ADIRS - BITE - DESCRIPTION AND OPERATION

** ON A/C NOT FOR ALL

1. General
The Built In Test Equipment facilitates maintenance on in-service aircraft.
It detects and identifies faults related to the Air Data/Inertial Reference System (ADIRS) and reports them to the Centralized Fault Display Interface Unit (CFDIU).
The BITE is included in the following LRUs:

Air Data/Inertial Reference Unit (ADIRU)
Air Data Module (ADM).

It is linked to the CFDIU through the ADIRU (ADR and IR portions) which summarizes the BITE results for its own channel.

ADIRU - Architecture and Interface with CFDIU ** ON A/C NOT FOR ALL

The ADM performs various tests to detect its own faults (watchdog timer, RAM addressing, ROM, CPU, RAM, NVM, etc.) and failed input signals (check of programming pins).
Faults are annunciated to the ADR by omission or labeling of a faulty output word (pressure label) and through the use of a discrete fault-code word output on the ARINC bus. Fault reports are also stored in a non-volatile memory inside the ADM.
The IR BITE monitors:

the performance of the Digital Signal Processor C25
the outputs of the INTEL 80960
external inputs (both digital and discrete)
the functionality of other IR internal hardware including the power supply and the inertial sensors (gyro, accelerometers).
These BITE tests are performed either at power up or continuously (Ref. Para. 3.A.(2)).
Some of them enable to monitor operation errors. These tests are:
Align in air
Excessive Motion
Latitude comparison test.
They result in IR warnings but without fault message sent to the CFDIU. Tests and fault reactions are described in Para. 3.B.
The ADR BITE monitors:
the ADR outputs of the INTEL 80960 processor
the functionality of other ADR internal hardware
the status of analog, digital and discrete inputs
cross-channel comparisons with the other ADRs.
These BITE tests are performed either at power-up or continuously (Ref. Para. 3.A.(3)) with the exception of cross-channel comparisons which are run once at takeoff.
The common BITE monitors the computer performances (INTEL 80960 processor and memories) with the following tests: watchdog timer, checksum, RAM pattern monitor.
The ADR and IR BITEs send reports to the CFDIU through the ARINC output bus, on label 356. These reports memorize the faults which occurred during the last 63 flight legs with their context. They operate in two modes:
NORMAL mode: fault reporting to the CFDIU during the flight
INTERACTIVE mode: on the ground (access by the MCDU MENU pages (Ref. Para. 3.B.)).

The Built In Test Equipment facilitates maintenance on in-service aircraft.
It detects and identifies faults related to the Air Data/Inertial Reference System (ADIRS) and reports them to the Centralized Fault Display Interface Unit (CFDIU).
The BITE is included in the following LRUs:

Air Data/Inertial Reference Unit (ADIRU)
Air Data Module (ADM).
Control and Display Unit (CDU).

It is linked to the CFDIU through the ADIRU (ADR and IR portions) which summarizes the BITE results for its own channel.

ADIRU - Architecture and Interface with CFDIU ** ON A/C NOT FOR ALL

The performance of the Digital Signal Processor C25
The outputs of the INTEL 80960
External inputs (both digital and discrete)
The functionality of other IR internal hardware including the power supply and the inertial sensors (gyro, accelerometers).
These BITE tests are performed either at power up or continuously (Ref. Para. 3.A.(2)).
Some of them enable to monitor operation errors. These tests are:
Align in air
Excessive Motion
Latitude comparison test.
They result in IR warnings but without fault message sent to the CFDIU. Tests and fault reactions are described in Para. 3.B.
The ADR BITE monitors:
The ADR outputs of the INTEL 80960 processor
The functionality of other ADR internal hardware
The status of analog, digital and discrete inputs
Cross-channel comparisons with the other ADRs.
These BITE tests are performed either at power-up or continuously (Ref. Para. 3.A.(3)) with the exception of cross-channel comparisons which are run once at takeoff.
The common BITE monitors the computer performances (INTEL 80960 processor and memories) with the following tests: watchdog timer, checksum, RAM pattern monitor.
The ADR and IR BITEs send reports to the CFDIU through the ARINC output bus, on label 356. These reports memorize the faults which occurred during the last 63 flight legs with their context. They operate in two modes:
NORMAL mode: fault reporting to the CFDIU during the flight
INTERACTIVE mode: on the ground (access by the MCDU MENU pages (Ref. Para. 3.B.)).

** ON A/C NOT FOR ALL

2. Component Location

A. Computers Directly Linked to the CFDS

FIN	FUNCTIONAL DESIGNATION	ZONE	ATA REF
** ON A/C NOT FOR ALL
1FP1	ADIRU-1	127	34-12-34
1FP2	ADIRU-2	128	34-12-34
1FP3	ADIRU-3	120	34-12-34

B. ADIRS Control Panel

-------------------------------------------------------------------------------

! FIN ! FUNCTIONAL DESIGNATION ! PANEL ! ZONE ! ACCESS ! ATA !

! ! ! ! ! DOOR ! REF. !

!-----------------------------------------------------------------------------!

! 41VU ! MSU-ADIRS ! 41VU ! 211 ! ! !

-------------------------------------------------------------------------------

C. Other LRUs of the System

FIN	FUNCTIONAL DESIGNATION	ZONE	ATA REF
** ON A/C NOT FOR ALL
3FP1	SENSOR-ANGLE OF ATTACK, 1	231	34-11-19
3FP2	SENSOR-ANGLE OF ATTACK, 2	232	34-11-19
3FP3	SENSOR-ANGLE OF ATTACK, 3	127	34-11-19
11FP1	SENSOR-TAT, 1	121	34-11-18
11FP2	SENSOR-TAT, 2	122	34-11-18
9DA1	PROBE-PITOT, 1	125	34-11-15
9DA2	PROBE-PITOT, 2	126	34-11-15
9DA3	PROBE-PITOT, 3	125	34-11-15
7DA1	PROBE-L STATIC, 1	127	34-11-16
7DA2	PROBE-L STATIC, 2	127	34-11-16
7DA3	PROBE-L STATIC, 3	121	34-11-16
8DA1	PROBE-R STATIC, 1	128	34-11-16
8DA2	PROBE-R STATIC, 2	128	34-11-16
8DA3	PROBE-R STATIC, 3	122	34-11-16
19FP1	ADM-L TOTAL PRESSURE	125	34-11-17
19FP2	ADM-R TOTAL PRESSURE	126	34-11-17
19FP3	ADM-STBY TOTAL PRESSURE	125	34-11-17
19FP4	ADM-R STATIC PRESSURE	128	34-11-17
19FP5	ADM-L STATIC PRESSURE	127	34-11-17
19FP6	ADM-R STATIC PRESSURE	128	34-11-17
19FP7	ADM-L STATIC PRESSURE	127	34-11-17
19FP8	ADM-STBY STATIC PRESSURE	121	34-11-17

** ON A/C NOT FOR ALL

3. System Description

A. Reporting Function - General
Each ADIRS BITE message is described in the following pages, with the corresponding fault description and the consequences on the system and in the cockpit.

IR faults are classified as follows:
. class 1 faults
. class 2 faults
. class 3 faults.
ADR faults:
. class 1 faults
. class 2 faults
. class 3 faults.
Common faults (IR + ADR)
. class 1 faults
. class 2 faults
. class 3 faults.

NOTE: Bit 13 of ADR label 270 indicates an ADR fault (bit 13 = 1)

use of i, j, k indexes in BITE messages:

. barring explicit restriction, ADIRUi stands for ADIRU 1,

ADIRU 2 or ADIRU 3

. ADMi, ADMj, or ADMk: i, j, and k values are specified

below the message.

ECAM messages:

. xxx stands for CAPT or F/O, depending on the ADIRU side (1

or 2)

. the letter in parentheses indicates the color used to

display the text: (A) Amber, (C) Cyan and (W) White.

B. Reporting Function - Inertial Reference Faults
-Class 1 External Faults

ADIRS BITE - IR System - Class 1 External Faults 1/2 ** ON A/C NOT FOR ALL

ADIRS BITE - IR System - Class 1 External Faults 2/2 ** ON A/C NOT FOR ALL

-Class 1 Internal Faults

ADIRS BITE - IR System - Class 1 Internal Faults 1/6 ** ON A/C NOT FOR ALL

ADIRS BITE - IR System - Class 1 Internal Faults 2/6 ** ON A/C NOT FOR ALL

ADIRS BITE - IR System - Class 1 Internal Faults 3/6 ** ON A/C NOT FOR ALL

ADIRS BITE - IR System - Class 1 Internal Faults 4/6 ** ON A/C NOT FOR ALL

ADIRS BITE - IR System - Class 1 Internal Faults 5/6 ** ON A/C NOT FOR ALL

ADIRS BITE - IR System - Class 1 Internal Faults 6/6 ** ON A/C NOT FOR ALL

-Class 2 External Faults

ADIRS BITE - IR System - Class 2 External Faults ** ON A/C NOT FOR ALL

-Class 2 Internal Faults

ADIRS BITE - IR System - Class 2 Internal Faults ** ON A/C NOT FOR ALL

-Class 3 External Faults

ADIRS BITE - IR System - Class 3 External Faults ** ON A/C NOT FOR ALL

-Class 3 Internal Faults

ADIRS BITE - IR System - Class 3 Internal Faults ** ON A/C NOT FOR ALL

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

(1) Align in air
The test fails if, with the OFF/NAV/ATT selector switch in NAV position on the MSU, 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 pushbutton switch flashes on the MSU.
All BNR output labels are coded Failure Warning (F/W) and all BCD labels are not transmitted.

The IR portion can be recovered by setting the OFF/NAV/ATT selector switch on the MSU to ATT and by applying the procedure (level flight) to initialize the ATT mode.

(2) Align in air
The test fails if, with the OFF/NAV/ATT selector switch in NAV position on the CDU, 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 pushbutton switch flashes on the MSU.
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.

(3) 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 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 MSU on, invalid outputs.

(4) 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 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.

(5) 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.

C. Reporting Function - Air Data Reference Faults
.Class 1 External Faults

ADIRS BITE - ADR System - Class 1 External Faults 1/2 ** ON A/C NOT FOR ALL

ADIRS BITE - ADR System - Class 1 External Faults 2/2 ** ON A/C NOT FOR ALL

.Class 1 Internal Faults

ADIRS BITE - ADR System - Class 1 Internal Faults 1/8 ** ON A/C NOT FOR ALL

ADIRS BITE - ADR System - Class 1 Internal Faults 2/8 ** ON A/C NOT FOR ALL

ADIRS BITE - ADR System - Class 1 Internal Faults 3/8 ** ON A/C NOT FOR ALL

ADIRS BITE - ADR System - Class 1 Internal Faults 4/8 ** ON A/C NOT FOR ALL

ADIRS BITE - ADR System - Class 1 Internal Faults 5/8 ** ON A/C NOT FOR ALL

ADIRS BITE - ADR System - Class 1 Internal Faults 6/8 ** ON A/C NOT FOR ALL

ADIRS BITE - ADR System - Class 1 Internal Faults 7/8 ** ON A/C NOT FOR ALL

ADIRS BITE - ADR System - Class 1 Internal Faults 8/8 ** ON A/C NOT FOR ALL

.Class 2 Internal Faults

ADIRS BITE - ADR System - Class 2 Internal Faults ** ON A/C NOT FOR ALL

.Class 3 Faults

ADIRS BITE - ADR System - Class 3 Faults ** ON A/C NOT FOR ALL

.Class 2 and 3 External Faults

ADIRS BITE - ADR System - Class 2 and 3 External Faults ** ON A/C NOT FOR ALL

(1) 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

ADIRU - Architecture and Interface with CFDIU ** ON A/C NOT FOR ALL

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.
The tests are performed at takeoff with a CAS between 90 and 200 kts and only if the received ADR data are valid. The thresholds used in the comparison are:

------------------------------------------------

! Parameter ! Threshold !

!----------------------------------------------!

! Total pressure ! 5 hPa !

! Averaged static pressure ! 5 hPa !

! Left static pressure ! 2 hPa !

! Right static pressure ! 2 hPa !

! Angle-of-attack ! 4° !

! Total air temperature ! 3°C !

------------------------------------------------

Table 1 : Comparison Thresholds

The messages resulting from a miscompare between parameters point the faulty sensor if it can be identified (one data differs from the two others which are identical) or the sensors which disagree. They are sent to the CFDIU in normal mode through label 356 of the ADR output and can be accessed by "Class 3 Faults" page on the MCDU menu.

D. Reporting Function - Air Data and Inertial Reference Faults
.Class 1 Internal Faults

ADIRS BITE - ADR and IR Systems - Class 1 Internal Faults ** ON A/C NOT FOR ALL

.Class 2 Internal Faults

ADIRS BITE - ADR and IR Systems - Class 2 Internal Faults ** ON A/C NOT FOR ALL

.Class 3 Faults

ADIRS BITE - ADR and IR Systems - Class 3 Faults ** ON A/C NOT FOR ALL

.Faults without any message

ADIRS BITE - ADR and IR Systems - Faults without any Message 1/2 ** ON A/C NOT FOR ALL

ADIRS BITE - ADR and IR Systems - Faults without any Message 2/2 ** ON A/C NOT FOR ALL

E. Interactive Function

(1) General
The interactive mode is activated via the SYSTEM REPORT/TEST page ATA 34 chapter (Navigation) including Air Data and Inertial Reference System (ADIRS).
As this system includes two parts (Air Data Reference and Inertial Reference), two interactive functions are available :

(a) ADR interactive function : select NAV from the SYSTEM REPORT/TEST page and then the selected ADR (1 to 3) to activate the ADR interactive mode and display the main menu

ADIRS BITE - Activation of ADR Interactive Function ** ON A/C NOT FOR ALL

(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

ADIRS BITE - Activation of IR Interactive Function ** ON A/C NOT FOR ALL

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

ADIRS BITE - ADR Main Menu 1/2 ** ON A/C NOT FOR ALL

(b) Previous Legs Reports

ADIRS BITE - ADR Main Menu 1/2 ** ON A/C NOT FOR ALL

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

ADIRS BITE - ADR Ground Scanning ** ON A/C NOT FOR ALL

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

ADIRS BITE - ADR Main Menu 2/2 ** ON A/C NOT FOR ALL

A maximum of sixteen 16-bit words can be recorded for the Trouble Shooting Data.

(f) Class 3 Faults

ADIRS BITE - ADR Main Menu 1/2 ** ON A/C NOT FOR ALL

(g) System test

ADIRS BITE - ADR System Test ** ON A/C NOT FOR ALL

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.

(h) Output Tests
The output tests are divided in three parts :
- Slew tests
- Interface test
- AOA test.

1 Slew tests

ADIRS BITE - ADR Slew Tests ** ON A/C NOT FOR ALL

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

ADIRS BITE - ADR Interface Test ** ON A/C NOT FOR ALL

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.
5-10 seconds (Altitude Ramp Test)
For 5-10 seconds after initiation of the test mode the ADR outputs are transmitted per tables as follows. Since this is the altitude ramp test period, the altitude outputs are slewed in a positive direction for the entire 5-second period at a rate of 600 ft/min, starting at the ambient computed altitude. Timing tolerance is plus or minus 0.5 second.

10 second until test completion (Fixed Output Test)
From 10 seconds after initialization of the test mode until the test completion is commanded, the ADR outputs are transmitted per tables as follows, outputting the fixed values specified by these tables. Timing tolerance is +/- 0.5 second.
ADR Interface test values are shown in the following tables:

------------------------------------------------------------------------

! ! ! SELF TEST VALUE !

! LABEL ! PARAMETER !--------------------------------------!

! ! ! 0 to 5 s ! 5 to 10 s ! Over 10 s !

!----------------------------------------------------------------------!

! 176 ! LEFT STATIC PRESSURE ! Last Valid ! Last Valid ! 696.8 hPa !

! 177 ! RIGHT STATIC PRESSURE ! Last Valid ! Last Valid ! 696.8 hPa !

! 203 ! STANDARD ALTITUDE ! Last Valid ! Slewed ! 10,000 ft !

! 204 ! BARO COR ALT 1 ! Last Valid ! Slewed ! 10,000 ft !

! 205 ! MACH ! 0 ! 0 ! 0.66 !

! 206 ! COMPUTED AIRSPEED ! 0 Kts ! 0 Kts ! 367.7 Kts !

! 207 ! MAX ALLOWABLE AIRSPEED! Last Valid ! Last Valid ! Last Valid !

! 210 ! TRUE AIRSPEED ! 0 Kts ! 0 Kts ! 433 Kts !

! 211 ! TOTAL AIR TEMP ! Last Valid ! Last Valid ! 35°C !

! 212 ! ALTITUDE RATE ! Last Valid ! 600 ft/mn ! 0 ft/mn !

! 213 ! STATIC AIR TEMP ! Last Valid ! Last Valid ! 10.3 °C !

! 215 ! IMPACT PRESSURE ! Last Valid ! Last Valid ! 236.6 hPa !

! 220 ! BARO COR ALT 2 ! Last Valid ! Slewed ! 10,000 ft !

! 221 ! IND ANGLE OF ATTACK ! See note ! See note ! 5 ° !

! 241 ! CORCTD ANGLE OF ATTACK! See note ! See note ! 5 ° !

! 242 ! TOTAL PRESSURE ! Last Valid ! Last Valid ! 933.4 hPa !

! 245 ! UNCRCTD AVG STAT PRESS! Last Valid ! Last Valid ! 696.8 hPa !

! 246 ! CORCTD AVG STAT PRESS ! Last Valid ! Last Valid ! 696.8 hPa !

! 251 ! BARO CORR ALT 3 ! Last Valid ! Slewed ! 10,000 ft !

------------------------------------------------------------------------

NOTE : Indicated AOA is a function of the AOA sensor position. Corrected

AOA is function of AOA alternate discrete inputs and indicated

AOA.

Table 2 : Output Binary Words

--------------------------------------------------------------------------

! ! ! SELF TEST VALUE !

! LABEL ! PARAMETER !----------------------------------------!

! ! ! 0 to 5 s ! 5 to 10 s ! Over 10 s. !

!------------------------------------------------------------------------!

! 034 ! BARO CORR (hPa) 3 !Not Transmit.! Last Valid ! 1013.3 hPa !

! 035 ! BARO CORR (in.Hg) 3 !Not Transmit.! Last Valid ! 29.92 in.Hg !

! 230 ! TRUE AIRSPEED !Not Transmit.! 0 Kts ! 433 Kts !

! 231 ! TOTAL AIR TEMP !Not Transmit.! Last Valid ! 35°C !

! 232 ! ALTITUDE RATE !Not Transmit.! 600 ft/min ! 0 ft/min !

! 233 ! STATIC AIR TEMP !Not Transmit.! Last Valid ! 10°C !

! 234 ! BARO CORR (hPa) 1 !Not Transmit.! Last Valid ! 1013.3 hPa !

! 235 ! BARO CORR (in.Hg) 1 !Not Transmit.! Last Valid ! 29.92 in.Hg !

! 236 ! BARO CORR (hPa) 2 !Not Transmit.! Last Valid ! 1013.3 hPa !

! 237 ! BARO CORR (in.Hg) 2 !Not Transmit.! Last Valid ! 29.92 in.HG !

--------------------------------------------------------------------------

Table 3 : Output BCD Words

--------------------------------------------------------------------------

! ! ! SELF TEST VALUE !

! LABEL ! BIT - PARAMETER !----------------------------------------!

! ! ! 0 to 5 s ! 5 to 10 s ! Over 10 s !

!------------------------------------------------------------------------!

! 270 ! 13 - ADR FAULT ! 1 ! 0 ! 0 !

! 270 ! 19 - OVERSPEED WARNING! 0 ! 0 ! 1 !

! 271 ! 13 - LOW SPD WARN 1 ! 0 ! 0 ! 1 !

! 271 ! 14 - LOW SPD WARN 2 ! 0 ! 0 ! 1 !

! 271 ! 15 - LOW SPD WARN 3 ! 0 ! 0 ! 0 !

! 271 ! 16 - LOW SPD WARN 4 ! 1 ! 1 ! 0 !

--------------------------------------------------------------------------

Table 4 : Output Discrete Words

--------------------------------------------------------------------------

! ! SELF TEST VALUE !

! PARAMETER !----------------------------------------!

! ! 0 to 5 s ! 5 to 10 s ! Over 10 s !

!------------------------------------------------------------------------!

! LOW SPEED WARNING 1 ! OPEN ! OPEN ! GROUND !

! LOW SPEED WARNING 2 ! OPEN ! OPEN ! GROUND !

! LOW SPEED WARNING 3 ! OPEN ! OPEN ! OPEN !

! LOW SPEED WARNING 4 ! GROUND ! GROUND ! OPEN !

! OVERSPEED WARNING ! OPEN ! OPEN ! GROUND !

! ADR FAULT ! GROUND ! OPEN ! OPEN !

! ADR OFF ! GROUND ! OPEN ! OPEN !

--------------------------------------------------------------------------

Table 5 : Discrete Outputs

3 AOA Test

ADIRS BITE - ADR AOA Test ** ON A/C NOT FOR ALL

The AOA test function set the AOA test output discrete to command the AOA sensor to fixed position greater than the stall warning threshold. So, the Flight Warning Computer activates the aural stall warning.

(i) Ground Report

ADIRS BITE - ADR Ground Scanning ** ON A/C NOT FOR ALL

(j) Current Status

ADIRS BITE - ADR Current Status ** ON A/C NOT FOR ALL

The Current Status function displays on 8 pages the state (as read by the computer) of the discrete inputs, digital inputs (ADM and baro-correction), analog inputs and power condition.

(3) Inertial Interactive function description

(a) Last Leg Report

ADIRS BITE - IR Main Menu 1/3 ** ON A/C NOT FOR ALL

(b) Previous Legs Report

ADIRS BITE - IR Main Menu 1/3 ** ON A/C NOT FOR ALL

The Part Numbers and the Serial Numbers of the ADIRU are displayed.

(d) Ground Scanning

ADIRS BITE - IR Main Menu 2/3 ** ON A/C NOT FOR ALL

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

ADIRS BITE - IR Main Menu 2/3 ** ON A/C NOT FOR ALL

A maximum of sixteen 16-bit words can be recorded for the Trouble Shooting Data.

(f) Class 3 Fault

ADIRS BITE - IR Main Menu 1/3 ** ON A/C NOT FOR ALL

(g) System Test

ADIRS BITE - ADR System Test ** ON A/C NOT FOR ALL

The system test function performs power-up tests and various continuous tests to provide a complete status of the IR part of the ADIRS.
The layout of the System test pages of the ADR and IR parts are equivalent except of the title ADR which is replaced by IR.
It is necessary to re-initialize the system because the navigation data are erased by the test of the RAM performed at the power-up.

(h) Interface Test

ADIRS BITE - IR Interface Test ** ON A/C NOT FOR ALL

Initiation of the IR Interface Test shall cause the following sequence to occur:

0-2 seconds
BCD, BNR and Discrete Words - output with SSM set to Functional Test and data set as shown in next tables. Annunciator discretes shall be energized.

Over 2 seconds
BCD, BNR and Discrete Words - output with SSM set to Functionnal Test and data set as shown in next tables. Annunciator discretes released to indicated status.

-----------------------------------------------------------------------

! LABEL ! PARAMETER ! SELF TEST VALUE !

!----------------------------------------------------------------------

! 052 ! PITCH ANGULAR ACCEL ! 5.0° /s/s !

! 053 ! ROLL ANGULAR ACCEL ! 5.0° /s/s !

! 054 ! YAW ANGULAR ACCEL ! 5.0° /s/s !

! 310 ! PRESENT POSITION LAT ! N 22.50° !

! 311 ! PRESENT POSITION LONG ! E 22.50° !

! 312 ! GROUND SPEED ! 200 Kts !

! 313 ! TRACK ANGLE-TRUE ! 00.0° !

! 314 ! TRUE HEADING ! 10.0° !

! 315 ! WIND SPEED ! 100 Kts !

! 316 ! WIND DIRECTION-TRUE ! 30° !

! 317 ! TRACK ANGLE-MAG ! 5° !

! 320 ! MAGNETIC HEADING ! 15° !

! 321 ! DRIFT ANGLE ! -10° (Left) !

! 322 ! FLIGHT PATH ANGLE ! -5° !

! 323 ! FLIGHT PATH ACCEL ! 0.2g !

! 324 ! PITCH ANGLE ! 5° !

! 325 ! ROLL ANGLE ! 45° (Right) !

! 326 ! BODY AXIS PITCH RATE ! 10°/s !

! 327 ! BODY AXIS ROLL RATE ! 10°/s !

! 330 ! BODY AXIS YAW RATE ! 10°/s !

! 331 ! BODY LONGIT ACCEL ! 0.02g !

! 332 ! BODY LATERAL ACCEL ! 0.10g !

! 333 ! BODY NORMAL ACCEL ! 0.10g !

! 334 ! PLATFORM HEADING ! 22.50° !

! 335 ! TRACK ANGLE RATE ! 4.0°/s !

! 336 ! PITCH ATT RATE ! 10°/s !

! 337 ! ROLL ATT RATE ! 10°/s !

! 340 ! TRACK ANGLE GRID ! 10°/s !

! 341 ! GRID HEADING ! 20°/s !

! 360 ! POTENTIAL VERT SPEED ! -600 ft/mn !

! 361 ! INERTIAL ALTITUDE ! 10,000 ft !

! 362 ! ALONG TRACK HORIZ ACCEL ! 0.02g !

! 363 ! CROSS TRACK HORIZ ACCEL ! 0.02g !

! 364 ! VERTICAL ACCEL ! 0.1g !

! 365 ! INERTIAL VERT SPEED ! -600 ft/mn !

! 366 ! N-S VELOCITY ! 200 Kts (N) !

! 367 ! E-W VELOCITY ! 200 Kts (E) !

! 076 ! GPS ALTITUDE ! 10,000 FT !

! 101 ! HDOP ! 500 !

! 102 ! VDOP ! 500 !

! 103 ! GPS TRACK ANGLE TRUE-BNR ! 00.0° !

! 110 ! GPS PRES POS-LAT ! N22.50° !

! 111 ! GPS PRES POS-LONG ! E22.50° !

! 112 ! GPS GROUND SPEED-BNR ! 200 KTS !

! 120 ! GPS PRES POS-LAT FRAC ! N00.00° !

! 121 ! GPS PRES POS-LONG FRAC ! E00.00° !

! 130 ! GPS INTEGRITY LIMIT ! 8 !

! 131 ! HYBRID INTEGRITY LIMIT ! 8 !

! 132 ! HYBRID TRUE HEADING ! 10° !

! 135 ! HYBRID VERT FIGURE OF MERIT ! 512 !

! 136 ! GPS VERT FIGURE OF MERIT ! 512 !

! 137 ! HYBRID TRACK ANGLE TRUE-BNR ! 00.0° !

! 150 ! UTC-BNR ! 12:00:00 !

! 165 ! GPS VERT SPEED ! -600 FT/MIN !

! 166 ! GPS N-S VELOCITY ! 200 KTS !

! 174 ! GPS E-W VELOCITY ! 200 KTS !

! 175 ! HYBRID GROUND SPEED-BNR ! 200 KTS !

! 247 ! GPS HORIZ FIGURE OF MERIT ! 1.0 !

! 254 ! HYBRID PRES POS-LAT ! N22.50° !

! 255 ! HYBRID PRES POS-LONG ! E22.50° !

! 256 ! HYBRID PRES POS-LAT FRAC ! N00.00° !

! 257 ! HYBRID PRES POS-LONG FRAC ! E00.00° !

! 261 ! HYBRID ALTITUDE ! 10,000 FT !

! 263 ! HYBRID FLIGHT PATH ANGLE ! -5.0° !

! 264 ! HYBRID HORIZ FIGURE OF MERIT ! 1.0 !

! 266 ! HYBRID N-S VELOCITY ! 200 KTS !

! 267 ! HYBRID E-W VELOCITY ! 200 KTS !

! 273 ! GPS SENSOR STATUS ! Not Applicable !

! 274 ! GPADIRS STATUS ! Not Applicable !

! 345 ! HYBRID VERT SPEED ! -600 FT/MIN !

-----------------------------------------------------------------------

Table 6 : Binary Output Labels

----------------------------------------------------------------

! ! ! SELF TEST VALUE !

! LABEL ! PARAMETER !--------------------------!

! ! ! 0 to 2 s. ! Over 2 s. !

!--------------------------------------------------------------!

! 010 ! PRESENT POSITION LAT ! 188°88.8' ! N 22°30.0' !

! 011 ! PRESENT POSITION LONG ! 188°88.8' ! E 22°30.0' !

! 012 ! GROUND SPEED ! 6888 Kts ! 200 Kts !

! 013 ! TRACK ANGLE TRUE ! 688.8° ! 00.0° !

! 014 ! MAGNETIC HEADING ! 688.8° ! 15° !

! 015 ! WIND SPEED ! 688 Kts ! 100 Kts !

! 016 ! WIND DIRECTION TRUE ! 688° ! 30° !

! 041 ! SET LATITUDE ! 188°88.8' ! N 22°30.0' !

! 042 ! SET LONGITUDE ! 188°88.8' ! E 22°30.0' !

! 043 ! SET MAGNETIC HEADING ! 688° ! 15° !

! 044 ! TRUE HEADING ! 688.8° ! 10° !

! 125 ! GPS UTC ! 78:88.8 ! 12:00:00 !

! 260 ! GPS DATE ! 38/18/88 ! 01/01/88 !

----------------------------------------------------------------

Table 8 : Output BCD Words

(i) Ground Report

ADIRS BITE - IR Main Menu 2/3 ** ON A/C NOT FOR ALL

(j) Current Status

ADIRS BITE - IR Current Status ** ON A/C NOT FOR ALL

The Current Status function displays on 8 pages the state (as read by the computer) of the discrete inputs, digital inputs (Set Lat and Long from FMGC), power condition.

(k) GPIRS REPORT

GPIRS REPORT ** ON A/C NOT FOR ALL

The GPIRS Report function displays GPS primary (AIME) parameters which are stored either in case of GPS primary failure or routinely at the end of each flight (historic on several flights).

(l) GPIRS HISTORY

ADIRS BITE - IR Main Menu 3/3 ** ON A/C NOT FOR ALL

The GPIRS HISTORY function displays the number of events stored in memory and their accumulated durations.

CNT: Number of produced events (approximately 10).
HRS: Total event durations.

F. 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 MSU) 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 passed/tests failed).

(a) Test passed:

FAULT legend of the IR 1 (2) (3) annunciator off.

(b) Test failed:

ECAM warning
- NAV IR 1 (2) (3) FAULT or
- NAV ADR 1 (2) (3) FAULT
depending on the faulty part.
ADIRS MSU:
- 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.

(4) 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 MSU) set to OFF for 20 s at least then to NAV.

(5) 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.

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

(a) Test passed:

FAULT legend of the IR 1 (2) (3) annunciator off.

(b) Test failed:

ECAM warning
- NAV IR 1 (2) (3) FAULT or
- NAV ADR 1 (2) (3) FAULT
Depending on the faulty part.
ADIRS MSU:
-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.

[Rev.10 from 2021] 2026.04.02 06:23:12 UTC