Gas Path Cleaning with a Cleaning Solution [CFML]

TASK 72-00-00-100-803-A
Gas Path Cleaning with a Cleaning Solution

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.

ZONE: 210
ZONE: 400

1. Reason for the Job
This task is for the engine gas path cleaning with a cleaning solution.

NOTE: When a cleaning agent is used, the proper aircraft maintenance configuration, the engine rinsing and the post engine wash test must be completed to prevent the possibility of fumes in the cabin when aircraft resumes revenue flight operation.

NOTE: The engine bleed system must be operative prior to proceeding with the engine washing with a cleaning agent.

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	AIR SOURCE FILTERED, DRY
No specific	AR	COVER - PROTECTION
No specific	1	TDS TOTAL DISSOLVED SOLID METER OR EQUIVALENT
No specific	AR	WARNING NOTICE(S)

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
210	CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD
400	POWER PLANT, NACELLES AND PYLONS
FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
437AL, 438AR, 451AL, 452AR
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL, 448AR, 461AL, 462AR

C. Referenced Information

REFERENCE	DESIGNATION
TASK 12-13-79-610-805-A	Check of the Oil Level and Replenishing
TASK 21-00-00-615-803-A	Level B Decontamination of the Environmental Control System (ECS)
TASK 24-41-00-861-002-A	Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01	Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-861-002-A-02	Energize the Aircraft Electrical Circuits from Engine 1(2)
TASK 24-41-00-862-002-A	De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01	De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02	De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 71-00-00-700-805-A	Dry-Motoring Check
TASK 71-00-00-860-827-A	Start the Engine (Normal Automatic Start)
TASK 71-00-00-860-828-A	Start the Engine (Normal Manual Start)
TASK 71-00-00-860-829-A	Engine Shutdown
TASK 71-13-00-010-803-A	Opening of the Fan Cowl Doors
TASK 71-13-00-410-803-A	Closing of the Fan Cowl Doors
TASK 72-00-00-100-805-A	Engine Cleaning Specifications
TASK 72-00-00-740-801-A	Water Wash Procedure (Menu Mode)
TASK 73-21-45-000-801-A	Removal of the Pressure Sub-System
TASK 73-21-45-400-801-A	Installation of the Pressure Sub-System
TASK 78-30-00-040-809-A	Deactivation of the Thrust Reverser System for Ground Maintenance
TASK 78-30-00-440-809-A	Reactivation of the Thrust Reverser System after Ground Maintenance
TASK 78-36-00-010-806-A	Opening of the Thrust Reverser Cowl Doors
TASK 78-36-00-410-806-A	Closing of the Thrust Reverser Cowl Doors
Engine Gas Path Cleaning
Cleaning Solution Injection

3. Job Set-up
Subtask 72-00-00-941-240-A

A. Safety Precautions
(1) On the center pedestal, on ENG panel 115VU:
(a) Make sure that the ENG/MODE selector switch is in the NORM position.
(b) Make sure that the ENG/MASTER 1(2) control switch was in the OFF position not less than five minutes before you do this procedure.
(c) Put a WARNING NOTICE(S) in position to tell persons not to operate:

The ENG/MODE selector switch
The ENG/MASTER 1(2) control switch.

(2) On the ENG section of maintenance panel 50VU:
(a) Make sure that the ON legend of the FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2).

Subtask 72-00-00-010-324-A

B. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-803):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
437AL 438AR.
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL 448AR.
(2) Put an ACCESS PLATFORM 1M(3 FT) in position.

Subtask 72-00-00-040-178-A

DELETED

Subtask 72-00-00-010-377-A

D. Get Access
(1) If the specified tool makes it necessary to open the Thrust Reverser (T/R) cowl doors to clean the engine gas path, open the T/R cowl doors:

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.

(a) Do the deactivation of the T/R system for ground maintenance (Ref. AMM TASK 78-30-00-040-809).
(b) Open the T/R cowl doors (Ref. AMM TASK 78-36-00-010-806):
1 FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
451AL 452AR.
2 FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
461AL 462AR.

4. Procedure

CAUTION: DO NOT WASH AN ENGINE UNLESS THE EGT IS BELOW 150 DEG.F (66 DEG.C).

CAUTION: DO NOT WASH AN ENGINE AT TEMPERATURE BELOW 14 DEG.F (-10 DEG.C).

CAUTION: DO NOT OPERATE THE WING ANTI-ICE SYSTEM BEFORE THE END OF THE FIVE MINUTE PERIOD AT IDLE. IF YOU DO NOT OBEY THIS INSTRUCTION, OVERHEAT OF THE ANTI-ICE SYSTEM CAN OCCUR.

CAUTION: MAKE SURE THAT DRY MOTOR CYCLE DURATIONS DO NOT EXCEED THE STARTER LIMITS. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE CAN OCCUR.

Subtask 72-00-00-110-096-A

A. Engine Gas Path Cleaning with Cleaning Solution

WARNING: USE PERSONAL PROTECTION EQUIPMENT. USE THE ENGINE OIL IN A WELL-VENTILATED AREA. ENGINE OIL IS TOXIC.

WARNING: USE PROTECTIVE GLOVES AND BE CAREFUL WITH OIL SPLASHES WHEN YOU DISCONNECT OIL TUBES. HOT OIL CAN CAUSE DEEP BURNS.

CAUTION: IF CLEANING AGENT IS USED, PROPER AIRCRAFT MAINTENANCE CONFIGURATION, ENGINE RINSING AND POST ENGINE WASH TEST MUST BE COMPLETED TO PREVENT THE POSSIBILITY OF FUMES IN THE CABIN WHEN AIRCRAFT RESUMES REVENUE FLIGHT OPERATION.

CAUTION: DO NOT USE METHANOL. IF YOU DO, THIS CAN CAUSE DAMAGE TO ENGINE TITANIUM PARTS.

CAUTION: DO NOT WASH AN ENGINE WHICH HAS BEEN EXPOSED TO DRY CHEMICAL FIRE EXTINGUISHING AGENTS.

(1) Preparation of the engine for washing:

CAUTION: IF YOU DO NOT OPERATE THE ENGINE LESS THAN 24 HOURS AFTER THE POST ENGINE-WASH TEST, YOU MUST DO THE ENGINE PRESERVATION PROCEDURE.

(a) Disconnect the P3B line (2) and PS3 line (3) from the pressure sub-system box (1) (Ref. AMM TASK 73-21-45-000-801).
(b) Put COVER - PROTECTION on the open P3B line (2), PS3 line (3) and open ports of the pressure sub-system box (1).
(c) Prepare a cleaning solution, refer to engine cleaning specifications (Ref. AMM TASK 72-00-00-100-805).
(d) Do the oil level check and replenishing (Ref. AMM TASK 12-13-79-610-805).

CAUTION: WHEN YOU INSTALL THE WASH TOOL (WASH PROBE), MAKE SURE THAT THE WASH TOOL (WASH PROBE) DOES NOT TOUCH THE ENGINE PARTS THAT MOVE. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE EQUIPMENT CAN OCCUR.

(e)

Cleaning Solution Injection

Subtask 72-00-00-861-059-A

B. Energize the Aircraft Electrical Circuits (Ref. AMM TASK 24-41-00-861-002)

Subtask 72-00-00-860-122-A

C. Aircraft Maintenance Configuration
(1) On the overhead control and indicating panel 25VU, make sure that the ON legend of the ANTI-ICE/ENG 1(2) pushbutton switch is off.
(2) On the AIR COND panel 30VU, make sure that the OFF legend of the ENG 1(2) BLEED pushbutton switch is on.
(3) On the AIR COND panel 30VU, make sure that the OFF legends of the PACK 1 and the PACK 2 pushbutton switches are on.

Subtask 72-00-00-110-098-A

WARNING: USE RUBBER GLOVES AND EYE PROTECTION WHEN HANDLING LIQUID DETERGENT. LIQUID DETERGENT AND ANTI-FREEZE SOLVENT HAVE LOW FLASHPOINTS. KEEP AWAY FROM HEAT AND OPEN FLAME. PROVIDE ADEQUATE VENTILATION. STAND AT LEAST 3 FEET (1M) AWAY FROM COWLING INLET WHEN SPRAYING LIQUIDS INTO ENGINE TO AVOID PERSONAL INJURY.

CAUTION: THE N1 ROTOR MUST ROTATE FREELY THROUGHOUT WASH TO PREVENT OIL SYSTEM CONTAMINATION.

CAUTION: DO NOT APPLY WATER AT MORE THAN 5 US GAL (19 LITERS) PER MINUTE WITH TWO WASH PROBES. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE ENGINE CAN OCCUR.

CAUTION: DO NOT OPERATE THE ENGINE IF THE FUEL INLET PRESSURE IS NOT POSITIVE. THE FUEL IS NECESSARY TO LUBRICATE THE ENGINE FUEL PUMP AND THE HMU AND THUS PREVENT DAMAGE.

D. Engine Washing (with the Total Dissolved Solid Meter or an Equivalent)

NOTE: Two persons are necessary to do this test. One person operates the engine controls while the other person:

Makes sure that no one is injured when the surfaces move
Monitors the engine.

NOTE: This function is conducted as part of the overall cleaning solution wash procedure. When this function runs, the Variable Stator Vane (VSV) and the Variable Bleed Valve (VBV) systems are moved to facilitate the engine cleaning solution wash. The function opens the VSVs and closes the VBVs so that the cleaning solution wash mixture will enter the compressor. This is a dry motoring test.

(1) Collect a sample of the wash supply water and measure the TDS TOTAL DISSOLVED SOLID METER OR EQUIVALENT (supply water total dissolved solid).
(a) Make a record of the initial measurement.

NOTE: Use a TDS TOTAL DISSOLVED SOLID METER OR EQUIVALENT with the properties that follow:

A measurement range from 0 to 9990 ppm (total dissolved solid)
A resolution of one ppm
A readout accuracy of plus or minus two percent.

(2) Select the water wash procedure menu mode (Ref. AMM TASK 72-00-00-740-801).
(3)

Cleaning Solution Injection

(4) Stop the cleaning solution injection before the end of the engine motoring and do these steps:
(a) During the engine coast-down, collect a sample of the wash water that drains from the exhaust area of the engine.

NOTE: Calibration of the total dissolved solid meter is not necessary if the same total dissolved solid meter is used to collect the sample of the wash supply water.

(b) Measure and make a record of the total dissolved solid with the TDS TOTAL DISSOLVED SOLID METER OR EQUIVALENT.
(c) Subtract the initial supply water total dissolved solid value measured in Para 4.D.(1) above, from the rinse effluent value.
1 If the net total dissolved solid value is less than 150 ppm, additional rinse cycles are not necessary.
2 If this value is more than 150 ppm, do the additional wash/soak cycles until the net total dissolved solid falls below 150 ppm, up to a maximum of four wash cycles.
(5) Let the water soak for 10-15 minutes between the cycles.

NOTE: The 10-15 minutes between the cycles will maximize the cleaning of the engine.

(6) Repeat Paras 4.D.(1) to 4.D.(5) as necessary.
(7) Dry-motor the engine (Ref. AMM TASK 71-00-00-700-805).

Subtask 72-00-00-100-056-A

E. Rinsing of the Cleaning Solution from the Engine Gas Path with Pure Water

NOTE: To prevent fumes in the cockpit and cabin when the airplane is put back into service, make sure to do this rinse procedure.

(1) Do the water wash procedure menu mode (Ref. AMM TASK 72-00-00-740-801).
(2)

Cleaning Solution Injection

(3) Stop the water injection before the end of the engine motoring.
(4) Let the water soak for 10-15 minutes between cycles.

NOTE: The 10-15 minutes between cycles will maximize the cleaning of the engine.

(5) Dry-motor the engine for two minutes (Ref. AMM TASK 71-00-00-700-805).
(6) Repeat the Para. 4.E. for a total of three rinses.

Subtask 72-00-00-420-102-A

F. Installation of the Disconnected Lines
(1) Connect the PS3 line (3) and the P3B line (2) to the pressure subsystem box (1) (Ref. AMM TASK 73-21-45-400-801):

NOTE: The compressed air pressure is approximately 100 psi (689 KPa). The compressed air pressure should not exceed 200 psi (1379 KPa).

(a) Blow the P3B line (2) clear of the cleaning solution with the AIR SOURCE FILTERED, DRY.
(b) Blow the PS3 line (3) clear of the cleaning solution with the AIR SOURCE FILTERED, DRY.
(c) Do a visual inspection to make sure that the PS3 line (3) and the P3B line (2) weep holes are clear and that there is no blockage.
(d) Connect the PS3 line (3) and the P3B line (2).
(e)

Cleaning Solution Injection

Subtask 72-00-00-410-330-A

G. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) If you opened the T/R cowl doors, close them (Ref. AMM TASK 78-36-00-410-806):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
451AL 452AR.
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
461AL 462AR.

Subtask 72-00-00-440-170-A

H. Do the reactivation of the T/R system after ground maintenance (Ref. AMM TASK 78-30-00-440-809).

Subtask 72-00-00-410-331-A

I. Close Access
(1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-803):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
437AL 438AR.
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL 448AR.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).

Subtask 72-00-00-710-067-A

J. Testing
(1) Post engine wash test:
(a) On the AIR COND panel 30VU, make sure that:

PACK 1 and PACK 2 are OFF before the start of the procedure.

(b) The cross bleed valve selector switch is in the OPEN position.
(c) Start the engine within two hours (or 30 minutes in icing condition) of the last wash cycle to purge the lube/sump system of any cleaning solution ingestion (Ref. AMM TASK 71-00-00-860-827) (Ref. AMM TASK 71-00-00-860-828).
(d) Start the opposite engine (Ref. AMM TASK 71-00-00-860-827) (Ref. AMM TASK 71-00-00-860-828) and let it at idle.

NOTE: APU bleed valve must be closed (the ON legend of the APU bleed pushbutton switch is OFF) after the engine start, to avoid the supply of air to the Wing Anti-Ice (WAI) systems from the APU.

NOTE: This engine run is done to make sure that the bleed system is free from contaminant. Smoke/smell in the cabin and starter air valve contamination can result if contaminant enters the bleed system.

1 Let the "washed" engine run at idle for five minutes, then do as follows:
a Press the ENG 1(2) BLEED pushbutton switch to operate the engine bleed system.
b Select the "ENGINE BLEED" SD page.
c Make sure that the OFF legend of the ENG 1(2) BLEED pushbutton switch goes off when the engine bleed system operates.

CAUTION: DO NOT PUSH THE WING/ANTI ICE PUSHBUTTON SWITCH MORE THAN TWICE AND WAIT FOR A MINIMUM OF FIVE MINUTES BETWEEN THE TWO ATTEMPTS. IF YOU DO NOT OBEY THIS INSTRUCTION, AN OVERHEAT OF THE WING ANTI-ICE SYSTEMS CAN OCCUR.

d The wing anti-ice pushbutton operation:

Press the ANTI-ICE/WING pushbutton switch to operate the WAI system.

NOTE: The aim is to purge cleaning solution, potentially trapped in HP bleed ducts and HP engine bleed chambers.

e Make sure that the ON legend of the ANTI-ICE/WING pushbutton switch comes on when the WAI system operates.

NOTE: The WAI valves will automatically close 30 seconds after the WAI system is selected ON. This is to prevent wing slats overheat. However, the ON legend remains illuminated until the switch is deselected.

f Make sure that the Pressure Regulating Valve (PRV) and HP Bleed Valve (HPV) are open on the Electronic Centralized Aircraft Monitoring (ECAM) bleed page with the engine running at this speed while the WAI valve is open.

CAUTION: DO NOT OPERATE THE WING ANTI-ICE SYSTEM (WAI) BEFORE THE FIVE- MINUTE PERIOD AT IDLE IS COMPLETED. IF YOU DO NOT OBEY THIS PRECAUTION, AN OVERHEAT OF THE WAI SYSTEM CAN OCCUR.

g Five minute period at idle:

Once the WAI valve is closed, let the engine run at idle for five minutes.

h On the engine which has been washed, increase and stabilize engine thrust to a minimum of 70 to 73 percent fan (N1) up to HP valve closure for ten minutes.

i Wing anti-ice pushbutton operation:

Press twice the ANTI-ICE/WING pushbutton switch to operate the WAI system once more.

NOTE: The aim is to purge cleaning solution, potentially trapped in Intermediate Pressure (IP) bleed ducts and IP engine bleed chambers.

NOTE: If the WAI ON legend is still on, pressing twice the WAI pushbutton switch enables a second WAI cycle of 30 seconds to be started.

j Make sure that the ON legend of the ANTI-ICE/WING pushbutton switch comes ON when the WAI system operates.
k Make sure that the PRV is open and the HPV is closed on the ECAM bleed page with engine running at this speed while the WAI valve is open.
2 Once the WAI valve is closed, pull the throttle to stabilize the engine thrust at idle for five minutes, then, do as follows:
a Press the ANTI-ICE/WING pushbutton switch and make sure that the ON legend of the ANTI-ICE/WING pushbutton switch goes OFF.
b Turn the cross bleed valve selector switch to the auto position.
c Press the PACK 1(2) pushbutton switch to operate the air conditioning pack.
d Make sure that the OFF legend of the PACK 1(2) pushbutton switch goes OFF.
e Check for evidence of anti-freeze mixture odor/smoke in the cabin:

If trace is found, continue to operate the engine at idle until no odor/smoke remains in the cabin.
After ten minutes engine running, if continuous odor/smoke remains in the cabin, shut down the engines (Ref. AMM TASK 71-00-00-860-829) and decontaminate the Environmental Control System (ECS). The APU bleed valve must be open before engine shutdown.
Level B decontamination of the ECS (Ref. AMM TASK 21-00-00-615-803).
If no trace is found, shut down the engines (Ref. AMM TASK 71-00-00-860-829).

5. Close-up
Subtask 72-00-00-862-063-A

A. De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

Subtask 72-00-00-410-327-A

DELETED

Subtask 72-00-00-440-168-A

DELETED

Subtask 72-00-00-410-281-A

DELETED

[Rev.10 from 2021] 2026.04.01 13:03:34 UTC