W DOC AIRBUS | AMM A320F

Leak Test of the Principal Static and Total Air Data System

TASK 34-13-00-790-002-A
Leak Test of the Principal Static and Total Air Data System

WARNING: MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. UNWANTED ELECTRICAL POWER CAN BE DANGEROUS.
WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR:
  • THE FLIGHT CONTROLS
  • THE FLIGHT CONTROL SURFACES
  • THE LANDING GEAR AND RELATED DOORS
  • COMPONENTS THAT MOVE.
MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
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).
ZONE: 120
ZONE: 210
ZONE: 230
1. Reason for the Job
To make sure that there are no leaks in the Captain and the First Officer pitot and static circuits.
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
TAPE - ADHESIVE
No specific
AR
WARNING NOTICE(S)
ALT34100001
1
PITOT AND STATIC TEST SET
 B. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
120
AVIONICS COMPARTMENT
210
CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD
230
FWD PASSENGER COMPARTMENT
 C. Referenced Information
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 31-60-00-860-002-A
EIS Stop Procedure
TASK 34-10-00-860-005-A
ADIRS Stop Procedure
TASK 34-11-15-200-001-A
Inspection/Check of the Pitot Probe
F Static and Pitot Probes
F Setting of the AOA Sensor Vane to the High Stop Position
3. Job Set-up
Subtask 34-13-00-860-074-A
A. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
Subtask 34-13-00-875-058-A ** ON A/C NOT FOR ALL
WARNING: OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED.
WARNING: BEFORE YOU OPEN PHC CIRCUIT BREAKERS 2DA1(2,3), OPEN PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND 5DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE: - THE PROBES WILL BECOME TOO HOT. - THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.
B. Open, safety and tag these circuit breakers in this sequence:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
105VUELEC/CSM/G /EV AUTO/SPLY7XEC01
122VUANTI ICE/PROBES/1/TAT1DA1Z12
122VUANTI ICE/PROBES/2/TAT1DA2Y15
49VUANTI ICE/PROBES/PITOT/13DA1D02
122VUANTI ICE/PROBES/2/PITOT3DA2Y14
122VUANTI ICE/PROBES/3/PITOT3DA3Z16
49VUANTI ICE/PROBES/AOA/14DA1D04
122VUANTI ICE/PROBES/2/AOA4DA2Y13
122VUANTI ICE/PROBES/3/AOA4DA3Z15
122VUANTI ICE/PROBES/1/STATIC5DA1Z13
122VUANTI ICE/PROBES/2/STATIC5DA2Y11
122VUANTI ICE/PROBES/3/STATIC5DA3Z14
49VUANTI ICE/PROBES/PHC/12DA1D03
122VUANTI ICE/PROBES/PHC/22DA2Y12
122VUANTI ICE/PROBES/PHC/32DA3Y16
Subtask 34-13-00-875-058-B ** ON A/C NOT FOR ALL
WARNING: OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED.
WARNING: BEFORE YOU OPEN PHC CIRCUIT BREAKERS 2DA1(2,3), OPEN PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND 5DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE: - THE PROBES WILL BECOME TOO HOT. - THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.
B. Open, safety and tag these circuit breakers in this sequence:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
105VUELEC/CSM/G /EV AUTO/SPLY7XEC01
122VUANTI ICE/PROBES/1/TAT1DA1Z12
122VUANTI ICE/PROBES/2/TAT1DA2Y15
49VUANTI ICE/PROBES/PITOT/13DA1D02
122VUANTI ICE/PROBES/2/PITOT3DA2Y14
122VUANTI ICE/PROBES/3/PITOT3DA3Z16
49VUANTI ICE/PROBES/AOA/14DA1D04
122VUANTI ICE/PROBES/2/AOA4DA2Y13
122VUANTI ICE/PROBES/3/AOA4DA3Z15
122VUANTI ICE/PROBES/1/STATIC5DA1Z13
122VUANTI ICE/PROBES/2/STATIC5DA2Y11
122VUANTI ICE/PROBES/3/STATIC5DA3Z14
121VUCOM NAV/RAD ALTM/11SA1K11
121VUCOM NAV/RAD ALTM/21SA2K12
49VUANTI ICE/PROBES/PHC/12DA1D03
122VUANTI ICE/PROBES/PHC/22DA2Y12
122VUANTI ICE/PROBES/PHC/32DA3Y16
Subtask 34-13-00-860-111-A
C. On the center pedestal, on the ATC/TCAS control unit, set the master switch to the STBY or SBY position.
Subtask 34-13-00-480-051-B
D. Installation of the Main Air Data System (for Rosemount (Aerospace)/ Goodrich Pitot probes).
   (1) Remove the slip on covers from the static probes and the pitot probes of the main system.
   (2)
F Static and Pitot Probes
For the CAPT circuit (Air Data/Inertial Reference Unit (ADIRU) 1) and the F/O circuit (ADIRU 2):
  • Left static probe 1 7DA1, zone 127, Station (STA) 8750, for left static-pressure Air Data Module (ADM) (19FP5)
  • Left static probe 2 7DA2, zone 127, STA 8700, for left static-pressure ADM (19FP7)
and
  • Right static probe 1 8DA1, zone 128, STA 9300, for right static-pressure ADM (19FP4)
  • Right static probe 2 8DA2, zone 128, STA 9350, for right static-pressure ADM (19FP6).
   (3) Connect the ground pressure generator to the pitot probe with the ADAPTER PITOT PROBE (3).
For the CAPT circuit:
  • Pitot probe 1 9DA1, zone 125.
    For the F/O circuit:
  • Pitot probe 2 9DA2, zone 126.
   (4) Seal the drain holes:
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 drain holes of the pitot probes with a piece of plastic and/or TAPE - ADHESIVE of very bright color.
   (5) Turn the vane of Angle Of Attack (AOA) sensors 1 and 2 to the high stop position.
F Setting of the AOA Sensor Vane to the High Stop Position
Maintain the vane in position with colored adhesive tape.
Subtask 34-13-00-860-076-A ** ON A/C NOT FOR ALL
E. Aircraft Maintenance Configuration
   (1) Do the EIS start procedure (PFD only)
(Ref. AMM TASK 31-60-00-860-001).
   (2) Make sure that the flaps are in the fully retracted position (Ref. AMM TASK 27-50-00-866-009).
   (3) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to NAV.
   (4) Start the ground pressure generator.
Subtask 34-13-00-860-076-B ** ON A/C NOT FOR ALL
E. Aircraft Maintenance Configuration
   (1) Do the EIS start procedure (PFD only)
(Ref. AMM TASK 31-60-00-860-001).
   (2) Make sure that the flaps are in the fully retracted position (Ref. AMM TASK 27-50-00-866-009).
   (3) On ADIRS MSU panel 41VU, set the OFF/NAV/ATT selector switches to NAV.
   (4) Start the ground pressure generator.
Subtask 34-13-00-860-076-C ** ON A/C NOT FOR ALL
E. Aircraft Maintenance Configuration
   (1) Do the EIS start procedure (PFD only)
(Ref. AMM TASK 31-60-00-860-001).
   (2) Make sure that the flaps are in the fully retracted position (Ref. AMM TASK 27-50-00-866-009).
   (3) On the ENG section of the panel 50VU:
  • Make sure that the ON legend of the ENG/FADEC GND PWR 1 and ENG/FADEC GND PWR 2 pushbutton switches are off.
  • Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC system.
   (4) On ADIRS MSU panel 41VU, set the OFF/NAV/ATT selector switches to NAV.
   (5) Start the ground pressure generator.
4. Procedure
Subtask 34-13-00-790-050-H ** ON A/C NOT FOR ALL
A. Leak Test of the Main Air Data System
NOTE: You can do this test for a static pressure of 691.4 hPa (20.4170 in.Hg) and an impact pressure of 59 hPa (1.7423 in.Hg) (or a total pressure of 750.4 hPa (22.1592 in.Hg)) but it is less accurate.
NOTE: The input parameters for the ground test (speed and altitude) and the values shown on the cockpit displays are different. This is because of the sum of the tolerances of the air data circuit (ground test unit, Air Data Modules (ADM), Air Data/Inertial Reference Units (ADIRU)).
   (1) Make sure that:
  • The CAPT (or F/O) PFD shows the altitude value 10000 ft. (3047.94 m) +/- 30 ft. (9.14 m) and the airspeed value 180 kts +/- 3 kts.
    After five minutes:
  • The change of altitude must not be more than 275 ft. (83.82 m).
  • The change of speed must not be more than 10 kts.
ACTION
RESULT
1.On glareshield 13VU, on the EFIS control section of the FCU, set a barometric pressure of 1013 hPa (29.9138 in.Hg).

2.On the ground pressure generator:
  • Set a static pressure of 455.4 hPa (13.4479 in.Hg).

  • Set an impact pressure of 186.4 hPa (5.5044 in.Hg) (or a total pressure of 641.8 hPa (18.9523 in.Hg)).

3.Close the electrovalves to isolate the static and total pressure lines of the aircraft from the ground pressure generator.
  • Make sure that:
    The CAPT (or F/O) PFD shows the altitude value 20000 ft. (6095.89 m) +/- 40 ft. (12.19 m) and the airspeed value 320 kts +/- 3 kts.
    After five minutes, on the CAPT (or F/O) PFD:
  • Make sure that the change of altitude is not more than 320 ft. (97.53 m).
    After 10 minutes, on the CAPT (or F/O) PFD:
  • Make sure that the change of speed is not more than 10 kts.
4.On the ground pressure generator:
  • Slowly balance the pressure in the main static and total pressure lines.
  • Open the electrovalves to get the atmospheric pressure.
The rate of descent must not be more than 6000 ft.min (1828.77 m.min).
5.Stop the ground pressure generator.

Subtask 34-13-00-790-050-I ** ON A/C NOT FOR ALL
A. Leak Test of the Main Air Data System
NOTE: You can do this test for a static pressure of 690 hPa (20.3756 in.Hg) and an impact pressure of 60.4 hPa (1.7836 in.Hg) (or a total pressure of 750.4 hPa (22.1592 in.Hg)) but it is less accurate.
NOTE: The input parameters for the ground test (speed and altitude) and the values shown on the cockpit displays are different. This is because of the sum of the tolerances of the air data circuit (ground test unit, Air Data Modules (ADM), Air Data/Inertial Reference Units (ADIRU)).
   (1) Make sure that:
  • The CAPT (or F/O) PFD shows the altitude value 10000 ft. (3047.94 m) +/- 30 ft. (9.14 m) and the airspeed value 180 kts +/- 3 kts.
    After five minutes:
  • The change of altitude must not be more than 275 ft. (83.82 m).
  • The change of speed must not be more than 10 kts.
ACTION
RESULT
1.On glareshield 13VU, on the EFIS control section of the FCU, set a barometric pressure of 1013 hPa (29.9138 in.Hg).

2.On the ground pressure generator:
  • Set a static pressure of 447.9 hPa (13.2264 in.Hg).

  • Set an impact pressure of 193.9 hPa (5.7258 in.Hg) (or a total pressure of 641.8 hPa (18.9523 in.Hg)).

3.Close the electrovalves to isolate the static and total pressure lines of the aircraft from the ground pressure generator.
  • Make sure that:
    The CAPT (or F/O) PFD shows the altitude value 20000 ft. (6095.89 m) +/- 40 ft. (12.19 m) and the airspeed value 320 kts +/- 3 kts.
    After five minutes, on the CAPT (or F/O) PFD:
  • Make sure that the change of altitude is not more than 320 ft. (97.53 m).
    After 10 minutes, on the CAPT (or F/O) PFD:
  • Make sure that the change of speed is not more than 10 kts.
4.On the ground pressure generator:
  • Slowly balance the pressure in the main static and total pressure lines.
  • Open the electrovalves to get the atmospheric pressure.
The rate of descent must not be more than 6000 ft.min (1828.77 m.min).
5.Stop the ground pressure generator.

Subtask 34-13-00-790-050-L ** ON A/C NOT FOR ALL
A. Leak Test of the Main Air Data System
NOTE: You can do this test for a static pressure of 690 hPa (20.3756 in.Hg) and an impact pressure of 60.4 hPa (1.7836 in.Hg) (or a total pressure of 750.4 hPa (22.1592 in.Hg)) but it is less accurate.
NOTE: The input parameters for the ground test (speed and altitude) and the values shown on the cockpit displays are different. This is because of the sum of the tolerances of the air data circuit (ground test unit, Air Data Modules (ADM), Air Data/Inertial Reference Units (ADIRU)).
   (1) Make sure that:
  • The CAPT (or F/O) PFD shows the altitude value 10000 ft. (3047.94 m) +/- 30 ft. (9.14 m) and the airspeed value 180 kts +/- 3 kts.
    After five minutes:
  • The change of altitude must not be more than 275 ft. (83.82 m).
  • The change of speed must not be more than 10 kts.
ACTION
RESULT
1.On glareshield 13VU, on the EFIS control section of the FCU, set a barometric pressure of 1013 hPa (29.9138 in.Hg).

2.On the ground pressure generator:
  • Set a static pressure of 447.9 hPa (13.2264 in.Hg).

  • Set an impact pressure of 193.9 hPa (5.7258 in.Hg) (or a total pressure of 641.8 hPa (18.9523 in.Hg)).

3.Close the electrovalves to isolate the static and total pressure lines of the aircraft from the ground pressure generator.
  • Make sure that:
    The CAPT (or F/O) PFD shows the altitude value 20000 ft. (6095.89 m) +/- 40 ft. (12.19 m) and the airspeed value 320 kts +/- 3 kts.
    After five minutes, on the CAPT (or F/O) PFD:
  • Make sure that the change of altitude is not more than 320 ft. (97.53 m).
    After 10 minutes, on the CAPT (or F/O) PFD:
  • Make sure that the change of speed is not more than 10 kts.
4.On the ground pressure generator:
  • Slowly balance the pressure in the main static and total pressure lines.
  • Open the electrovalves to get the atmospheric pressure.
The rate of descent must not be more than 6000 ft.min (1828.77 m.min).
5.Stop the ground pressure generator.

Subtask 34-13-00-790-050-M ** ON A/C NOT FOR ALL
A. Leak Test of the Main Air Data System
NOTE: You can do this test for a static pressure of 691 hPa (20.4052 in.Hg) and an impact pressure of 59.3 hPa (1.7511 in.Hg) (or a total pressure of 750.3 hPa (22.1563 in.Hg)) but it is less accurate.
NOTE: The input parameters for the ground test (speed and altitude) and the values shown on the cockpit displays are different. This is because of the sum of the tolerances of the air data circuit (ground test unit, Air Data Modules (ADM), Air Data/Inertial Reference Units (ADIRU)).
   (1) Make sure that:
  • The CAPT (or F/O) PFD shows the altitude value 10000 ft. (3047.94 m) +/- 30 ft. (9.14 m) and the airspeed value 180 kts +/- 3 kts.
    After five minutes:
  • The change of altitude must not be more than 275 ft. (83.82 m).
  • The change of speed must not be more than 10 kts.
ACTION
RESULT
1.On glareshield 13VU, on the EFIS control section of the FCU, set a barometric pressure of 1013 hPa (29.9138 in.Hg).

2.On the ground pressure generator:
  • Set a static pressure of 462.4 hPa (13.6546 in.Hg).

  • Set an impact pressure of 179.1 hPa (5.2888 in.Hg) (or a total pressure of 641.5 hPa (18.9434 in.Hg)).

3.Close the electrovalves to isolate the static and total pressure lines of the aircraft from the ground pressure generator.
  • Make sure that:
    The CAPT (or F/O) PFD shows the altitude value 20000 ft. (6095.89 m) +/- 40 ft. (12.19 m) and the airspeed value 320 kts +/- 3 kts.
    After five minutes, on the CAPT (or F/O) PFD:
  • Make sure that the change of altitude is not more than 320 ft. (97.53 m).
    After 10 minutes, on the CAPT (F/O) PFD:
  • Make sure that the change of speed is not more than 10 kts.
4.On the ground pressure generator:
  • Slowly balance the pressure in the main static and total pressure lines.
  • Open the electrovalves to get the atmospheric pressure.
The rate of descent must not be more than 6000 ft.min (1828.77 m.min).
5.Stop the ground pressure generator.

Subtask 34-13-00-790-050-A0 ** ON A/C NOT FOR ALL
A. Leak Test of the Main Air Data System
NOTE: You can do this test for a static pressure of 690 hPa (20.3756 in.Hg) and an impact pressure of 60.2 hPa (1.7777 in.Hg) (or a total pressure of 750.2 hPa (22.1533 in.Hg)) but it is less accurate.
NOTE: The input parameters for the ground test (speed and altitude) and the values shown on the cockpit displays are different. This is because of the sum of the tolerances of the air data circuit (ground test unit, Air Data Modules (ADM), Air Data/Inertial Reference Units (ADIRU)).
   (1) Make sure that:
  • The CAPT (or F/O) PFD shows the altitude value 10000 ft. (3047.94 m) +/- 30 ft. (9.14 m) and the airspeed value 180 kts +/- 3 kts.
    After five minutes:
  • The change of altitude must not be more than 275 ft. (83.82 m).
  • The change of speed must not be more than 10 kts.
ACTION
RESULT
1.On glareshield 13VU, on the EFIS control section of the FCU, set a barometric pressure of 1013 hPa (29.9138 in.Hg).

2.On the ground pressure generator:
  • Set a static pressure of 448.5 hPa (13.2442 in.Hg).

  • Set an impact pressure of 193.2 hPa (5.7052 in.Hg) (or a total pressure of 641.7 hPa (18.9493 in.Hg)).

3.Close the electrovalves to isolate the static and total pressure lines of the aircraft from the ground pressure generator.
  • Make sure that:
    The CAPT (or F/O) PFD shows the altitude value 20000 ft. (6095.89 m) +/- 40 ft. (12.19 m) and the airspeed value 320 kts +/- 3 kts.
    After five minutes, on the CAPT (or F/O) PFD:
  • Make sure that the change of altitude is not more than 320 ft. (97.53 m).
    After 10 minutes, on the CAPT (or F/O) PFD:
  • Make sure that the change of speed is not more than 10 kts.
4.On the ground pressure generator:
  • Slowly balance the pressure in the main static and total pressure lines.
  • Open the electrovalves to get the atmospheric pressure.
The rate of descent must not be more than 6000 ft.min (1828.77 m.min).
5.Stop the ground pressure generator.

Subtask 34-13-00-790-050-AA ** ON A/C NOT FOR ALL
A. Leak Test of the Main Air Data System
NOTE: You can do this test for a static pressure of 689 hPa (20.3461 in.Hg) and an impact pressure of 61.3 hPa (1.8102 in.Hg) (or a total pressure of 750.3 hPa (22.1563 in.Hg)) but it is less accurate.
NOTE: The input parameters for the ground test (speed and altitude) and the values shown on the cockpit displays are different. This is because of the sum of the tolerances of the air data circuit (ground test unit, Air Data Modules (ADM), Air Data/Inertial Reference Units (ADIRU)).
   (1) Make sure that:
  • The CAPT (or F/O) PFD shows the altitude value 10000 ft. (3047.94 m) +/- 30 ft. (9.14 m) and the airspeed value 180 kts +/- 3 kts.
    After five minutes:
  • The change of altitude must not be more than 275 ft. (83.82 m).
  • The change of speed must not be more than 10 kts.
ACTION
RESULT
1.On glareshield 13VU, on the EFIS control section of the FCU, set a barometric pressure of 1013 hPa (29.9138 in.Hg).

2.On the ground pressure generator:
  • Set a static pressure of 455.2 hPa (13.4420 in.Hg).

  • Set an impact pressure of 186.4 hPa (5.5044 in.Hg) (or a total pressure of 641.6 hPa (18.9464 in.Hg)).

3.Close the electrovalves to isolate the static and total pressure lines of the aircraft from the ground pressure generator.
  • Make sure that:
    The CAPT (or F/O) PFD shows the altitude value 20000 ft. (6095.89 m) +/- 40 ft. (12.19 m) and the airspeed value 320 kts +/- 3 kts.
    After five minutes, on the CAPT (or F/O) PFD:
  • Make sure that the change of altitude is not more than 320 ft. (97.53 m).
    After 10 minutes, on the CAPT (or F/O) PFD:
  • Make sure that the change of speed is not more than 10 kts.
4.On the ground pressure generator:
  • Slowly balance the pressure in the main static and total pressure lines.
  • Open the electrovalves to get the atmospheric pressure.
The rate of descent must not be more than 6000 ft.min (1828.77 m.min).
5.Stop the ground pressure generator.

Subtask 34-13-00-790-050-AC ** ON A/C NOT FOR ALL
A. Leak Test of the Main Air Data System
NOTE: You can do this test for a static pressure of 690 hPa (20.3756 in.Hg) and an impact pressure of 60.3 hPa (1.7807 in.Hg) (or a total pressure of 750.3 hPa (22.1563 in.Hg)) but it is less accurate.
NOTE: The input parameters for the ground test (speed and altitude) and the values shown on the cockpit displays are different. This is because of the sum of the tolerances of the air data circuit (ground test unit, Air Data Modules (ADM), Air Data/Inertial Reference Units (ADIRU)).
   (1) Make sure that:
  • The CAPT (or F/O) PFD shows the altitude value 10000 ft. (3047.94 m) +/- 30 ft. (9.14 m) and the airspeed value 180 kts +/- 3 kts.
    After five minutes:
  • The change of altitude must not be more than 275 ft. (83.82 m).
  • The change of speed must not be more than 10 kts.
ACTION
RESULT
1.On glareshield 13VU, on the EFIS control section of the FCU, set a barometric pressure of 1013 hPa (29.9138 in.Hg).

2.On the ground pressure generator:
  • Set a static pressure of 448.5 hPa (13.2442 in.Hg).

  • Set an impact pressure of 193.1 hPa (5.7022 in.Hg) (or a total pressure of 641.6 hPa (18.9464 in.Hg)).

3.Close the electrovalves to isolate the static and total pressure lines of the aircraft from the ground pressure generator.
  • Make sure that:
    The CAPT (or F/O) PFD shows the altitude value 20000 ft. (6095.89 m) +/- 40 ft. (12.19 m) and the airspeed value 320 kts +/- 3 kts.
    After five minutes, on the CAPT (or F/O) PFD:
  • Make sure that the change of altitude is not more than 320 ft. (97.53 m).
    After 10 minutes, on the CAPT (or F/O) PFD:
  • Make sure that the change of speed is not more than 10 kts.
4.On the ground pressure generator:
  • Slowly balance the pressure in the main static and total pressure lines.
  • Open the electrovalves to get the atmospheric pressure.
The rate of descent must not be more than 6000 ft.min (1828.77 m.min).
5.Stop the ground pressure generator.

5. Close-up
Subtask 34-13-00-080-051-B
A. Disconnect the ground pressure generator.
   (1) Remove the adapters from the static probes and the pitot probes.
   (2) Remove the adhesive tape from the vane of the AOA.
   (3) Install the slip-on covers on the static probes and the pitot probes.
   (4) Make sure that the work area is clean and clear of tools and other items.
   (5) Make sure that the drain holes on the pitot probes are not blocked by unwanted materials (Ref. AMM TASK 34-11-15-200-001).
Subtask 34-13-00-875-059-A ** ON A/C NOT FOR ALL
WARNING: CLOSE THE PHC CIRCUIT BREAKERS 2DA1(2,3) BEFORE YOU CLOSE THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND 5DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE, THE PROBES WILL BECOME TOO HOT. THIS CAN CAUSE INJURY TO MAINTENANCE PERSONNEL AND/OR DAMAGE TO EQUIPMENT.
B. Remove the safety clips and tags and close these circuit breakers in this sequence:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUANTI ICE/PROBES/PHC/12DA1D03
122VUANTI ICE/PROBES/PHC/22DA2Y12
122VUANTI ICE/PROBES/PHC/32DA3Y16
105VUELEC/CSM/G /EV AUTO/SPLY7XEC01
122VUANTI ICE/PROBES/1/TAT1DA1Z12
122VUANTI ICE/PROBES/2/TAT1DA2Y15
49VUANTI ICE/PROBES/PITOT/13DA1D02
122VUANTI ICE/PROBES/2/PITOT3DA2Y14
122VUANTI ICE/PROBES/3/PITOT3DA3Z16
49VUANTI ICE/PROBES/AOA/14DA1D04
122VUANTI ICE/PROBES/2/AOA4DA2Y13
122VUANTI ICE/PROBES/3/AOA4DA3Z15
122VUANTI ICE/PROBES/1/STATIC5DA1Z13
122VUANTI ICE/PROBES/2/STATIC5DA2Y11
122VUANTI ICE/PROBES/3/STATIC5DA3Z14
Subtask 34-13-00-875-059-B ** ON A/C NOT FOR ALL
WARNING: CLOSE THE PHC CIRCUIT BREAKERS 2DA1(2,3) BEFORE YOU CLOSE THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND 5DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE, THE PROBES WILL BECOME TOO HOT. THIS CAN CAUSE INJURY TO MAINTENANCE PERSONNEL AND/OR DAMAGE TO EQUIPMENT.
B. Remove the safety clips and tags and close these circuit breakers in this sequence:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUANTI ICE/PROBES/PHC/12DA1D03
122VUANTI ICE/PROBES/PHC/22DA2Y12
122VUANTI ICE/PROBES/PHC/32DA3Y16
105VUELEC/CSM/G /EV AUTO/SPLY7XEC01
122VUANTI ICE/PROBES/1/TAT1DA1Z12
122VUANTI ICE/PROBES/2/TAT1DA2Y15
49VUANTI ICE/PROBES/PITOT/13DA1D02
122VUANTI ICE/PROBES/2/PITOT3DA2Y14
122VUANTI ICE/PROBES/3/PITOT3DA3Z16
49VUANTI ICE/PROBES/AOA/14DA1D04
122VUANTI ICE/PROBES/2/AOA4DA2Y13
122VUANTI ICE/PROBES/3/AOA4DA3Z15
122VUANTI ICE/PROBES/1/STATIC5DA1Z13
122VUANTI ICE/PROBES/2/STATIC5DA2Y11
122VUANTI ICE/PROBES/3/STATIC5DA3Z14
121VUCOM NAV/RAD ALTM/11SA1K11
121VUCOM NAV/RAD ALTM/21SA2K12
Subtask 34-13-00-860-075-A
C. Put the aircraft back to its initial configuration.
   (1) Do a reset of each ELAC:
  • On panel 49VU, open then close the ELAC1 circuit breaker
  • On panel 121VU, open then close the ELAC2 circuit breaker.
   (2) Do the ADIRS stop procedure (Ref. AMM TASK 34-10-00-860-005).
   (3) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).
   (4) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
   (5) Remove the WARNING NOTICE(S).
[Rev.10 from 2021] 2026.04.01 04:47:39 UTC
"Aviabrain" 2025