W DOC AIRBUS | AMM A320F

Operational Test of the Bleed Air System

TASK 36-11-00-710-803-A
Operational Test of the Bleed Air System

ZONE: 210
1. Reason for the Job
To do a check of the bleed air system with the two air conditioning packs, first with the bleed air system of the engine 1 then with the bleed air system of the engine 2.
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
98F10103500000
AR
CHOCK-MLG,ENGINE RUN-UP
 B. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
210
CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD
 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 31-60-00-860-001-A
EIS Start Procedure
TASK 31-60-00-860-002-A
EIS Stop Procedure
TASK 49-00-00-860-008-A
APU Start by External Power
TASK 49-00-00-860-008-A-01
APU Start by Batteries
TASK 49-00-00-860-009-A
APU Shutdown by External Power (131-9(A))
TASK 49-00-00-860-009-A-01
APU Shutdown by Batteries (131-9(A))
TASK 71-00-00-860-827-A
Start the Engine (Normal Automatic Start)
TASK 71-00-00-860-829-A
Engine Shutdown
TASK 71-00-00-869-803-A
Safety Precautions During Engine Ground Operations
F Tool Installation
3. Job Set-up
Subtask 36-11-00-860-120-A
A. Safety Precautions
   (1) Obey the safety precautions during engine ground operations (Ref. AMM TASK 71-00-00-869-803).
   (2) Make sure that the 98F10103500000 CHOCK-MLG,ENGINE RUN-UP are in position in front of each forward outboard Main Landing Gear (MLG) wheel.
F Tool Installation
Subtask 36-11-00-861-154-A
B. Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
Subtask 36-11-00-865-148-A
C. Make sure that this(these) circuit breaker(s) is(are) closed:
PANELDESIGNATIONFINLOCATION
** ON A/C 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 36-11-00-860-137-A
D. Aircraft Maintenance Configuration
   (1) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).
   (2) In the cockpit, on AIR COND panel 30VU:
  • Push the PACK 1 and PACK 2 pushbutton-switches to the engaged position (the OFF legends are off).
  • Set the PACK FLOW selector-switch to LO.
  • Make sure that the X BLEED selector-switch is in the AUTO position.
  • Make sure that the APU BLEED pushbutton-switch is released (the ON legend is off).
  • Push the ENG 1 BLEED and ENG 2 BLEED pushbutton-switches to the released position (the OFF legends come on).
   (3) Start the APU to pressurize the pneumatic system (Ref. AMM TASK 49-00-00-860-003) and/or (Ref. AMM TASK 49-00-00-860-008):
     (a) After the APU starts, Airbus recommends you to wait for a minimum of 3 minutes for the warm up period, before you select the APU BLEED.
   (4) In the cockpit, on AIR COND panel 30VU:
  • Push the APU BLEED pushbutton-switch (the ON legend comes on).
   (5) Start engine 1 and engine 2 (Ref. AMM TASK 71-00-00-860-827):
  • Keep engine 1 and engine 2 at idle.
4. Procedure
Subtask 36-11-00-710-060-B
A. Operational Test
ACTION
RESULT
1.On AIR COND panel 30VU:
  • Push the ENG 1(2) BLEED pushbutton switch.
On AIR COND panel 30VU:
  • The OFF legend of the ENG 1(2) BLEED pushbutton switch goes off.
2.On AIR COND panel 30VU:
  • Release the APU BLEED pushbutton switch.
On AIR COND panel 30VU:
  • The ON legend of the APU BLEED pushbutton switch goes off.

On the lower ECAM DU, on the BLEED page:
  • The APU bleed-valve symbol is shown in crossline green
  • The CROSSBLEED valve symbol is shown in crossline green
  • The engine 1(2) PRV symbol is shown in line green
  • The engine 1(2) HPV symbol is shown in line green
  • The engine 1(2) pressure is shown in between 20 psi (1.38 bar) and 40 psi (2.76 bar)
  • The engine 1(2) temperature is shown in between 100 deg.C (212.00 deg.F) and 205 deg.C (401.00 deg.F).
3.On the throttle levers:
  • Increase the speed of engine 1(2) between 35% and 40% of N1.
On the lower ECAM DU, on the BLEED page:
  • The APU bleed-valve symbol is shown in crossline green
  • The CROSSBLEED valve symbol is shown in crossline green
  • The engine 1(2) PRV symbol is shown in line green
  • The engine 1(2) HPV symbol is shown in line green
  • The engine 1(2) pressure is shown in between 48 psi (3.31 bar) and 52 psi (3.59 bar)
  • The engine 1(2) temperature is shown in 200 -25 DEG.C or +25 DEG.C (392 -45 DEG.F or +45 DEG.F).
CAUTION: DO NOT OPERATE THE ENGINE AT A SPEED HIGHER THAN 60% N1 FOR MORE THAN 25 SECONDS. IF YOU DO NOT OBEY THIS INSTRUCTION, THERE IS A RISK OF VORTEX AT THE ENGINE AIR INLET, WHICH CAN CAUSE: - FAN FLOW DISTORTION - TOO HIGH FATIGUE LOADS ON THE FAN BLADES - ENGINE STALL.
4.On the throttle levers:
  • Increase the speed of engine 1(2) to 80% of N1.
On the lower ECAM DU, on the BLEED page:
  • The APU bleed-valve symbol is shown in crossline green
  • The CROSSBLEED valve symbol is shown in crossline green
  • The engine 1(2) PRV symbol is shown in line green
  • The engine 1(2) HPV symbol is shown in crossline green
  • The engine 1(2) pressure is shown in between 48 psi (3.31 bar) and 52 psi (3.59 bar)
  • The engine 1(2) temperature is shown in 200 -25 DEG.C or +25 DEG.C (392 -45 DEG.F or +45 DEG.F).
5.On the throttle levers:
  • Move the throttle control lever to the idle position.
On the lower ECAM DU, on the BLEED page:
  • The APU bleed-valve symbol is shown in crossline green
  • The CROSSBLEED valve symbol is shown in crossline green
  • The engine 1(2) PRV symbol is shown in line green
  • The engine 1(2) HPV symbol is shown in line green
  • The engine 1(2) pressure is shown in between 20 psi (1.38 bar) and 52 psi (3.59 bar)
  • The engine 1(2) temperature is shown in between 100 deg.C (212.00 deg.F) and 205 deg.C (401.00 deg.F).
6.On AIR COND panel 30VU:
  • Push the APU BLEED pushbutton switch.
On AIR COND panel 30VU:
  • The ON legend of the APU BLEED pushbutton switch comes on.

On the lower ECAM DU, on the BLEED page:
  • The APU bleed-valve symbol is shown in line green
  • The CROSSBLEED valve symbol is shown in line green
  • The engine 1(2) PRV symbol is shown in cross line green
  • The engine 1(2) HPV symbol is shown in cross line green.
7.On AIR COND panel 30VU:
  • Release ENG 1(2) BLEED pushbutton switch.
On AIR COND panel 30VU:
  • The OFF legend of ENG 1(2) BLEED pushbutton switch comes on.
8.Do the same test for the opposite engine.

5. Close-up
Subtask 36-11-00-860-122-A
A. Put the aircraft back to its initial configuration.
   (1) Stop engines 1 and 2 (Ref. AMM TASK 71-00-00-860-829).
   (2) Stop the APU (Ref. AMM TASK 49-00-00-860-004) or (Ref. AMM TASK 49-00-00-860-009).
   (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 98F10103500000 CHOCK-MLG,ENGINE RUN-UP from the MLG wheel.
F Tool Installation
[Rev.10 from 2021] 2026.04.01 01:07:41 UTC
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