4. Interface_________
A. Interface Signals For each side:
(1) Control signal (2 wires) The control order signal is transmitted through a two-wire twisted lead (high point and low point).
(2) Position transducer signal (4 wires) Two voltages : V1 and V2 (2 wires each).
(3) Enable signal (1 wire) This signal is transmitted by the FAC control logic and controls the coil of a relay inside the rudder travel-limitation unit (+28VDC = motor activated ; open circuit = motor not activated).
(4) Return to low speed signal (2 wires) This signal controls the coil of a relay inside the rudder travel-limitation unit. +28VDC = return to low speed order (delivered by the FAC control logic command). Ground = return to low speed order (delivered by the FAC control logics monitor) The FAC provides the coil with the electrical ground.
(5) Monitoring signal (1 wire) This signal which is transmitted by the rudder travel-limitation unit to the FAC is used during the test procedure of the rudder travel-limitation unit: Ground = rudder travel-limitation unit declared good. Open circuit = rudder travel-limitation unit failed.
R 5. Operation_________
R R R A. Principle (Ref. Fig. 001) There are two modes of operation:
R (1) Normal operation The active system controls the limitation unit through its motor. It limits the rudder travel according to a parameter specific to the flight envelope ie the corrected airspeed (VC). This parameter which is delivered by the ADIRS (Air Data/Inertial Reference System) is monitored by the FAC (Ref. 22-65-00).
Rudder Travel-Limitation Unit - Block Diagram
Figure 001
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Each motor has its own power electronic set. A FAC logic interrupts the power of the electronic set on the side which is not active and thus de-activates the associated motor (Ref. para. C). Two position transducers enable slaving and monitoring of the channel.
(2) Return to low speed conditions This mode, which is the emergency mode, serves in case of failure of the FAC or of the power electronic set (when the failure prevents the normal operation of the rudder travel-limitation unit). This mode which is independent from the normal control, is only initiated at low speed (in slats extended configuration). A FAC internal logic (Ref. para. C) controls a relay which switches the limitation unit to a control order called emergency control order (independent 26 V/400 Hz power supply).
B. Structure of the Control Law
**ON A/C 001-049, 051-099, 101-149, 201-299,
(Ref. Fig. 002)
R **ON A/C 151-199, 401-499,
(Ref. Fig. 002A)
**ON A/C 301-399,
(Ref. Fig. 002B)
**ON A/C ALL
The control law generates a deflection order.
A synchronization is achieved for the channel in standby mode or not
engaged, from the position of the motor position feedback.
C. Operating Logic
(1) Normal operation (Ref. Fig. 003) The rudder travel-limitating system operates using the changeover technique when a channel is detected faulty. The priority is given to the side 1 through the aircraft wiring (side 1 signal).
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Rudder Travel-Limitation Unit - Control Law
Figure 002
Rudder Travel-Limitation Unit - Control Law
Figure 002A
R Rudder Travel-Limitation Unit - Control Law R Figure 002B
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Rudder Travel-Limitation - Changeover Logic Figure 003
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In normal operation the RTL (Rudder Travel-Limiting) channel No. 1 is
active and drives the associated motor.
The other channel is in standby (synchronization mode) and the power
electronic set of the associated motor is not supplied.
This changeover is accomplished through hard-wired logic as follows:
-
A logic signal C (+28VDC = motor activated) controls a relay inside the motor
-
A logic signal M (+28VDC = motor activated) controls an intermediary relay 13CC1(2) which supplies (+28VDC via the circuit breaker 5CC1 (2)) the power electronic set of the associated servomotor.
The logic is identical (on command and monitoring channels) and uses:
-
The hard-wired signal on side 1
-
The hard-wired signal of the active opposite RTL function
-
The general monitoring of the FAC
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