-Centralized Fault Display Interface Unit (CFDIU),
-two Multipurpose Control and Display Units (MCDU).
BCL's are type 2 systems, i.e. they are connected to the CFDIU with:
-a discrete input used to initiate a test from CFDS,
-an ARINC 429 output bus.
TR's are type 3 systems, i.e. they are connected to the CFDIU with 2
discrete links:
- one of them used to send a ground signal to CFDIU in case of TR FAULT.
-the other used for the reset from CFDIU.
CFDS Architecture (Liaison with TR's and BCL's)
Figure 006
1EFF : ALL 1 24-30-00 Page 15
1 1 Feb 01/99
1 1
1CES 1
DC GENERATION - DEACTIVATION/REACTIVATION
_________________________________________ TASK 24-30-00-040-001 Perform a Charging Cycle on the Battery Associated With the Operative Battery
Charge Limiter (BCL)
1. Reason for the Job
__________________
Refer to the MMEL TASK: 24-30-03
DC Generation
Battery Charge Limiter
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific access platform 1.8 m (5 ft. 11 in.)
B. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
24-38-51-000-001 Removal of the Batteries (2PB1, 2PB2) 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 31-60-00-860-001 EIS Start Procedure 31-60-00-860-002 EIS Stop Procedure
3. Job Set-up
__________ Subtask 24-30-00-010-053
A. Get access to the Avionics Compartment
(1)
Put an access platform at the avionics compartment door 822.
(2)
Open the access door 822.
(3)
Open the access panel of the BATTERY power center 105VU.
Subtask 24-30-00-865-051
B. Make sure that this(these) circuit breaker(s) is(are) closed:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------105VU ELEC/HOT BUS/702PP SPLY 5PB2 D02 105VU ELEC/HOT BUS/701PP SPLY 5PB1 D01 105VU ELEC/BAT REF/BCL2 9PB2 F02 105VU ELEC/BAT REF/BCL1 9PB1 F01 105VU ELEC/BAT BUS/REF/BCL1 8PB1 G01 105VU ELEC/BAT BUS/REF/BCL2 8PB2 J02 125VU BAT BUS/301PP/SPLY 11PB CC01
Subtask 24-30-00-860-052
C. Aircraft Maintenance Configuration
(1)
Energize the aircraft electrical circuits
(Ref. TASK 24-41-00-861-002).
(2)
In the cockpit, on the ELEC panel 35VU:
-make sure that the BAT 1 and BAT 2 pushbutton switches are released (the OFF legends are on).
(3)
Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001).
4. Procedure
_________
R **ON A/C 001-049, 051-099, 101-149, 201-299,
Subtask 24-30-00-040-050
A. Do a charging cycle of the battery 1 (2) related to the BCL 1 (2) in operation.
(1) If:
-
the failure of the BCL 1(2) occurred during the last flight and the time the aircraft was on ground was not more than 3 hours, or
-
the BCL 1(2) did not operate during the last flight and the time the aircraft was on ground was not more than 3 hours:
(a)
on the ECAM control panel:
-push the ELEC key to get the ELEC system page.
(b)
In the cockpit, on the ELEC panel 35VU:
-push the related BAT 1 (2) pushbutton switch to start the charging cycle of the battery 1 (2).
(c)
On the lower ECAM display unit:
-
the green line between the BAT 1 (2) indication and the DC BAT busbar indication comes into view. The arrow points to the BAT 1 (2) indication,
-
the related parameter indications (voltage and current) come into view green.
(d)
On the ELEC system page, make sure that the ground power-unit voltage stays above 114VAC during the charge.
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