ADIRS BITE - ADR and IR Systems - Class 3 Faults
 Figure 029

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 ADIRS BITE - ADR and IR Systems - Faults without any Message 1/2
 Figure 030

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 ADIRS BITE - ADR and IR Systems - Faults without any Message 2/2
 Figure 031

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 ADIRS BITE - Activation of ADR Interactive Function
 Figure 032

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 (b) IR interactive function : select NAV from the SYSTEM REPORT/TEST page and then the selected IR (1 to 3) to activate the IR interactive mode and display the main menu (Ref. Fig. 033)
 NOTE : The figures enclosed in this document are provided for the
____ layout of the different pages. Fault messages, trouble shooting data and input discrete status are provided for information.
 (2) Air Data Interactive function description
 (a)
 Last Leg Report
 (Ref. Fig. 034)

 (b)
 Previous Legs Reports
 (Ref. Fig. 034)

 (c)
 LRU Ident (Ref. Fig. 034) On page 1/2, the Part Numbers and the Serial Numbers of the ADIRU and the total pressure ADM are displayed. On page 2/2, the associated data to the remaining ADM are displayed.

 (d)
 Ground Scanning (Ref. Fig. 035) The Ground Scanning function performs most of the continuous tests. All tests with an important time delay (temperature ...) are not performed within this function.

 (e)
 Trouble Shooting Data (Ref. Fig. 036) A maximum of sixteen 16-bit words can be recorded for the Trouble Shooting Data.

 (f)
 Class 3 Faults
 (Ref. Fig. 034)

 (g)
 System test (Ref. Fig. 037) The system test function performs power-up tests and various continuous tests to provide a complete status of the ADR part of the ADIRS. It is necessary to re-initialize the system for IR part because the navigation data are erased by the test of the RAM performed at the power-up.

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 ADIRS BITE - Activation of IR Interactive Function
 Figure 033

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 ADIRS BITE - ADR Main Menu 1/2
 Figure 034

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 ADIRS BITE - ADR Ground Scanning
 Figure 035

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 ADIRS BITE - ADR Main Menu 2/2
 Figure 036

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 ADIRS BITE - ADR System Test
 Figure 037

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 (h) Output Tests The output tests are divided in three parts :
 -Slew tests
 -Interface test
 -AOA test.
 1 Slew tests
_
 (Ref. Fig. 038)
 The Slew tests are divided in two parts :

 -Altitude dynamic slew This function slews the altitude (label 203) between the lower limit and the upper limit (up or down)) at the altitude slew rate. These data are entered by the operator. The altitude limit values are tested to be within -2000 and +50000 feet. 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 +20000 ft/mn.
 -CAS dynamic slew This function slews the Computed Air Speed (label 206) between the lower limit and the upper limit (up or down) at the CAS slew rate. These data are entered by the operator. The CAS limit values are tested to be within 0 and +450 knots. The CAS lower limit is tested to be less than the CAS upper limit. The CAS slew rate is tested to be within 1 to +100 Kts/mn. When the upper (or lower) limit is reached at the end of the ramp (END OF SLEWING page), the limit value is maintained till the operator pushes the key adjacent to the RETURN or the ALT DYNAMIC SLEW indication.
 2 Interface test
_ (Ref. Fig. 039) Initiation of the ADR Interface Test causes the following sequence to occur :
 -0-5 seconds (Failure Warning Test) For 0-5 seconds after initiation of the test mode, the ADR outputs are transmitted per tables as follows. Since this is the failure warning test period, the BCD output parameters are not transmitted and the SSM of the BNR parameters are set to F/W. Timing tolerance is plus or minus 0.5 second.
　
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