-Power off conditions
Discrete 1 = OPEN
Discrete 2 = OPEN
Discrete 3 = OPEN
Discrete 4 = OPEN
-CAS detected failure condition
Discrete 1 = previous state
Discrete 2 = previous state
Discrete 3 = previous state
Discrete 4 = OPEN
4 AOA special test
_ The ADR provides an OPEN/GROUND output discrete to drive the AOA self-test. The AOA self-test is commanded via the CFDIU interface bus. When the AOA test is active, the AOA sensor is offset to +15 deg. (plus or minus 1 deg.). All AOA dependent parameters reflect this offset and their SSMs indicate Functional Test (FT). The RETURN command from the MCDU results in the discrete output set to OPEN. Ref. 34-18-00 for more details.
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3. Operation/Control and Indicating
________________________________
A. Control
(1) ADIRS Control and Display Unit (CDU) (Ref. Fig. 010) The ADIRS CDU provides the control and warning of the three ADRs by means of three ADR illuminated pushbutton switches:
-the pushbutton switch is used to disable the ADR output buses. It is a momentary action pushbutton switch
-
when the ADR output buses are disabled, the ADR controls the activation of the ADR OFF legend by its output discrete: ADR OFF status
-
when an ADR failure is detected, the ADR controls the activation of the ADR FAULT legend by its output discrete: ADR FAULT
-each ADR is de-energized when the associated OFF/NAV/ATT selector switch is set to OFF
-when the associated OFF/NAV/ATT selector switch is set to NAV or ATT, each ADR is switched on independently of the previous selection on the ADR pushbutton switch.
B. Indicating Altitude (ALT), Computed Airspeed (CAS), Mach number (M) and Vertical Speed (V/S) are computed by the ADIRU (ADR portion), processed by the associated DMC and displayed on the PFDs. True Airspeed (TAS) is supplied in the same way but is displayed on the NDs. In normal configuration, with the AIR DATA selector switch in NORM position, the ADR 1 displays information on CAPT PFD and ND. The ADR 2 displays information on F/O PFD and ND. Static Air Temperature (SAT) and Total Air Temperature (TAT) are also supplied in the same way but are permanently displayed on the lower part of the lower ECAM DU. These items of information are displayed by the ADR 2.
(1) PFD display For further details concerning speed, altitude or vertical speed scale, Ref. 31-64-00.
(a) Computed Airspeed (CAS) (Ref. Fig. 011) The CAS indication is displayed in analog form by means of a white tape with graduations every 10 kts and digital values every 20 kts. This tape moves up and down so as to indicate the A/C actual speed value in front of a fixed yellow reference line.
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ADR Control on CDU
Figure 010
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Computed Airspeed and Mach Indication Display
Figure 011
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The displayed part of the scale represents an 84 kts range. The
scale is graduated from 30 kts to 520 kts and the digital values
from 40 to 520 kts (item A).
In no case can the displayed CAS be lower than 30 kts.
In case of computed airspeed failure, the speed scale goes out of
view and is replaced by a red SPD flag (item B).
(b)
Mach number (M) When the Mach number is above 0.5, it is displayed just below the speed scale. In case of failure, a red MACH flag is presented.
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