(b)
3 or FULL.
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E. Computer Behavior upon Power Rise and Cutoff
(1) Transparency The computer behavior is not altered if its power supply disappears for a period of less than or equal to 25 ms.
F. Automatic Integrity Test (AIT) Initialization and Cockpit Repercussions
(1) Conditions of AIT initialization
(a) How long the computer must be de-energized:
-more than or equal to 50 ms
(b) A/C configuration:
- on the ground with the slats and flaps stopped
-CFDS label 227 set to NULL
-new date from CFDS compared to last date AIT satisfactorily done or
- on the ground with the slats and flaps stopped
-no date information from CFDS
-CFDS label 227 possibly not received = AIT done
NOTE : For the AIT to function, A/C on the ground is specified as
____ follows: the CFDS label 227 is transmitting code NULL and the A/C on the Ground (AOG) discrete (through a relay controlled by the LGCIU) is showing ON GROUND. If CFDS data is not available, only the AOG discrete is used.
NOTE : The AIT is run automatically once a day. If the SFCC is
____ de-powered (through CBs or after engines stopped) the same day, the AIT will not run. But if the last AIT has failed or date information is not available from the CFDIU (channel not serviceable and failure shown on ECAM display), the test will run again 60 s after SFCC power-up (or if power interrupt is more than 50 ms).
(2) Progress of AIT
(a)
Duration: approximately 2 s
(b)
Cockpit repercussions directly linked to AIT accomplishment (other repercussions may occur depending on the A/C configuration, but these can be ignored):
NONE
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(c) The AIT checks the following areas of hardware:
-Processors
-EPROM code stores
-Areas of RAM
-Output consolidation logic
-Power supply
-Input circuitry
-Cross computer WTB ARM signals
(3) Results of AIT (cockpit repercussions, if any, in case of test passed or test failed)
(a) Test passed
-ECAM warning
* none
(b) Test failed
-
ECAM warning (if hydraulic circuit is pressurized or in flight phase 1 or 10)
* FLT CTL FLAP SYS 1(2) FAULT or FLT CTL SLAT SYS 1(2) FAULT
-
ECAM warning (if hydraulic circuit is de-pressurized and not in flight phase 1 or 10)
* none
8. Parameter List
______________
A. Description of the Parameter List
The parameter list is put in sequence to refer to the connected ARINC 429
data buses.
The connected systems (e.g. FAC, ECU, EEC, etc.) and the ATA chapter
numbers that agree with it are shown in the header on the left side of
each page of the given lists.
The columns are described as follows:
---------------------------------------------------------------------Column | Description -------------------|-------------------------------------------------1st | EQ.SYS.LAB.SDI = Parameter number
SYS.LAB.SDI | | System number: Refer to the system which | sends out the parameter that agrees with it: | 1 for system one | 2 for system two | 3 for system three | Label of the parameter, octal value | refer to ARINC 429.
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---------------------------------------------------------------------
Column | Description -------------------|-------------------------------------------------
| SDI gives the Source/Destination Identifier
| which is used by the system for the
| parameter that agrees it:
| 00 means SDI 00 (0)
| 01 means SDI 01 (1)
| 10 means SDI 10 (2)
| 11 means SDI 11 (3)
------------------|-------------------------------------------------
2nd | PARAMETER
PARAMETER | Parameter name
------------------|-------------------------------------------------
3rd | RANGE
RANGE |
| Three different types of ranges are shown in
| this column:
| The first one, shown by a W (WORDRANGE),
| is related to the ARINC 429 data bus. This
| shows the maximum value of the parameter that
| can be transmitted on the bus. It must agree
| with the number of data bits (see column DATA
| BITS) and the resolution (R) of the
| parameter (see column ACCURACY).
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