DOC AIRBUS | AMM A320FInspection/Check After the Engine has Exceeded the Operational Limits [CFML]
TASK 72-00-00-200-818-A
Inspection/Check After the Engine has Exceeded the Operational Limits
This tasks provides operational limits applicable to the engine and actions required if limits are exceeded. List of engine exceedances covered in this task:
N1, N2, EGT, low oil pressure, oil temperature, oil consumption, after In-Flight Shut Down (IFSD), rough landing limits are exceeded, excessive vertical loads.
A. Work Zones and Access Panels
B. Referenced Information
3. Job Set-up
Subtask 72-00-00-860-130-A
Subtask 72-00-00-290-134-A
[Rev.10 from 2021]
2026.04.01 12:57:40 UTC
Inspection/Check After the Engine has Exceeded the Operational Limits
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.
1. Reason for the JobThis tasks provides operational limits applicable to the engine and actions required if limits are exceeded. List of engine exceedances covered in this task:
N1, N2, EGT, low oil pressure, oil temperature, oil consumption, after In-Flight Shut Down (IFSD), rough landing limits are exceeded, excessive vertical loads.
NOTE: the DMC will freeze on ECAM any exceedance indication for N1, N2 and EGT till the next engine start is performed.
2. Job Set-up InformationA. Work Zones and Access Panels
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 210 | CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD |
| 400 | POWER PLANT, NACELLES AND PYLONS |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 12-13-79-610-808-A | Draining of the Oil Tank |
| TASK 71-00-00-700-805-A | Dry-Motoring Check |
| TASK 71-00-00-710-816-A | Power Assurance Check |
| TASK 71-00-51-000-803-A | Removal of the Power Plant with 2D Bootstrap |
| TASK 72-00-00-100-803-A | Gas Path Cleaning with a Cleaning Solution |
| TASK 72-00-00-100-804-A | Gas Path Cleaning with Water (Non Detergent) |
| TASK 72-00-00-290-822-A | Borescope Inspection of the Low Pressure Turbine (LPT) Blades |
| TASK 72-21-00-290-802-A | Borescope Inspection of the Booster Blades and Vanes (PRE SB 72-00-0080) |
| TASK 72-21-00-290-802-A-01 | Borescope Inspection of the Booster Blades and Vanes (POST SB 72-00-0080) |
| TASK 72-21-20-210-802-A | Visual Inspection of the Fan Blade |
| TASK 72-23-01-210-801-A | Visual Inspection of the Fan Case |
| TASK 72-24-00-210-801-A | Visual Inspection of the Fan Frame Module |
| TASK 72-30-00-290-801-A | Borescope Inspection of the High Pressure Compressor Section |
| TASK 72-40-00-290-801-A | Borescope Inspection of Combustion Section and Fuel Nozzles |
| TASK 72-52-00-290-803-A | Borescope Inspection of High Pressure Turbine |
| TASK 72-59-00-210-801-A | Visual Inspection of the Turbine Rear Frame Module |
| TASK 73-29-00-740-819-A | Exceedance Report (Menu Mode) |
| TASK 79-00-00-200-806-A | Visual Inspection of the A, B and C Sumps, the Accessory Gearbox (AGB) and the Transfer Gearbox Sump Scavenge Screen Plugs for Debris |
| TASK 79-00-00-281-805-A | Analyze Oil Particles |
| TASK 79-21-05-000-801-A | Removal of the Scavenge Screen Plugs |
| TASK 79-21-05-000-803-A | Removal of the Oil Filter Cartridge |
| TASK 79-21-05-210-801-A | Visual Inspection of the Oil filter Cartridge |
| TASK 79-21-05-400-801-A | Installation of the Scavenge Screen Plugs |
| TASK 79-36-00-220-801-A | Detailed Inspection of the Oil Debris Monitoring System (ODMS) Sensor for Debris |
| TASK 79-36-10-000-801-A | Removal of the Oil Debris Monitoring System (ODMS) Sensor |
| TASK 80-11-05-210-801-A | Detailed Inspection of the Air Turbine Starter Magnetic Chip Detector |
| TSM 73-00-00-810-945 | Stall of the Engine 1 or 2 / Audible Stall / Engine: ENG 1(2) STALL ECAM |
| TSM 77-11-00-810-817 | N2 Speed Redline Limit Exceedance on Engine 1(2) on both Channels |
| TSM 77-11-00-810-819 | N1 Speed Redline Limit Exceedance on Engine 1(2) on both Channels |
| TSM 77-21-00-810-813 | EGT Redline Exceedance |
| TSM 79-00-00-810-842 | High Oil Consumption |
| TSM 79-32-00-810-854 | The Engine Oil Pressure is Operating below the Minimum Limit |
| TSM 79-32-00-810-857 | The Engine Oil Pressure too High on Engine 1(2) on both Channels |
| TSM 80-11-00-810-834 | Hot Start on Engine 1(2) |
Operational EGT (T48) Limits for Ground Starting OperationsSubtask 72-00-00-860-130-A
A. System Configuration
(1) In case of N1, N1, Exhaust Gas Temperature (EGT) exceedance, record the max indicated value on ECAM. Note the indication is present until the next transition from phase 1 to phase 2 (next engine start).
Through the MCDU (before a next engine start is attempted) get access to the FADEC "EXCEEDANCE REPORT" (Ref. AMM TASK 73-29-00-740-819). This report gives the Max Value reached for the following parameters: N1 Actual (physical), N1 Indicated, N2, EGT, Oil Pressure Max (over-pressure), Oil Pressure Min (Low pressure), Oil Temperature.
Important: These values are cleared when EEC flight leg is incremented are manual reset in the Menu Mode.
4. Procedure(1) In case of N1, N1, Exhaust Gas Temperature (EGT) exceedance, record the max indicated value on ECAM. Note the indication is present until the next transition from phase 1 to phase 2 (next engine start).
Through the MCDU (before a next engine start is attempted) get access to the FADEC "EXCEEDANCE REPORT" (Ref. AMM TASK 73-29-00-740-819). This report gives the Max Value reached for the following parameters: N1 Actual (physical), N1 Indicated, N2, EGT, Oil Pressure Max (over-pressure), Oil Pressure Min (Low pressure), Oil Temperature.
Important: These values are cleared when EEC flight leg is incremented are manual reset in the Menu Mode.
Subtask 72-00-00-290-134-A
A. Checks to be Done after a Hot Start
(a) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight TSM 80-11-00-810-834.
(2) Area B: EGT (T48) is more than 1418 deg.F (770.00 deg.C) but less than or equal to 1472 deg.F (800.00 deg.C) for less than 10 seconds.
(a) Do a borescope inspection of the HPT blades (Ref. AMM TASK 72-52-00-290-803).
(b) Do a borescope inspection of the stage 1 and 7 LPT blades (Ref. AMM TASK 72-00-00-290-822).
(c) Do a visual inspection of the turbine rear frame.
(d) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight TSM 80-11-00-810-834.
(e) A maximum service extension of one start is permitted and, if that start is satisfactory, one cycle is permitted before you must correct the problem.
(3) Area C: Stop the start and do these checks before you try to start the engine again.
(a) Do a borescope inspection of the HPT blades and stage 1 LPT blades (Ref. AMM TASK 72-52-00-290-803) (Ref. AMM TASK 72-00-00-290-822).
(4) Area D: If the start was in Area D, remove the engine (Ref. AMM TASK 71-00-51-000-803).
(a) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight TSM 80-11-00-810-834.
(5) If the EGT is more than 900 deg.C (1652.00 deg.F), reset the EGT max pointer after you correct the problem.
Subtask 72-00-00-290-135-A NOTE: Through the MCDU (before a next engine start is attempted) get access to the FADEC "EXEEDANCE REPORT" (Ref. AMM TASK 73-29-00-740-819). This report gives the Max Value reached during the event as well as the duration of the exceedance.
NOTE: Ground starting Exhaust Gas Temperature (EGT) (T48) limits are given.
(1) Area A: EGT (T48) is more than 1382 deg.F (750.00 deg.C) but less than or equal to 1418 deg.F (770.00 deg.C) for a period of less than 30 seconds. (a) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight TSM 80-11-00-810-834.
(2) Area B: EGT (T48) is more than 1418 deg.F (770.00 deg.C) but less than or equal to 1472 deg.F (800.00 deg.C) for less than 10 seconds.
(a) Do a borescope inspection of the HPT blades (Ref. AMM TASK 72-52-00-290-803).
(b) Do a borescope inspection of the stage 1 and 7 LPT blades (Ref. AMM TASK 72-00-00-290-822).
(c) Do a visual inspection of the turbine rear frame.
(d) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight TSM 80-11-00-810-834.
(e) A maximum service extension of one start is permitted and, if that start is satisfactory, one cycle is permitted before you must correct the problem.
(3) Area C: Stop the start and do these checks before you try to start the engine again.
(a) Do a borescope inspection of the HPT blades and stage 1 LPT blades (Ref. AMM TASK 72-52-00-290-803) (Ref. AMM TASK 72-00-00-290-822).
(4) Area D: If the start was in Area D, remove the engine (Ref. AMM TASK 71-00-51-000-803).
(a) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight TSM 80-11-00-810-834.
(5) If the EGT is more than 900 deg.C (1652.00 deg.F), reset the EGT max pointer after you correct the problem.
B. Checks to Be Done if an Over Temperature Condition Occurs at Operating Conditions Other Than Starting
(1) Through the MCDU (before a next engine start is attempted) get access to the FADEC "EXEEDANCE REPORT" (Ref. AMM TASK 73-29-00-740-819). This report gives the maximum value reached during the event as well as the duration of the exceedance.
(a) (b) If there are ten EGT excursions into Area A and Area B together, remove the engine (Ref. AMM TASK 71-00-51-000-803).
(c) If the EGT was in the Area A, and you do not know the cause, do these inspections:
1 Do a visual inspection of the engine inlet for damage before subsequent flight.
2 Do a visual inspection of the engine exhaust for damage before subsequent flight.
3 Do a borescope inspection on the High Pressure Turbine (HPT) stage 1 blades within ten cycles (Ref. AMM TASK 72-52-00-290-803).
4 Do the troubleshooting for EGT over limit as specified in TSM 77-21-00-810-813.
5 If the inspections are satisfactory, continue the engine in service.
(d) If the EGT was in the Area A, and you know the cause, do these steps:
2 Monitor the engine EGT performance trend and make sure that the engine stays in the serviceable EGT margins.
(e) If the EGT was in the Area B, do these tasks:
1 Do a visual inspection of the engine inlet for damage before subsequent flight.
2 Do a visual inspection of the engine exhaust for damage before subsequent flight.
3 Do the borescope inspection on the HPT stage one blades within ten cycles (Ref. AMM TASK 72-52-00-290-803).
4 Do the troubleshooting for EGT over limit as specified in TSM 77-21-00-810-813.
5 If the inspections are satisfactory, continue the engine in service.
6 Monitor the engine EGT performance trend and make sure the engine stays in the serviceable EGT margins.
(f) If the EGT was in Area C, remove the engine:
1 One flight is permitted before the engine is removed, if there is no damage beyond the serviceable limits:
a Do a borescope inspection of the combustion chamber (Ref. AMM TASK 72-40-00-290-801).
b Do a borescope inspection of the HPT stage one blades (Ref. AMM TASK 72-52-00-290-803).
c Do a borescope inspection of the stage 1 and 7 blades (Ref. AMM TASK 72-00-00-290-822).
d Do a visual inspection of the engine inlet, engine exhaust and turbine rear frame.
e Do the troubleshooting for EGT over limit as specified in TSM 77-21-00-810-813.
(g) After you do all the troubleshooting and problem resolution, do these steps:
1 Erase any applicable ECAM messages.
2 Erase the ECAM snapshot data saves.
3 Reset the EGT display box.
Subtask 72-00-00-290-136-A (1) Through the MCDU (before a next engine start is attempted) get access to the FADEC "EXEEDANCE REPORT" (Ref. AMM TASK 73-29-00-740-819). This report gives the maximum value reached during the event as well as the duration of the exceedance.
NOTE: There can be many causes for an Exhaust Gas Temperature (EGT) over temperature condition, such as:
- Engine warm up before take-off is not sufficient.
- Full rated take-off in hot day condition.
- Dirty compressor airfoils, engine deterioration (low remaining EGT margin), engine bleed selected during take-off after throttle push.
- Foreign object damage, engine system malfunction (for example: variable bleed valve actuation) or engine hardware malfunction (for example: airfoil failure, hot air leak, etc.).
NOTE: Some positive EGT margin can result by doing an engine gas path water wash (Ref. AMM TASK 72-00-00-100-803) (Ref. AMM TASK 72-00-00-100-804). This makes engine performance better but is temporary. It is not a long term repair for high EGT or engine deterioration. Read the FADEC Exceedance Report (Ref. AMM TASK 73-29-00-740-819), to find the maximum EGT value that was recorded during the event, as well the duration of the exceedance. If this report is not available, get the data from the CEOD.
(2) Examine the take-off and maximum continuous EGT for the over limits (Exceedance) condition as follows: (a) (b) If there are ten EGT excursions into Area A and Area B together, remove the engine (Ref. AMM TASK 71-00-51-000-803).
(c) If the EGT was in the Area A, and you do not know the cause, do these inspections:
1 Do a visual inspection of the engine inlet for damage before subsequent flight.
2 Do a visual inspection of the engine exhaust for damage before subsequent flight.
3 Do a borescope inspection on the High Pressure Turbine (HPT) stage 1 blades within ten cycles (Ref. AMM TASK 72-52-00-290-803).
4 Do the troubleshooting for EGT over limit as specified in TSM 77-21-00-810-813.
5 If the inspections are satisfactory, continue the engine in service.
(d) If the EGT was in the Area A, and you know the cause, do these steps:
NOTE: If the EGT over temperature conditions is known to be caused by engine deterioration (low remaining EGT margin, EGTHDM), no troubleshooting is necessary.
1 Correct the cause of the over temperature. 2 Monitor the engine EGT performance trend and make sure that the engine stays in the serviceable EGT margins.
(e) If the EGT was in the Area B, do these tasks:
1 Do a visual inspection of the engine inlet for damage before subsequent flight.
2 Do a visual inspection of the engine exhaust for damage before subsequent flight.
3 Do the borescope inspection on the HPT stage one blades within ten cycles (Ref. AMM TASK 72-52-00-290-803).
4 Do the troubleshooting for EGT over limit as specified in TSM 77-21-00-810-813.
5 If the inspections are satisfactory, continue the engine in service.
6 Monitor the engine EGT performance trend and make sure the engine stays in the serviceable EGT margins.
(f) If the EGT was in Area C, remove the engine:
1 One flight is permitted before the engine is removed, if there is no damage beyond the serviceable limits:
a Do a borescope inspection of the combustion chamber (Ref. AMM TASK 72-40-00-290-801).
b Do a borescope inspection of the HPT stage one blades (Ref. AMM TASK 72-52-00-290-803).
c Do a borescope inspection of the stage 1 and 7 blades (Ref. AMM TASK 72-00-00-290-822).
d Do a visual inspection of the engine inlet, engine exhaust and turbine rear frame.
e Do the troubleshooting for EGT over limit as specified in TSM 77-21-00-810-813.
(g) After you do all the troubleshooting and problem resolution, do these steps:
1 Erase any applicable ECAM messages.
2 Erase the ECAM snapshot data saves.
3 Reset the EGT display box.
C. Checks to be Performed when Abnormal Rotation Speeds are Reached
(a) The speed limits are as follows:
1 Fan speed (N1 Actual): 101 percent.
2 Core speed (N2): 116.5 percent.
(b) Fan (N1) overspeed inspections:
1 If fan is operated at speeds from 101 percent to 105 percent, do an inspection of the engine as follows:
(c) Core engine (N2) overspeed inspections:
1 If core engine rotor is operated at speeds from 116.5 percent to 128 percent the engine must be inspected as follows:
Subtask 72-00-00-290-137-A NOTE: Through the MCDU (before a next engine start is attempted) get access to the FADEC "EXEEDANCE REPORT" (Ref. AMM TASK 73-29-00-740-819). This report gives the maximum value reached during the event as well as the duration of the exceedance.
(1) Overspeed: (a) The speed limits are as follows:
1 Fan speed (N1 Actual): 101 percent.
2 Core speed (N2): 116.5 percent.
(b) Fan (N1) overspeed inspections:
1 If fan is operated at speeds from 101 percent to 105 percent, do an inspection of the engine as follows:
- Visually examine the engine inlet, the fan blades, the exhaust nozzle, the stage 4 and stage 7 LPT blades
- Examine the abradable material in fan inlet case for rubbing (Ref. AMM TASK 72-23-01-210-801)
- Troubleshoot and correct cause for overspeed TSM 77-11-00-810-819.
(c) Core engine (N2) overspeed inspections:
1 If core engine rotor is operated at speeds from 116.5 percent to 128 percent the engine must be inspected as follows:
- Inspect exhaust nozzles for particles
- Do a borescope inspection of the High Pressure Compressor (HPC) through port C (stage 1 blisk Leading Edge (LE)), port G (stage 3 Trailing Edge (TE) and stage 4 LE) and port L (stage 8 TE and stage 9 LE) (Ref. AMM TASK 72-30-00-290-801)
- Borescope inspect HPT blades (Ref. AMM TASK 72-52-00-290-803)
- Troubleshoot and correct cause for overspeed TSM 77-11-00-810-817.
D. Checks Required after Lubrication System Operation Limits are Exceeded
(a) The figure gives the relation between engine oil pressure and N2 speed.
(b) Critical Zone A, with oil pressure lower than 17.4 psi (1.20 bar) to 29 psi (2.00 bar) depending on N2 speed:
1 If engine operation with no oil or very LP has exceeded any one of the following, remove engine and return to shop:
a If no particles are found, no further inspections needed.
b If particles are found, check for presence of metal/debris (Ref. AMM TASK 79-00-00-281-805).
1 For Zone B do troubleshooting TSM 79-32-00-810-854.
2 For Zone D do troubleshooting TSM 79-32-00-810-857.
(2) Supply oil temperature:
(a) Maximum oil temperature for continuous engine operations is 140 deg.C (284.00 deg.F).
(b) Engine operation with oil between 140 deg.C (284.00 deg.F) and 155 deg.C (311.00 deg.F) is allowed for 15 minutes.
(c) Above 155 deg.C (311.00 deg.F) the oil system must be drained (Ref. AMM TASK 12-13-79-610-808).
(d) After abnormally high oil temperature, do the following:
1 Remove the oil filter cartridge (Ref. AMM TASK 79-21-05-000-803).
2 Remove the ODMS and check for the presence of metal particles. ODMS for debris (Ref. AMM TASK 79-36-10-000-801) and (Ref. AMM TASK 79-00-00-281-805).
(3) Oil consumption:
(a) Calculate the oil consumption of the engine on a rolling average basis as follows:
1 Find the total quantity of oil that the engine used during a minimum period of 100 flight hours.
2 Divide the total oil quantity used for this period by the total flight hours for this period.
(c) As soon as one of the following cases occur, do the troubleshooting TSM 79-00-00-810-842:
1 TSM 79-00-00-810-842 must be performed as soon as the oil consumption rate overshoots the limit.
2 If the result of the troubleshooting is not conclusive and no action can be taken to reduce the oil consumption rate, contact CFM.
(4) The oil quantity required for the engine start is 10.6 qts on display plus additional quantity for the anticipated oil consumption based on the duration of operation and typical oil consumption rate:
(a) The oil quantity low-exceedance advisory is set when the indicated oil quantity is less than 1.35 qts on display.
Subtask 72-00-00-290-139-A NOTE: Through the MCDU (before a next engine start is attempted) get access to the FADEC "EXEEDANCE REPORT" (Ref. AMM TASK 73-29-00-740-819). This report gives the maximum value reached during the event as well as the duration of the exceedance.
(1) Oil pressure: (a) The figure gives the relation between engine oil pressure and N2 speed.
(b) Critical Zone A, with oil pressure lower than 17.4 psi (1.20 bar) to 29 psi (2.00 bar) depending on N2 speed:
1 If engine operation with no oil or very LP has exceeded any one of the following, remove engine and return to shop:
- Take-off power for 14 seconds
- Cruise power for 14 seconds
- Idle (flight or ground) for 14 seconds.
a If no particles are found, no further inspections needed.
b If particles are found, check for presence of metal/debris (Ref. AMM TASK 79-00-00-281-805).
CAUTION:
IF ENGINE OIL-PRESSURE LEVELS ARE IN ZONE B, A MAINTENANCE ACTION IS MANDATORY BEFORE NEXT FLIGHT. FOR ENGINE OPERATION WITH OIL PRESSURE LEVELS IN ZONES B AND D, YOU MUST CAREFULLY MONITOR THE OTHER OIL SYSTEM PARAMETERS.
IF YOU DO NOT OBEY THESE INSTRUCTIONS, DAMAGE TO THE ENGINE WILL OCCUR.
(c) Zones B and/or D: 1 For Zone B do troubleshooting TSM 79-32-00-810-854.
2 For Zone D do troubleshooting TSM 79-32-00-810-857.
(2) Supply oil temperature:
(a) Maximum oil temperature for continuous engine operations is 140 deg.C (284.00 deg.F).
(b) Engine operation with oil between 140 deg.C (284.00 deg.F) and 155 deg.C (311.00 deg.F) is allowed for 15 minutes.
(c) Above 155 deg.C (311.00 deg.F) the oil system must be drained (Ref. AMM TASK 12-13-79-610-808).
(d) After abnormally high oil temperature, do the following:
1 Remove the oil filter cartridge (Ref. AMM TASK 79-21-05-000-803).
2 Remove the ODMS and check for the presence of metal particles. ODMS for debris (Ref. AMM TASK 79-36-10-000-801) and (Ref. AMM TASK 79-00-00-281-805).
(3) Oil consumption:
(a) Calculate the oil consumption of the engine on a rolling average basis as follows:
1 Find the total quantity of oil that the engine used during a minimum period of 100 flight hours.
2 Divide the total oil quantity used for this period by the total flight hours for this period.
NOTE: If you calculate the oil consumption based on a smaller duration than 100 flight hours, the calculation will be less accurate.
(b) Normal oil consumption is not expected to exceed 0.32 qt/hr (0.30 l/hr). (c) As soon as one of the following cases occur, do the troubleshooting TSM 79-00-00-810-842:
- Oil consumption exceeds 0.35 qt/hr (0.33 l/hr)
- Oil consumption calculated per methodology described in Para. 4.D.(3)(a) increases by 0.20 qt/hr (0.19 l/hr) or more over the last 100 flight hours.
1 TSM 79-00-00-810-842 must be performed as soon as the oil consumption rate overshoots the limit.
2 If the result of the troubleshooting is not conclusive and no action can be taken to reduce the oil consumption rate, contact CFM.
(4) The oil quantity required for the engine start is 10.6 qts on display plus additional quantity for the anticipated oil consumption based on the duration of operation and typical oil consumption rate:
(a) The oil quantity low-exceedance advisory is set when the indicated oil quantity is less than 1.35 qts on display.
E. Checks Necessary after Rough Landing Limits are Exceeded
(1) General inspections after a hard landing or a hard overweight landing for aircraft with enhanced DMU/FDIMU load report 15 (Ref. AMM D/O 05-51-11-20):
(a) The procedure that follows is to be used after a rough landing.
(2) Visual inspection/checks. Do an inspection of:
(b) Wear of abradable material in fan inlet case at the 6 and 12 o'clock positions (Ref. AMM TASK 72-23-01-210-801).
(c) Do a visual inspection of the fan frame assembly (Ref. AMM TASK 72-24-00-210-801).
(d) Engine mounting pads forward and aft (Ref. AMM TASK 72-24-00-210-801) and inspection check of the turbine frame assembly (Ref. AMM TASK 72-59-00-210-801).
(e) Accessory and hardware attachments for metal fractures or excessive distortion.
(f) Piping connections for leaks.
(g) Lines and tubing for possible interferences.
(h) Turbine frame aft flange (Ref. AMM TASK 72-59-00-210-801).
(3) If finding after Para. 4.E.(2) do a borescope inspection of the HPC blades:
(a) Do a borescope inspection of the HPC through port C (stage 1 blisk LE), port G (stage 3 TE and stage 4 LE) and port L (stage 8 TE and stage 9 LE) (Ref. AMM TASK 72-30-00-290-801).
(4) Do a visual inspection thru the exhaust nozzle of the LPT stage 7 blades for indication:
(a) If findings, do a borescope inspection of the stage 7 LPT blades (Ref. AMM TASK 72-00-00-290-822).
(5) In case of severe hard landing:
(a) Do a borescope inspection of the HPC blades:
1 Do a borescope inspection of the HPC through port C (stage 1 blisk LE), port G (stage 3 TE and stage 4 LE) and port L (stage 8 TE and stage 9 LE) (Ref. AMM TASK 72-30-00-290-801).
(b) Do a visual inspection thru the exhaust nozzle of the LPT stage 7 blades for indication:
1 If findings, do a borescope inspection of the stage 7 LPT blades (Ref. AMM TASK 72-00-00-290-822).
(6) Do an inspection of the lubrication unit scavenge screens (Ref. AMM TASK 79-21-05-000-801) and (Ref. AMM TASK 79-21-05-400-801), oil filter cartridge (Ref. AMM TASK 79-21-05-210-801) and ODMS sensor (Ref. AMM TASK 79-36-00-220-801):
(a) If you do not find metal particles, do the inspection each day for one week, then each week for one month.
Subtask 72-00-00-290-140-A (1) General inspections after a hard landing or a hard overweight landing for aircraft with enhanced DMU/FDIMU load report 15 (Ref. AMM D/O 05-51-11-20):
(a) The procedure that follows is to be used after a rough landing.
(2) Visual inspection/checks. Do an inspection of:
WARNING:
BE CAREFUL WHEN YOU TURN THE FAN ROTOR MANUALLY. USE HEAVY PROTECTIVE GLOVES AND MAKE SURE THAT YOU CANNOT SLIP. IF YOU DO NOT OBEY THESE INSTRUCTIONS, INJURY CAN OCCUR.
(a) Turn the fan rotor with your hand. Make sure that there is (are) no bearing roughness, unusual noises or binding. (b) Wear of abradable material in fan inlet case at the 6 and 12 o'clock positions (Ref. AMM TASK 72-23-01-210-801).
(c) Do a visual inspection of the fan frame assembly (Ref. AMM TASK 72-24-00-210-801).
(d) Engine mounting pads forward and aft (Ref. AMM TASK 72-24-00-210-801) and inspection check of the turbine frame assembly (Ref. AMM TASK 72-59-00-210-801).
(e) Accessory and hardware attachments for metal fractures or excessive distortion.
(f) Piping connections for leaks.
(g) Lines and tubing for possible interferences.
(h) Turbine frame aft flange (Ref. AMM TASK 72-59-00-210-801).
(3) If finding after Para. 4.E.(2) do a borescope inspection of the HPC blades:
(a) Do a borescope inspection of the HPC through port C (stage 1 blisk LE), port G (stage 3 TE and stage 4 LE) and port L (stage 8 TE and stage 9 LE) (Ref. AMM TASK 72-30-00-290-801).
(4) Do a visual inspection thru the exhaust nozzle of the LPT stage 7 blades for indication:
(a) If findings, do a borescope inspection of the stage 7 LPT blades (Ref. AMM TASK 72-00-00-290-822).
(5) In case of severe hard landing:
(a) Do a borescope inspection of the HPC blades:
1 Do a borescope inspection of the HPC through port C (stage 1 blisk LE), port G (stage 3 TE and stage 4 LE) and port L (stage 8 TE and stage 9 LE) (Ref. AMM TASK 72-30-00-290-801).
(b) Do a visual inspection thru the exhaust nozzle of the LPT stage 7 blades for indication:
1 If findings, do a borescope inspection of the stage 7 LPT blades (Ref. AMM TASK 72-00-00-290-822).
(6) Do an inspection of the lubrication unit scavenge screens (Ref. AMM TASK 79-21-05-000-801) and (Ref. AMM TASK 79-21-05-400-801), oil filter cartridge (Ref. AMM TASK 79-21-05-210-801) and ODMS sensor (Ref. AMM TASK 79-36-00-220-801):
(a) If you do not find metal particles, do the inspection each day for one week, then each week for one month.
F. Inspection after Stall
(1) General
(a) If a stall or suspected stall has occurred, the inspection and troubleshooting that follows must be done TSM 73-00-00-810-945 Stall of the engine 1 or 2/Audible Stall/Engine/ENGX STALL ECAM.
(2) Visual Inspection/Checks. Do an inspection of:
(a) Fan rotor and abradable material (Ref. AMM TASK 72-21-20-210-802).
(3) Borescope Inspection/Checks. Examine the following:
(a) Do a borescope inspection of the booster blades (Ref. AMM TASK 72-21-00-290-802).
(b) For engine stalls in the start region, or for off-idle stalls which result in engine rollback into sub-idle N2 range:
1 If the start region EGT limit of 750°C was exceeded, perform a borescope inspection/checks per requirements in Step A. Check to be done after a hot start.
2 Do a borescope inspection of the HPC through port C (stage 1 blisk LE), port G (stage 3 TE and stage 4 LE) and port L (stage 8 TE and stage 9 LE) (Ref. AMM TASK 72-30-00-290-801).
(c) For engine stalls at or above idle which do not result in engine rollback into sub-idle N2:
1 Borescope inspect stage 1 HPT blades and stage 1 LPT blades (Ref. AMM TASK 72-52-00-290-803) and (Ref. AMM TASK 72-00-00-290-822).
2 Do a borescope inspection of the HPC through port C (stage 1 blisk LE), port G (stage 3 TE and stage 4 LE) and port L (stage 8 TE and stage 9 LE) (Ref. AMM TASK 72-30-00-290-801).
Subtask 72-00-00-290-141-A (1) General
(a) If a stall or suspected stall has occurred, the inspection and troubleshooting that follows must be done TSM 73-00-00-810-945 Stall of the engine 1 or 2/Audible Stall/Engine/ENGX STALL ECAM.
(2) Visual Inspection/Checks. Do an inspection of:
(a) Fan rotor and abradable material (Ref. AMM TASK 72-21-20-210-802).
(3) Borescope Inspection/Checks. Examine the following:
(a) Do a borescope inspection of the booster blades (Ref. AMM TASK 72-21-00-290-802).
(b) For engine stalls in the start region, or for off-idle stalls which result in engine rollback into sub-idle N2 range:
1 If the start region EGT limit of 750°C was exceeded, perform a borescope inspection/checks per requirements in Step A. Check to be done after a hot start.
2 Do a borescope inspection of the HPC through port C (stage 1 blisk LE), port G (stage 3 TE and stage 4 LE) and port L (stage 8 TE and stage 9 LE) (Ref. AMM TASK 72-30-00-290-801).
(c) For engine stalls at or above idle which do not result in engine rollback into sub-idle N2:
1 Borescope inspect stage 1 HPT blades and stage 1 LPT blades (Ref. AMM TASK 72-52-00-290-803) and (Ref. AMM TASK 72-00-00-290-822).
2 Do a borescope inspection of the HPC through port C (stage 1 blisk LE), port G (stage 3 TE and stage 4 LE) and port L (stage 8 TE and stage 9 LE) (Ref. AMM TASK 72-30-00-290-801).
G. Excessive Vertical Loading Greater than the Specified Limits Page 14 (1)
(1) General
(a) Engine suspected of experiencing excessive g loading during transportation must be given the following inspection. The inspection consists of visual and manual checks followed by a functional check (Ref. AMM D/O 05-51-11-20).
(2) Check engine for obvious damage as follows:
(a) Visually examine for buckling, deformation or cracking in engine skin and flange areas around transportation mounts.
(b) To turn fan rotor by hand:
(d) After functional test run, check scavenge screens and Oil Debris Monitoring Sensor (ODMS) for the presence of metal particles caused by bearing damage. (Ref. AMM TASK 79-00-00-200-806) (Ref. AMM TASK 79-36-00-220-801). Return engine to shop for inspection if unusual deposits are found.
(1) General
(a) Engine suspected of experiencing excessive g loading during transportation must be given the following inspection. The inspection consists of visual and manual checks followed by a functional check (Ref. AMM D/O 05-51-11-20).
(2) Check engine for obvious damage as follows:
(a) Visually examine for buckling, deformation or cracking in engine skin and flange areas around transportation mounts.
(b) To turn fan rotor by hand:
WARNING:
BE CAREFUL WHEN YOU TURN THE FAN ROTOR MANUALLY. USE HEAVY PROTECTIVE GLOVES AND MAKE SURE THAT YOU CANNOT SLIP. IF YOU DO NOT OBEY THESE INSTRUCTIONS, INJURY CAN OCCUR.
1 Turn fan rotor by hand; do a check for bearing roughness, unusual noises and binding. Clear indications of this type of damage requires engine disassembly. NOTE: Light rubbing of seals and shrouds is normal.
(c) If seal or shroud interference is found and appears minimal, the engine can be considered serviceable after completing a successful dry motoring check (Ref. AMM TASK 71-00-00-700-805) and power assurance check (Ref. AMM TASK 71-00-00-710-816). (d) After functional test run, check scavenge screens and Oil Debris Monitoring Sensor (ODMS) for the presence of metal particles caused by bearing damage. (Ref. AMM TASK 79-00-00-200-806) (Ref. AMM TASK 79-36-00-220-801). Return engine to shop for inspection if unusual deposits are found.