ADIRS BITE - Inertial Reference System - Class 3 Faults
 Figure 008A

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 ADIRS BITE - Inertial Reference System - Class 2 Internal Faults
 Figure 009

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 (a) Align in air The test fails if, with the OFF/NAV/ATT selector switch on the CDU in NAV position, the aircraft is detected in flight (TAS greater than 100 kts) at power-up or during the ALIGN phase. The following occurs:
 -NAV IRi FAULT message is displayed on the upper ECAM display unit.
 -
the FAULT legend of the IR pushbutton switch, on the CDU, comes on.

 -
the IN FLIGHT ALIGNMENT message is sent to the CFDIU

 -all BNR output labels are coded Failure Warning (F/W) and all BCD labels are not transmitted.
 -the SELECT ATT indication is displayed on the CDU (DATA DISPLAY
 selector switch in STS position). The IR portion can be recovered by setting the OFF/NAV/ATT selector switch on the CDU to ATT and by applying the procedure (level flight) to initialize the ATT mode.
 (b) Position-entry test
 -Initial position (latitude, longitude) must compare within one degree of the last computed latitude and longitude from the previous flight. If a miscompare exists, then the NOT ALIGN message is displayed on the upper ECAM display unit with a text indicating to enter again the initial position (Ref. 34-14 Para. 3.). The miscompare is removed if the new entered position is identical to the previous one or is within the one-degree threshold. If not, the system waits for other position entry.
 -At the end of the alignment submode, the IR portion compares the initial latitude to a self-computed latitude. The test fails and the NOT ALIGN message is displayed on the upper ECAM display unit with action to enter again the position, when:
 . the cosine of entered latitude differs from the cosine of computed latitude by more than 0.01234 or
 . the sine of entered latitude differs from the sine of computed latitude by
 more than 0.01234. The miscompare is removed if a subsequent entry of latitude passes the test. If the sin/cos test fails two times with identical initial latitude entries, the IR system goes in a fault reaction: IR FAULT warning message on the upper ECAM display unit and FAULT legend on the CDU on, invalid outputs.
 NOTE : No fault message is sent to the CFDIU.
____
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 (c) Test on motion If taxiing or towing causes a step input which exceeds 0.11 ft/s in the X or Y velocity, the align process is stopped with a message on the upper ECAM display unit indicating IR NOT ALIGN and excessive motion (Ref. 34-14). The status matrix of the attitude data (pitch, roll, heading) is set at NCD which implies a flag on the PFD.
 NOTE : No fault message is sent to the CFDIU.____
 When the motion is no more detected, the IR reverts to the beginning of the align submode. It is not necessary to re-initialize the position.
 (3) Air data reference faults 
R  **ON A/C 051-099, 106-149, 204-299, 301-399, 
R  (Ref. Fig. 010) 
R  **ON A/C 401-499, 
R  (Ref. Fig. 010A) 
R  **ON A/C 051-099, 106-149, 204-299, 301-399, 401-499, 
R  (Ref. Fig. 011, 012, 013, 014, 015, 016)
 (a) SDI validity test at power-up A number of data are computed in the ADR portion according to air data correction laws (SSEC, AOA) which are dependent on the ADR side (SDI = 1, 2, 3). The determination of the SDI at power-up is consolidated by the ADR with a logic vote between the SDI discrete inputs and the SDI read on the labels received from the total pressure ADM and the static pressure ADM. Faults are either miscompare between the different sources of SDI or unability to compute the SDI. In this last case, detection of the fault leads to the ADR FAULT annunciation (message on the upper ECAM display unit; FAULT legend on the CDU) associated to invalid outputs. A number of messages can be sent to the CFDIU on the label 356 according to the detected miscompare. These messages point the ADIRU or ADM pin program or a mix of them: 

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 ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 1/4

 Figure 010 
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R ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 1/4
　
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