Failure of Engine 2

TASK 72-00-00-810-807-A
Failure of Engine 2

1. Possible Causes

engine
low-pressure fuel shut-off valve
VALVE-AIR RELEASE, R WING TK [87QM]
PS3 Sense line
IP bleed check valve
HMU-2 [4000KC2]
fuel pump
filter assy
VALVE-BLEED PRESS REG [4001HA]
CTL SW-ENG/MASTER 2 [2KC]

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
ESPM 204521
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 36-11-52-000-040	Removal of the Bleed Pressure-Regulator Valve
AMM 36-11-52-000-042	Removal of the Bleed Pressure Regulator Valve
AMM 36-11-52-400-040	Installation of the Bleed Pressure-Regulator Valve
AMM 36-11-52-400-042	Installation of the Bleed Pressure Regulator Valve
AMM 71-00-00-710-006	Minimum Idle Check
AMM 72-00-00-200-026	Inspection/Check of the PS3 Line
AMM 72-00-00-200-029	Inspection/Check of the PS3 Line
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 72-63-00-000-001	Removal of the Accessory Gearbox Module
AMM 72-63-00-000-003	Removal of the Accessory Gearbox Assembly
AMM 72-63-00-400-001	Installation of the Accessory Gearbox Module
AMM 72-63-00-400-003	Installation of the Accessory Gearbox Assembly
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 73-11-10-400-001	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)
AWM 761201
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 72-00-00-710-062-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.

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.

A. Test

NOTE: Even if you do not get a fault, do the troubleshooting procedure in Para 4., Fault Isolation.

NOTE: The normal cause of ENG 1(2) FAIL ECAM warning is when the engine rolls back sub idle. In example, below fifty percent of N2 with the associated engine master lever switched to the ON position.

(1) If the flight crew reported the ENG 1(2) FAIL ECAM warning message:
(a) When the engine was normally running at the time this warning occurred.

Or

(b) When the engine was shut down (engine master lever switched to the OFF position) at the time this warning occurred.
- For any above conditions, consider the warning as not applicable. No other maintenance action is necessary.
(2) If the engine was started again after the event:
(a) Do the operational test of the FADEC 2A and 2B (with the engine motoring) AMM 73-29-00-710-040.
1 If you get the ENG2 FAIL ECAM message:
a Go to the Para. 4., Fault Isolation.
2 If you do not get the ENG2 FAIL ECAM message:
a No maintenance action is necessary.
(3) If the engine could not start again after the event or no one tried to start it:
(a) Do the operational test of the FADEC 2A and 2B (with the engine non motoring) AMM 73-29-00-710-040.
(b) Go to the Para. 4., Fault Isolation.

Subtask 72-00-00-710-062-B ** ON A/C NOT FOR ALL

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.

A. Test

NOTE: Even if you do not get a fault, do the troubleshooting procedure in Para 4., Fault Isolation.

NOTE: The normal cause of ENG 1(2) FAIL ECAM warning is when the engine rolls back sub idle. In example, below fifty percent of N2 with the associated engine master lever switched to the ON position.

4. Fault Isolation
Subtask 72-00-00-810-056-A ** ON A/C NOT FOR ALL

A. Do the trouble shooting related to the failure message(s). If there is no failure message, go to Para 4.B.:
(1) Triggered (if any) during the fault confirmation test referred to in Para. 3.A.
(2) Available (if any) in the Post Flight Report (PFR), the FADEC Last Leg Report and SMR/Class 3 Report for ECU, HMU, FMV, VSV, PS3 failure messages.

Subtask 72-00-00-810-058-A ** ON A/C NOT FOR ALL

B. If there is no fault message:
(1) If no failure message and the fault (ECAM WARNING) occurred just after the engine start sequence or during taxi out or at first engine acceleration with no other symptom than the engine spooling down sub idle:

Do a check for 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.

(2) If no failure message is found:

Inspect the VALVE-AIR RELEASE, R WING TK [87QM] and fuel supply tubes in the wing fuel tank for condition,
Repair or replace as necessary.

(3) If no failure message is found, and if at the time of the event, the Crew reported symptoms such as Stall, high EGT, sudden power loss, high vibration, do the following:

Make sure the fan rotates freely and smoothly,
Do a visual inspection of the LPT stage 4 rotor blades,
Do a check of the Lubrication Unit Magnetic Plugs and Screens AMM 79-21-10-210-002,
Examine the fuel filter cartridge, do a contamination check of the fuel filter AMM 73-11-10-000-001 and AMM 73-11-10-400-001,
Visually examine the VSV actuation system hardware for abnormal condition AMM 72-32-00-200-001.

(a) If nothing is found:

Do an inspection/check of the PS3 Sense line AMM 72-00-00-200-029.

(b) 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.

Visually examine the alternator stator and rotor for evidence of contact.

1 If evidence of contact is found:

Do a check for correct installation of the rotor and the stator,
Repair as required.

2 If any play is noticed in the drive shaft assembly:

Replace the AGB AMM 72-63-00-000-001 and AMM 72-63-00-400-001.

(4) If nothing is found, do the following inspection:
(a) Do a borescope inspection of the high-pressure compressor-rotor assembly AMM 72-31-00-290-001,
(b) Do a borescope inspection of the high-pressure turbine blades/nozzles AMM 72-51-00-290-002,
(c) Do a borescope inspection of the low pressure turbine AMM 72-54-00-290-001 and AMM 72-54-00-290-002 and AMM 72-54-00-290-003 and AMM 72-54-00-290-004 and AMM 72-54-00-210-002,
(d) Do a borescope inspection of the combustor chamber AMM 72-41-00-290-001,
(e) Do a borescope inspection of the low pressure compressor AMM 72-21-00-290-001.
(f) If the problem occurred again:

Troubleshoot as per (Ref. TSM TASK 36-11-00-810-830) to check the 10HA2 and 4001HA2.

(g) If nothing is found:

Replace the HMU-2 [4000KC2] AMM 73-21-10-000-001 and AMM 73-21-10-400-001.

(h) If the problem occurred again:

Replace the fuel pump and filter assy AMM 73-11-10-000-001 AMM 73-11-10-400-001.

(i) If the problem occurred again:

Replace the VALVE-BLEED PRESS REG [4001HA] AMM 36-11-52-000-040 and AMM 36-11-52-400-040.

Subtask 72-00-00-810-056-B ** ON A/C NOT FOR ALL

C. Do the trouble shooting related to the failure message(s). If there is no failure message, go to Para 4.B.:
(1) Triggered (if any) during the fault confirmation test referred to in Para. 3.A.
(2) Available (if any) in the Post Flight Report (PFR), the FADEC Last Leg Report and SMR/Class 3 Report for ECU, HMU, FMV, VSV, PS3 failure messages.

Subtask 72-00-00-810-058-B ** ON A/C NOT FOR ALL

D. If there is no fault message:
(1) If no failure message and the fault (ECAM WARNING) occurred just after the engine start sequence or during taxi out or at first engine acceleration with no other symptom than the engine spooling down sub idle:

Do a check for 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.

(2) If no failure message is found and 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 as necessary.

(3) If no failure message is found, and if at the time of the event, the Crew reported symptoms such as Stall, high EGT, sudden power loss, high vibration, do the following:

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 73-11-10-000-003 and AMM 73-11-10-400-003,
Visually examine the VSV actuation system hardware for abnormal condition AMM 72-32-00-210-002.

(a) If nothing is found:

Do an inspection/check of the PS3 Sense line AMM 72-00-00-200-026.

(b) If the fault continues:

Do a check of the aircraft wiring between C/B (1KC2) pin 2 and CTL SW-ENG/MASTER 2 (2KC) pin 3G then CTL SW-ENG/MASTER 2 (2KC) pin 1G to HMU (HPSOV) connector A pin 1.

Replace the CTL SW-ENG/MASTER 2 [2KC] on the panel 115VU AWM 761201 ESPM 204521.

(d) 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.

(e) If nothing is found:

Visually examine the alternator stator and rotor for evidence of contact.

1 If evidence of contact is found:

Do a check for correct installation of the rotor and the stator,
Repair as required.

2 If any play is noticed in the drive shaft assembly:

Replace the AGB AMM 72-63-00-000-003 and AMM 72-63-00-400-003.

(4) If nothing is found, do the following inspection:
(a) Do a borescope inspection of the high-pressure compressor-rotor assembly AMM 72-31-00-290-002,
(b) Do a borescope inspection of the high-pressure turbine blades/nozzles AMM 72-51-00-290-004,
(c) Do a borescope inspection of the low pressure turbine AMM 72-54-00-290-005 and AMM 72-54-00-290-006 and AMM 72-54-00-290-007 and AMM 72-54-00-290-008 and AMM 72-54-00-210-005,
(d) Do a borescope inspection of the combustor chamber AMM 72-41-00-290-001,
(e) Do a borescope inspection of the low pressure compressor AMM 72-21-00-290-003.
(f) If the problem occurred again:

Troubleshoot as per (Ref. TSM TASK 36-11-00-810-830) to check the 10HA2 and 4001HA2.

(g) If nothing is found:

Replace the HMU-2 [4000KC2] AMM 73-21-10-000-002 and AMM 73-21-10-400-002.

(h) If the problem occurred again:

Replace the fuel pump and filter assy AMM 73-11-10-000-003 AMM 73-11-10-400-003.

(i) If the problem occurred again:

Replace the VALVE-BLEED PRESS REG [4001HA] AMM 36-11-52-000-042 and AMM 36-11-52-400-042.

Subtask 72-00-00-710-063-A ** ON A/C NOT FOR ALL

E. 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 04:40:59 UTC