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This SAE Aerospace Specification (AS) is applicable to all aircraft. This AS defines the minimum design and operating requirements for the aircraft refueling interface. These requirements establish the minimum criteria for the aircraft design that provides practical standardized refueling system requirements, provides minimum standardized criteria for the operation and performance of any aircraft refueling equipment, and establishes an integrated minimum performance for aircraft refueling operations. This standardization provides the minimum design criteria to assure full compatibility between the aircraft refueling system connection point(s), aircraft operating characteristics, and the design and operation of ground based aircraft refueling equipment in all steady state and dynamic refueling and defueling conditions. The criteria that shall be used to test the operation and performance of the aircraft refueling system and equipment are also specified.

This document describes the major design drivers and considerations when designing a fuel system for a large commercial aircraft. It discusses the design at a system/aircraft level, and is not intended as a design manual for individual system components, though it does refer out to other SAE specifications where more detail on specific components and sub systems is given. It does include examples of a number of calculations associated with sizing of fuel systems, based on those given in NAV-AIR-06-5-504, as well as an appendix summarizing basic fluid mechanical equations which are key for fuel system design. It is acknowledged that most of these calculations would today be performed by modelling tools, rather than by hand, but it is considered important for the designer to understand the principles. It is intended that later issues of this document will include appendices which give specific considerations for military aircraft, smaller commercial aircraft, and rotorcraft.

This SAE Aerospace Information Report presents a glossary of terms commonly used in the ground delivery of fuel to an aircraft and pertinent terms relating to the aircraft being refueled.

This document describes the requirements for air vehicle fuel, vent, and propulsion fuel system functional components.

This document is applicable to commercial and military aircraft fuel quantity indication systems. It is intended to give guidance for system design and installation. It describes key areas to be considered in the design of a modern fuel system and builds upon experiences gained in the industry in the last 10 years.

This SAE Aerospace Information Report (AIR) is limited to the subject of aircraft fuel systems and the questions concerning the requirements for electrical bonding of the various components of the system as related to Static Electric Charges, Fault Current, Electromagnetic Interference (EMI) and Lightning Strikes (Direct and Indirect Effects). This AIR contains engineering guidelines for the design, installation, testing (measurement) and inspection of electrical bonds.

This SAE Aerospace Information Report presents a glossary of terms commonly used in the ground delivery of fuel to an aircraft and pertinent terms relating to the aircraft being refueled.

This SAE Aerospace Information Report (AIR) provides background information, technical data, and related technical references for minimization of electrostatic hazards in aircraft fuel systems.

The scope of this document is to provide pertinent information on demonstrating the performance of Flame Arrestors, also known as Fuel Vent Protectors (FVPs), in preventing the propagation of a deflagration when the arrestors are subjected to aerospace-representative flames produced by the venting of flammable gas through the arrestor. Test procedures for two separate combustion-loading profiles are presented herein: The flame hold test condition, and the flame propagation test condition. For the flame hold test condition, the applicability of two separate critical flows is discussed in which one flow results in the greatest flame arrestor temperature and a second flow results in the greatest temperature of the surrounding structure.

This report is intended to identify the various errors typically encountered in capacitance fuel quantity measurement systems. In addition to identification of error sources, it describes the basic factors which cause the errors. When coupled with appraisals of the relative costs of minimizing the errors, this knowledge will furnish a tool with which to optimize gauging system accuracy, and thus, to obtain the optimum overall system within the constraints imposed by both design and budgetary considerations. Since the subject of fuel measurement accuracy using capacitance based sensing is quite complex, no attempt is made herein to present a fully-comprehensive evaluation of all factors affecting gauging system accuracy. Rather, the major contributors to gauging system inaccuracy are discussed and emphasis is given to simplicity and clarity, somewhat at the expense of completeness. An overview of capacitive fuel gauging operation can be found in AIR5691.

This report is intended to identify the various existing technologies used for a fuel level sensing system. In addition to sensing technologies, it describes the basic architecture of fuel level sensing systems and their association with fuel gauging system to increase integrity of fuel measurement and management. As the fuel level sensing system is generally based on electrical components within fuel tanks, a specific focus is made on fuel tank explosion safety protection. An overview of the capacitive fuel gauging operation can be found in AIR5691.

Ice formation in aircraft fuel systems results from the presence of dissolved and undissolved water in the fuel. Dissolved water or water in solution with hydrocarbon fuels constitutes a relatively small part of the total water potential in a particular system with the quantity dissolved being primarily dependent on the fuel temperature and the water solubility characteristics of the fuel. One condition of undissolved water is entrained water, such as water particles suspended in the fuel as a result of mechanical agitation of free water or conversion of dissolved water through temperature reduction. This can be considered as analogous to an emulsion state. Another condition of undissolved water is free water which may be introduced as a result of refueling or the settling of entrained water which collects at the bottom of a fuel tank in easily detectable quantities separated by a continuous interface from the fuel above.

MIL-STD-1290, 14 CFR 27.952, and 14 CFR 29.952 provide crash resistant fuel system design and test criteria that significantly minimize fuel leaks and occurrence of post-crash fire in survivable impacts. This document does not change and does not authorize changes in or deviations from MIL-Standard or regulatory requirements. This document provides guidance for the design, performance, and test criteria for self-sealing breakaway valves.

This document describes the major design drivers and considerations when designing a fuel system for a large commercial aircraft. It discusses the design at a system/aircraft level, and is not intended as a design manual for individual system components, though it does refer out to other SAE specifications where more detail on specific components and sub-systems is given. It does include examples of a number of calculations associated with sizing of fuel systems, based on those given in NAV-AIR-06-5-504, as well as an appendix summarizing basic fluid mechanical equations which are key for fuel system design. It is acknowledged that most of these calculations would today be performed by modelling tools, rather than by hand, but it is considered important for the designer to understand the principles. It is intended that later issues of this document will include appendices which give specific considerations for military aircraft, smaller commercial aircraft, and rotorcraft.

This report lists documents that aid and govern the design of aircraft and missile fuel systems. The report lists the military and industry specifications and standards and the most notable design handbooks that are commonly used in fuel system design. Note that only the principle fuel specifications for the U.S. and Europe (Military Specifications, ASTM, and Def Stan) have been included within this report. The specifications and standards section has been divided into two parts: a master list arranged numerically of all industry and military specifications and standards, and a component list that provides a functional breakdown and a cross-reference of these documents. It is intended that this report be a supplement to specifications ARP8615, MIL-F-17874, and JSSG 2009. Revisions and amendments which are correct for the specifications and standards are not listed. The fuel system design handbooks are listed for fuels and for system and component design.

This SAE Aerospace Information Report (AIR) is a compilation of engineering references and data useful to the technical community that can be used to ensure fuel system compatibility with composite structure. This AIR is not a complete detailed design guide and is not intended to satisfy all potential fuel system applications. Extensive research, design, and development are required for each individual application.

This SAE Aerospace Information Report (AIR) includes general information about the various types and styles of flexible tanks and the tank-mounted fittings that adapt the tank to the surrounding structure and fluid-system plumbing. Recommendations are given relative to the dimensional layout of the tank when these recommendations serve to avoid tank fabrication problems and tank/structure interface problems. As a part of these recommendations, critical dimensions of plumbing adapter fittings are discussed and recommendations made. Tank manufacturing tolerances are given. Recommendations are made relative to cavity design and preparation to facilitate a reliable installation. The special installation requirements of nonself-sealing, self-sealing, and crash-resistant tanks are discussed. This document is not intended to replace the information or requirements of the military and commercial procurement specifications listed in Section 2.

This project aims to develop a framework of requirements which support safe installation and operation of optical devices within an aircraft fuel tank, specifically: 1: To determine optical power and energy limits which ensure safe operation of optical installations within an aircraft fuel tank over aircraft life and under all phases of flight, taking the limits provided in IEC 60079-28:20015 as a starting point. 2: To demonstrate optical and electrical power and energy equivalences, where possible. 3: To determine requirements for optical installations, including bonding and electrostatic discharge for non-conductive components such as optical fibres. 4: To provide guidelines for analysis of the hazards presented by the typical internal components of optical devices, such as failure modes of photo diodes and cells.

This document is applicable to commercial and military aircraft fuel quantity indication systems. It is intended to give guidance for system design and installation. It describes key areas to be considered in the design of a modern fuel system, and builds upon experiences gained in the industry in the last 10 years.

Applications include specifications, reports, ratings, texts etc., where fluid leakage rates are treated.