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This document defines design, performance, and test criteria for self-sealing breakaway valves for use in crash-resistant aircraft fuel systems.

This document defines design, performance, and test criteria for self-sealing breakaway valves.

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 defines design, performance, and test criteria for self-sealing breakaway valves.

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.

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 SAE Aerospace Standard (AS) defines the maximum allowable free opening dimensions for airframe fueling ports on civil aircraft that require the exclusive use of gasoline as an engine fuel and the minimum free opening dimensions for airframe fueling ports on civil aircraft that operate with turbine fuels as the primary fuel type. In addition, this document defines the minimum fuel nozzle tip dimensions for turbine fuel ground service equipment and the maximum fuel nozzle tip diameter for gasoline ground service equipment.

This SAE Aerospace Standard (AS) defines the maximum allowable free opening dimensions for airframe fueling ports on civil aircraft that require the exclusive use of gasoline as an engine fuel, and the minimum free opening dimensions for airframe fueling ports on civil aircraft that operate with turbine fuels as the primary fuel type and with gasoline as the emergency fuel type. This SAE Aerospace Standard (AS) also defines the features and dimensions for airframe refueling ports on civil aircraft that require the exclusive use of turbine fuel as an engine fuel. In addition, this document defines the minimum fuel nozzle spout dimensions for turbine fuel ground service equipment, and the maximum fuel nozzle spout diameter for gasoline ground service equipment.

This SAE Aerospace Standard (AS) defines the maximum allowable free opening dimensions for airframe fueling ports on civil aircraft that require the exclusive use of gasoline as an engine fuel, and the minimum free opening dimensions for airframe fueling ports on civil aircraft that operate with turbine fuels as the primary fuel type and with gasoline as the emergency fuel type. This SAE Aerospace Standard (AS) also defines the features and dimensions for airframe refueling ports on civil aircraft that require the exclusive use of turbine fuel as an engine fuel. In addition, this document defines the minimum fuel nozzle spout dimensions for turbine fuel ground service equipment, and the maximum fuel nozzle spout diameter for gasoline ground service equipment.

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 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.

This specification covers the requirements for installation of fuel and oil lines in aircraft, except those lines furnished as part of the engine.

This specification covers the requirements for installation of fuel and oil lines in aircraft, except those lines furnished as part of the engine.

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 (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 (AIR) is limited to the subject of aircraft fuel system plumbing systems and the questions concerning the requirements for electrical bonding of the various components of the system as related to Static Electric Charges, Electromagnectic Interference (EMI) and Lightning Strikes (Direct and Indirect Effects)

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 document establishes requirements, test procedures, and acceptance criteria for the fire testing of fluid handling components and materials used in aircraft fluid systems. It is applicable to fluid handling components other than those prescribed by AS1055 (e.g., hoses, tube assemblies, coils, fittings). It also is applicable to materials, wiring, and components such as reservoirs, valves, gearboxes, pumps, filter assemblies, accumulators, fluid-cooled electrical/electronic components, in-flight fluid system instrumentation, hydromechanical controls, actuators, heat exchangers, and manifolds. These components may be used in fuel, lubrication, hydraulic, or pneumatic systems.

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.