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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 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 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.
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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 SAE Standard was developed to provide a method for indicating the direction of engine rotation and numbering of engine cylinders. The document is intended for use in designing new engines to eliminate the differences which presently exist in industry.
This standard establishes the common requirements for training of DPRV personnel for use at all levels of the aerospace engine supply chain. This standard shall apply when an organization elects to delegate product release verification by contractual flow down to its suppliers (reference 9100 and 9110 standards) and to perform product acceptance on its behalf. It is intended that organizations specify their DPRV requirements through the application of AS9117. While the delegating organization will use the AS13001 standard as the baseline for establishing DPRV process and product training, it may include additional contractual training requirements to meet its specific needs. The DPRV training material was primarily developed for aerospace engine supply chain requirements. However, this standard may also be used in other aerospace industry sectors where a DPRV process requiring specific training can be of benefit.
SAE JA1012 (“A Guide to the Reliability-Centered Maintenance (RCM) Standard”) amplifies and clarifies each of the key criteria listed in SAE JA1011 (“Evaluation Criteria for RCM Processes”), and summarizes additional issues that must be addressed in order to apply RCM successfully.
This Surface Vehicle & Aerospace Recommended Practice offers best practices and a methodology by which IVHM functionality relating to components and subsystems should be integrated into vehicle or platform level applications. The intent of the document is to provide practitioners with a structured methodology for specifying, characterizing and exposing the inherent IVHM functionality of a component or subsystem using a common functional reference model, i.e., through the exchange of design-time data and the application of standard vehicle data communications interfaces. This document includes best practices and guidance related to the specification of the information that must be exchanged between the functional layers in the IVHM system or between lower-level components/subsystems and the higher-level control system to enable health monitoring and tracking of system degradation severity. The intent is to provide an IVHM system that can robustly report the degradation of a given
This SAE Standard for reliability-centered maintenance (RCM) is intended for use by any organization that has or makes use of physical assets or systems that it wishes to manage responsibly.
The importance of reliability in design engineering has significantly grown since the early 1960’s. Competition has been a primary driver in this growth. The three realities of competition today are: world class quality and reliability, cost-effectiveness, and fast time-to-market. Formerly, companies could effectively compete if they could achieve at least two of these features in their products and product development processes, often at the expense of the third. However, customers today, whether military, aerospace, or commercial, have been sensitized to a higher level of expectation and demand products that are highly reliable, yet affordable. Product development practices are shifting in response to this higher level of expectation. Today, there is seldom time, or necessary resources to extensively test, analyze, and fix to achieve high quality and reliability. It is also true that the rapid growth in technology prevents the accumulation of historical data on the field performance
This standard defines a color index system used by, but not limited to, Government activities in a format suitable for color identification, color selection, color matching, and quality control inspection. It also describes the designation and use of color media that is available to conduct these activities. Use of the color index referenced in this standard is intended to promote standardization and consistency in the color of items produced for Government use. Color media is described as follows: Color Chip Representation, Fan Deck: Suitable for color identification and selection. Color Chip Representation, Color Book: Suitable for color identification and selection. Precise Color Matching, Individual Color Chips: Suitable for color matching and quality control inspection purposes. Precise Color Matching, Set of Color Chips: Suitable for color matching and quality control inspection purposes.
This standard is applicable to all phases of the system acquisition life cycle. It is intended for use on all programs with manufacturing content. It requires proven manufacturing management practices with the goal of delivering affordable and capable systems to the extent that it is invoked contractually. The term “organization” as used in this document refers to the company or facility that is implementing this standard, such as when imposed contractually by the customer.
This SAE Aerospace Standard (AS) establishes supplemental requirements for 9100 and 9145 and applies to any organization receiving it as part of a purchase order or other contractual document from a customer. AS13100 also provides details of the reference materials (RM13xxx) developed by the SAE G-22 AESQ committee and listed in Section 2 that can also be used by organizations in conjunction with this standard.
This specification covers a corrosion-resistant steel in the form of wire.
This SAE Recommended Practice incorporates a track-based test procedure that produces a representative value for vehicle top speed when operating on a level paved road with a fully charged battery.
This SAE Standard defines a method for evaluating the immunity of automotive electrical/electronic devices to radiated electromagnetic fields coupled to the vehicle wiring harness. The method, called bulk current injection (BCI), uses a current probe to inject RF onto the wiring harness in the frequency range of 1 to 400 MHz. BCI is one of a number of test methods that can be used to simulate the electromagnetic field. The test method refers to ISO 11452-4 (please refer to ISO 11452-4 for test procedures). In addition to ISO 11452-4, this test method also includes a differential bulk current injection (DBCI) test. DBCI is described in Section 4 of this document.
This SAE Recommended Practice is intended for testing of manual slack adjusters as they are used in service, emergency, or parking brake systems for vehicles that can be licensed for on-road use.
This specification covers a corrosion-resistant steel in the form of sheet, strip, and plate.
This SAE Standard sets forth measurement procedures and instrumentation to be used for determining a “representative” sound level during a representative time period at selected measurement locations on a construction site boundary. The document is not intended for use in determining occupational hearing damage risk. Determination of a representative time period is left to the judgment of the user.
This specification covers a corrosion and heat-resistant iron-nickel alloy in the form of welding wire.
This specification covers a corrosion and heat-resistant steel in the form of welding wire.
This specification covers a palladium-silver alloy in the form of round wire 0.004 to 0.080 inch (0.10 to 2.03 mm) inclusive, in nominal diameter (see 8.5).
This specification covers a corrosion- and heat-resistant nickel alloy in the form of welding wire.
This specification covers a low-expansion iron-nickel-cobalt alloy in the form of wire.
This specification covers a magnetically soft nickel-iron alloy in the form of sheet and strip.
This specification covers a corrosion-resistant steel in the form of welding wire.
This specification covers a corrosion- and heat-resistant cobalt alloy in the form of bars, forgings, flash-welded rings, and stock for forging, flash-welded rings, or heading.
This specification covers a heat-resistant iron-nickel alloy in the form of bars, wire, forgings, flash welded rings. Product covered by this specification is limited to 8.0 inches (203 mm) and under in nominal diameter or maximum cross sectional dimension between parallel sides (thickness), and stock of any size for forging or flash welded rings.
This specification covers a corrosion and heat-resistant cobalt alloy in the form of covered welding electrodes.
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