Results
This SAE Standard establishes the test procedure, environment, and instrumentation for determining the sound levels of snowmobiles in the stationary test mode. This test method is intended to provide an accurate measurement of exhaust and other engine noise and may be used to evaluate new and in-use snowmobiles to determine compliance with noise control regulations. Sound level measurements obtained with this test method are not intended as an engineering determination of overall machine noise. For this purpose, the use of SAE J192 is recommended.
This SAE Aerospace Recommended Practice (ARP) outlines the functional and design requirements for a self-propelled belt conveyor for handling baggage and cargo at aircraft bulk cargo holds. Additional considerations and requirements may legally apply in other countries. As an example, for operation in Europe (EU and EFTA), the applicable EN standards shall be complied with.
This specification covers two types of thickened, water base temporary coating remover in the form of an alkaline liquid.
This Aerospace Standard (AS) 5659/4 Physical Layer Specification provides guidance for the physical layer of optical networks which use Wavelength Division Multiplexing (WDM), within the AS5659 WDM LAN specification document family. The physical layer consists of the optical interconnections between the functional components of the network. Performance requirements for general interconnections are described. For guidance, standards are identified, corresponding to each of several environments, which describe physical layer design, installation, maintenance, and training.
This ARP provides definitions and background information regarding the physical performance and testing of DDVs. This ARP also provides extensive guidance for the preparation of procurement specifications and functional testing.
This SAE Aerospace Recommended Practice (ARP) is intended as a guide toward standard practice for selection of nominal hex widths for fittings.
This SAE Aerospace Standard (AS) provides general requirements for components that are used in commercial aircraft hydraulic systems. It also includes the 14 CFR Part 25/CS 25 regulations that apply to hydraulic components. It also provides information to be included in the Procurement Specification in Appendix A and a checklist for design reviews in Appendix B. It does not provide requirements for distribution elements such as hoses, pipe fittings and general tubing.
The accompanying mounting and gear locations are applicable for all general installations of power take-off on the transmission gear box of motor trucks and tractors where the size of the transmission permits. The heavy-duty type opening can be adapted to the regular-duty type by the use of an adapter with 6.35 mm (0.25 in) flange thickness with appropriate bolt pattern and thread engagement. (See Figures 1 and 2.)
CLARA identifies four functions: Data Space Generator, Truth Data Generator, Coefficient Generator, and Reconstructor. Together these four functions standardize the solution to the LAR problem. This ICD defines the logical interfaces of the four functions.
This report lists documents that aid and govern the design, development, certification, and utilization of aerospace electronic engine control systems. The report lists the military and industry specifications and standards that are commonly used in electronic engine control system design. Also included are Airworthiness Authority documents and requirements associated with certification. However, these lists are not necessarily complete. The specifications and standards section has been divided into two parts: a master list, and a categorized list that provides a functional breakdown and cross-reference of these documents. For specifications and standards, the issue available during the latest revision to this document is listed. Details of current revisions for many documents are available in the Department of Defense Index of Specifications and Standards (DODISS). It should be noted that not all of these documents are referenced or even recognized by all certification authorities. In
The requirements presented in this document address the key considerations for mechanical and electrical safety in aircraft fuel pump design. Document sections focus on understanding safety relative to an electrically motor driven fuel pump assembly acting as an ignition source for explosive fuel vapors within the airplane tank.
This specification covers an aluminum alloy in the form of plate.
This specification establishes the requirements for various types of identification sleeving that will shrink to a predetermined size upon the application of heat after it has been marked. Continuous operating temperature ratings range from -55° to 175°C (-67° to 347°F). (See 6.1).
This specification covers a premium aircraft-quality, high-alloy steel gas-atomized and HIP-consolidated in the form of bars, wire, forgings, and forging stock.
This document applies to safety observers or spotters involved with the use of outdoor laser systems. It may be used in conjunction with AS4970.
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 SAE Recommended Practice applies to a decorative lamp(s) installed on the front of motor vehicles. This lamp(s) is intended only to be decorative and is not to impair the effectiveness of any required lighting device. This recommended practice establishes uniformity in use guidelines for the performance, installation, activation, and switching of a front decorative lamp(s).
This SAE Information Report establishes procedures and terminology for measuring, calculating, and referencing the percent vehicle overlap for a case vehicle in real-world or staged end plane collisions where the end plane of the case vehicle is engaged at one of the two bumper corners but not both. This SAE Information Report may be applied to rear or front plane impacts.
This document describes guidelines, methods, and tools used to perform the ongoing safety assessment process for transport airplanes in commercial service (hereafter, termed “airplane”). The process described herein is intended to support an overall safety management program. It is associated with showing compliance with the regulations, and also with assuring a company that it meets its own internal standards. The methods identify a systematic means, but not the only means, to assess ongoing safety. While economic decision-making is an integral part of the safety management process, this document addresses only the ongoing safety assessment process. To put it succinctly, this document addresses the “Is it safe?” part of safety management; it does not address the “How much does it cost?” part of the safety management. This document also does not address any specific organizational structures for accomplishing the safety assessment process. While the nature of the organizational
This SAE Aerospace Standard (AS) covers ULDs utilized in finding submerged aircraft. Such ULDs are installed within the aircraft in a manner that they are unlikely to become separated during crash conditions. The low frequency ULD should be attached to the airframe in accordance with the manufacturer’s recommendations in order to maximize the underwater detection range. ARINC Standard 677 also provides installation guidance for Low Frequency ULDs.
This SAE Aerospace Standard (AS) establishes the requirements for fluid fittings that combine both beaded hose connections and 37 degree flared connections for use in all types of fluid systems.
The present Aerospace Recommended Practice specifies for airplane operator and tow vehicle manufacturers the basic testing requirements for towbarless tow vehicles to be used on the nose gear of conventional tricycle type landing gears of commercial civil transport aircraft with maximum ramp weight between 8600 kg (19 000 lb) and 50 000 kg (110 000 lb), commonly designated as “regional aircraft”. Its purpose is to achieve testing results, or equivalent computer modeling, demonstrating that the loads induced by the tow vehicle will not exceed the design loads of the airplane’s nose landing gear and associated structure, reduce the certified safe life limit of the nose landing gear, or otherwise compromise the airplane’s structural integrity and airworthiness certification.
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