ADIRS BITE - IR System - Class 1 Internal Faults 5/6
 Figure 008

R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 12 1 1 Config-1 May 01/05 1 1 1CES 1

 ADIRS BITE - IR System - Class 1 Internal Faults 6/6
 Figure 009

R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 13 1 1 Config-1 May 01/05 1 1 1CES 1

 ADIRS BITE - IR System - Class 2 External Faults
 Figure 010

R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 14 1 1 Config-1 May 01/05 1 1 1CES 1R **ON A/C 001-049, 101-105, 151-199, 201-203,

 -Class 2 Internal Faults
 (Ref. Fig. 011)
 -Class 3 External Faults
 (Ref. Fig. 012)
 -Class 3 Internal Faults
 (Ref. Fig. 013)
 The IR portion performs tests which result in warnings (fault
 annunciation, invalid outputs).
 But, for these warnings, no message is sent to the CFDIU as these
 faults are due to an incorrect operational use of the system and not
 to a system fault.
 These tests are:

 -align in air
 -position-entry test (comparison with the last stored position and computed latitude).
 -Test on motion
 (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:
 -
the NAV IRi FAULT message is displayed on the upper ECAM DU.

 -
the FAULT legend of the IR annunciator, on the CDU, flashes.

 -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.
R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 15 1 1 Config-1 May 01/05 1 1 1CES 1

 ADIRS BITE - IR System - Class 2 Internal Faults
 Figure 011

R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 16 1 1 Config-1 May 01/05 1 1 1CES 1

 ADIRS BITE - IR System - Class 3 External Faults
 Figure 012

R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 17 1 1 Config-1 May 01/05 1 1 1CES 1

 ADIRS BITE - IR System - Class 3 Internal Faults
 Figure 013

R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 18 1 1 Config-1 May 01/05 1 1 1CES 1

 -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 DU with action to enter again the position, when: . The difference between the entered latitude and the computed
 latitude is greater than 0,5.. 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 DU and FAULT legend on the CDU on, invalid outputs.
 (c) Test on motion If taxiing or towing causes a step input which exceeds 0.2 ft/s in the X or Y velocity, or 2./s for the azimuth rate, the align process is stopped with a message on the upper ECAM DU indicating IR NOT ALIGN and excessive motion (Ref. 34-14) with the code NCD on the status matrix of the attitude (pitch, roll, heading) which implies a flag on the PFD. 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 .Class 1 External Faults (Ref. Fig. 014, 015) .Class 1 Internal Faults (Ref. Fig. 016, 017, 018, 019, 020, 021, 022, 023) .Class 2 Internal Faults (Ref. Fig. 024) .Class 3 Faults (Ref. Fig. 025) .Class 2 and 3 External Faults (Ref. Fig. 026)
 (a) Cross-channel comparison tests A cross-channel comparison of pressures, angle-of-attack, and temperature parameters is performed to identify drifted air data input sensors. These tests are done for maintenance purpose only and they have no operational effects (no fault warning, output parameters are always valid, class 3 failures). To run these tests each ADR portion receives one ADR output bus of the other side, computers (Ref. Fig. 001) As the air data sensors are installed per design in different zones and measure different values, the comparison can only be done in an identified flight phase.
　
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