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Simplified Fuel Systems for Light Aircraft
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1969 by SAE International in United States
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Considerable loss of life, injury, property damage, and monetary loss is caused by improper fuel management of both single and multiengine general aviation aircraft each year. To reduce this loss, it is up to the manufacturer to design simplicity into the operation of fuel systems so that ultimately, the pilot need only turn his fuel system on prior to each flight without any further requirements for fuel management until engine shutdown. The fuel capacity required by the modern high performance single and twin engine aircraft generally requires multiple tank fuel systems with the associated selector valves that require numerous careful and timely tank selections during the course of the flight.
It is the object of this paper to describe the history of development of the multiple tank fuel system used in all the AEROSTAR series of aircraft. The finalized system is an on-off system that does not require any in-flight fuel management and is of a fail-safe type of design.
|Technical Paper||General Design Aspects Of Turbo-Prop & Turbo-Jet Aircraft Fuel Systems|
|Technical Paper||“High-Speed Pressure Refueling Of Aircraft”|
|Aerospace Standard||Thesaurus for Fuel System Components|
CitationReese, R., "Simplified Fuel Systems for Light Aircraft," SAE Technical Paper 690334, 1969, https://doi.org/10.4271/690334.
- National Transportation Safety Board, “Aircraft Design - Induced Pilot Error.” National Transportation Safety Board, Department of Transportation, Washington, D. C. 20591, Report No. PB 175 629, July 1967.
- Wyle Laboratories, “Qualification Test of Sweeney Engineering Corp. Low Pressure Fuel Check Valve Elements” Wyle Laboratories, El Segundo, Calif., Test Report No. 3147, Sept. 30, 1956.