(b) Warning Annunciators
-FAIL indicator light
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R (c) Not Applicable
R **ON A/C 051-099,
R (3) Indicators
R R R (a) ON A green LED, which is on when the 115V is powered on.
R R R (b) STATUS A red LED is on when an operating error is detected.
R R R (c) DISK LOW A red LED is on when the remaining unrecorded disk capacity is less than 30%. (The value of 30% is modifiable by software)
**ON A/C ALL
7. Operation/Control and Indicating________________________________
R **ON A/C 001-049, 051-099, 101-105,
(Ref. Fig. 019)
R A. Energization With the oil pressurization of one or both engines, the power interlock is released for supply of the DFDR with 115V/400 Hz. The FDIU and the QAR are supplied directly from the busbar. The power interlock switches the QAR RUN control. A dimmable power bus supplies the CTL PNL indicators. For maintenance and test purposes on the ground and for preflight checks there is an override function to supply the DFDR and to run the QAR. When the GND/CTL button on the CTL PNL is pushed an electric latch holds the override function. The blue 'ON' pushbutton light comes on. The override function supplies the equipment until the GND/CTL button is pushed again or the automatic power interlock becomes active.
QAR - Interface
Figure 018A
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1 1
1CES 1
Power Interlock Figure 019
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R **ON A/C 106-149, 211-299, 301-399, 401-499,
(Ref. Fig. 019A)
A. Energization With the oil pressurization of one or both engines, the power interlock is released for supply of the DFDR with 115V/400 Hz. The FDIMU is supplied directly from the busbar. A dimmable power bus supplies the CTL PNL indicators. For maintenance and test purposes on the ground and for preflight checks there is an override function to supply the DFDR. When the GND/CTL button on the CTL PNL is pushed an electric latch holds the override function. The blue 'ON' pushbutton light comes on. The override function supplies the equipment until the GND/CTL button is pushed again or the automatic power interlock becomes active.
**ON A/C 151-199, 201-210,
(Ref. Fig. 019B)
A. Energization With the oil pressurization of one or both engines, the power interlock is released for supply of the DFDR with 115V/400 Hz. The FDIU is supplied directly from the busbar. A dimmable power bus supplies the CTL PNL indicators. For maintenance and test purposes on the ground and for preflight checks there is an override function to supply the DFDR. When the GND/CTL button on the CTL PNL is pushed an electric latch holds the override function. The blue 'ON' pushbutton light comes on. The override function supplies the equipment until the GND/CTL button is pushed again or the automatic power interlock becomes active.
**ON A/C ALL
B. Control
(Ref. Fig. 020)
(1) Override of Power Interlock With the electrically latched GND/CTL button it is possible to override the power interlock, so that the system can be supplied for preflight checks or for maintenance and test purposes. The GND/CTL button is installed on the CTL PNL. To prevent the erasure of stored data, you must not unnecessarily activate the override function of the power interlock.
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Power Interlock Figure 019A
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R Power Interlock Figure 019B
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CTL PNL Figure 020
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(2) Event Mark (Ref. Fig. 021) An EVENT BUTTON is installed to record an EVENT MARK on the DFDR.
**ON A/C 001-049, 051-099, 101-105,
C. Indication (Ref. Fig. 020) If you push the GND/CTL button on the control panel, an electric latch holds the override function. The blue GND/CTL button light comes on . The status line of the DFDR and the QAR are connected to the FDIU. In case of a Class II fault the FDIU transmits a failure message to the CFDS. These failures are not indicated to the crew in flight but are the subject of an ECAM report on the ground after shut down of the engines. If a Class III fault occurs the related flag is set in the fault memory of the FDIU (up to 30 faults). This fault information is sent to the CFDIU. These Class III faults can be displayed on the MCDU screen via menu function (System Report/ Instruments/FDIU). These faults can wait until the next scheduled maintenance check. In case of malfunction of the CFDS, DFDR FAIL and FDIU FAIL are sent directly via SDAC to the ECAM screen. The status signal DFDR FAULT and FDIU FAULT are suppressed in flight phase 3,4,5,7 and 8 by the FWC.
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