DOC AIRBUS | AMM A320FAIR DATA, INERTIAL REFERENCE SYSTEM (ADIRS) BUILT-IN TEST EQUIPMENT (BITE) - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
1. General
The Built-in Test Equipment (BITE) 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:
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:
** ON A/C NOT FOR ALL The Built-in Test Equipment (BITE) 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).
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).
ADIRS - Interface between one ADIRU and the CFDIUFaults 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 both IR NAV and IR I/O processors
- external inputs (both digital and discrete)
- the functionality of the other 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 tests enable to monitor operation errors: - Align in air
- Excessive Motion
- Latitude Sin/Cos 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 performance of the ADR 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 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.).
2. Component Location
A. Computers Directly Linked to the CFDS
| FIN | FUNCTIONAL DESIGNATION | PANEL | ZONE | ACCESS DOOR | 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
C. Other LRUs of the System
| FIN | FUNCTIONAL DESIGNATION | PANEL | ZONE | ACCESS DOOR | 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 | ||
3. System Description
A. Reporting Function
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.
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.
(1) General
- IR and ADR faults are classified as follows:
. class 1: faults with cockpit effect
. class 2: non-critical faults
. class 3: minor faults without cockpit effects. - use of indexes in BITE messages:
ADIRUi stands for ADIRU 1, ADIRU 2 or ADIRU 3. - 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.
- IR FAULT:
the FAULT legend of the IR pushbutton switch flashes in NAV mode and is steady in ATT mode.
(2) Inertial reference faults
Some IR faults resulting in warnings (fault annunciation, invalid outputs) are due to an incorrect operational use of the system and not to a system fault.
These tests are:
Some IR faults resulting in warnings (fault annunciation, invalid outputs) are due to an incorrect operational use of the system and not to a system fault.
These tests are:
- align in air
- position-entry (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 the 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 test fails if, with the OFF/NAV/ATT selector switch on the CDU in the 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) and on the MCDU.
(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 the entered latitude differs from the cosine of the computed latitude by more than 0.01234 or
. the sine of the entered latitude differs from the sine of the computed latitude by more than 0.01234.
NOTE: No fault message is sent to the CFDIU.
(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.
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
(a) SDI validity test at power-up
A number of data is 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 inability 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 with invalid outputs.
A number of messages can be sent to the CFDIU on label 356 according to the detected miscompare. These messages point the ADIRU or ADM pin program or a mix of them:
341117 ADMi (19FPi) (i = 1, 2 or 3)
341117 ADMi (19FPi)/ADMj(19FPj) (i,j) = (1,5), (2,7) or (3,8)
341234 WRG: SDI PIN PROG/ADIRUi (1FPi)
341234 WRG: SDI PIN PROG/ADMi (19FPi)/ADIRUi (1FPi)
341234 WRG: SDI PIN PROG/ADMj (19FPj)/ADIRUi (1FPi) (i,j) = (1,5), (2,7) or (3,8).
341234 WRG: SDI PIN PROG/ADMi/j ADIRUi (1FPi) (19FPi/j) (i,j) = (1,5), (2,7) or (3,8).
A number of data is 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 inability 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 with invalid outputs.
A number of messages can be sent to the CFDIU on label 356 according to the detected miscompare. These messages point the ADIRU or ADM pin program or a mix of them:
341117 ADMi (19FPi) (i = 1, 2 or 3)
341117 ADMi (19FPi)/ADMj(19FPj) (i,j) = (1,5), (2,7) or (3,8)
341234 WRG: SDI PIN PROG/ADIRUi (1FPi)
341234 WRG: SDI PIN PROG/ADMi (19FPi)/ADIRUi (1FPi)
341234 WRG: SDI PIN PROG/ADMj (19FPj)/ADIRUi (1FPi) (i,j) = (1,5), (2,7) or (3,8).
341234 WRG: SDI PIN PROG/ADMi/j ADIRUi (1FPi) (19FPi/j) (i,j) = (1,5), (2,7) or (3,8).
(b) 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.
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 is valid. The thresholds used in the comparison are:
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 through the LAST (PREVIOUS) LEG REPORT page on the MCDU menu.
The messages have the following format: e.g. for the AOA sensors
341119 AOA SENSORi (3FPi)
or
341119 AOA SENSORi (3FPi)/AOA SENSORj (3FPj)
or
341119 AOA SNSR1 (3FP1)/SNSR2 (3FP2)/SNSR3 (3FP3)
The principle of the messages is the same for other sensors (ADM, TAT).
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.
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 is 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 through the LAST (PREVIOUS) LEG REPORT page on the MCDU menu.
The messages have the following format: e.g. for the AOA sensors
341119 AOA SENSORi (3FPi)
or
341119 AOA SENSORi (3FPi)/AOA SENSORj (3FPj)
or
341119 AOA SNSR1 (3FP1)/SNSR2 (3FP2)/SNSR3 (3FP3)
The principle of the messages is the same for other sensors (ADM, TAT).
B. Interactive Function
(1) General
The interactive mode is activated via the SYSTEM REPORT/TEST page related to the ATA 34 chapter (Navigation) including the Air Data and Inertial Reference System (ADIRS).
As this system includes two parts (Air Data Reference and Inertial Reference), two interactive functions are available:
The interactive mode is activated via the SYSTEM REPORT/TEST page related to the ATA 34 chapter (Navigation) including the Air Data and Inertial Reference System (ADIRS).
As this system includes two parts (Air Data Reference and Inertial Reference), two interactive functions are available:
- IR interactive function
- ADR interactive function.
(a) LAST LEG REPORT
This item describes the in-flight class 1 and 2 fault status of the selected IR during the last leg (flight leg 00).
This item describes the in-flight class 1 and 2 fault status of the selected IR during the last leg (flight leg 00).
(b) PREVIOUS LEGS REPORT
This item describes the in-flight class 1 and 2 fault status of the selected IR during the previous legs (flight legs 01-62).
This item describes the in-flight class 1 and 2 fault status of the selected IR during the previous legs (flight legs 01-62).
(c) LRU IDENTIFICATION
This item provides the ADIRU Part Number and Serial Number, as well as the part number of the ADIRU software: P/N-SWAPP for OPS (Operational Software), P/N-SWA/C for OPC 1 (Anemometric correction tables) and P/N-SWMAG for OPC 2 (MAGVAR tables).
The Part Number and the Serial Number of the CDU are also displayed.
This item provides the ADIRU Part Number and Serial Number, as well as the part number of the ADIRU software: P/N-SWAPP for OPS (Operational Software), P/N-SWA/C for OPC 1 (Anemometric correction tables) and P/N-SWMAG for OPC 2 (MAGVAR tables).
The Part Number and the Serial Number of the CDU are also displayed.
(d) GROUND SCANNING
This page layout contains the list of all failures detected while using this function.
This page layout contains the list of all failures detected while using this function.
(e) TROUBLE SHOOTING DATA
This item provides, for each fault message stored in the LAST LEG or PREVIOUS LEGS REPORT, additional data required by the maintenance for failure investigation.
This item provides, for each fault message stored in the LAST LEG or PREVIOUS LEGS REPORT, additional data required by the maintenance for failure investigation.
(f) CLASS 3 FAULTS
This item reports all class 3 faults recorded since the last takeoff.
This item reports all class 3 faults recorded since the last takeoff.
(g) SYSTEM TEST
This item activates a complete test of the IR system and presents a report to the user.
This item activates a complete test of the IR system and presents a report to the user.
(h) SPECIFIC DATA
This item provides access to GPIRS REPORT and GPIRS HISTORY.
This item provides access to GPIRS REPORT and GPIRS HISTORY.
(i) INTERFACE TEST
This item controls the functional test modes of the selected IR.
The test mode is inhibited whenever any of the following conditions exists:
This item controls the functional test modes of the selected IR.
The test mode is inhibited whenever any of the following conditions exists:
- ground speed greater than or equal to 20 kts
- IR in the ATT mode.
- 0-2 seconds
BCD, BNR and Discrete Words are output with SSM set to Functional Test and data set as shown in the following tables.
Annunciator discretes are energized:
. ALIGN
. ON BAT
. DC FAIL (See note)
. IR FAULT
. IR OFF (See note)
. SPARE IR OUT 1 (See note)
. SPARE IR OUT 2 (See note) - after 2 seconds
BCD, BNR and Discrete Words are output with SSM set to Functional Test and data set as shown in the following tables. Annunciator discretes are de-energized to the previously indicated status.
NOTE: No associated annunciator in the cockpit.
| ---------------------------------------------------------------- |
| ! ! ! SELF TEST VALUE ! |
| ! LABEL ! PARAMETER !--------------------------! |
| ! ! ! 0 to 2 s. ! After 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° ! |
| ---------------------------------------------------------------- |
| Table 2: Output BCD Words |
| ---------------------------------------------------------------- |
| ! 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 ! 0.02g ! |
| ! 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° ! |
| ! 341 ! GRID HEADING ! 20° ! |
| ! 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) ! |
| ---------------------------------------------------------------- |
| Table 3: Binary Output Labels |
(j) GROUND REPORT
This item reports all internal faults detected since the last landing.
This item reports all internal faults detected since the last landing.
(k) INPUT STATUS
This item describes the current state/value of the selected IR inputs (discrete and binary inputs).
This item describes the current state/value of the selected IR inputs (discrete and binary inputs).
(3) ADR interactive function
(a) LAST LEG REPORT
This item describes the in-flight class 1 and 2 fault status of the selected ADR and related LRUs during the last leg (flight leg 00).
This item describes the in-flight class 1 and 2 fault status of the selected ADR and related LRUs during the last leg (flight leg 00).
(b) PREVIOUS LEGS REPORT
This item describes the in-flight class 1 and 2 fault status of the selected ADR and related LRUs during the previous legs (flight legs 01-62).
This item describes the in-flight class 1 and 2 fault status of the selected ADR and related LRUs during the previous legs (flight legs 01-62).
(c) LRU IDENTIFICATION
This item describes the Part Number and Serial Number of the selected ADIRU, as well as the Part Number of the ADMs.
This item describes the Part Number and Serial Number of the selected ADIRU, as well as the Part Number of the ADMs.
(d) GROUND SCANNING
This page layout contains the list of all the failures detected while using this function.
This page layout contains the list of all the failures detected while using this function.
(e) TROUBLE SHOOTING DATA
This item provides, for each fault message stored in the LAST LEG or PREVIOUS LEGS REPORT, additional data required by the maintenance for failure investigation.
This item provides, for each fault message stored in the LAST LEG or PREVIOUS LEGS REPORT, additional data required by the maintenance for failure investigation.
(f) CLASS 3 FAULTS
This item reports all class 3 faults recorded since the last takeoff.
This item reports all class 3 faults recorded since the last takeoff.
(g) SYSTEM TEST
This item activates a complete test of the ADR system and presents a report to the user.
This item activates a complete test of the ADR system and presents a report to the user.
(h) INTERFACE TEST (OUTPUT TESTS MENU)
This item controls the functional test modes of the selected ADR.
The displayed text describes the various steps of the interface test; when you push the line key adjacent to the START TEST indication, the following test sequence is run:
This item controls the functional test modes of the selected ADR.
The displayed text describes the various steps of the interface test; when you push the line key adjacent to the START TEST indication, the following test sequence is run:
- 0-5 seconds: Failure Warning Test
For 0-5 seconds after initiation of the test mode, the ADR outputs are transmitted as per the following tables. 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 as per the following tables with an SSM coded FT (except for discrete words). 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 seconds 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 as per the following tables, outputting the fixed values specified by these tables with an SSM coded FT (except for discrete words). Timing tolerance is plus or minus 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 ! After 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 CORR 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 CORR ALT 2 ! Last Valid ! Slewed ! 10,000 ft ! ! 221 ! IND ANGLE OF ATTACK ! NOTE 1 ! NOTE 1 ! 5° ! ! 241 ! CORCTD ANGLE OF ATTACK! NOTE 1 ! NOTE 1 ! 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: The indicated AOA is a function of the AOA sensor position. The corrected AOA is a function of the AOA alternate discrete inputs, SDI discrete inputs and indicated AOA. The corrected AOA is set to 0° when CAS is less than 60 kts.
| Output Binary Words |
| -------------------------------------------------------------------------- |
| ! ! ! SELF TEST VALUE ! |
| ! LABEL ! PARAMETER !----------------------------------------! |
| ! ! ! 0 to 5 s ! 5 to 10 s ! After 10 s ! |
| !------------------------------------------------------------------------! |
| ! 034 ! BARO CORR (hPa) 3 !Not Transmit.! 745.0 hpa ! 1013.3 hPa ! |
| ! 035 ! BARO CORR (in.Hg) 3 !Not Transmit.! 22.0 in.Hg ! 29.92 in.Hg ! |
| ! 230 ! TRUE AIRSPEED !Not Transmit.! 0 Kts ! 433 Kts ! |
| ! 231 ! TOTAL AIR TEMP !Not Transmit.! Last Valid ! 35 °C ! |
| ! 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 ! |
| -------------------------------------------------------------------------- |
| Output BCD Words |
| -------------------------------------------------------------------------- |
| ! ! ! SELF TEST VALUE ! |
| ! LABEL ! BIT - PARAMETER !----------------------------------------! |
| ! ! ! 0 to 5 s ! 5 to 10 s ! After 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 ! |
| -------------------------------------------------------------------------- |
| Output Discrete Words |
| -------------------------------------------------------------------------- |
| ! ! SELF TEST VALUE ! |
| ! PARAMETER !----------------------------------------! |
| ! ! 0 to 5 s ! 5 to 10 s ! After 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 ! |
| -------------------------------------------------------------------------- |
| Discrete Outputs |
(i) ALT DYNAMIC SLEW (OUTPUT TESTS menu/SLEW TESTS submenu)
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.
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)
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.
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)
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.
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
This item reports all internal faults detected since the last landing.
This item reports all internal faults detected since the last landing.
(m) INPUT STATUS
This item describes the current state/value of the selected ADR inputs (discrete, analog and binary inputs).
This item describes the current state/value of the selected ADR inputs (discrete, analog and binary inputs).
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).
(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.