The TFE731 was based on the core of the TSCP700, which was specifically developed for use as the auxiliary power unit (APU) on the McDonnell Douglas DC-10. The design featured two important factors: low fuel consumption, and low noise profiles that met the newly established U.S. noise abatement regulations. The first test run of the TFE731 occurred in 1970 at Garrett’s plant in Torrance, California.[2] The first production model, the TFE731-2, began rolling off the assembly line in August, 1972, and was used on the Learjet 35/36 and Dassault Falcon 10, both of which entered production in 1973. The TFE731-3 was developed for use in the Lockheed JetStar re-engining program, and subsequent versions of it have been used on a number of aircraft, including the Learjet 55. In 1975, the TFE731 was named Aviation Product of the Year by Ziff-Davis Publishing Company.[3] The -5 model was certified in 1982, and a decade later, an engine utilizing the TFE731-5 power section and a TFE731-3 fan was built and designated the TFE731-4, intended to power the Cessna Citation VII aircraft.[4] The most recent version is the TFE731-50, based on the -60 used on the Falcon 900DX, which underwent its flight test program in 2005. Honeywell has developed this engine com


TFE731-2, TFE731-3, TFE731-4, TFE731-5, TFE731-20, TFE731-40, TFE731-50, TFE731-60, TFE731-1100


Aero L-139 (prototype only), AIDC AT-3, Boeing Skyfox, British Aerospace BAe 125 Series 700, CASA C-101, Cessna Citation III/VI/VII, Dassault Falcon 10, Dassault Falcon 20 (retrofit), Dassault Falcon 50, Dassault Falcon 900, FMA IA 63 Pampa, Gulfstream G100/G150/C-38 Courier (formerly IAI 1125 Astra SPX), Hawker 800/850XP/900XP, Hongdu JL-8, IAI Westwind, Learjet 31, Learjet 35/C-21, Learjet 40, Learjet 45, Learjet 55, Learjet 70, Lockheed JetStar/Jetstar II, North American Sabreliner (NA-465 model), Textron AirLand Scorpion


General characteristics
• Type: Turbofan
• Length: 50 in (127 cm)
• Diameter: 39 in (100 cm)
• Dry weight: 734 lb (333 kg)

• Compressor: 1 stage fan, 4 axial low pressure compressor stages, 1 centrifugal high pressure compressor stage
• Combustors: Annular
• Turbine: 1 stage high pressure turbine, 3 stage low pressure turbine

• Maximum thrust: 3500 lbf (15.6 kN)
• Overall pressure ratio: 13:1
• Fuel consumption: 875 lb. per hour[7]
• Specific fuel consumption: 0.5 lb/lbf-hr
• Thrust-to-weight ratio: 4.7:1

For more information please call (425)742-0333 or email richard@turbine-tool.com.