W DOC AIRBUS | TSM A320F

Roll Back on Engine 2

TASK 72-00-00-810-804-A
Roll Back on Engine 2

1. Possible Causes
  • engine
  • ECU
  • low pressure fuel shut-off valve
  • IP bleed check valve
  • PS3 sense line
  • HMU-2 [4000KC2]
  • fuel pump
  • VALVE-AIR RELEASE, R WING TK [87QM]
2. Job Set-up Information
 A. Referenced Information
REFERENCE
DESIGNATION
TSM TASK 36-11-00-810-830-A
Loss of the Non-Return Function and Temperature Limitation Function of the Bleed Pressure-Regulator Valve of the Engine 2
AMM 28-24-00-720-001
Functional Test of the LP Fuel Shut Off Valves
AMM 36-11-41-200-001
Check of the IP Bleed Check Valve for Condition
AMM 71-00-00-710-006
Minimum Idle Check
AMM 72-00-00-200-026
Inspection/Check of the PS3 Line
AMM 72-00-00-220-001
Inspection of the PS3 Line Connections
AMM 72-21-00-290-001
Standard Borescope Inspection of Booster Rotor Blades, Stages 2, 3 and 4 through the Booster Inlet and Borescope Port SO
AMM 72-21-00-290-003
Borescope Inspection of the Booster Rotor Blades, Stages 2, 3, 4 and 5 through the Booster Inlet and Borescope Ports SO3 and SO5
AMM 72-31-00-290-001
Inspection of the High Pressure Compressor Rotor Assembly
AMM 72-31-00-290-002
Inspection of the High Pressure Compressor Rotor Assembly
AMM 72-32-00-200-001
Inspection/Check of the HPC Front Stator Assembly
AMM 72-32-00-210-002
Inspection/Check of the HPC Front Stator Assembly
AMM 72-41-00-290-001
Borescope Inspection of the Combustion Chamber Liners, Dome Areas, HPT Nozzle Vanes and Shrouds (as far as visible through two opposite ports)
AMM 72-51-00-290-002
Borescope Inspection of the High-Pressure Turbine-Nozzle Assembly
AMM 72-51-00-290-004
Borescope Inspection of High-Pressure Turbine Nozzle Assembly
AMM 72-54-00-210-002
Inspection of the Turbine Case
AMM 72-54-00-210-005
Inspection of the Turbine Case
AMM 72-54-00-290-001
Inspection of the Stage 1-3 Blades
AMM 72-54-00-290-002
Inspection of the Stage 4 Blades
AMM 72-54-00-290-003
Inspection of the Stage 2-4 Nozzle Segments
AMM 72-54-00-290-004
Inspection of the Stage 1-4 Stationary Air Seals
AMM 72-54-00-290-005
Inspection of the Stage 1-3 Blades
AMM 72-54-00-290-006
Inspection of the Stage 4 Blades
AMM 72-54-00-290-007
Inspection of the Stage 2-4 Nozzle Segments
AMM 72-54-00-290-008
Inspection of the Stage 1-4 Stationary Air Seals
AMM 73-11-10-000-001
Removal of the Fuel Pump and Filter Assembly
AMM 73-11-10-000-003
Removal of the Fuel Pump and Filter Assembly
AMM 73-11-10-210-003
Visual Inspection of the Fuel Filter Cartridge
AMM 73-11-10-210-004
Visual Inspection of the Fuel Filter Cartridge
AMM 73-11-10-400-001
Installation of the Fuel Pump and Filter Assembly
AMM 73-11-10-400-003
Installation of the Fuel Pump and Filter Assembly
AMM 73-21-10-000-001
Removal of the Hydromechanical Unit (HMU)
AMM 73-21-10-000-002
Removal of the Hydromechanical Unit (HMU)
AMM 73-21-10-400-001
Installation of the Hydromechanical Unit (HMU)
AMM 73-21-10-400-002
Installation of the Hydromechanical Unit (HMU)
AMM 73-29-00-710-040
Operational Test of the FADEC on the ground (with Engine Motoring)
AMM 79-00-00-281-002
Check of the Electrical Master Chip Detector (EMCD) for Particles
AMM 79-21-10-210-002
Check of the Lubrication Unit Magnetic Plugs and Scavenge Screens
3. Fault Confirmation
Subtask 72-00-00-710-056-A ** ON A/C NOT FOR ALL
A. Test
CAUTION: IF THE ENGINE WAS NOT RESTARTED AFTER THE EVENT OR WITHIN 24 HRS, DO THE ENGINE DRY OUT PROCEDURE, OR FURTHER DAMAGE TO ENGINE MAY OCCUR.
   (1) If the engine was successfully restarted after the event:
  • do the operational test of the FADEC 2A and 2B (with the engine non motoring) AMM 73-29-00-710-040.
   (2) If the engine could not restart after the event or no start attempt was done:
  • not applicable. No test must be attempted.
Subtask 72-00-00-710-056-B ** ON A/C NOT FOR ALL
A. Test
CAUTION: IF THE ENGINE WAS NOT RESTARTED AFTER THE EVENT OR WITHIN 24 HRS, DO THE ENGINE DRY OUT PROCEDURE, OR FURTHER DAMAGE TO ENGINE MAY OCCUR.
   (1) If the engine was successfully restarted after the event:
  • do the operational test of the FADEC 2A and 2B (with the engine non motoring) AMM 73-29-00-710-040.
   (2) If the engine could not restart after the event or no start attempt was done:
  • not applicable. No test must be attempted.
4. Fault Isolation
Subtask 72-00-00-810-053-A ** ON A/C NOT FOR ALL
CAUTION: WHEN THE "ENG/MASTER" LEVER IS IN THE "ON" POSITION, BE VERY CAREFUL NOT TO SET THE "ENG/MODE" SELECTOR SWITCH TO "CRANK" OR "IGN/START". IF YOU SET THE SELECTOR SWITCH TO ONE OF THESE POSITIONS, THE ENGINE WILL START. THERE IS THUS A RISK OF INJURY TO PERSONS AND OF DAMAGE TO EQUIPMENT.
A. This ECAM warning is shown if the engine is running below minimum idle and N2 is less than 50% with the Master Lever set to ON.
  • Do the trouble shooting related to the failure message(s) triggered (if any) during the fault confirmation test referred to in Para. 3.A.
  • Do a check of the Post Flight Report (PFR), of the FADEC Last Leg Report and SMR/Class 3 Report for ECU , HMU, ALT, FMV, VSV, PS3 failure messages.

   (1) If any failure message is shown:
  • do the trouble shooting related to the failure message(s).

   (2) If the fault occurred just after the engine start sequence or during taxi out or at first engine acceleration:
  • do a check of correct operation of the low pressure fuel shut-off valve AMM 28-24-00-720-001,
  • check that the drive mechanism of the valve is not broken.
   (3) If no failure message is found, or if at the time of the event, the crew reported symptoms such as stall, high EGT, sudden power loss, high vibration:
  • make sure the fan rotates freely and smoothly,
  • do a visual inspection of the LPT stage 4 rotor blades,
  • do a check of the magnetic plugs and screens of the lubrication unit AMM 79-21-10-210-002,
  • examine the fuel filter cartridge, do a contamination check of the fuel filter AMM 73-11-10-210-004,
  • visually inspect the PS3 sense line to make sure that there is no leakage or blockage AMM 72-00-00-220-001,
  • visually examine the VSV actuation system hardware, look for broken, loose or damaged hardware AMM 72-32-00-200-001.
     (a) If nothing is found:
       1 do the following inspection as necessary:
       2 If nothing is found:
  • do an inspection of the IP bleed check valve for free operation and condition of the flappers AMM 36-11-41-200-001.
         a If nothing is found:
         b If nothing is found:
   (4) If no failure message was found and if at the time of the event, the crew did not report symptoms such as stall, high EGT, sudden power loss, high vibrations:
     (a) If nothing is found:
       1 If nothing is found:
       2 If nothing is found:
     (b) If the fault occurred during engine operation in gravity feeding (boost pump off):
  • inspect the VALVE-AIR RELEASE, R WING TK [87QM] and fuel supply tubes in the wing fuel tank for condition,
  • repair or replace if necessary.
   (5) Do the operational test of the FADEC 2A and 2B (with the engine motoring) AMM 73-29-00-710-040.
Subtask 72-00-00-810-053-B ** ON A/C NOT FOR ALL
CAUTION: WHEN THE "ENG/MASTER" LEVER IS IN THE "ON" POSITION, BE VERY CAREFUL NOT TO SET THE "ENG/MODE" SELECTOR SWITCH TO "CRANK" OR "IGN/START". IF YOU SET THE SELECTOR SWITCH TO ONE OF THESE POSITIONS, THE ENGINE WILL START. THERE IS THUS A RISK OF INJURY TO PERSONS AND OF DAMAGE TO EQUIPMENT.
A. This ECAM warning is shown if the engine is running below minimum idle and N2 is less than 50% with the Master Lever set to ON.
  • Do the trouble shooting related to the failure message(s) triggered (if any) during the fault confirmation test referred to in Para. 3.A.
  • Do a check of the Post Flight Report (PFR), of the FADEC Last Leg Report and SMR/Class 3 Report for ECU , HMU, ALT, FMV, VSV, PS3 failure messages.

   (1) If any failure message is shown:
  • do the trouble shooting related to the failure message(s).

   (2) If the fault occurred just after the engine start sequence or during taxi out or at first engine acceleration:
  • do a check of correct operation of the low pressure fuel shut-off valve AMM 28-24-00-720-001,
  • check that the drive mechanism of the valve is not broken.
   (3) If no failure message is found, or if at the time of the event, the crew reported symptoms such as stall, high EGT, sudden power loss, high vibration:
  • make sure the fan rotates freely and smoothly,
  • do a visual inspection of the LPT stage 4 rotor blades,
  • do a check of the Master Magnetic Chip Detector for particles AMM 79-00-00-281-002,
  • examine the fuel filter cartridge, do a contamination check of the fuel filter AMM 73-11-10-210-003,
  • visually inspect the PS3 sense line to make sure that there is no leakage or blockage AMM 72-00-00-200-026,
  • visually examine the VSV actuation system hardware, look for broken, loose or damaged hardware AMM 72-32-00-210-002.
     (a) If nothing is found:
       1 do the following inspection as necessary:
       2 If nothing is found:
  • do an inspection of the IP bleed check valve for free operation and condition of the flappers AMM 36-11-41-200-001.
         a If nothing is found:
         b If nothing is found:
   (4) If no failure message was found and if at the time of the event, the crew did not report symptoms such as stall, high EGT, sudden power loss, high vibrations:
     (a) If nothing is found:
       1 If nothing is found:
         a If nothing is found:
     (b) If the fault occurred during engine operation in gravity feeding (boost pump off):
  • inspect the VALVE-AIR RELEASE, R WING TK [87QM] and fuel supply tubes in the wing fuel tank for condition,
  • repair or replace if necessary.
   (5) Do the operational test of the FADEC 2A and 2B (with the engine motoring) AMM 73-29-00-710-040.
Subtask 72-00-00-710-057-A ** ON A/C NOT FOR ALL
B. Do a minimum idle check AMM 71-00-00-710-006.
   (1) No additional maintenance action is required if the fault is not confirmed.
   (2) Repeat the fault isolation procedure if the fault continues.
[Rev.8 from Aug 2018] 2026.04.04 04:35:09 UTC
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