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 These computers generate the surface deflection orders which correspond to
 the pilot orders and perform control of these surfaces through the
 electrically-controlled servocontrols.
 These orders are monitored.
 Another type of computer is provided :

 -2 FCDCs (Flight Control Data Concentrator) They isolate the ELACs and the SECs from the other A/C systems and are used for maintenance tasks and data concentration. The electrical flight control system (EFCS) performs several functions:
 -pitch control
 -lateral control
 -speedbrake function
 -ground spoiler function The electrical flight control system uses the three A/C hydraulic systems. In case of complete loss of electrical supply, the A/C remains controleable through the rudder mechanical control and THS mechanical control.

 EFCS General (A320) Figure 001 
R 1EFF : 1 1 1CES  001-049, 051-099, 101-149, 201-299,  1 111 27-90-00 Page 2 May 01/05

 

 EFCS General (A319) Figure 001A 
R 1EFF : 1 1 1CES  151-199, 401-499,  1 111 27-90-00 Page 3 Aug 01/05

 

R  EFCS General (A321) 
R  Figure 001B 
R 1EFF :  301-399,  1  27-90-00 Page 4 
1  1  May 01/04
 1  1
 1CES  1

 

R 2. Component Location
__________________
R -------------------------------------------------------------------------------R FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA R I I I I DOOR I REF. R -------------------------------------------------------------------------------R 33CE1 SERVO CTL-L AILERON, INBD G 575 27-14-51 R 33CE2 SERVO CTL-R AILERON, INBD G 675 27-14-51 R 33CE3 SERVO CTL-L AILERON, OUTBD B 575 27-14-51 R 33CE4 SERVO CTL-R AILERON, OUTBD B 675 27-14-51 R 31CE1 SERVO CTL - SPLR1, L G 574 27-64-51 R 31CE2 SERVO CTL - SPLR1, R G 674 27-64-51 R 31CE3 SERVO CTL - SPLR2, L Y 582 27-64-51 R 31CE4 SERVO CTL - SPLR2, R Y 682 27-64-51 R 31CE5 SERVO CTL - SPLR3, L B 583 27-64-51 R 31CE6 SERVO CTL - SPLR3, R B 683 27-64-51 R 31CE7 SERVO CTL - SPLR4, L Y 584 27-64-52 R 31CE8 SERVO CTL - SPLR4, R Y 684 27-64-52 R 31CE9 SERVO CTL - SPLR5, L G 585 27-64-52 R 31CE10 SERVO CTL - SPLR5, R G 685 27-64-52 R 9CE ACTUATOR - THS 311 27-44-51 R 34CE1 SERVO CTL-L ELEVATOR, INBD G 345 27-34-51 R 34CE2 SERVO CTL-R ELEVATOR, INBD Y 335 27-34-51 R 34CE3 SERVO CTL-L ELEVATOR, OUTBD B 345 27-34-51 R 34CE4 SERVO CTL-R ELEVATOR, OUTBD B 335 27-34-51 R 2CE1 ELAC-1 83VU 127 27-93-34 R 2CE2 ELAC-2 84VU 128 27-93-34 R 3CE1 FCDC-1 83VU 127 27-95-34 R 3CE2 FCDC-2 84VU 128 27-95-34 R 1CE1 SEC-1 83VU 127 27-94-34 R 1CE2 SEC-2 84VU 128 27-94-34 R 1CC1 FAC-1 83VU 127 22-66-34 R 1CC2 FAC-2 84VU 128 22-66-34 R 4CE1 SSTU - ROLL CTL, CAPT 193VU 211 27-92-41 R 4CE2 SSTU - ROLL CTL, F/O 182VU 212 27-92-41 R 4CE3 SSTU - PITCH CTL, CAPT 193VU 211 27-92-41 R 4CE4 SSTU - PITCH CTL, F/O 182VU 212 27-92-41 R 7CE XDCR UNIT - SPD BRK CTL 11VU 210 27-92-14 R 25CE1 XDCR UNIT - PEDAL POS, L 121 27-92-15 R 25CE2 XDCR UNIT - PEDAL POS, R 122 27-92-15 R 49CE1 XDCR UNIT - ELEVATOR POS, L R 49CE2 XDCR UNIT - ELEVATOR POS, R R 2CC XDCR UNIT - YAW DAMPER POS 325 R 42WV XDCR UNIT - RUDDER POS 325 R 12CE1 ACCLRM-1 131 27-92-16 R 12CE2 ACCLRM-2 132 27-92-16 R 12CE3 ACCLRM-3 131 27-92-16

 -------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA I I I I DOOR I REF.
 -------------------------------------------------------------------------------R 12CE4 ACCLRM-4 132 27-92-16 R 10CE1 PRESS SW - HYD 140 27-92-17 R 10CE2 PRESS SW - HYD 140 27-92-17 R 10CE3 PRESS SW - HYD 140 27-92-17 R 8KS1 CTL UNIT - THROTTLE, ENG 1 210 73-R 8KS2 CTL UNIT - THROTTLE, ENG 2 210 73-
3. System Description
__________________ The Electrical Flight Control System (EFCS) performs several functions : (Ref. Fig. 002)
 A. Flight Control Surfaces (Ref. Fig. 002) There is 1 aileron and 5 spoilers on each wing. The roll control is ensured by:
 -
the 2 ailerons

 -
the 4 outboard spoilers on each wing. The spoilers 2, 3 and 4 of each wing ensure the speedbrake function. All the spoilers ensure the ground spoiler function. The pitch control is ensured by: the 2 elevator control surfaces, each one actuated by 2 servocontrols. 1 trimmable horizontal stabilizer (THS) actuated by an electrohydraulic actuator. The yaw control is ensured by the rudder which is actuated by 3 servocontrols mechanically controlled and simultaneously active.

 4. Power Supply
____________
 A. Hydraulic Power Supply
 (Ref. Fig. 003)
 There are three independent hydraulic systems:

 -
the Blue system pressurized by an electric pump.

 -
the Green system pressurized by a pump driven by the left engine.
　
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