DOC AIRBUS | TSM A320FSurge or Stall on Engine 2
1. Possible Causes
2 Job Set-up Information
A. Referenced Information
REFERENCE DESIGNATION
73-22-00-810-818-B Loss of the P2/T2 Sensor on Engine 2
73-22-00-810-872-A Disagreement of T2 Indication between Engine 2 and Aircraft Sensors
Ref. AMM 31-32-00-860-012 Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page
Ref. AMM 31-36-00-740-008 Access to the Parameter Call-Up Menus
Ref. AMM 31-36-00-740-011 Printout of the Manually Requested Reports
Ref. AMM 36-11-41-200-010 Check of the IP Bleed Check Valve for Condition
REFERENCE DESIGNATION
Ref. AMM 71-00-00-710-013 Test No.11 : High Power Assurance Test
Ref. AMM 71-13-00-010-010 Opening of the Fan Cowls 437AL(447AL),438AR(448AR)
Ref. AMM 72-00-00-200-016 Inspection of the HP Compressor
Ref. AMM 72-00-00-600-011 Lubrication of the LPC Bleed Valve Mechanism
Ref. AMM 73-22-00-710-040 Operational Test of the FADEC SYSTEM on the Ground
Ref. AMM 73-22-34-710-040 Operational Test of the EEC
Ref. AMM 73-22-49-220-040 Purge the Burner Pressure Sensor Tube
Ref. AMM 75-32-42-200-010 Inspection of the VSV Mechanism
Ref. AMM 75-32-51-000-010 Removal of the HPC Stage 7 Solenoid Valve
Ref. AMM 75-32-51-000-012 Removal of the HPC Stage 7 Solenoid Valve
Ref. AMM 75-32-51-000-013 Removal of the HPC Stage 7 Solenoid Valve
Ref. AMM 75-32-51-400-010 Installation of the HPC Stage 7 Solenoid Valve
Ref. AMM 75-32-51-400-012 Installation of the HPC Stage 7 Solenoid Valve
Ref. AMM 75-32-51-400-013 Installation of the HPC Stage 7 Solenoid Valve
Ref. AMM 75-32-51-700-010 Functional Test of the HPC Stage 7 Solenoid Valve with Test Set
IAE2R19437
Ref. AMM 75-32-52-000-010 Removal of the HPC Stage 7 Bleed Valve - Upper Right
Ref. AMM 75-32-52-000-011 Removal of the HPC Stage 7 Bleed Valve - Lower Right
Ref. AMM 75-32-52-000-012 Removal of the HPC Stage 7 Bleed Valve - Lower Left
Ref. AMM 75-32-52-400-010 Installation of the HPC Stage 7 Bleed Valve - Upper Right
Ref. AMM 75-32-52-400-011 Installation of the HPC Stage 7 Bleed Valve - Lower Right
Ref. AMM 75-32-52-400-012 Installation of the HPC Stage 7 Bleed Valve - Lower Left
Ref. AMM 75-32-52-700-011 Functional Test of the HPC Stage 7 Bleed Valve with Test Set
IAE2R19437
Ref. AMM 75-32-53-000-010 Removal of the HPC Stage 10 Solenoid Valve
Ref. AMM 75-32-53-400-010 Installation of the HPC Stage 10 Solenoid Valve
Ref. AMM 75-32-54-000-010 Removal of the HPC Stage 10 Bleed Valve
Ref. AMM 75-32-54-400-010 Installation of the HPC Stage 10 Bleed Valve
Ref. AMM 78-32-00-010-010 Opening of the Thrust Reverser Halves
Surge or Stall on Engine 1 (2) SHEET 1
Figure 71(IAE)-00-00-991-00100-A / SHEET 1/1 - Surge or Stall on Engine 1 (2) not printed, as per
printing preferences
3. Fault Confirmation
Subtask 71-00-00-710-061-A
A. Not applicable
4. Fault Isolation
Subtask 71-00-00-810-080-A
A. Procedure: Initial Checks
(Ref. Fig. Surge or Stall on Engine 1 (2) SHEET 1)
(1) Check in the aircraft/engine technical logs if this engine is on a 10 cycle fly-on because of a stall/
surge.
(a) If the engine is on a 10 cycle fly-on, then do the troubleshooting procedure in section 4.D.
(b) If the engine is not on a 10 cycle fly-on, then continue with this procedure.
(2) Do a check in the aircraft technical logs for crew observation of the stall/surge felt or heard by the
crew, which could include records of clear sound of stall/surge, aircraft yaw or engine parameter split.
(a) If there is no crew confirmation of the stall/surge, then continue with this procedure.
(b) If there is crew confirmation of the stall/surge, then continue with this troubleshooting procedure
in section 4.C, from step (1).
Subtask 71-00-00-810-059-A
B. Procedure: STALL ECAM message/No Crew Observation
NOTE: For A5 engines that are post-EEC software SCN 17 (SB V2500-ENG-73-0184), all stalls/surges
will be indicated on the ECAM by a warning ENG 2 STALL and the related clear language message
VSV MECH/BLD VLV/LPC2 regardless of the duration of the stall/surge. Unselected continuous
ignition may be captured on the lower ECAM panel as this is part of the stall recovery logic.
(1) Examine the inlet and the exhaust for foreign material or indication of internal engine damage.
(a) If foreign material or internal damage is present, then do the troubleshooting procedure in section
4.D.
(b) If foreign material or damage is not present, continue with this procedure.
(2) Do a check of the CFDS or engine records for all ECAM messages or fault acronyms during the last
flight related to powerplant or engine.
(a) If other ENG 2 STALL ECAM messages are found, do an engine power assurance test Ref.
AMM 71-00-00-710-013 .
1 If the engine stalls during the power assurance test, then do the troubleshooting procedure
in section 4.D.
2 If powerplant or engine related Class 1 or 2 CFDS messages or fault acronyms are found,
then do the troubleshooting, refer to TSM/AMM.
3 If the messages are not related to stall/surge issues, then do the troubleshooting procedure
in section 4.D. But this can be put on hold until the next possible time for maximum of 10
cycles, on condition that engine 1 is not on a 10 cycle fly-on. If it is, do the troubleshooting
before the aircraft is released for flight.
4 If the power assurance test is successful, then do the troubleshooting procedure in section
4.D. But this can be put on hold until the next possible time for maximum of 10 cycles, on
condition that engine 1 is not on a 10 cycle fly-on. If it is, do the troubleshooting before the
aircraft is released for flight.
(b) If other powerplant or engine related ECAM messages are found, then do the troubleshooting,
refer to TSM/AMM before the aircraft is released and do the troubleshooting procedure in
section 4.D. But this can be put on hold until the next possible time for maximum of 10 cycles,
on condition that engine 1 is not on a 10 cycle fly-on. If it is, do the troubleshooting before the
aircraft is released for flight.
NOTE: If there is an indication of stall/surge during these 10 cycles, then do the troubleshooting
procedure in section 4.D.
Subtask 71-00-00-810-081-A
C. Procedure: Crew Observation
(1) Do a check of the CFDS or engine records for ENG 2 STALL ECAM messages.
(a) If messages are found, then do the troubleshooting in section 4.D.
(b) If no messages are found, then continue with this procedure.
NOTE: A noise from the aircraft can be monitored by the flight crew and reported as a possible
stall/surge, when the noise actually had other cause. In this case no ECAM warning will
be set.
(2) Do the operational test of the FADEC System Ref. AMM 73-22-00-710-040 .
(a) If powerplant or engine related Class 1 or 2 CFDS messages or fault acronyms are found, then
do the troubleshooting, refer to TSM/AMM.
(b) If no messages are recorded, then to help you in identifying the noise and to confirm if a real
stall/surge occurred, do section 4.B, step (1) to examine the engine and then do section 4.D, step
(10). If nothing is found, no more troubleshooting is necessary.
Subtask 71-00-00-810-060-A
D. Procedure: Full Troubleshooting
NOTE: It is recommended to do the HPC borescope procedure within the first steps of troubleshooting in
order to make an estimate of the engine serviceability as soon as possible.
(1) Open the fan cowls 437AL, 438AR Ref. AMM 71-13-00-010-010 . Open the thrust reverser halves
451AL, 452AR Ref. AMM 78-32-00-010-010 .
(2) Examine the inlet, the exhaust and the bleed valves for foreign material or indication of internal
engine damage.
(a) If foreign material or internal damage is present then do a borescope inspection of the HPC
stages 3 and 6 Ref. AMM 72-00-00-200-016 .
1 If damage is outside of limits, reject the engine.
2 If no damage is found or any damage is not outside of limits, continue with this procedure.
(b) If foreign material or damage is not present, continue with this procedure.
(3) Do the Operational Test of the FADEC System Ref. AMM 73-22-00-710-040 .
(a) Address all powerplant or engine related CFDS messages or EEC fault codes found and do the
troubleshooting, refer to TSM/AMM.
(4) Do a detailed visual inspection on the Burner Pressure Sensor Tube and purge the Burner Pressure
Sense Line Ref. AMM 73-22-49-220-040 .
NOTE: If difference is found and corrected during troubleshooting steps (5) to (9), it is acceptable to
skip to step (10), do the engine power assurance test and return the aircraft to service.
(5) Do a functional check of the HPC 7th stage 7A and 7C bleed valves (P/N AC69924) and
the associated solenoids (P/N AC69572) operation (4020KS1-A and 4020KS3-A only) Ref.
AMM 75-32-52-700-011 and Ref. AMM 75-32-51-700-010 using the bleed valve test set TEST SETBLEED
VALVE (IAE2R19437) or equivalent.
NOTE: The stage 7B bleed valve (bleed valve without silencer) operates only during starting and
the stage 10 bleed valve during starting and surge recovery. The bleed valves are scheduled
open as necessary to prevent/recover compressor surge. When a valve is stuck open or
open when it must be closed, the result is good for engine operation and will not cause a compressor
surge.
(6) Do an inspection and lubrication of the VSV mechanism Ref. AMM 75-32-42-200-010 .
(7) Do a check of condition of the Intermediate Pressure Check Valve (IPCV) Ref.
AMM 36-11-41-200-010 .
(8) Lubricate and do a general visual inspection on the 2.5 bleed system Ref. AMM 72-00-00-600-011 .
(9) Look for SMR messages Ref. AMM 31-32-00-860-012 .
(a) If P2T2/ADIRS/1/2/EEC2 with fault acronym T2SSF is present, do the troubleshooting for this
fault (Ref. TSM 73-22-00-810-872) . If P2T2 SENS/HC/EEC2 with fault acronym T2XCF is
present, do the troubleshooting for this fault (Ref. TSM 73-22-00-810-818) .
(b) If messages are not apparent, get one or more of the AIDS reports that follow:
Start, Take-off, Cruise or Gas path advisory Ref. AMM 31-36-00-740-011 . Do a cross check of
the T2 readings between the engines and each engine against the aircraft TAT. This can also be
checked by an alpha parameter call up on the MCDU Ref. AMM 31-36-00-740-008 . If there is a
difference of more than 8 deg.C between the readings then do the troubleshooting for this fault
(Ref. TSM 73-22-00-810-872) .
NOTE: If this procedure is followed for an engine that was on a 10 cycle fly-on which followed
step 4.B.(2)(a)3, then section 4.D, step (10) can be replaced by an operational test of the
EEC Ref. AMM 73-22-34-710-040 .
(10) Do an engine power assurance test Ref. AMM 71-00-00-710-013 .
(a) If the engine stalls during the power assurance test, remove and replace all bleed
valves and solenoids Ref. AMM 75-32-51-000-010 , Ref. AMM 75-32-51-400-010 , Ref.
AMM 75-32-51-000-012 , Ref. AMM 75-32-51-400-012 , Ref. AMM 75-32-51-000-013 , Ref.
AMM 75-32-51-400-013 , Ref. AMM 75-32-52-000-010 , Ref. AMM 75-32-52-400-010 , Ref.
AMM 75-32-52-000-011 , Ref. AMM 75-32-52-400-011 , Ref. AMM 75-32-52-000-012 , Ref.
AMM 75-32-52-400-012 , Ref. AMM 75-32-53-000-010 , Ref. AMM 75-32-53-400-010 , Ref.
AMM 75-32-54-000-010 and Ref. AMM 75-32-54-400-010 and continue the engine power
assurance test.
1 If the engine stalls again, do a borescope inspection of the HPC from stage 12 and working
forward to stage 6 and then stage 3 Ref. AMM 72-00-00-200-016 .
a Reject the engine if damage is outside of limits.
(b) If powerplant or engine related class 1 or 2 CFDS messages or fault acronyms are found, then
do the troubleshooting, refer to TSM/AMM.
(c) If the power assurance test is successful, return the engine to service.
(11) If no differences are found in the above paragraphs, but the engine power assurance test is not
successful, contact IAE for more troubleshooting advice. [Rev.6 from Feb 2017] 2026.04.04 04:35:01 UTC