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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 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 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 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 SAE Standard provides test procedures, requirements, and guidelines for stop lamps and turn signal lamps intended for use on vehicles 2032 mm or more in overall width. Stop lamps and front- and rear-turn signal lamps conforming to the requirements of this document may be used on vehicles less than 2032 mm in overall width.
This document provides recommended practices for the design and selection of tube, hose, and fitting systems that are used to transmit hydraulic fluid on aircraft. NOTE: Guidance for the sizing of hydraulic tubing is contained in Appendix A.
This SAE Aerospace Standard (AS) provides the essential minimum design, installation, and removal standard for AS5103 plugs and is applicable when specified on engineering drawing, or in procurement documents.
This specification covers one type of nylon tape.
This engineering design specification provides parameters and general requirements for auxiliary front lamps to be used on motorcycles.
This specification establishes the requirements for shielded, detachable high tension spark plug leads for reciprocating engines.
This procedure establishes the ignition system power supply design parameters for aeronautical engine ignition system testing.
The purpose of this SAE Information Report is to list and explain major equipment, instrumentation, and procedure variables which can affect inter-laboratory differences and repeatability of photometric measurements of various lighting devices listed in SAE Technical Reports. The accuracy guidelines listed in the report are for the purpose of controlling variables that are not a direct function of the lighting device being measured. The control of these individual variables is necessary to control the overall accuracy of photometric measurements. These accuracy guidelines apply to the measurement of the luminous intensities and reflected intensities of devices at the specified geometrically distributed test points and areas. These guidelines do not apply to photometric equipment used to measure license plate lamps.
AIR1608 ESTIMATION OF TOTAL ERROR IN ALTIMETRY proposes a method of estimating overall error of altimetry in order to provide a basis for safe vertical separation of aircraft.
This standard covers oronasal type masks which use a continuous flow oxygen supply. Each such mask comprises a facepiece with valves as required, a mask suspension device, a reservoir, or rebreather bag (when used), a length of tubing for connection to the oxygen supply source, and a means for allowing the crew to determine if oxygen is being delivered to the mask. The assembly shall be capable of being stowed suitably to meet the requirements of its intended use.
This SAE Recommended Practice provides test procedures, requirements, and guidelines for rear fog lamp systems.
This document provides a description of a process for development of fly-by-wire actuation systems. Included are (1) the development of requirements for the servo-actuator hardware and the electronics hardware and software, (2) actuator and servo-electronics interface definitions and, (3) the required communications and interactions between the servo-actuator and the servo-electronics designers.
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