(2)
Power supply monitoring
-5V : permanently monitored by a "hardware" comparator.
-transducer supply voltage and 15VDC : permanently monitored and encoded (software comparator).
(3)
Permanent software monitorings
Software monitorings are performed as "background tasks":
-checksum computations of the program memories.
-crossed monitoring between the processors of a same unit which use the dual-access memories. Monitoring of the co-processor by the main processor Mutual monitoring of the main processor/ARINC processor : the ARINC processor can directly cut off all the discrete outputs and relays.
(4)
Quartz clock monitoring Each of the ARINC and main processors has its own quartz clock. A "hardware" comparator permits to detect any relative variation between the two clocks.
(5)
Inter-unit monitoring Two ARINC 429 links are dedicated to crosstalk between the two units. The monitoring is made at software level and consists in the comparison of variables which transit on these buses.
E. Behavior upon Power Rise and Cutoff R (Ref. Fig. 028)
(1)
Transparency The computer behavior is not altered if its power supply disappears for a period less than or equal to 20 ms.
(2)
Startup If the power supply is absent for more than 20 ms, two cases are considered:
(a) If at least one hydraulic supply is present, the computer starts after it has performed short tests (duration <1.5 s ):
-timer test
-interrupt test
-RAM partial test
(b) If the 3 hydraulic power supplies are low, two cases are considered: 1- Power supply switch-off less than 3s, the short test is performed (see (a)) 2- Power supply switch-off during more than 3s, the long test is performed :
-UC test
-watchdog test
-checksum test
-complete RAM test
-timer test
-IT test
-bus error test
F. Behavior upon Action on the OFF/R Pushbutton Switch
R (Ref. Fig. 029) In normal configuration, the pushbutton switch is pushed. The change from OFF to ON (startup) when the power supply is present leads to computer startup:
-
if 1 hydraulic pressure is high : short test
-
if 3 hydraulic pressures are low : long test
R ELAC Behavior Upon Power Supply Rise Figure 028
1EFF : 1 1 1CES ALL 1 111 27-93-00 Page 61 May 01/02
R ELAC Behavior Upon Pushbutton Reset Figure 029
1EFF : 1 1 1CES ALL 1 111 27-93-00 Page 62 May 01/02
R **ON A/C 001-049, 051-060, 101-101,
G. Power-up Tests Initialization and Cockpit Repercussions
(1)
Conditions of power-up tests initialization
-How long must the computer be de-energized ?
30 ms by C/B
or
ELAC P/BSW selected OFF then ON
-A/C configuration: hydraulic system depressurized
(2)
Progress of power-up tests
(a)
Duration: 8 s
(b)
Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration, but these can be disregarded):
-
ECAM F/CTL page
* ELAC in amber and associated aileron servo control amber boxed
-
ECAM warning
*
F/CTL ELAC 1(2) FAULT during 8 s if subsequent to C/B reset
*
none if subsequent to P/BSW reset
-F/CTL panel
* FAULT legend of ELAC P/BSW on during 8 s
(3)
Results of power-up tests (cockpit repercussions, if any, in case of tests passed failed)
(a) Tests passed
-
ECAM F/CTL page
* ELAC in green
-
ECAM warning
* F/CTL ELAC 1(2) disappears
-F/CTL panel
* FAULT legend of ELAC P/BSW off
(b) Tests failed
-
ECAM F/CTL page
* ELAC in amber and associated aileron servo control amber boxed
-
ECAM warning
* F/CTL ELAC 1(2) FAULT
-F/CTL panel
* FAULT legend of ELAC P/BSW on
R 1EFF : 001-049, 051-060, 101-101, 1 27-93-00Page 63 1 1 May 01/05 1 1 1CES 1 ELAC SYSTEM (ELEVATOR AILERON COMPUTER) - DEACTIVATION/REACTIVATION
___________________________________________________________________
TASK 27-93-00-040-001
Deactivation of the Elevator Aileron Computer
1. Reason for the Job__________________
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