Announced at the 2006 NBAA convention. The engine was originally designed as a 8,500- to 10,500-pound thrust turbofan to power super mid-size to large cabin business jets or 40 to 60-seat regional jets with a MTOW between 45,000 and 60,000 lb. Since original development the thrust range has been raised and is currently quoted as 9,500 to 12,000 pounds of thrust.
The engine architecture includes a solid wide-chord swept fan without booster, followed by a 4 axial stage + 1 centrifugal stage high pressure compressor. The overall pressure ratio is 27:1 with a core pressure ratio of "over 17". The high pressure compressor is driven by a single stage turbine, while the 40 inch fan is coupled to a 3-stage low pressure turbine.
The high pressure spool and combustor have been run in a core-demonstrator reaching the take-off speed of 20,300rpm. A full engine demonstrator is due to run towards the end of 2008, while engine certification is pencilled in for the end of 2010 or early 2011 and should be available towards 2012. As of january 2008, no aircraft manufacturer had selected this engine.