W DOC AIRBUS | AMM A320F

Functional Test of the HP Bleed Valve with the Test Set P/N 98D36109001000

TASK 36-11-51-720-804-A
Functional Test of the HP Bleed Valve with the Test Set P/N 98D36109001000

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.
WARNING: YOU MUST NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN CAUSE AN INJURY.
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: BEFORE YOU INSTALL/REMOVE THE GSE TOOL, READ THE MANUFACTURER'S INSTRUCTIONS, AND, WHILE YOU OPERATE THIS TOOL, CAREFULLY OBEY THEM. IF YOU DO NOT DO THIS, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT 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.
NOTE: Two persons are necessary to do this test.
1. Reason for the Job
Self explanatory
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
1
AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY
No specific
AR
WARNING NOTICE(S)
No specific
Torque wrench: range to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in ) T
98D36109001000
1
TEST SET-EBAS,BLEED
 B. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
FOR [1000EM1] (ENGINE-1)
437AL, 438AR, 451AL, 452AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR, 461AL, 462AR
 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 36-11-00-740-802-A
BITE Test of the Engine Bleed Air System (EBAS) (System Test)
TASK 71-13-00-010-802-A
Opening of the Fan Cowl Doors
TASK 71-13-00-410-802-A
Closing of the Fan Cowl Doors
TASK 78-36-00-010-802-A
Opening of the Thrust Reverser Cowl-Doors
TASK 78-36-00-410-802-A
Closing of the Thrust Reverser Cowl-Doors
F Functional Test of the HP Bleed Valve with the Test Set P/N 98D36109001000
3. Job Set-up
Subtask 36-11-51-861-070-A ** ON A/C NOT FOR ALL
A. Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
Subtask 36-11-51-941-072-A ** ON A/C NOT FOR ALL
B. Safety Precautions
   (1) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
   (2) On the AIR COND panel 30VU:
  • Make sure that the APU BLEED pushbutton switch is released (the ON legend is off).
  • Put a WARNING NOTICE(S) in position to tell persons not to operate the pneumatic system.
   (3) On the ENG panel 115VU:
  • Put a WARNING NOTICE(S) in position to tell persons not to start the engine 1(2).
   (4) On the HP ground connector:
  • Put a WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system.
   (5) On the ENG section of 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) in position to tell persons not to energize the FADEC 1(2).
Subtask 36-11-51-865-072-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/APU BLEED VLV CTL/BMC1 OVRD11HVD14
49VUAIR BLEED/X FEED/VALVE/BAT2HVD13
49VUAIR BLEED/ENG 2/MONG3HA2D12
49VUAIR BLEED/ENG 1/CTL2HA1D11
122VUAIR BLEED/ENG 1/MONG3HA1Z23
122VUAIR BLEED/ENG 2/CTL2HA2Z22
122VUAIR BLEED/X FEED VALVE/NORM1HVZ20
122VUAIR BLEED/APU BLEED VLV CTL/BMC2 OVRD12HVZ19
Subtask 36-11-51-010-093-A ** ON A/C NOT FOR ALL
D. Get Access
   (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802):
     (a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
     (b) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
Subtask 36-11-51-010-094-A ** ON A/C NOT FOR ALL
E. Get Access
   (1) Open the thrust reverser cowl doors (Ref. AMM TASK 78-36-00-010-802):
     (a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
     (b) FOR [1000EM2] (ENGINE-2)
461AL 462AR.
   (2) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the applicable engine.
4. Procedure
Subtask 36-11-51-750-050-A ** ON A/C NOT FOR ALL
A. Manual Test of the HP Bleed Valve
   (1) On the valve position indicator, record the position of the valve butterfly.
   (2) Make sure that the valve butterfly moves freely:
  • On the position indicator, use a WRENCH - STANDARD to fully open and fully close the valve butterfly.
  • Put the valve butterfly in the CLOSED position.
Subtask 36-11-51-480-068-A ** ON A/C NOT FOR ALL
B. Preparation for the Functional Test
   (1) Remove the blanking plug from the test port of the HP Bleed Valve.
   (2) Connect manually the 98D36109001000 TEST SET-EBAS,BLEED to the test port of the HP Bleed Valve.
   (3) Close the shutoff valve, the purge valve and the pressure regulator valve on the 98D36109001000 TEST SET-EBAS,BLEED.
NOTE: If the air cylinder has a regulator valve, it is not necessary to install the primary regulator valve supplied with the test set.
   (4) Connect the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY to the 98D36109001000 TEST SET-EBAS,BLEED.
   (5) Set the digital pressure gage to zero.
Subtask 36-11-51-720-075-A ** ON A/C NOT FOR ALL
C. Functional Test of the HP Bleed Valve with the Test Set - Engine Bleed System
   (1) Do this test:
ACTION
RESULT
1.On the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY, open the shutoff valve.
  • On the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY the cylinder pressure gage shows the pressure.
2.On the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY, use the primary ergulator to pressurize the pressure source to 43.5 psi (3.00 bar).
  • On the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY, the primary gage shows 43.5 psi (3.00 bar).
3.On the 98D36109001000 TEST SET-EBAS,BLEED:
  • Slowly pressurize the system to get a pressure value to 30 psi (2.07 bar).
On the HP Bleed Valve:
  • Make sure that you hear the airflow through the vent of the valve.
4.On the cockpit:
On the HP Bleed Valve:
  • Make sure that the position indicator shows OPEN.
5.On the cockpit:
  • Complete the BITE test.
NOTE: The pressure must be applied during all the test.
6.On the 98D36109001000 TEST SET-EBAS,BLEED:
  • Depressurize the system and close the shutoff valve.
NOTE: The HPV stay open and will close automatically at the next engine start.

Subtask 36-11-51-080-068-A ** ON A/C NOT FOR ALL
D. Disconnection of the Test Set.
WARNING: BEFORE YOU START TO REMOVE THE TOOLING, MAKE SURE THAT THERE IS NO PRESSURIZED GAS LEFT INSIDE THE DUCTS. IT CAN CAUSE AN INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT.
   (1) Disconnect the 98D36109001000 TEST SET-EBAS,BLEED from the test port of the HP bleed valve.
   (2) Install the blanking plug on the test port.
   (3) TORQUE the blanking plug to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in ) T.
   (4) Disconnect the 98D36109001000 TEST SET-EBAS,BLEED from the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY.
5. Close-up
Subtask 36-11-51-410-089-A ** ON A/C NOT FOR ALL
A. Close Access
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Remove the access platform(s).
   (3) Close the thrust-reverser cowl door (Ref. AMM TASK 78-36-00-410-802):
     (a) FOR [1000EM1] (ENGINE-1)
451AL 452AR.
     (b) FOR [1000EM2] (ENGINE-2)
461AL 462AR.
Subtask 36-11-51-410-090-A ** ON A/C NOT FOR ALL
B. Close Access
   (1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-802):
     (a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
     (b) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
   (2) Remove the WARNING NOTICE(S).
Subtask 36-11-51-862-067-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 01:12:30 UTC
"Aviabrain" 2025