The test procedure applies to the refueling manifold system connecting the receiver aircraft fuel tanks to the refueling source fuel pump(s) for both ground and aerial refueling. The test procedure is intended to verify that the limit value for surge pressure specified for the receiver fuel system is not exceeded when refueling from a refueling source which meets the requirements of AS 1284 (reference 2). This recommended practice is not directly applicable to surge pressure developed during operation of an aircraft fuel system, such as initiating or stopping engine fuel feed or fuel transfer within an aircraft, or the pressure surge produced when the fuel pumps are first started to fill an empty fuel manifold.
The test procedure applies to the refueling manifold system connecting the receiver aircraft fuel tanks to the refueling source fuel pump(s) for both ground and aerial refueling. The test procedure is intended to verify that the limit value for surge pressure specified for the receiver fuel system is not exceeded when refueling from a refueling source which meets the requirements of AS1284 (reference 2). This recommended practice is not directly applicable to surge pressure developed during operation of an aircraft fuel system, such as initiating or stopping engine fuel feed or fuel transfer within an aircraft, or the pressure surge produced when the fuel pumps are first started to fill an empty fuel manifold.
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 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.
It is intended to provide capacitance gaging system "specifiers" with the necessary tools to make value judgements concerning the various errors typically encountered in systems of this type. Thus, in addition to merely identifying the error-causes, descriptions are given concerning the basic factors from which these error-causes derive. This knowledge, when complemented with appraisals of the relative costs of minimizing the error-causes, will furnish the system specifier with a powerful tool with which to optimize gaging system accuracy, and thus, to obtain the "best possible" overall system within the constraints imposed by both design and budgetary considerations. Since the subject of capacitance gaging accuracy is quite extensive, and in some instances very complex, no attempt is made herein to present an all-inclusive and fully comprehensive evaluation of the subject. Rather, the major contributors to gaging system inaccuracy are discussed.
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.
The test procedure applies to the refueling manifold system connectingn the receiver aircraft fuel tanks to the refueling source fuel pump(s) for both ground and aerial refueling. The test procedure is intended to verify that the limit value for surge pressure specified for the receiver fuel system is not exceeded when refueling from a refueling source which meets the requirements of AS1284 (reference 2). This recommended practice is not directly applicable to surge pressure developed during operation of an aircraft fuel system, such as initiating or stopping engine fuel feed or fuel transfer within an aircraft, or the pressure surge produced when the fuel pumps are first started to fill an empty fuel manifold.
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 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.
The importance of adequate component procurement specifications to the success of a hardware development program cannot be overemphasized. Specifications which are too stringent can be as detrimental as specifications which are too lax. Performance specifications must not only identify all of the component requirements, but they must also include sufficient quality assurance provisions so that compliance can be verified. It should be understood that in almost every case specifications for components will ultimately become part of a BINDING, WRITTEN CONTRACT (PO). The purpose of this document is to describe types of specifications, provide guidance for the preparation of fluid component specifications, and identify documents commonly referenced in fluid component specifications.