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This AIR provides information about the specific requirements for missile hydraulic pumps and their associated power sources.
AMS6885/1 gives information about the technical requirements and qualification procedure for unidirectional carbon fiber tape epoxy repair prepreg capable of curing under vacuum for repair of carbon fiber reinforced epoxy structures. The repair system includes an epoxy film adhesive to be applied in a co-bonding process with the prepreg for solid laminate and sandwich bonding.
This test method outlines the standard procedure for measuring the radial and axial internal clearance of rolling element bearings used in airframe controls.
This document describes the major design drivers and considerations when designing a fuel system for a large commercial aircraft. While not intended as a design manual for individual system components, it does refer out to other SAE specifications where more detail on specific components and subsystems is given. It does include examples of a number of calculations associated with sizing of fuel systems, based on those given in NAVAIR 06-5-504, as well as an appendix summarizing basic fluid mechanical equations that are key for fuel system design. It is acknowledged that most of these calculations would today be performed by modeling tools rather than by hand, but it is considered important for the designer to understand the principles. Some details specific to military aircraft are included, but it is intended that later issues of this document will include appendices that give specific considerations for military aircraft, smaller commercial aircraft, and rotorcraft. Features unique
SCOPE IS UNAVAILABLE.
This SAE Aerospace Recommended Practice (ARP) is intended to be used for laser systems mounted on aircraft and propagated into navigable airspace. This does not include lasers onboard aircraft where the beam is contained within an enclosure so that the beam cannot enter into airspace, nor does it include lasers from satellites and spacecraft in outer space. It may be used in conjunction with AS4970, ARP5535, ARP5572, ARP5293, and the ANSI Z136 laser safety standards.
This document and the EUROCAE equivalent, ED-107, provides detailed information, guidance, and methods in support of the Federal Aviation Administration (FAA) Advisory Circular (AC) 20-158 and to the European Union Aviation Safety Agency (EASA) AMC 20-158. AC 20-158 provides a means, but not the only means, for demonstrating compliance with Title 14 of the Code of Federal Regulations (14 CFR) 23.1308 (Amendment 57 and lower), 23.2520 (Amendment 64 and higher), 25.1317, 27.1317, 29.1317, and applicable FAA HIRF special conditions addressing HIRF Protection. AMC 20-158 is applicable to Certification Specifications CS 23.1308 (Amendment 4 and lower), 23.2520 (Amendment 5 and higher), 25.1317, 27.1317, and 29.1317. It should be noted that this document is neither mandatory nor regulatory in nature and does not constitute a regulation or legal interpretation of the regulation. Therefore, an applicant may elect to establish an alternative method of compliance that is acceptable to the
This specification covers the requirements for electrodeposited gold plate.
This specification covers a corrosion- and heat-resistant nickel alloy in the form of sheet, strip, and foil 0.100 inch (2.54 mm) and under in nominal thickness.
This specification covers a copper alloy in the form of strip (see 8.6).
This specification establishes the engineering requirements for the uphill quenching process of aluminum alloy product. Uphill quenching immerses product in liquid nitrogen followed by exposure to a high-pressure/high-velocity steam blast or boiling water.
This specification covers the properties of a mixed dimer.
This specification covers an aluminum alloy in the form of die forgings up to 4 inches in nominal thickness, hand forgings up to 8 inches in nominal thickness, rolled rings up to 3 inches in nominal thickness, and forging stock (see 8.6).
This specification covers a gloss, black baking enamel based on a glyceryl phthalate resin.
This specification covers an aluminum alloy in the form of two types of welding wire.
This specification covers an aluminum alloy in the form of seamless drawn tubing having nominal wall thickness of 0.018 to 0.500 inch (0.46 to 12.70 mm), inclusive (see 8.4).
This specification covers an aluminum alloy in the form of plate 0.250 to 1.500 inches (6.35 to 38.10 mm), inclusive, in nominal thickness (see 8.5).
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 extruded bars, rods, and profiles up to 0.499 inches (12.67 mm) in nominal diameter, or least thickness, and under 10 in2 (65 cm2) in cross-sectional area.
This specification covers an aluminum alloy in the form of wire, sheet, foil, pig, grains, shot, and chips (see 8.6).
This specification covers one type of organic (para-aramid) fiber in the form of yarn. The product shall be formed as a multiplicity of filaments drawn together and gathered into an approximately parallel arrangement.
This specification covers an aluminum alloy in the form of wire, sheet, foil, pig, grains, shot, and chips (see 8.6).
This specification covers an aluminum alloy in the form of die forgings and forging stock.
This specification covers one type of organic (para-aramid) fiber in the form of yarn. The product shall be formed as a multiplicity of filaments drawn together and gathered into an approximately parallel arrangement.
This specification covers an aluminum alloy in the form of bars, rods, and wire.
This specification covers an aluminum alloy in the form of sheet and plate with thickness from 0.008 to 4.000 inches (0.20 to 101.6 mm), inclusive, clad on two sides (see 8.6).
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