD-704 and RTCA DO-160G have been considered when determining the performance standards for the designated classes of SSPCs. To support older aircraft platforms, legacy versions of these specifications were also considered as
This document establishes the minimum requirements for an environmental test chamber and test procedures to carry out anti-icing performance tests according to the current materials specification for aircraft deicing/anti-icing fluids. The primary purpose for such a test method is to determine the anti-icing performance under controlled laboratory conditions of AMS1424 Type I and AMS1428 Type II, III, and IV fluids.
This specification covers an aluminum alloy in the form of die forgings and hand forgings up to 6.000 inches (152.40 mm) in nominal thickness at the time of heat treatment (see 8.6).
This specification covers an aluminum alloy in the form of sheet 0.011 to 0.126 inch (0.28 to 3.20 mm), inclusive, in nominal thickness, with a grain size of ASTM No. 6 or finer (see 8.5).
The scope of this report is to capture fundamental principles of selecting a wire size for an aerospace application using the method prescribed in AS50881 and additional calculations, not found in AS50881, to ensure the wire selection will adequately perform in the specific physical and environmental conditions. This report covers wire selection and sizing as part of the electrical wire interconnection systems (EWIS) used in aerospace vehicles. Aerospace vehicles include manned and unmanned airplanes, helicopters, lighter-than-air vehicles, missiles, and external pods. This document does not apply to wiring inside of airborne electronic equipment but shall apply to wiring externally attached to such equipment. Wire selection must consider physical and environmental factors to size wires such that they have sufficient mechanical strength, do not exceed allowable voltage drop levels, are protected by materials or circuit protection devices, and meet circuit current carrying requirements
This specification covers an aluminum alloy in the form of sheet and plate 0.020 to 0.499 inch (0.51 to 12.67 mm), inclusive, in nominal thickness alclad two sides (see 8.5).
This specification covers a corrosion- and heat-resistant nickel alloy in the form of bars, forgings, and flash-welded rings up to 4.00 inches (101.6 mm), exclusive, in least distance between parallel sides (thickness) or diameter, and stock of any size for forging or flash-welded rings.
This specification establishes a procedure for designating minimum elevated temperature tensile property requirements of castings by means of this AMS number and a series of dash numbers.
This specification covers one type of fluorescent magnetic particles in the form of a mixed, ready-to-use suspension in an odorless, inspection oil vehicle and packaged in aerosol cans.
This Recommended Practice provides a procedure to locate driver seat tracks, establish seat track length, and define the SgRP in Class B vehicles (heavy trucks and buses). Three sets of equations that describe where drivers position horizontally adjustable seats are available for use in Class B vehicles depending on the percentages of males to females in the expected driver population (50:50, 75:25, and 90:10 to 95:5). The equations can also be used as a checking tool to estimate the level of accommodation provided by a given length of horizontally adjustable seat track. These procedures are applicable for both the SAE J826 HPM and the SAE J4002 HPM-II.
This specification covers the engineering requirements for cadmium deposited on ferrous and nonferrous metals using a low hydrogen embrittlement (LHE) electroplating process.
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