DOC AIRBUS | AMM A320FFunctional Test of the Altitude and Airspeed Data (A/C without RVSM capability on ADIRU 3)
TASK 34-13-00-720-009-A
Functional Test of the Altitude and Airspeed Data (A/C without RVSM capability on ADIRU 3)
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Work Zones and Access Panels
C. Referenced Information
3. Job Set-up
Subtask 34-13-00-860-054-A ** ON A/C NOT FOR ALL
Subtask 34-13-00-480-050-A ** ON A/C NOT FOR ALL
Subtask 34-13-00-720-065-D ** ON A/C NOT FOR ALL
Subtask 34-13-00-080-050-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.02 06:23:09 UTC
Functional Test of the Altitude and Airspeed Data (A/C without RVSM capability on ADIRU 3)
CAUTION:
TO PREVENT DAMAGE TO INSTRUMENTS, OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST:
- THE PRESSURES SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN 115 hPa (3.39 in Hg)
- CHANGES IN STATIC AND TOTAL PRESSURES MUST NOT BE MORE THAN 6000 FEET/MINUTE
- DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE GENERATOR IS CONNECTED.
CAUTION:
THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN THE STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg).
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | SAFETY CLIP - CIRCUIT BREAKER |
| No specific | AR | TAPE - ADHESIVE |
| ALT34100001 | 1 | PITOT AND STATIC TEST SET |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 120 | AVIONICS COMPARTMENT |
| 210 | CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 24-41-00-861-002-A | Energize the Aircraft Electrical Circuits from the External Power |
| TASK 24-41-00-861-002-A-01 | Energize the Aircraft Electrical Circuits from the APU |
| TASK 24-41-00-861-002-A-02 | Energize the Aircraft Electrical Circuits from Engine 1(2) |
| TASK 24-41-00-862-002-A | De-energize the Aircraft Electrical Circuits Supplied from the External Power |
| TASK 24-41-00-862-002-A-01 | De-energize the Aircraft Electrical Circuits Supplied from the APU |
| TASK 24-41-00-862-002-A-02 | De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) |
| TASK 27-50-00-866-009-A | Retraction of the Flaps on the Ground |
| TASK 27-50-00-866-009-A-01 | Retraction of the Flaps/Slats on the Ground |
| TASK 31-60-00-860-001-A | EIS Start Procedure |
| TASK 34-10-00-860-002-A | ADIRS Start Procedure |
| TASK 34-10-00-860-005-A | ADIRS Stop Procedure |
| TASK 34-11-15-200-001-A | Inspection/Check of the Pitot Probe |
| TASK 34-13-00-790-002-A | Leak Test of the Principal Static and Total Air Data System |
Setting of the AOA Sensor Vane to the High Stop PositionSubtask 34-13-00-860-054-A ** ON A/C NOT FOR ALL
A. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(2) Do the EIS start procedure (PFD DUs only) (Ref. AMM TASK 31-60-00-860-001).
(3) Do the ADIRS start procedure (Ref. AMM TASK 34-10-00-860-002).
(4) On the SWITCHING panel 8VU, make sure that the AIR DATA selector switch is at NORM.
(5) Make sure that the flaps are fully retracted (Ref. AMM TASK 27-50-00-866-009).
(6) On the FCU, set the CAPT (F/O) Baro-Correction to display STD below the altitude scale on the CAPT (F/O) PFD.
(7) Do the Leak Test of the main Air Data System (Ref. AMM TASK 34-13-00-790-002).
Subtask 34-13-00-865-086-A ** ON A/C NOT FOR ALL (1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(2) Do the EIS start procedure (PFD DUs only) (Ref. AMM TASK 31-60-00-860-001).
(3) Do the ADIRS start procedure (Ref. AMM TASK 34-10-00-860-002).
(4) On the SWITCHING panel 8VU, make sure that the AIR DATA selector switch is at NORM.
(5) Make sure that the flaps are fully retracted (Ref. AMM TASK 27-50-00-866-009).
(6) On the FCU, set the CAPT (F/O) Baro-Correction to display STD below the altitude scale on the CAPT (F/O) PFD.
(7) Do the Leak Test of the main Air Data System (Ref. AMM TASK 34-13-00-790-002).
WARNING:
OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED.
B. Open, safety and tag this(these) circuit breaker(s):| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | ANTI ICE/PROBES/PITOT/1 | 3DA1 | D02 |
| 105VU | ELEC/CSM/G /EV AUTO/SPLY | 7XE | C01 |
| 122VU | ANTI ICE/PROBES/2/PITOT | 3DA2 | Y14 |
| 122VU | ANTI ICE/PROBES/2/STATIC | 5DA2 | Y11 |
| 122VU | ANTI ICE/PROBES/3/PITOT | 3DA3 | Z16 |
| 122VU | ANTI ICE/PROBES/3/STATIC | 5DA3 | Z14 |
| 122VU | ANTI ICE/PROBES/1/STATIC | 5DA1 | Z13 |
C. Install the Ground Pressure Generator
(2) Connect the static port of the ALT34100001 PITOT AND STATIC TEST SET to the static probes and/or the total probes on which you do the test.
(4) Turn the vane of the three Angle Of Attack (AOA) sensors to the high stop position.
Keep the AOA sensors in position with TAPE - ADHESIVE.
(5) Start the ground pressure generator.
4. ProcedureNOTE: It is necessary to use a ground pressure generator with this minimum data:
(1) Remove the slip-on covers from the static probes and the pitot probes. - Altitude between -1000 ft and 50.000 ft, accuracy +/- 0,1 hPa (0.00145 psi) or the values in ft given below related to the altitude level:
. Sea level: +/- 3 ft
. 5000 ft: +/- 4 ft
. 30000 ft: +/- 8 ft
. 50000 ft: +/- 18 ft - Speed between 0 to 500 kts
- Mach Nbr: 0 to 1.000
- Climb Rate: 0 to +/- 6000ft/mn (accuracy +/- 7%).
(2) Connect the static port of the ALT34100001 PITOT AND STATIC TEST SET to the static probes and/or the total probes on which you do the test.
NOTE: For the CAPT and F/O circuits, it is necessary to connect the ground pressure generator to the two static probes (left and right).
For CAPT circuit (Air Data/Inertial Reference Unit (ADIRU) 1) and F/O circuit (ADIRU 2), connect the ground pressure generator to the static probes with the ADAPTER STATIC PROBE:
Connect the ground pressure generator to the pitot probes with the ADAPTER PITOT PROBE for Thales probes, or the ADAPTER PITOT PROBE for Rosemount (Aerospace)/Goodrich probes.
For CAPT circuit:
For F/O circuit:
For the standby circuit:
(3) Seal the drain holes of the pitot probes with a piece of platic and TAPE - ADHESIVE. For CAPT circuit (Air Data/Inertial Reference Unit (ADIRU) 1) and F/O circuit (ADIRU 2), connect the ground pressure generator to the static probes with the ADAPTER STATIC PROBE:
- Left static probe 1 7DA1, zone 127, Station (STA) 8750, for the left static-pressure Air Data Module (ADM) (19FP5)
- Left static probe 2 7DA2, zone 127, STA 8700, for the left static-pressure ADM (19FP7)
- Right static probe 1 8DA1, zone 128, STA 9300, for the right static-pressure ADM (19FP4)
- Right static probe 2 8DA2, zone 128, STA 9350, for the right static-pressure ADM (19FP6)
- Left static probe 3 7DA3, zone 121, STA 4250, for the static pressure ADM (19FP8) or
- Right static probe 3 8DA3, zone 122, STA 4250, for the static pressure ADM (19FP8).
Connect the ground pressure generator to the pitot probes with the ADAPTER PITOT PROBE for Thales probes, or the ADAPTER PITOT PROBE for Rosemount (Aerospace)/Goodrich probes.
For CAPT circuit:
- Pitot probe 1 9DA1, zone 125, for the left total-pressure ADM (19FP1).
For F/O circuit:
- Pitot probe 2 9DA2, zone 126, for the right total-pressure ADM (19FP2).
For the standby circuit:
- Pitot probe 3 9DA3, zone 125, for the standby total-pressure ADM (19FP3).
CAUTION:
WHEN YOU SEAL THE DRAIN HOLE IN THE PITOT PROBE, DO NOT SEAL THE HOLE DIRECTLY WITH THE COLORED ADHESIVE TAPE. ALWAYS PUT A PIECE OF PLASTIC ON THE HOLE FIRST AND USE THE COLORED ADHESIVE TAPE TO ATTACH THE PLASTIC.
IF YOU SEAL THE DRAIN HOLE DIRECTLY WITH THE ADHESIVE TAPE, THERE IS A RISK THAT SOME OF THE ADHESIVE WILL STAY ON THE HOLE AND COLLECT PARTICLES. THIS CAN SUBSEQUENTLY CAUSE BLOCKAGE OF THE HOLE AND THUS INCORRECT OPERATION OF THE PROBE.
(a) Seal the opposite static probe of the standby ADM with the ADAPTER STATIC PROBE.(4) Turn the vane of the three Angle Of Attack (AOA) sensors to the high stop position.
Keep the AOA sensors in position with TAPE - ADHESIVE.
(5) Start the ground pressure generator.
Subtask 34-13-00-720-065-D ** ON A/C NOT FOR ALL
A. Functional Test of the Altitude and Airspeed Data
(*) These indications are not shown when the Mach value is less than 0.5.
5. Close-up| ACTION | RESULT |
|---|---|
| 1.On the ground pressure generator, set a static pressure and a total pressure as given in the table below. | On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 1 and 2. |
| 2.On the SWITCHING panel 8VU: | |
| On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 and 2. |
| On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 1 and 3. |
| 3.At the end of the test, on the ground pressure generator: | |
| The rate of descent must not be more than 6000 ft/mn. |
| 4.Stop the pressure generator. | |
| ------------------------------------------------------------------------------- |
| Pressure ! CAPT PFD and F/O PFD |
| generator ! AIR DATA switch at ! AIR DATA switch |
| ! NORM ! at CAPT/3 or F/O/3 |
| ------------------------------!-----------------------!------------------------ |
| Ps ! Pt ! QC !Hp 1/2!Vc 1/2 !Mach 1/2! Hp 3 ! Vc 3 ! Mach 3 |
| (ft)!(hpa)! (ft)!(hpa)!Pt-Ps ! (ft) ! (Kts) ! ! (ft) !(Kts) ! |
| ! ! ! ! (hpa)! !+/- 2.5! ! !+/-2.5! |
| ! ! ! ! (Kts)! ! ! ! ! ! |
| -----!-----!-----!-----!------!------!-------!--------!------!------!---------- |
| 5257!835.0! 1829!948,1!113.1 ! 5000 ! 250 !0.413(*)! 5305 ! 261 ! 0.433 (*) |
| ! ! ! !259.14!+/-25 ! !+/-0.006!+/- 25! !+/-0.006 |
| -----!-----!-----!-----!------!------!-------!--------!------!------!---------- |
| 10254!690.0! 6335!801.8!111.8 !10000 ! 250 !0.452(*)! 10371! 261 ! 0.475 (*) |
| ! ! ! !257.7 !+/-30 ! !+/-0.006!+/- 30! !+/-0.006 |
| -----!-----!-----!-----!------!------!-------!--------!------!------!---------- |
| 20189!462.0!13010!619.2!157.2 !20000 ! 300 ! 0.651 ! 20789! 314 ! 0.690 |
| ! ! ! !303.7 !+/- 40! !+/-0.006!+/- 40! !+/-0.006 |
| -----!-----!-----!-----!------!------!-------!--------!------!------!---------- |
| 30055!300.1!20579!454.4!154.3 !30000 ! 300 ! 0.790 ! 31363! 316 ! 0.852 |
| ! ! ! !300.7 !+/- 55! !+/-0.006!+/- 55! !+/-0.006 |
| -----!-----!-----!-----!------!------!-------!--------!------!------!---------- |
| 40003!187.5!30618!292.5!105.0 !40000 ! 250 ! 0.823 ! 41319! 263 ! 0.884 |
| ! ! ! !250.02!+/- 80! !+/-0.006!+/- 80! !+/-0.006 |
| ------------------------------------------------------------------------------- |
Subtask 34-13-00-080-050-A ** ON A/C NOT FOR ALL
A. Remove the ground support and maintenance equipment, the special and standard tools and all other items.
Make sure that there is no remaining piece of plastic and/or adhesive tape on the pitot probes and AOA sensors. Make sure the pitot drain holes are operational and that the AOA sensors move freely.
Subtask 34-13-00-865-088-A ** ON A/C NOT FOR ALL Make sure that there is no remaining piece of plastic and/or adhesive tape on the pitot probes and AOA sensors. Make sure the pitot drain holes are operational and that the AOA sensors move freely.
B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 34-13-00-860-055-A ** ON A/C NOT FOR ALL | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | ANTI ICE/PROBES/PITOT/1 | 3DA1 | D02 |
| 105VU | ELEC/CSM/G /EV AUTO/SPLY | 7XE | C01 |
| 122VU | ANTI ICE/PROBES/2/PITOT | 3DA2 | Y14 |
| 122VU | ANTI ICE/PROBES/2/STATIC | 5DA2 | Y11 |
| 122VU | ANTI ICE/PROBES/3/PITOT | 3DA3 | Z16 |
| 122VU | ANTI ICE/PROBES/3/STATIC | 5DA3 | Z14 |
| 122VU | ANTI ICE/PROBES/1/STATIC | 5DA1 | Z13 |
C. Put the aircraft back to its initial configuration.
(1) Do a reset of each ELAC:
(3) Make sure that the drain holes on the pitot probes are not blocked by unwanted materials (Ref. AMM TASK 34-11-15-200-001).
(4) Do the ADIRS stop procedure (Ref. AMM TASK 34-10-00-860-005).
(5) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
(1) Do a reset of each ELAC:
- On the panel 49VU, open then close the ELAC1 C/B
- On the panel 121VU, open then close the ELAC2 C/B.
(3) Make sure that the drain holes on the pitot probes are not blocked by unwanted materials (Ref. AMM TASK 34-11-15-200-001).
(4) Do the ADIRS stop procedure (Ref. AMM TASK 34-10-00-860-005).
(5) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).