Visual Examination of the Engine (after Exposure to Volcanic Ash/Sand) [PW11]

TASK 72-00-00-210-815-A
Visual Examination of the Engine (after Exposure to Volcanic Ash/Sand)

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AFTER SHUTDOWN. THE ENGINE CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY CAN OCCUR.

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

ZONE: 400

1. Reason for the Job
Use this inspection procedure after the ingestion of volcanic ash or sand into the engine during flight operation.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 1M(3 FT)
No specific	1	MAT - WORK

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
400	POWER PLANT, NACELLES AND PYLONS
FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
437AL, 438AR, 451AL, 452AR
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
447AL, 448AR, 461AL, 462AR

C. Referenced Information

REFERENCE	DESIGNATION
TASK 71-00-00-720-811-A	Test No. 3A - Idle Power Test
TASK 71-00-00-860-833-A	Procedure to Prevent Engine Motoring
TASK 71-00-00-910-803-A	Engine Operation Limits and Guidelines
TASK 71-13-00-010-802-A	Opening of the Fan Cowl Doors
TASK 71-13-00-410-802-A	Closing of the Fan Cowl Doors
TASK 71-61-10-210-801-A	General Visual Inspection of the Inlet Cowl
TASK 71-61-12-000-801-A	Removal of the T2 Probe
TASK 71-61-12-400-801-A	Installation of the T2 Probe
TASK 72-00-00-210-809-A	Visual Examination (after an Exhaust Gas Temperature (EGT) Overtemperature)
TASK 72-00-00-210-812-A	General Visual Inspection (GVI) of the Engine Exhaust Area
TASK 72-00-00-210-813-A	General Visual Inspection (GVI) of the Engine Inlet Area
TASK 72-31-00-290-802-A	Borescope Inspection of the Low Pressure Compressor (LPC) Assembly
TASK 72-35-00-290-801-A	Borescope Inspection of the High Pressure Compressor (HPC) Assembly
TASK 72-41-00-290-802-A	Borescope Inspection of Combustion Chamber and HPT Nozzle Guide Vanes
TASK 72-51-00-290-802-A	Borescope Inspection of the 1st and 2nd Stage Turbine Blades
TASK 72-53-00-200-801-A	Borescope Inspection of the Low Pressure Turbine (LPT) Assembly
TASK 73-21-22-000-801-A	Removal of the P2.5/T2.5 Probe
TASK 73-21-22-400-801-A	Installation of the P2.5/T2.5 Probe
TASK 73-21-23-000-801-A	Removal of the Burner Pressure Sensor
TASK 73-21-23-400-801-A	Installation of the Burner Pressure Sensor
TASK 75-24-01-000-801-A	Removal of the Turbine Active Clearance Control (ACC) Air Valve
TASK 75-24-01-400-801-A	Installation of the Turbine Active Clearance Control (ACC) Air Valve
TASK 75-24-49-000-802-A	Removal of the Turbine Active Clearance Control (ACC) Ducts
TASK 75-24-49-400-802-A	Installation of the Turbine Active Clearance Control (ACC) Ducts
TASK 75-25-49-000-802-A	Removal of the Turbine Cooling Air System
TASK 75-25-49-400-802-A	Installation of the Turbine Cooling Air System
TASK 75-26-01-000-801-A	Removal of the Buffer Air Heat Exchanger
TASK 75-26-01-400-801-A	Installation of the Buffer Air Heat Exchanger
TASK 75-26-02-000-801-A	Removal of the LPC Buffer Air Valve
TASK 75-26-02-400-801-A	²nstallation of the LPC Buffer Air Valve
TASK 75-32-02-000-801-A	Removal of the HPC Bleed Valve
TASK 75-32-02-400-801-A	Installation of the HPC Bleed Valve
TASK 75-32-21-000-801-A	Removal of the High Pressure Compressor (HPC) Bleed Valve Air Pressure Sensor (Passive)
TASK 75-32-21-400-801-A	Installation of the High Pressure Compressor (HPC) Bleed Valve Air Pressure Sensor (Passive)
TASK 75-32-22-000-801-A	Removal of the HPC Bleed Valve Air Pressure Sensor - Active
TASK 75-32-22-400-801-A	Installation of the HPC Bleed Valve Air Pressure Sensor - Active
TASK 77-21-21-000-801-A	Removal of the Exhaust Gas Temperature (EGT) Probe
TASK 77-21-21-400-801-A	Installation of the Exhaust Gas Temperature (EGT) Probe
TASK 78-30-00-040-805-A	Deactivation of the Thrust Reverser System for Ground Maintenance
TASK 78-30-00-440-805-A	Reactivation of the Thrust Reverser System after Ground Maintenance
TASK 78-36-00-010-802-A	Opening of the Thrust Reverser Cowl-Doors
TASK 78-36-00-410-802-A	Closing of the Thrust Reverser Cowl-Doors
TASK 79-00-00-210-809-A	Visual Inspection of the Main Oil Filter Element for Contamination
TASK 79-00-00-210-811-A	Laboratory Analysis of the Engine Oil for Contamination
TASK 79-00-00-281-802-A	Inspection of the Magnetic Chip Collectors for Oil Contamination
TASK 79-00-00-281-804-A	Sampling of the Engine Oil
TASK 79-00-00-610-801-A	Check and Fill the Engine Oil
TASK 79-00-00-610-802-A	Change the Engine Oil
TASK 79-00-00-680-801-A	Drain the Engine Oil
TASK 79-21-06-960-801-A	Replace the Oil Filter Element

3. Job Set-up
Subtask 72-00-00-941-190-A ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) Do the procedure to prevent engine motoring
(Ref. AMM TASK 71-00-00-860-833).

Subtask 72-00-00-010-267-A ** ON A/C NOT FOR ALL

B. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
437AL 438AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
447AL 448AR.
(2) Put an ACCESS PLATFORM 1M(3 FT) in position.

Subtask 72-00-00-040-133-A ** ON A/C NOT FOR ALL

C. Deactivation of the Thrust Reverser for Maintenance

WARNING: YOU MUST DEACTIVATE THE THRUST REVERSER BEFORE YOU DO WORK ON OR AROUND IT. IF YOU DO NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE AN INJURY AND/OR DAMAGE.

(1) Do the deactivation of the thrust reverser system for maintenance (Ref. AMM TASK 78-30-00-040-805).

Subtask 72-00-00-010-268-A ** ON A/C NOT FOR ALL

D. Get Access
(1) Open the thrust reverser cowl-doors (Ref. AMM TASK 78-36-00-010-802):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
451AL 452AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
461AL 462AR.

4. Procedure
Subtask 72-00-00-210-166-A ** ON A/C NOT FOR ALL

A. Visual Examination (after Exposure to Volcanic Ash/Sand)

CAUTION: YOU MUST EXAMINE THE ENGINE VERY CAREFULLY AFTER FLIGHT THROUGH VOLCANIC ASH OR SAND. THE INGESTION OF MUCH VOLCANIC ASH OR SAND INTO THE ENGINE CAN CAUSE OPERATIONAL PROBLEMS AND UNSATISFACTORY ENGINE PERFORMANCE. IF YOU DO NOT OBEY THE STEPS THAT FOLLOW, AN IN-FLIGHT SHUTDOWN CAN OCCUR.

(1) Make sure that you remove and install protection covers as necessary to prevent damage to the engine.
(2) Make sure that you wipe clean all parts and tools as necessary to remove debris and prevent damage to the engine.
(3) Check the flight records for any engine operational problems after the ingestion of volcanic ash or sand as follows:
(a) Check the records for increased Exhaust Gas Temperature (EGT). Check if the engine operated more than the EGT limit and for how long time (Ref. AMM TASK 71-00-00-910-803).
(b) Check the records for increased engine vibration. Check if the engine operated more than the vibration limits (N1 and N2) and what the peak vibration was for each rotor (Ref. AMM TASK 71-00-00-910-803).
(c) Check the records for engine surge or stall during operation (loss of surge margin). Check if the engine had one stall or many stalls.
(d) Check the records for engine In-Flight ShutDown (IFSD) or flameout. Check if the engine was restarted during flight.
(4) If the engine had any operational problems as described above, do the steps that follow:
(a) Remove the engine from service.
(b) Send the engine to the shop with the engine records. Include all the records of any operational problems.
(c) Carefully examine and disposition the engine.
(d) If the engine operated more than the maximum EGT limit, it will be necessary to remove and inspect the engine after EGT over temperature operation (Ref. AMM TASK 72-00-00-210-809).
(5) If the engine did not have operational problems and the engine parameters were in the limits, do the steps that follow:
(a) Do a visual examination of the engine air inlet cowl (Ref. AMM TASK 71-61-10-210-801).
1 Put a MAT - WORK inside the engine air inlet cowl.
2 Examine the leading edge for erosion, dents and damage.
3 Examine the inlet anti-ice system for ash deposits, clogged tubes and discharge slots. Refer to PW1000G-1100-30-21-00-00A-310A-A.
(b) Do a visual examination of the engine inlet parts as follows (Ref. AMM TASK 72-00-00-210-813):
1 Examine the inlet cone (spinner) for ash deposits, erosion and damage.
2 Examine the fan blades for ash deposits, erosion and damage. Look carefully at the leading edge.
3 Examine the fan exit stator for ash deposits, erosion and damage. Look carefully at the leading edge.
4 Examine the fan exit fairing (splitter) for ash deposits, erosion and damage. Look carefully at the leading edge.
5 Examine the fan exit guide vanes for ash deposits, erosion and damage. Look carefully at the leading edge.
(6) Do a borescope inspection of the engine primary gas path as follows:
(a) Do a borescope inspection of the Low Pressure Compressor (LPC) (Ref. AMM TASK 72-31-00-290-802).
1 Look for damage and erosion on the leading edge of the LPC blades and vanes.
(b) Do a borescope inspection of the High Pressure Compressor (HPC) (Ref. AMM TASK 72-35-00-290-801).
1 Look for damage and erosion on the leading edge of the HPC blades and vanes.
(c) Do a borescope inspection of the combustion chamber area (Ref. AMM TASK 72-41-00-290-802).
1 Look for ash deposits on the combustion liner segments and fuel nozzles.
2 Look for ash deposits, erosion and clogged cooling holes on the first stage turbine vanes.
(d) Do a borescope inspection of the High Pressure Turbine (HPT) (Ref. AMM TASK 72-51-00-290-802).
1 Look for ash deposits and clogged cooling holes on the HPT blades and vanes.
2 Look for leading edge erosion on the HPT blades and vanes.
(e) Do a borescope inspection of the Low Pressure Turbine (LPT) (Ref. AMM TASK 72-53-00-200-801).
1 Look for leading edge erosion on the LPT blades and vanes.
(7) Visually inspect the turbine exhaust area for damage (Ref. AMM TASK 72-00-00-210-812).
(a) Do a visual examination of the gas path surfaces of the turbine exhaust case for erosion and damage.
(b) Examine the support struts for erosion and damage. Look carefully at the leading edge.
(8) Visually inspect the FADEC system and sensing probes for ash deposits, clogging, erosion or damage.
(a) Examine the T2, P2.5/T2.5 and burner pressure (PB) sensing probes. If the connecting sense manifolds are clogged, they must be removed and cleaned. If the probes are clogged or damaged, clean or replace the probes as follows:
1 Remove and install the T2 probe (Ref. AMM TASK 71-61-12-000-801) and (Ref. AMM TASK 71-61-12-400-801).
2 Remove and install the P2.5/T2.5 probe (Ref. AMM TASK 73-21-22-000-801) and (Ref. AMM TASK 73-21-22-400-801).
3 Remove and install the burner pressure (PB) sensor (Ref. AMM TASK 73-21-23-000-801) and (Ref. AMM TASK 73-21-23-400-801).
(b) Examine the EGT probes for ash deposits, erosion, thermocouple damage or other damage. Clean or replace the probes if necessary as follows:
1 Remove and install the EGT probe (Ref. AMM TASK 77-21-21-000-801) and (Ref. AMM TASK 77-21-21-400-801).
(9) Visually inspect the HPC bleed system for clogging, erosion or other damage.
(a) Examine the HPC bleed valve for ash deposits, clogging, erosion or damage. If the connecting manifolds are clogged, they must be removed and cleaned as follows.

Remove and install the HPC bleed valve (Ref. AMM TASK 75-32-02-000-801) and (Ref. AMM TASK 75-32-02-400-801).

(10) Examine the HPC bleed valve air pressure sensor for clogging, erosion or damage. If the connecting manifolds are clogged, they must be removed and cleaned as follows.

Remove and install the HPC bleed valve air pressure sensors (Ref. AMM TASK 75-32-21-000-801), (Ref. AMM TASK 75-32-22-000-801), (Ref. AMM TASK 75-32-21-400-801) and (Ref. AMM TASK 75-32-22-400-801).

(11) Visually inspect the turbine active clearance control (ACC) system for clogging, erosion or other damage.
(a) Examine the turbine ACC valve for ash deposits, clogging, erosion or damage. If the connecting ducts are clogged, they must be removed and cleaned as follows.
1 Remove and install the turbine active clearance control (ACC) air valve (Ref. AMM TASK 75-24-01-000-801) and (Ref. AMM TASK 75-24-01-400-801).
2 Remove and install the turbine cooling ducts (Ref. AMM TASK 75-24-49-000-802) and (Ref. AMM TASK 75-24-49-400-802).
(12) Visually inspect the Turbine Cooling Air (TCA) system for clogging, erosion or other damage.
(a) Examine the turbine cooling air tubes and metering plates for ash deposits, clogging, erosion or damage. If the connecting ducts are clogged, they must be removed and cleaned as follows.
1 Remove and install the turbine cooling air tubes (Ref. AMM TASK 75-25-49-000-802) and (Ref. AMM TASK 75-25-49-400-802).
(13) Visually inspect the engine bearing cooling system for clogging, erosion or other damage.
(a) Examine the buffer air valve for clogging, erosion or damage. If the connecting manifolds are clogged, they must be removed and cleaned as follows.
1 Remove and install the buffer air valve (Ref. AMM TASK 75-26-02-000-801) and (Ref. AMM TASK 75-26-02-400-801).
(b) Examine the buffer air heat-exchanger for clogging, erosion or damage. If the heat exchanger is clogged, it must be removed and cleaned as follows.
1 Remove and install the buffer air heat exchanger (Ref. AMM TASK 75-26-01-000-801) and (Ref. AMM TASK 75-26-01-400-801).
(14) Change the engine oil as follows.
(a) Drain the engine oil (Ref. AMM TASK 79-00-00-680-801).
(b) Replace and inspect the main oil filter element (Ref. AMM TASK 79-21-06-960-801) and (Ref. AMM TASK 79-00-00-210-809).
(c) Remove and inspect the magnetic chip collectors for metal contamination (Ref. AMM TASK 79-00-00-281-802).
(d) Fill the engine with new oil (Ref. AMM TASK 79-00-00-610-801).
(e) Start the engine and operate at idle power for two to five minutes and shutdown (Ref. AMM TASK 71-00-00-720-811).
(f) Drain the engine oil (Ref. AMM TASK 79-00-00-680-801).
(g) Replace the main oil filter element (Ref. AMM TASK 79-21-06-960-801).
(h) Fill the engine with new oil (Ref. AMM TASK 79-00-00-610-801).
(15) After the completion of the engine oil drain and flush, take a sample of the engine oil (Ref. AMM TASK 79-00-00-281-804):
(a) Analyze the oil sample for Total Acid Number (TAN), sulfur and silicon (Ref. AMM TASK 79-00-00-210-811).
(16) If the visual examinations and oil sample are within the acceptable limits, the engine can continue in service.
(17) If the oil sample (TAN, sulfur and silicon levels) is not within the acceptable limits, do the steps that follow:
(a) Flush the engine oil and change the engine main oil filter element (Ref. AMM TASK 79-00-00-610-802) and (Ref. AMM TASK 79-21-06-960-801).
(b) Analyze for TAN, sulfur and silicon levels. If the results are within the acceptable limits, the engine can continue in service (Ref. AMM TASK 79-00-00-210-811).
(18) Remove the MAT - WORK from the intake cowl.
(19) Examine the assembly for foreign objects, damage, and correct assembly.
(20) Make sure that you install protection covers as necessary to prevent damage to the engine.

5. Close-up
Subtask 72-00-00-410-229-A ** ON A/C NOT FOR ALL

A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the MAT - WORK from the intake cowl.
(3) Close the thrust reverser cowl-doors (Ref. AMM TASK 78-36-00-410-802):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
451AL 452AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
461AL 462AR.

Subtask 72-00-00-440-127-A ** ON A/C NOT FOR ALL

B. Do the reactivation of the thrust reverser system after maintenance (Ref. AMM TASK 78-30-00-440-805).

Subtask 72-00-00-410-230-A ** ON A/C NOT FOR ALL

C. Close Access
(1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-802):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
437AL 438AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
447AL 448AR.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 04:08:26 UTC