(i)
 ALT DYNAMIC SLEW (OUTPUT TESTS menu/SLEW TESTS submenu) (Ref. Fig. 029, 030) The activation of the ALT DYNAMIC SLEW test causes the ADR to output a simulated ramp of altitude (label 203) between low and high altitude limits specified by the operator. These limits, as well as the slew rate, are entered by the operator by means of the MCDU keyboard. The altitude limit values are tested to be within -2000 and +50,000 ft. The altitude lower limit is tested to be less than the altitude upper limit. The altitude slew rate is tested to be within 1 to +20,000 ft/mn.

 (j)
 CAS DYNAMIC SLEW (OUTPUT TESTS menu/SLEW TESTS submenu) (Ref. Fig. 029, 031) The activation of the CAS DYNAMIC SLEW test causes the ADR to output a simulated ramp of computed airspeed (label 206) between low and high speed limits specified by the operator. These limits, as well as the slew rate, are entered by the operator by means of the MCDU keyboard. The CAS limit values are tested to be within 0 and +450 kts. The CAS lower limit is tested to be less than the CAS upper limit. The speed slew rate is tested to be within 1 to +100 Kts/mn.

 (k)
 AOA SENSOR TEST (OUTPUT TESTS menu) (Ref. Fig. 029, 032) The activation of the AOA SENSOR TEST causes the ADR to output the actual measured values of indicated and corrected AOA with an SSM coded FT, and the AOA special test discrete output to be commanded to the ground state, which causes the AOA sensor to be commanded to a fixed position greater than the stall warning threshold. Thus, the Flight Warning Computer (FWC) activates the aural stall warning.

 (l)
 GROUND REPORT (Ref. Fig. 029) This item reports all internal faults detected since the last landing.

 (m)
 INPUT STATUS (Ref. Fig. 029, 033) This item describes the current state/value of the selected ADR inputs (discrete, analog and binary inputs).

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 ADIRS BITE - ADR Main Menu 6/8
 Figure 031

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 ADIRS BITE - ADR Main Menu 7/8
 Figure 032

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 ADIRS BITE - ADR Main Menu 8/8
 Figure 033

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 C. Power-up Test Initialization and Cockpit Repercussions
 (1)
 Conditions of power-up test initialization

 -How long the computer must be de-energized: >20 s.
 -A/C configuration:
 -A/C on ground and OFF/NAV/ATT selector switch related to IR 1 (2)
 (3) (located on the ADIRS panel) set to OFF for 20 s at least then to NAV.

 (2)
 Progress of power-up tests

 (a)
 Duration: 5 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):

 -ADIRS panel:
 -ON BAT legend annunciator on for 5 s, 2 s after power-up test initialization.

 (3)
 Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed).

 (a) Test pass:
 -ALIGN legend of the IR 1 (2) (3) annunciator on.
 NOTE : It means that the system is in align mode.
____
 (b) Test failed:
 -ECAM warning
 -
NAV IR 1 (2) (3) FAULT or

 -
NAV ADR 1 (2) (3) FAULT
 depending on the faulty part.

 -ADIRS panel:
 -FAULT legend of the IR 1 (2) (3) annunciator on or FAULT/OFF
 of the ADR 1 (2) (3) pushbutton switch on.
 depending on the faulty part.

 NOTE : In case of failure, set the DISPLAY/DATA selector switch
____ to STS then do the troubleshooting procedure on the system according to the error code displayed on the ADIRS panel.
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 STANDBY NAVIGATION SYSTEMS - ADJUSTMENT/TEST
____________________________________________ TASK 34-20-00-710-001 ISIS Reset
 1.
 Reason for the Job

__________________
 Refer to the MPD TASK: 342200-04

 2.
 Job Set-up Information

______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
　
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