-
PHASE 1: The FAC sends a null advisory value and does not validate the activation signal. As the input value does not correspond to the fixed threshold value, the monitoring function must be triggered. The test signal changes to an open circuit (= warning). This validates the non-blocked status of the monitoring.
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PHASE 2: The FAC sends an advisory value which is the one expected by the actuator and the activation signal is not valid. This advisory value is set to half the travel. If the control order is generated correctly, the monitoring must not be trigged (feedback value equal to the threshold) and the test signal returns to good status (ground). This validates the electronic section which ensures the slaving and tapping of the monitoring signals.
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PHASE 3: The FAC sends again a null advisory value but validates the activation signal. This puts the actuator into service without displacement of the rudder. A specific stage detects the closing of the control motor. Its signal serves for forcing the monitoring logic to the good status.
During this procedure initiated at FAC energization, the activation signal
of the monitoring logic which puts into service the actuator 28 V power,
must always be validated.
This relay is tested to check its capability to open, in a specific phase of
the automatic test.
1EFF : ALL 1 22-62-00Page 20 1 1 Feb 01/00 1 1 1CES 1
RUDDER TRIM COMPUTATION - ADJUSTMENT/TEST
_________________________________________
TASK 22-62-00-710-001
Operational Test of the Rudder Trim Function
WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.
WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE
_______
CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM.
1. Reason for the Job
__________________
Make sure that the rudder trim system No.1 (No.2) operates correctly.
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
R 29-10-00-863-003 Pressurize the Blue Hydraulic System with a Ground
R Power Supply 29-10-00-864-003 Depressurize the Blue Hydraulic System 29-23-00-863-001 Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump 29-23-00-864-001 Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU 31-60-00-860-001 EIS Start Procedure 31-60-00-860-002 EIS Stop Procedure
1EFF : ALL 1 22-62-00Page 501 1 1 Nov 01/02 1 1 1CES 1
3. Job Set-up
__________
Subtask 22-62-00-860-050
A. Aircraft Maintenance Configuration
(1)
Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).
(2)
On the overhead panel, on the FLT CTL panel 23VU and 24VU:
-Make sure that the FAC1 and FAC2 pushbutton switches are pushed (the FAULT and OFF legends are off).
(3)
Do the EIS start procedure (ECAM only) (Ref. TASK 31-60-00-860-001).
(4)
On the center pedestal, on the ECAM control panel:
-Get the F/CTL page.
(5)
Pressurize the aircraft hydraulic systems (Ref. TASK 29-23-00-863-001) (Ref. TASK 29-10-00-863-003).
Subtask 22-62-00-865-050
B. Make sure that this(these) circuit breaker(s) is(are) closed:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 121VU AUTO FLT/RUDDER/TRIM/IND 15CC M20 121VU AUTO FLT/FAC2/28VDC 5CC2 M19 121VU AUTO FLT/FAC2/26VAC 14CC2 M18
4. Procedure
_________ Subtask 22-62-00-710-050
A. Operational Test of the Rudder Trim Function
NOTE : This test is for the system 1. For the system 2, use the
____
indications between the parentheses.
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