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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
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 the requirements for electrodeposited gold plate.
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
SCOPE IS UNAVAILABLE.
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 a magnetically soft nickel-iron alloy in the form of bars, rods, forgings, mechanical tubing, and forging stock.
The following schematic diagrams reflect various methods of illustrating automotive transmission arrangements. These have been developed to facilitate a clear understanding of the functional interrelations of the gearing, clutches, hydrodynamic drive unit, and other transmission components. Two variations of transmission diagrams are used: in neutral (clutches not applied) and in gear. For illustrative purposes, some typical transmissions are shown.
This standard includes ISO 9001:20152 quality management system requirements and specifies additional aviation, space, and defense industry requirements, definitions, and notes. It is emphasized that the requirements specified in this standard are complementary (not alternative) to customer and applicable statutory and regulatory requirements. If there is a conflict between the requirements of this standard and customer or applicable statutory or regulatory requirements, the latter shall take precedence. This International Standard specifies requirements for a quality management system when an organization: a needs to demonstrate its ability to consistently provide products and services that meet customer and applicable statutory and regulatory requirements, and b aims to enhance customer satisfaction through the effective application of the system, including processes for improvement of the system and the assurance of conformity to customer and applicable statutory and regulatory
This specification covers a corrosion- and heat-resistant alloy in the form of sheet, strip, and plate.
This specification covers an acrylonitrile-butadiene (NBR) rubber in the form of molded rings, compression seals, O-ring cord, and molded-in-place gaskets for aeronautical and aerospace applications. For sheet, strip, tubing, extrusions, and molded shapes, use the AMS3XXX specification which is intended for that use.
This specification covers a corrosion- and heat-resistant cobalt alloy in the form of strip up to 0.100-inch (2.54-mm) thick.
This specification covers flash-welded rings made of titanium and titanium alloys (see 8.5).
This specification covers a blend of tungsten carbide-cobalt aggregate, a nickel alloy, and a nickel aluminum aggregate in the form of powder.
This specification covers quality assurance sampling and testing procedures used to determine conformance to applicable material specification requirements of wrought corrosion- and heat-resistant steel and alloy products and of forging stock.
This document discusses the history and development of endurance requirements, provides an analysis of test contaminant material and includes a discussion of future requirements.
The scope of this SAE Aerospace Standard (AS) is to define the following dimensional requirements for double hexagon, hexagon head and tee headed bolts, and nuts with AS8879 UNJ inch series threads primarily for use in propulsion systems. Design requirements are based on UNJC threads for sizes 0.1640 and smaller and UNJF threads for sizes 0.1900 and larger.
This specification covers an optical-quality, transparent, polycarbonate plastic, to which a hard protective surface coating has been applied, supplied in the form of flat sheet or formed parts made from flat sheet.
This specification covers requirements for a coating consisting of finely powdered molybdenum disulfide in a heat-resistant inorganic binder applied to parts.
This specification covers the requirements for vacuum deposited cadmium.
This specification covers requirements for electrodeposited porous chromium plate.
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