AMM A320F | ENGINE FUEL AND CONTROL - GENERAL

1. General

Fuel System Schematic ** ON A/C NOT FOR ALL

The fuel system enables delivery of a fuel flow corresponding to the power required and compatible with engine limits.
The system consists of:

the two stage fuel pump with low pressure and high pressure elements,
the Fuel Metering Unit (FMU),
the engine Fuel Cooled Oil Cooler (FCOC),
the Integrated Drive Generator (IDG) Fuel Cooled Oil Cooler (FCOC),
the fuel filter,
the fuel distribution valve,
the fuel flow meter,
20 fuel nozzles,
the fuel diverter and return (to tank) valve.

2. Component Location

Component Location ** ON A/C NOT FOR ALL

Aft Avionics Compartment - Component Location ** ON A/C NOT FOR ALL

Engine Electronic Control (EEC) - Component Location ** ON A/C NOT FOR ALL

Component Location ** ON A/C NOT FOR ALL

-------------------------------------------------------------------------------

FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA

I I I I DOOR I REF.

-------------------------------------------------------------------------------

1KS1 EIU-1 85VU 127 824 73-25-34

1KS2 EIU-2 86VU 128 824 73-25-34

5KS1 ANN-ENG/1 115VU 210

5KS2 ANN-ENG/2 115VU 210

6KS0 SEL SW-ENG/MODE/CRANK/NORMAL/

IGN/START 115VU 210

7KS1 P/BSW-ENG/FADEC GND PWR/1 50VU 212

7KS2 P/BSW-ENG/FADEC GND PWR/2 50VU 212

8KS1 CTL UNIT-THROTTLE, ENG 1 211 831 76-11-19

8KS2 CTL UNIT-THROTTLE, ENG 2 211 831 76-11-19

9KS1 P/BSW-ENG/MAN START/1 22VU 212

9KS2 P/BSW-ENG/MAN START/2 22VU 212

4000KS EEC 436 448AR 73-22-34

2000EM FILTER ELEMENT-FUEL 430 447AL 73-12-42

2001EM PUMP-HP/LP FUEL 430 447AL 73-12-41

2002EM VALVE-FUEL DISTRIBUTION 440 438AR 73-13-43

4010KS FLOWMETER-FUEL 430 447AL 73-31-17

4018KS VALVE-FUEL DIVERTER AND RETURN 430 447AL 73-13-42

2005EM NOZZLE-FUEL 400 73-13-41

4000KC FUEL METERING UNIT 435 437AL 73-22-52

2004EM SENSOR AND MANIFOLD-P4.9 454 452AR 73-22-51

4005EV STATOR-ENGINE DEDICATED ALTERNATOR 435 437AL 73-22-38

- DATA ENTRY PLUG 436 438AR 73-22-35

2003EM SENSOR-P3/T3 454 452AR 73-22-15

4014KS SENSOR-P2/T2 431 73-22-11

4017KS SENSOR-FUEL TEMPERATURE 435 437AL 73-35-15

3. Distribution

Fuel System Schematic ** ON A/C NOT FOR ALL

The fuel supplied from aircraft tanks flows through a centrifugal pump Low Pressure (LP) stage then through the FCOC and then through a filter and a gear pump High Pressure (HP) stage.
The fuel from the HP pump is delivered to the FMU which controls the fuel flow supplied to the fuel nozzles (through the fuel flow-meter and the fuel distribution valve).
The FMU also provides hydraulic pressure to all hydraulic system external actuators. These include the booster stage bleed valve actuators, stator vane actuator, Air Cooler Oil Cooler (ACOC) air modulating valve, High Pressure Turbine Active Clearance Control (HPTACC) and Low Pressure Turbine Active Clearance Control (LPTACC) valve. Low pressure return fuel from the actuators is routed back into the fuel diverter and return valve.
The fuel diverter and return valve enables the selection of one of the four basic configurations between which the flow paths of the fuel in the engine are varied to maintain the IDG oil, engine oil and fuel temperatures within specified limits.
The transfer between configurations is determined by a software logic contained in the Electronic Engine Control (EEC).

4. Controlling
The Full Authority Digital Electronic Control (FADEC) system provides full range control of the engine to achieve steady state and transient performance when operated in combination with aircraft subsystems.
The FADEC is a dual channel EEC with crosstalk and failure detection capability.
In case of failure detection, the FADEC switches from one channel to the other.
The FADEC system operates in conjunction with the applicable aircraft systems to perform the following:

Control of fuel flow, stator vanes and bleeds to automatically maintain forward and reverse thrust settings and to provide satisfactory transient response.
Protect the powerplant from exceeding limits for N1, N2, maximum allowable thrust, and burner pressure.
Control of the High Pressure Turbine (HPT) 10th stage cooling air, and low and high turbine active clearance control systems.
Control of fuel, engine and IDG oil temperature.
Control of the thrust reverser.
Automatic sequencing of the start system components.
Diagnosis and maintenance capability.

5. Indicating
The engine fuel system is monitored from:

the ECAM display,
the warning and caution lights.

The indications cover all the main engine parameters through the FADEC.
The warnings and cautions reflect:

the engine health and status through the FADEC,
the FADEC health & status,
the fuel filter condition through a dedicated hardwired pressure switch.

ENGINE FUEL AND CONTROL - GENERAL - DESCRIPTION AND OPERATION