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V-4 Aviation Turbo Diesel Specifications: CONFIGURATION upright 90 degree V-4, turbocharged, direct  drive, two-stroke diesel with oil pump and external air-oil separator/sump top profile is 3.5 inches higher at the cylinder tops than an IO-360 Lycoming, referenced from the  crankshaft engine width under 24 inches COOLING liquid cooled FUEL jet-A (JP5) fuel, or #2 diesel where ambient temperatures are high enough to avoid gelling (above 20 degrees F) POWER 160 and 200 hp models, at 2,700 rpm, Displacement 3.3 Liter possible higher horsepower V-4 version (lower  TBO) FUEL CONSUMPTION BSFC = .39 lb/hp/hr for a 1,000 nm trip in a Velocity at 65% power,  this translates to: 40.9 gal Jet A for the V-4, versus 57.3 gal 100LL for Lycoming IO-360 WEIGHT currently about 327 lbs including starter, oil pump, fuel pump, water pump, turbocharger, all internal lines and internal exhaust system RELIABILITY lower part count and fewer potential leakage points than the current  4-cylinder gasoline-powered aircraft  engines: no cam shaft or valve train no head gaskets to blow and no head  bolts fully doweled, four bolt main construction (12 studs) inherently stout block and compact V-4 design no ignition system OTHER DESIGN CHARACTERISTICS single-lever power control configured for fixed or variable pitch propellers  (propeller governor pad provided) vacuum pump pad provided limited operation at reduced power without coolant limp-home capability without turbocharger, supplying approximately 100 hp with backup air no electromagnetic interference at normal  operating altitudes provisions for cold weather starting TBO of 2,000 hours (estimated) target price 30-50% under current competition B A C K