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THIS IS AN UNCONTROLLED DOCUMENT.
THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED.
THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE
FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE.
PRODUCT DATA JANUARY 2003
ENGINE CONTROL SYSTEM [FADEC]
A Full Authority Digital Electronic Control (FADEC) System is used on the 250-
C40B engine, as well as on other 250 engine models.
System objectives are to : 1. Improve engine performance 2. Enhance flight
safety 3. Reduce pilot work load 4. Increase mean time between removals/
overhauls 5. Reduce life cycle costs 6. Simplify engine maintenance and trouble
shooting
The FADEC fuel and control system consists of :
1. Hydromechanical Unit (HMU) 2. Fuel filter-oil filter assembly (CEFA)
3. Electronic Control Unit (ECU) 4. Permanent Magnet Alternator (PMA)
5. Compressor inlet air temperature sensor, inlet duet mounted
6. P1 compressor air inlet pressure sensor in the ECU
7. Engine sensors of RPM, MGT and Torque 8. Aircraft supplied inputs
The HMU contains the following components :
1. Two element fuel pump 2. Fuel metering valve
3. Manual fuel control 4. Three solenoid valves
5. Two check valves 6. Fuel shut-off valve with a pilot valve (windmill bypass valve)
7. Bypassing type pressure differential regulator valve
8. Power lever input shaft 9. Two feedback potentiometers
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