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This AIR provides information about the specific requirements for missile hydraulic pumps and their associated power sources.
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
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 a copper alloy in the form of strip (see 8.6).
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 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
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This specification covers the requirements for silver deposited on metal parts with a copper strike between the basis metal and the silver deposit.
This specification covers requirements for producing brazed joints in parts fabricated from corrosion- and heat-resistant steels, carbon or low-alloy steels, or copper alloys, and the properties of such joints.
This specification establishes the requirements for chromate conversion coatings on magnesium alloys.
This specification covers the requirements for electrodeposited cadmium on metal parts.
This specification covers the requirements for a layer of electrodeposited silver followed by a layer of electrodeposited rhodium.
This specification covers a standard acrylonitrile butadiene (NBR-L) rubber stock with low acrylonitrile content in the form of molded test slabs.
This specification covers an aluminum alloy in the form of extruded or drawn welding wire.
This specification covers a silver alloy in the form of wire, rod, sheet, strip, foil, pig, powder, shot, and chips, and a viscous mixture (paste) of powder in a suitable binder.
This specification covers a titanium alloy in the form of sheet, strip, and plate up to 4.000 inches (101.60 mm), inclusive, in thickness (see 8.6).
This specification covers elemental copper in the form of powder (see 8.5).
This specification covers a nickel-aluminum-bronze alloy in the form of sand, centrifugal, and continuous castings (see 8.5).
This specification covers an aluminum bronze alloy in the form of centrifugal and continuous-cast castings (see 8.6).
This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, flash welded rings, and stock for forging or flash welded rings.
This SAE Aerospace Standard (AS) defines an involute with a 30° pressure angle and a full radius at the roots thus reducing the stress concentration in the area of the root.
This specification covers a silver alloy in the form of wire, rod, sheet, strip, foil, pig, powder, shot, and chips and a viscous mixture (paste) of powder in a suitable binder.
This SAE AEROSPACE Standard (AS) covers all types of manually operated high pressure Oxygen line shut off valves utilizing either metallic or nonmetallic valve seats for use in general and commercial type aircraft.
This SAE Aerospace Standard (AS) applies to performance and testing of solid chemical oxygen generators which produce oxygen at essentially ambient pressure for use aboard aircraft whose cabin pressure altitude does not exceed 40,000 ft (about 12,200 m). Portable chemical oxygen devices are covered by AS1303.
This specification covers low-alloy steel springs made of annealed round wire heat treated after forming.
This specification covers a corrosion-resistant steel in the form of investment castings.
This specification covers a titanium alloy in the form of forgings up through 4.0 inches (102 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 forging (see 8.6).
This specification covers a polysulfide sealing compound with low adhesive strength, supplied as a two-component system that cures at room temperature.
The purpose of this SAE Aerospace Recommended Practice (ARP) is to provide the aerospace industry with recommendations concerning the minimization of stress corrosion cracking in wrought heat-treatable carbon and low-alloy steels and in austenitic, precipitation hardenable, and martensitic corrosion-resistant steels and alloys. The detailed recommendations are based on laboratory and field experience and reflect those design practices and fabrication procedures which should avoid in-service stress corrosion cracking.
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