W DOC AIRBUS | AMM A320F

Pressure Regulating Test after Overpressure at Take Off Events with Bleed Test Set P/N 98L36103002000

TASK 36-11-00-720-810-A
Pressure Regulating Test after Overpressure at Take Off Events with Bleed Test Set P/N 98L36103002000

FIN: 4001HA ** ON A/C NOT FOR ALL
1. Reason for the Job
The aim of this test is to do a check of the correct regulation of the Bleed Pressure Regulating Valve 4001HA after an over pressure at take off.
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE
No specific
AR
ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE
No specific
AR
AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY
No specific
AR
PLUG - BLANKING
No specific
AR
WARNING NOTICE(S)
No specific
1
WRENCH - SPANNER
No specific
1
WRENCH 5/16 IN (8MM) - SPANNER
No specific
Torque wrench: range to between 0.7 and 0.6 m.daN (61.95 and 53.10 lbf.in ) T
No specific
Torque wrench: range to between 0.80 and 0.65 m.daN (70.80 and 57.52 lbf.in ) T
No specific
Torque wrench: range to between 1.1 and 0.9 m.daN (97.35 and 79.65 lbf.in ) T
No specific
Torque wrench: range to between 1.2 and 1 m.daN (106.19 and 88.50 lbf.in ) T
No specific
Torque wrench: range to between 1.69 and 1.52 m.daN (12.46 and 11.21 lbf.ft ) T
98L36103002000
1
TEST SET - ENGINE BLEED
SBE2213
1
KIT TOOL-TESTER SENSE LINE
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.14QFB1)
Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -
No specific
short bend flexible-assembly
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
147AB, 147EB, 191BB, 191BT, 192BT, 192FB, 197BB, 472AR, 482AR, 521AB, 521BT, 521CB, 521EB, 521HB, 522AB, 621AB, 621BT, 621CB, 621EB, 621HB, 622AB
191DB, 481BR
FOR [1000EM1] (ENGINE-1)
437AL, 451AL
413CL, 413DL, 414CR, 414FR
413DT, 471AL, 471AR
FOR [1000EM2] (ENGINE-2)
447AL, 461AL
423DT, 481AL, 481AR
423CL, 423DL, 423FL, 424CR
 D. 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 31-60-00-860-001-A
EIS Start Procedure
TASK 53-35-11-000-001-A
Removal of the Wing-to-Fuselage Fairings
TASK 53-35-11-400-001-A
Installation of the Wing-to-Fuselage Fairings
TASK 57-41-37-000-004-A
Removal of the Pressure Relief Panels
TASK 57-41-37-400-002-A
Installation of the Pressure Relief Panels
TASK 71-13-00-010-010-A
Opening of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 71-13-00-010-040-A
Opening of the Fan Cowl Doors
TASK 71-13-00-010-040-B
Opening of the Fan Cowl Doors
TASK 71-13-00-410-010-A
Closing of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 71-13-00-410-040-A
Closing of the Fan Cowl Doors
TASK 71-13-00-410-040-B
Closing of the Fan Cowl Doors
TASK 78-32-00-010-010-A
Opening of the Thrust Reverser Halves
TASK 78-32-00-410-010-A
Closing of the Thrust Reverser Halves
TASK 78-36-00-010-040-A
Opening of the Thrust Reverser Doors
TASK 78-36-00-010-040-B
Opening of the Thrust Reverser Doors
TASK 78-36-00-410-040-A
Closing of the Thrust Reverser Doors
TASK 78-36-00-410-040-B
Closing of the Thrust Reverser Doors
F Connection of the PRV STD 6774B and 6714D (with Deactivation Screw on Butterfly valve and coupling tube) with the Bleed Test Set P/N 98L36103002000
F Connection of the PRV STD 6774E, 6774F and 6774G (with Deactivation Screw on regulator) with the Bleed Test Set P/N 98L36103002000
FOR [1000EM1] (ENGINE-1)
TASK 54-53-11-000-002-B
Removal of the Pylon-to-Wing Access Panels
TASK 54-53-11-400-002-B
Installation of the Pylon-to-Wing Access Panels
FOR [1000EM2] (ENGINE-2)
TASK 54-53-11-000-002-B
Removal of the Pylon-to-Wing Access Panels
TASK 54-53-11-400-002-B
Installation of the Pylon-to-Wing Access Panels
3. Job Set-up
Subtask 36-11-00-861-122-A ** ON A/C NOT FOR ALL
A. Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002)
Subtask 36-11-00-941-125-A ** ON A/C NOT FOR ALL
B. Safety Precautions
   (1) Make sure that the engine 1(2) is shut down for at least 5 minutes.
   (2) Put a WARNING NOTICE(S) on the panel 115VU to tell persons not to start the engine 1 (2).
   (3) In the cockpit:
  • put WARNING NOTICE(S) to the persons not to operate the pneumatic system,
  • put WARNING NOTICE(S) to the persons not to operate the slats,
  • put WARNING NOTICE(S) to the persons not to operate the APU switch.
   (4) On the maintenance panel 50VU:
  • make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off,
  • put a WARNING NOTICE(S) to tell persons not to operate the FADEC 1(2).
Subtask 36-11-00-865-093-A ** ON A/C NOT FOR ALL
C. Make sure that this(these) circuit breaker(s) is(are) closed:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUAIR BLEED/X FEED/VALVE/BAT2HVD13
49VUAIR BLEED/ENG 1/CTL3HA1D12
49VUAIR BLEED/ENG 1/MONG2HA1D11
49VUAIR BLEED/ENG 1/MONG2HA1D11
122VUAIR BLEED/ENG 2/CTL3HA2Z23
122VUAIR BLEED/ENG 2/MONG2HA2Z22
122VUAIR BLEED/X FEED VALVE/NORM1HVZ20
Subtask 36-11-00-010-144-A ** ON A/C NOT FOR ALL
D. Get Access
NOTE: Remove only the applicable access panels in the area where you will do the Pressure Regulating test.
   (1) Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the zones 191BB 192FB.
   (2) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the zones 521 and 621.
   (3) Remove the applicable access panels of the air conditioning units 191BB 192FB.
   (4) Remove the applicable access panels on the wings and belly fairings:
     (a) For the left wing and belly fairing:
     (b) For the right wing and belly fairing:
   (5) Remove these access panels on the pylon:
     (a) FOR [1000EM1] (ENGINE-1)
413CL 414CR 413DL 414FR.
     (b) FOR [1000EM2] (ENGINE-2)
423CL 424CR 423DL 423FL.
   (6) Open the left fan cowl door (Ref. AMM TASK 71-13-00-010-040):
     (a) FOR [1000EM1] (ENGINE-1)
437AL.
     (b) FOR [1000EM2] (ENGINE-2)
447AL.
   (7) Open the left thrust-reverser cowl door (Ref. AMM TASK 78-36-00-010-040):
     (a) FOR [1000EM1] (ENGINE-1)
451AL.
     (b) FOR [1000EM2] (ENGINE-2)
461AL.
Subtask 36-11-00-010-144-C ** ON A/C NOT FOR ALL
D. Get Access
NOTE: Remove only the applicable access panels in the area where you do the Pressure Regulating test.
   (1) Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the zones 191 and 192.
   (2) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the zones 521 and 621.
   (3) Remove the applicable access panels of the air conditioning units:
   (4) Remove the applicable access panels on the wing and belly fairing:
     (a) For the left wing and belly fairing:
     (b) For the right wing and belly fairing:
   (5) Remove these access panels on the pylon:
     (a) FOR [1000EM1] (ENGINE-1)
413CL 414CR 413DL 414FR.
     (b) FOR [1000EM2] (ENGINE-2)
423CL 424CR 423DL 423FL.
   (6) Open the left fan cowl door (Ref. AMM TASK 71-13-00-010-040):
     (a) FOR [1000EM1] (ENGINE-1)
437AL.
     (b) FOR [1000EM2] (ENGINE-2)
447AL.
   (7) Open the left thrust-reverser cowl door (Ref. AMM TASK 78-36-00-010-040):
     (a) FOR [1000EM1] (ENGINE-1)
451AL.
     (b) FOR [1000EM2] (ENGINE-2)
461AL.
Subtask 36-11-00-010-144-F ** ON A/C NOT FOR ALL
D. Get Access
NOTE: Remove only the applicable access panels in the area where you will do the Pressure Regulating test.
   (1) Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the zones 191BB 192FB.
   (2) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the zones 521 and 621.
   (3) Remove the applicable access panels 191BB 192FB of the air conditioning packs.
   (4) Remove the applicable access panels on the wings and belly fairings:
     (a) For the left wing and belly fairing:
     (b) For the right wing and belly fairing:
   (5) Remove these access panels on the pylon:
     (a) FOR [1000EM1] (ENGINE-1)
413DT 471AR.
     (b) FOR [1000EM2] (ENGINE-2)
423DT 481AL.
   (6) Open the left fan cowl door (Ref. AMM TASK 71-13-00-010-010):
     (a) FOR [1000EM1] (ENGINE-1)
437AL.
     (b) FOR [1000EM2] (ENGINE-2)
447AL.
   (7) Open the left thrust-reverser cowl door (Ref. AMM TASK 78-32-00-010-010):
     (a) FOR [1000EM1] (ENGINE-1)
451AL.
     (b) FOR [1000EM2] (ENGINE-2)
461AL.
   (8) Remove the access panel 191DB.
Subtask 36-11-00-860-091-A ** ON A/C NOT FOR ALL
E. Aircraft Maintenance Configuration
   (1) At the HP ground connection area put the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY in position.
   (2) In the air conditioning compartment:
  • disconnect the water tank, hyd reservoir and trim air valve pressurization interconnection line from the pressure service check valves (7272HM and 7270HM).
   (3) Cap the disconnected ends with PLUG - BLANKING.
   (4) Do the EIS start procedure (ECAM system only) (Ref. AMM TASK 31-60-00-860-001).
   (5) On valve-bleed pressure regulator 4001HA:
  • remove cap from test port,
  • connect AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY to the test port,
  • increase and stabilize the pressure to 40 psi (2.75 bar) to open the bleed pressure regulation valve. Check with the manual position indicator that the valve opens.
   (6) On the ECAM control panel 11VU:
  • push the BLEED pushbutton switch (the BLEED page comes into view on the lower display unit of the ECAM system).
   (7) On the AIR COND panel 30VU make sure that:
  • the PACK 1 and PACK 2 pushbutton switches are released (the OFF legends are on),
  • the X BLEED selector switch is set to OPEN (the BLEED page shows that the X BLEED valve is open),
  • the APU BLEED pushbutton switch is released (the ON legend is off) (the BLEED page shows that the APU BLEED valve is closed).
NOTE: Ignore the warnings that are caused by disagree between ENG 1 BLEED, ENG 2 BLEED pushbutton switches position and the Bleed Pressure Regulator Valve.
   (8) On the ANTI-ICE section of the panel 25VU:
  • make sure that the ANTI-ICE/WING pushbutton switch is released (the ON legend is off).
4. Procedure
Subtask 36-11-00-480-098-A ** ON A/C NOT FOR ALL
A. Installation of the tool for the Pressure Regulating Test of the Pressure Regulator Valve (PRV) standard 6774B and 6714D with deactivation screw on butterfly valve and with coupling tube on actuator.
F Connection of the PRV STD 6774B and 6714D (with Deactivation Screw on Butterfly valve and coupling tube) with the Bleed Test Set P/N 98L36103002000 ** ON A/C NOT FOR ALL
NOTE: For PRV (4001HA) standard 6714D Series 01 to 06 previous to bleed Improvement program this test is not possible.
NOTE: Use the SBE2213 KIT TOOL-TESTER SENSE LINE to do this test.
   (1) Removal of the lockwire:
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
     (a) Cut and discard the lockwire from the blanking cap of the test port of the Bleed PRV (4001HA).
     (b) Remove the blanking cap from the test port.
   (2) Disconnection of the sense line
CAUTION: USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT THE PNEUMATIC LINES ON UNIONS.
     (a) Loosen the pneumatic union a quarter turn with a WRENCH - SPANNER.
     (b) Shake the sense line with your hand to prevent cross thread damage to the pneumatic union.
NOTE: To prevent damage to the fitting end of the sense line, turn the union with your hand and not with WRENCH - SPANNER.
     (c) Disconnect the sense line from the PRV (4001HA).
     (d) Put a blanking plug (T23) on the disconnected sense line end.
   (3) Connection of the 98L36103002000 TEST SET - ENGINE BLEED:
     (a) Close the shutoff valve, the purge valve and the pressure regulator valve on the 98L36103002000 TEST SET - ENGINE BLEED.
CAUTION: BE CAREFUL WHEN YOU CONNECT/DISCONNECT THE TEST SET TO/FROM THE EQUIPMENT. THE PRESSURE REGULATING VALVE AND THE PRESSURE GAGE ASSEMBLY OF THE TEST SET ARE HEAVY AND CAN CAUSE DAMAGE TO THE ENGINE.
     (b) Connect the 98L36103002000 TEST SET - ENGINE BLEED with the short bend flexible-assembly to the test port of the PRV (4001HA).
     (c) Connect an Air Cylinder or a Pressure Supply 200 psi (13.79 bar) to the 98L36103002000 TEST SET - ENGINE BLEED.
     (d) Install the 98L36103002000 TEST SET - ENGINE BLEED.
       1 If there is a manometer in the Air Cylinder (Pressure source), the installation of the primary regulator valve is not necessary.
       2 If there is no manometer in the Air Cylinder (Pressure source), the installation of Primary regulator valve is mandatory.
NOTE: The pressure will be limited to 217 psi (15 bar) for the Primary regulator valve in test set.
     (e) Do a reset of the digital pressure gage in 98L36103002000 TEST SET - ENGINE BLEED.
   (4) Connection of the SBE2213 KIT TOOL-TESTER SENSE LINE to the PRV (4001HA).
     (a) Connect the adaptor (T25) to the port of the coupling tube on the PRV (4001HA).
     (b) TORQUE the adaptor (T25) to between 1.2 and 1 m.daN (106.19 and 88.50 lbf.in ) T.
     (c) Connect the sense line tester (T10) to the adaptor (T25).
       1 Make sure that the sense line tester valve 1 is in the CLOSE position.
       2 Make sure that the sense line tester valve 2 is in the OPEN position.
     (d) Connect the pressure gage to the sense line tester.
       1 Do a reset of the pressure gage connected in sense line tester (T10).
Subtask 36-11-00-480-099-A ** ON A/C NOT FOR ALL
B. Installation of the tool for the Pressure Regulating Test of the Pressure Regulator Valve (PRV) standard 6774E, 6774F and 6774G with deactivation screw on regulator.
F Connection of the PRV STD 6774E, 6774F and 6774G (with Deactivation Screw on regulator) with the Bleed Test Set P/N 98L36103002000 ** ON A/C NOT FOR ALL
NOTE: Use the SBE2213 KIT TOOL-TESTER SENSE LINE to do this test.
   (1) Removal the lockwire:
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
     (a) Cut and discard the lockwire from the deactivation screw.
     (b) Cut and discard the lockwire from the blanking cap of the test port of the PRV (4001HA).
   (2) Remove the deactivation screw.
     (a) If the deactivation screw has a preformed packing:
       1 Make sure that the preformed packing is installed on the deactivation screw and does not stay on the PRV.
   (3) Remove the blanking cap from the test port.
NOTE: Use a WRENCH 5/16 IN (8MM) - SPANNER if necessary.
   (4) Connect the test port adaptor (T14) or (T15) to the test port of the PRV (4001HA).
NOTE: First try to install the adaptor (T14), if you cannot install it, install the adaptor (T25).
   (5) TORQUE the test port adaptor (T14) or (T25) to between 1.2 and 1 m.daN (106.19 and 88.50 lbf.in ) T.
   (6) Connection of the 98L36103002000 TEST SET - ENGINE BLEED.
     (a) Close the shutoff valve, the purge valve and the pressure regulator valve on the 98L36103002000 TEST SET - ENGINE BLEED.
CAUTION: BE CAREFUL WHEN YOU CONNECT/DISCONNECT THE TEST SET TO/FROM THE EQUIPMENT. THE PRESSURE REGULATING VALVE AND THE PRESSURE GAGE ASSEMBLY OF THE TEST SET ARE HEAVY AND CAN CAUSE DAMAGE TO THE ENGINE.
     (b) Connect the 98L36103002000 TEST SET - ENGINE BLEED to the test port adaptor (T14) or (T25).
   (7) Connect an Air Cylinder or a Pressure Supply 200 psi (13.7895 bar) to the TEST SET - ENGINE BLEED.
   (8) Install the 98L36103002000 TEST SET - ENGINE BLEED.
  • If there is a manometer in the Air Cylinder (Pressure source), the installation of the Primary regulator valve is not necessary.
  • If there is no a manometer in the Air Cylinder (Pressure source), the installation of the Primary regulator valve is mandatory.
NOTE: The Primary regulator valve limit the pressure to 217 psi (14.96 bar).
   (9) Connection of the adaptor (T15) or (T19) to the PRV (4001HA):
CAUTION: FIRST TRY TO INSTALL THE ADAPTOR WITH THE SHORTEST THREADED AREA (T15). IF YOU CANNOT INSTALL IT, INSTALL THE OTHER ADAPTOR (T19). MAKE SURE THAT THE ADAPTOR (T15 OR T19) IS CORRECTLY TIGHTENED.
     (a) Connect the adaptor (T15) or (T19) to the PRV (4001HA).
     (b) TORQUE the test port adaptor (T15) or (T19) to between 1.1 and 0.9 m.daN (97.35 and 79.65 lbf.in ) T.
   (10) Connection of the SBE2213 KIT TOOL-TESTER SENSE LINE to the PRV (4001HA):
     (a) Connect the sense line tester (T10) to the adaptor (T15) or (T19).
     (b) Make sure the sense line tester valve 1 is in the CLOSE position.
     (c) Make sure the sense line tester valve 2 is in the OPEN position.
     (d) Connect the pressure gage to the sense line tester (T10).
     (e) Do a reset of the Pressure gage in sense line tester (T10)
Subtask 36-11-00-720-092-A ** ON A/C NOT FOR ALL
C. Pressure Regulating Test of the Bleed Pressure Regulator Valve (4001HA)
   (1) Pressurize the 98L36103002000 TEST SET - ENGINE BLEED.
WARNING: MAKE SURE THAT THE PRESSURE SUPPLIED TO BLEED TEST SET 98L36103002000 NEVER EXCEEDS 217 PSI (15 BAR). IF THE PRESSURE SUPPLIED TO THE BLEED TEST SET EXCEEDS THIS VALUE, THERE IS A RISK OF INJURY TO PERSONNEL AND DAMAGE TO EQUIPMENT. IF THE AIR CYLINDER DOES NOT HAVE A MANOMETER INSTALLED, YOU MUST INSTALL THE PRIMARY REGULATOR VALVE BETWEEN THE AIR BOTTLE AND BLEED TEST SET 98L36103002000. THE PRIMARY REGULATOR VALVE WILL LIMIT THE PRESSURE IN THE BLEED TEST SET TO 217 PSI (15 BAR).
     (a) Make sure that the shutoff valve, the purge valve and the pressure regulator valve on the test set are closed before you start pressurizing the 98L36103002000 TEST SET - ENGINE BLEED.
     (b) Pressurize the 98L36103002000 TEST SET - ENGINE BLEED.
       1 If there is manometer in the air cylinder:
  • Use the air cylinder shut off valve and the manometer to slowly pressurize the 98L36103002000 TEST SET - ENGINE BLEED to 200 psi (13.79 bar).
       2 If there is no manometer in the air cylinder:
  • Install the Primary Regulator valve.
  • Use the air cylinder shut off valve and the manometer to slowly pressurize the 98L36103002000 TEST SET - ENGINE BLEED to 200 psi (13.79 bar).
       3 Open the main pressure-source shut-off valve slowly and pressurize the 98L36103002000 TEST SET - ENGINE BLEED to 200 psi (13.79 bar).
   (2) Do the Test.
     (a) For PRV standard 6714D:
ACTION
RESULT
1.On the 98L36103002000 TEST SET - ENGINE BLEED
  • Open the shutoff valve.

2.On the 98L36103002000 TEST SET - ENGINE BLEED:
  • Use the regulator valve of the test set to slowly increase the pressure to between 126 psi (8.69 bar) and 128 psi (8.83 bar).
On the 98L36103002000 TEST SET - ENGINE BLEED:
  • The pressure shown on the pressure gage attached to the regulator valve.
  • The reference pressure value is shown on the pressure gage connected to the sense line test (T10).
3.On the SBE2213 KIT TOOL-TESTER SENSE LINE:
  • Wait until the pressure indicated in the digital pressure gage is stabilized.
  • Make sure that the reference pressure value shown on the pressure gage is between 42 psi (2.90 bar) and 56 psi (3.86 bar).
Take note of the pressure measured on the pressure gage.
     (b) For PRV standard 6774B, 6774E and 6774G:
ACTION
RESULT
1.On the 98L36103002000 TEST SET - ENGINE BLEED
  • Open the shutoff valve.

2.On the 98L36103002000 TEST SET - ENGINE BLEED:
  • Use the regulator valve of the test set to slowly increase the pressure to between 196 psi (13.51 bar) and 198 psi (13.65 bar).
On the 98L36103002000 TEST SET - ENGINE BLEED:
  • The pressure shown on the pressure gage attached to the regulator valve.
  • The reference pressure value is shown on the pressure gage connected to the sense line test (T10).
3.On the SBE2213 KIT TOOL-TESTER SENSE LINE:
  • Wait until the pressure indicated in the digital pressure gage is stabilized.
  • Make sure that the reference pressure value shown on the pressure gage is between 42 psi (2.90 bar) and 56 psi (3.86 bar).
Take note of the pressure measured on the pressure gage.
Subtask 36-11-00-080-091-A ** ON A/C NOT FOR ALL
D. Removal of the Tool for the Pressure Regulating Test of the PRV standard 6774B and 6714D with deactivation screw on butterfly valve and with coupling tube on actuator:
F Connection of the PRV STD 6774B and 6714D (with Deactivation Screw on Butterfly valve and coupling tube) with the Bleed Test Set P/N 98L36103002000 ** ON A/C NOT FOR ALL
WARNING: MAKE SURE THAT NO SOURCE OF COMPRESSED AIR IS IN OPERATION IN THE AIRCRAFT WHEN YOU DO THIS TASK. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY TO PERSONNEL CAN OCCUR.
CAUTION: BE CAREFUL WHEN YOU CONNECT/DISCONNECT THE TEST SET TO/FROM THE EQUIPMENT. THE PRESSURE REGULATING VALVE AND THE PRESSURE GAGE ASSEMBLY OF THE TEST SET ARE HEAVY AND CAN CAUSE DAMAGE TO THE ENGINE.
   (1) Depressurize the system:
     (a) If you used an Air Cylinder, close the shutoff valve of the Air cylinder.
     (b) If you used a pressure-source, close the main pressure-source shutoff valve.
     (c) Slowly open the purge valve in 98L36103002000 TEST SET - ENGINE BLEED.
   (2) Disconnect the pressure gage from the sense line tester (T10).
   (3) Disconnect the sense line tester (T10) from the adaptor (T25).
   (4) Disconnect the adaptor (T25) from the port of the coupling tube on the PRV (4001HA).
   (5) Remove the 98L36103002000 TEST SET - ENGINE BLEED from the test port of the PRV (4001HA).
   (6) Install the blanking cap on the test port of the PRV (4001HA).
   (7) TORQUE the blanking cap to between 1.2 and 1 m.daN (106.19 and 88.50 lbf.in ) T.
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
   (8) Safety the blanking cap with 14QFB1Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -.
   (9) Remove the blanking cap (T23) from the disconnected sense line.
   (10) Connect of the Sense Line:
     (a) Make sure that there is no grease or oil on the pneumatic and sense line unions.
     (b) Connect the sense line to the PRV (4001HA).
NOTE: To prevent damage to the fitting end of the sense line, turn the union with your hand and not with a WRENCH - SPANNER.
     (c) TORQUE the union of the sense line to between 1.69 and 1.52 m.daN (12.46 and 11.21 lbf.ft ) T. Use the double torque procedure that follows.
       1 Torque a first time the union of the sense line to the given value.
       2 Loosen the union of the sense line a quarter of a turn.
       3 Torque a second time the union to the given value.
     (d) Paint a mark on the union of the sense line.
Subtask 36-11-00-080-092-A ** ON A/C NOT FOR ALL
E. Removal of the tool for the Pressure Regulating Test of the PRV standard 6774E, 6774F and 6774G with deactivation screw on regulator.
F Connection of the PRV STD 6774E, 6774F and 6774G (with Deactivation Screw on regulator) with the Bleed Test Set P/N 98L36103002000 ** ON A/C NOT FOR ALL
WARNING: MAKE SURE THAT NO SOURCE OF COMPRESSED AIR IS IN OPERATION IN THE AIRCRAFT WHEN YOU DO THIS TASK. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY TO PERSONNEL CAN OCCUR.
CAUTION: BE CAREFUL WHEN YOU CONNECT/DISCONNECT THE TEST SET TO/FROM THE EQUIPMENT. THE PRESSURE REGULATING VALVE AND THE PRESSURE GAGE ASSEMBLY OF THE TEST SET ARE HEAVY AND CAN CAUSE DAMAGE TO THE ENGINE.
   (1) Depressurize the system:
     (a) If you used an Air Cylinder, close the shutoff valve of the Air cylinder,
     (b) If you used a Pressure-source, close the main pressure-source shutoff valve.
     (c) Slowly open the purge valve in 98L36103002000 TEST SET - ENGINE BLEED.
   (2) Disconnect the Sense line test (T10), from the adaptor (T15) or (T19).
   (3) Disconnect and remove the adaptor (T15) or (T19) and the test port adaptor (T14) or (T25) from the bleed-pressure regulating valve.
   (4) Installation of the deactivation screw:
CAUTION: WHEN YOU INSTALL THE DEACTIVATION SCREW ON THE VALVE, TIGHTEN THE SCREW WITH YOUR HAND BEFORE YOU TORQUE IT. IF YOU DO NOT OBEY THIS PRECAUTION, YOU CAN CAUSE DAMAGE TO THE SCREW AND THE VALVE.
CAUTION: BEFORE YOU INSTALL THE DEACTIVATION SCREW, MAKE SURE THAT THE PREFORMED PACKING IS INSTALLED ON THE DEACTIVATION SCREW.
     (a) Install the deactivation screw on the PRV.
NOTE: If the adaptor (T19) is installed, the deactivation screw has a preformed packing.
  • Replace the preformed packing.
  • Install the deactivation screw on the PRV.
     (b) TORQUE the deactivation screw to between 0.7 and 0.6 m.daN (61.95 and 53.10 lbf.in ) T.
   (5) Install the blanking cap on the test port of the PRV.
   (6) TORQUE the blanking cap to between 0.80 and 0.65 m.daN (70.80 and 57.52 lbf.in ) T.
   (7) Installation of the lockwire:
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
     (a) Safety the deactivation screw and the blanking cap with 14QFB1Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -.
5. Close-up
Subtask 36-11-00-860-092-A ** ON A/C NOT FOR ALL
A. Aircraft Maintenance Configuration
   (1) On valve-bleed pressure regulator 4001HA:
  • Stop the pressurization of the valve with the air supply and check that it closes with its manual position indicator.
  • Disconnect the air supply source.
  • Install the cap on test port.
   (2) On the ECAM Control Panel set the LOWER DISPLAY and the UPPER DISPLAY potentiometer to OFF.
   (3) In the air conditioning compartment:
  • remove the PLUG - BLANKING.
   (4) Make sure that the work area is clean and clear of tools and other items.
   (5) Put the aircraft back to its initial configuration.
Subtask 36-11-00-410-163-A ** ON A/C NOT FOR ALL
B. Close Access
   (1) Close the access doors of the air conditioning units:
   (2) Close the left thrust-reverser cowl door (Ref. AMM TASK 78-36-00-410-040):
     (a) FOR [1000EM1] (ENGINE-1)
451AL.
     (b) FOR [1000EM2] (ENGINE-2)
461AL.
   (3) Close the left fan cowl door (Ref. AMM TASK 71-13-00-410-040):
     (a) FOR [1000EM1] (ENGINE-1)
437AL.
     (b) FOR [1000EM2] (ENGINE-2)
447AL.
   (4) Install the access panels on the wings and belly fairing:
     (a) For the left wing and belly fairing:
     (b) For the right wing and belly fairing:
   (5) Install these access panels on the pylon:
     (a) FOR [1000EM1] (ENGINE-1)
413CL 414CR 413DL 414FR.
     (b) FOR [1000EM2] (ENGINE-2)
423CL 424CR 423DL 423FL.
   (6) Remove the WARNING NOTICE(S).
   (7) Remove the access platform(s).
Subtask 36-11-00-410-163-C ** ON A/C NOT FOR ALL
B. Close Access
   (1) Close the access doors of the air conditioning units:
   (2) Close the left thrust-reverser cowl door (Ref. AMM TASK 78-36-00-410-040):
     (a) FOR [1000EM1] (ENGINE-1)
451AL.
     (b) FOR [1000EM2] (ENGINE-2)
461AL.
   (3) Close the left fan cowl door (Ref. AMM TASK 71-13-00-410-040):
     (a) FOR [1000EM1] (ENGINE-1)
437AL.
     (b) FOR [1000EM2] (ENGINE-2)
447AL.
   (4) Install the access panels on the wing and belly fairing:
     (a) For the left wing and belly fairing:
     (b) For the right wing and belly fairing:
   (5) Install these access panels on the pylon:
     (a) FOR [1000EM1] (ENGINE-1)
413CL 414CR 413DL 414FR.
     (b) FOR [1000EM2] (ENGINE-2)
423CL 424CR 423DL 423FL.
   (6) Remove the WARNING NOTICE(S).
   (7) Remove the access platform(s).
Subtask 36-11-00-410-163-F ** ON A/C NOT FOR ALL
B. Close Access
   (1) Close the access doors of the air conditioning packs:
   (2) Close the left thrust-reverser cowl door (Ref. AMM TASK 78-32-00-410-010):
     (a) FOR [1000EM1] (ENGINE-1)
451AL.
     (b) FOR [1000EM2] (ENGINE-2)
461AL.
   (3) Close the left fan cowl door (Ref. AMM TASK 71-13-00-410-010):
     (a) FOR [1000EM1] (ENGINE-1)
437AL.
     (b) FOR [1000EM2] (ENGINE-2)
447AL.
   (4) Install the access panels on the wings and belly fairing:
     (a) For the left wing and belly fairing:
     (b) For the right wing and belly fairing:
   (5) Install these access panels on the pylon:
     (a) FOR [1000EM1] (ENGINE-1)
413DT 471AR.
     (b) FOR [1000EM2] (ENGINE-2)
423DT 481AL.
   (6) Install the access panel 191DB.
   (7) Remove the WARNING NOTICE(S).
   (8) Remove the access platform(s).
Subtask 36-11-00-862-110-A ** ON A/C NOT FOR ALL
C. De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
[Rev.10 from 2021] 2026.04.01 01:07:17 UTC
"Aviabrain" 2025