ENGINE FUEL & CONTROL SYS - INTROD.
ENGINE FUEL AND CONTROL SYSTEM
ENGINE FUEL & CONTROL SYSTEM - GENERAL
FUEL DISTRIBUTION SYSTEM - INTROD.
FUEL DISTRIBUTION SYSTEM - GENERAL
FUEL PUMP OPERATION
PB = 0 - 152 PSIPG = 1500 - 1700 PSI
FUEL FILTER
DISPOSABLE 10 MICRON UNIT
35±5 PSID
15±5 PSID
SERVO FUEL HEATER
60 PSID
FUEL TUBES (MANIFOLD)
30 FUEL NOZZLES
FUEL NOZZLES
IS CLOSED – LESS THAN
20 PSID
COMBUSTOR DRAIN VALVE
FUEL DISTRIBUTION SYSTEM - OPERATION
ENGINE FUEL CONTROL SYSTEM – INTROD.
ENGINE FUEL CONTROL SYSTEM - GENERAL
FUEL CONTROL SYSTEM
HYDROMECHANICAL T2 SENSOR
CONTROLS A FUEL PRESSURE SIGNAL TO THE MEC PROPORCIONAL TO THE FAN INLET TEMPERATURE FOR CORRECTING N2 AND TO LIMIT N1
CIT SENSOR
.. TO COMPUTE CORRECTED ACCELERATION FUEL FLOW AN
COMPRESSOR AIRFLOW.
HYDROMECHANICAL N1 SPEED SENSOR
.. PROVIDE A FUEL PRESURE TO THE MEC PROPORTIONAL TO FAN SPEED
MAIN ENGINE CONTROL
CONTROLS ENGINE THRUST, COMPRESSOR AIRFLOW AND
TURBINE COOLING, AND PROTECTS THE ENG FROM OVERSPEED AND
OVERPRESSURE
MAIN ENGINE CONTROL
HYDRAULIC
- CIT sensor, N1 speed sensor, T2 sensor.
MECHANICAL
- Thrust Lever. - Feedback Variable Stator Vane (VSV) & Variable Bypass Valve (VBV). ELECTRICAL
- Torquemotor (EEC). - Fuel Control Switches. - Aircraft Systems (Flight/Ground Idle solenoids). - N1 Resolver to EEC.
PNEUMATIC
- Compressor Discharge Pressure (CDP). - Ambient Pressure (PAMB).
MEC HYDROMECHANICAL OPERATION
MEC ELECTRICAL OPERATION
ELECT. FAN INLET TEMP. (T12) SENSOR
CONTROL ALTERNATOR
POWERS THE EEC AND GENERATES N2 SPEED
SIGNALS
THRUST LEVER ANGLE (TLA) TRANSDUCER
EEC DISCRETES PRINTED CIRCUIT CARD
ENGINE N2 SPEED CARDS
ELECTRONIC ENGINE CONTROL (EEC)
TO REDUCE CREW WORKLOAD BY MAINTAINING A DESIRED
TARGET N2 SPEED
FUEL CONTROL SYSTEM OPERATION
FUEL FLOW INDICATING SYSTEM - INTROD.
FUEL FLOW TRANSMITTER
FUEL FLOW INDICATING SYSTEM - OPERATION
FUEL FILTER BYPASS INDICATION SYSTEM
ENG FUEL & CONTROL SYS - ELECT. OPERAT.
ENG FUEL & CONTROL SYS - MECH OPERAT.