Washing of the Engine Gas Path with Pure Water [CFMB]

TASK 72-00-00-100-026-A
Washing of the Engine Gas Path with Pure Water

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

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.

ZONE: 400
FIN: 1000EM1 ** ON A/C NOT FOR ALL
FIN: 1000EM2 ** ON A/C NOT FOR ALL

1. Reason for the Job
For Exhaust Gas Temperature (EGT) margin recovery, it is recommended to perform the engine gas path water wash with pure water only.

NOTE: This task can contribute to fuel savings.

2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	TDS TOTAL DISSOLVED SOLID METER OR EQUIVALENT
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 160 and 150 lbf.in (1.81 and 1.70 m.daN )
No specific	Torque wrench: range to between 200 and 180 lbf.in (2.26 and 2.03 m.daN )
No specific	Torque wrench: range to between 300 and 270 lbf.in (3.39 and 3.05 m.daN )

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.CP8001)	lockwire 0.032 in. (0.8 mm) dia.
(Material No.CP8002)	lockwire 0.032 in. (0.8 mm) dia

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
400	POWER PLANT, NACELLES AND PYLONS
FOR [1000EM1] (ENGINE-1)
437AL, 438AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR

D. Referenced Information

REFERENCE	DESIGNATION
TASK 12-13-79-610-002-A	Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector)
TASK 12-13-79-610-002-A-01	Check oil level and replenish (Pressure Filling)
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 71-00-00-710-001-B	Dry Motoring Check
TASK 71-00-00-710-003-B	Engine Automatic Start
TASK 71-00-00-710-028-B	Engine Shutdown
TASK 71-00-00-710-802-A	Water Wash Crank
TASK 71-13-00-010-040-B	Opening of the Fan Cowl Doors
TASK 71-13-00-410-040-B	Closing of the Fan Cowl Doors
TASK 72-00-00-100-008-A	Engine Washing Requirements
Rigid Anti-Ice Muscle Line
Engine Cleaning (Washing with Pure Water)

3. Job Set-up
Subtask 72-00-00-941-065-A ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ENG/FADEC GND PWR/1(2) pushbutton switch is OFF (the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is OFF).
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

Subtask 72-00-00-010-072-A ** ON A/C NOT FOR ALL

B. Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040):
(1) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(2) FOR [1000EM2] (ENGINE-2)
447AL 448AR

4. Procedure
Subtask 72-00-00-110-057-A ** ON A/C NOT FOR ALL

A. Preparation of the Engine for Washing
(1) For engine washing requirements (Ref. AMM TASK 72-00-00-100-008).

NOTE: The disconnection of P25 line is only available for engines equipped with PMUX option.

(2) Disconnect PS3 line and P25 line (if installed) from the Electronic Control Unit (ECU).
(3) Plug the open tubes and ports of the ECU with standard protective covers.
(4) Disconnect the flexible hose (25) from the nacelle anti-ice (NAI) valve.

Rigid Anti-Ice Muscle Line ** ON A/C NOT FOR ALL

NOTE: Let the flexible hose free (not plugged) during the washing of the engine.

(5) Install a standard protective cover on the anti-ice servo pressure line port of the NAI valve.
(6) Prepare an anti-freeze mixture, if necessary, as defined in engine washing requirements (Ref. AMM TASK 72-00-00-100-008).
(7) Servicing of the oil tank:
(a) Check oil level of the engine (Ref. AMM TASK 12-13-79-610-002).

Subtask 72-00-00-861-051-A ** ON A/C NOT FOR ALL

B. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).

Subtask 72-00-00-860-051-A ** ON A/C NOT FOR ALL

C. Aircraft Maintenance Configuration
(1) On the ANTI-ICE section of panel 25VU, make sure that the ANTI ICE/ENG 1(2) pushbutton switch is OFF (the ON legend of the ANTI ICE/ENG 1(2) pushbutton switch is OFF).
(2) On the AIR COND panel 30VU, make sure that ENG 1(2) BLEED pushbutton switch is OFF (the OFF legend of the ENG1(2) BLEED is ON).
(3) On the AIR COND panel 30VU, make sure that PACK 1 and PACK 2 pushbutton switches are OFF (the OFF legend of the PACK 1 and the PACK 2 pushbutton switches are ON).

Subtask 72-00-00-110-058-A ** ON A/C NOT FOR ALL

D. Engine Washing

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

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: THE FUEL PUMP AND HYDRO-MECHANICAL UNIT (HMU) ARE FUEL LUBRICATED. DO NOT MOTOR, START, OR OPERATE ENGINE UNLESS A POSITIVE FUEL INLET PRESSURE IS INDICATED ON THE LOWER ECAM (FUEL SYSTEM PAGE). DAMAGE TO COMPONENTS MAY RESULT.

CAUTION: DO NOT EXCEED THE STARTER DUTY CYCLE. DAMAGE TO THE STARTER CAN OCCUR.

CAUTION: MAKE SURE THE N1 ROTOR TURNS FREELY THROUGHOUT WASHING TO PREVENT OIL SYSTEM CONTAMINATION.

CAUTION: DO NOT APPLY WATER AT MORE THAN 6 US GAL (23 LITERS) PER MINUTE. IF YOU DO, ENGINE DAMAGE CAN OCCUR.

CAUTION: DRY MOTOR CYCLE DURATIONS MUST NOT EXCEED 2 MINUTES (REFER TO AMM TASK 71-00-00-710-001).

(1) Dry motor the engine for two minutes (Ref. AMM TASK 71-00-00-710-001).
(2) After 10 seconds of motoring with a positive fan rotation, inject the water at 1 o'clock position (aft view) on the Low Pressure Compressor (LPC) inlet through the fan blades (or at the LPC inlet if a specific rig is used).
(3) Stop the water injection before the end of the engine motoring.
(4) Let the engine soak for 5 minutes.
(5) Repeat steps (1) to (4).
(6) Let the engine soak for 5 minutes.
(7) Dry motor the engine again (Ref. AMM TASK 71-00-00-710-001).

NOTE: Water can potentially drain out of the disconnected rigid anti-ice servo pressure line. If water drains out, continue to dry motor the engine until there is no more water draining out of the line.

Subtask 72-00-00-110-058-B ** ON A/C NOT FOR ALL

D. Engine Washing

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

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 EXCEED THE STARTER DUTY CYCLE. DAMAGE TO THE STARTER CAN OCCUR.

CAUTION: MAKE SURE THE N1 ROTOR TURNS FREELY THROUGHOUT WASHING TO PREVENT OIL SYSTEM CONTAMINATION.

CAUTION: DO NOT APPLY WATER AT MORE THAN 6 US GAL (23 LITERS) PER MINUTE. IF YOU DO, ENGINE DAMAGE CAN OCCUR.

CAUTION: DRY MOTOR CYCLE DURATIONS MUST NOT EXCEED 2 MINUTES (REFER TO AMM TASK 71-00-00-710-001).

(1) Dry motor the engine for two minutes (Ref. AMM TASK 71-00-00-710-001) or do the water wash crank (Ref. AMM TASK 71-00-00-710-802).

NOTE: The water Wash Crank is an alternate procedure available for FADEC POST 5BS2 software. This task is to optimize the washing procedure by positioning the valves in the better way.

(2) After 10 seconds of motoring with a positive fan rotation, inject the water at 1 o'clock position (aft view) on the Low Pressure Compressor (LPC) inlet through the fan blades (or at the LPC inlet if a specific rig is used).
(3) Stop the water injection before the end of the engine motoring.
(4) Let the engine soak for 5 minutes.
(5) Repeat steps (1) to (4).
(6) Let the engine soak for 5 minutes.
(7) Dry motor the engine again (Ref. AMM TASK 71-00-00-710-001).

Subtask 72-00-00-110-087-A ** ON A/C NOT FOR ALL

E. Alternative Procedure Available. Engine Washing (with TDS TOTAL DISSOLVED SOLID METER OR EQUIVALENT)

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

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 EXCEED THE STARTER DUTY CYCLE. DAMAGE TO THE STARTER CAN OCCUR.

CAUTION: MAKE SURE THE N1 ROTOR TURNS FREELY THROUGHOUT WASHING TO PREVENT OIL SYSTEM CONTAMINATION.

CAUTION: DO NOT APPLY WATER AT MORE THAN 6 US GAL (23 LITERS) PER MINUTE. IF YOU DO, ENGINE DAMAGE CAN OCCUR.

CAUTION: DRY MOTOR CYCLE DURATIONS MUST NOT EXCEED 2 MINUTES (REFER TO AMM TASK 71-00-00-710-001).

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

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

Measurement range of 0 to 9990 ppm Total Dissolved Solids (TDS)
Resolution of 1 ppm
readout accuracy of plus or minus two percent.

(2) Dry-motor the engine for two minutes (Ref. AMM TASK 71-00-00-710-001) or do the water-wash crank (Ref. AMM TASK 71-00-00-710-802).

NOTE: The water-wash crank is an alternative procedure available for FADEC POST 5BS2 software. This task is to optimize the washing procedure by positioning the valves in the better way.

(3) After 10 seconds of motoring with a positive fan rotation, inject the water at the 1 o'clock position (aft view) on the Low Pressure Compressor (LPC) inlet through the fan blades (or at the LPC inlet if a specific rig is used).
(4) Stop the water injection before the end of the engine motoring and, if necessary, 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.
(b) Measure and make a record of the TDS with the TDS TOTAL DISSOLVED SOLID METER OR EQUIVALENT.
(c) Subtract the initial supply water TDS value, measured in step (1) above, from the rinse effluent value.
1 If the net TDS value is less than 150 ppm, no additional rinse cycles are necessary.
2 If this value is more than 150 ppm, do additional wash/soak cycles until the net TDS falls below 150 ppm, up to a maximum of 4 wash cycles.
(5) Let the engine soak for five minutes.
(6) Repeat steps (1) to (4).
(7) Let the engine soak for five minutes.
(8) Dry motor the engine (Ref. AMM TASK 71-00-00-710-001).

Subtask 72-00-00-420-055-A ** ON A/C NOT FOR ALL

F. Installation of PS3 Line and P25 Line (if installed)

WARNING: USE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.

CAUTION: DO NOT BLOW COMPRESSED AIR OR NITROGEN INTO THE ECU AS DAMAGE TO THE ECU CAN OCCUR.

CAUTION: DURING INSTALLATION, MAKE SURE THAT THE PS3 LINE DOES NOT TOUCH THE LOWER STARTER DUCT OR OTHER PARTS IN THIS AREA. IF IT DOES, CHAFING OF THE PS3 HOSE CAN OCCUR.

(1) Remove the plugs from the PS3 and P25 lines and from the ECU.
(2) Blow PS3 and P25 lines clear of water using compressed air or nitrogen.
(a) Do a visual inspection to make sure that the PS3 line weep-hole is clear and there is no blockage.
(3) Connect PS3 line to ECU, TORQUE to between 300 and 270 lbf.in (3.39 and 3.05 m.daN )

and safety with CP8001lockwire 0.032 in. (0.8 mm) dia. or CP8002lockwire 0.032 in. (0.8 mm) dia.
(4) Connect P25 line to ECU, TORQUE to between 200 and 180 lbf.in (2.26 and 2.03 m.daN )

and safety with CP8001lockwire 0.032 in. (0.8 mm) dia. or CP8002lockwire 0.032 in. (0.8 mm) dia.
(5) Remove the standard protective cover from the nacelle anti-ice line port of the NAI valve.
(6) Connect the flexible hose (25) to the nacelle anti-ice valve (4000 DN). TORQUE the flexible hose coupling to between 160 and 150 lbf.in (1.81 and 1.70 m.daN )

Subtask 72-00-00-410-085-A ** ON A/C NOT FOR ALL

G. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the following engine fan cowl doors (Ref. AMM TASK 71-13-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR

Subtask 72-00-00-620-063-A ** ON A/C NOT FOR ALL

H. Post-Engine Wash Test (alternative procedure available)

Engine Cleaning (Washing with Pure Water) ** ON A/C NOT FOR ALL

NOTE: The aim of this post-engine wash test is:

To purge water from the oil system in order to prevent potential bearing/sump corrosion/deterioration
To prevent fumes in the cockpit and in the cabin when the airplane is put back into service.

(1) On AIR COND panel 30VU, make sure that:

The crossbleed valve selector switch is in the OPEN position.

(2) 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 water ingestion (Ref. AMM TASK 71-00-00-710-003).

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

NOTE: This engine run is done to ensure that the bleed system is free from contaminants. Smoke/smell in the cabin and Starter Air Valve (SAV) contamination can result if contaminants go into the bleed system.

(a) Let the engine run at idle for five minutes and after, do the following:
1 Press the ANTI-ICE/ENG pushbutton switch to operate the engine anti-ice system.
2 After five minutes, set the ANTI-ICE/ENG pushbutton switch to OFF.
3 Press the ENG 1(2) BLEED pushbutton switch to operate the engine bleed system.
4 Make sure that the OFF legend of the ENG1 (2) BLEED pushbutton switch goes off when the engine bleed system operates.
5 Press the ANTI ICE/WING pushbutton switch to operate the WAI system.

NOTE: The aim is to purge water potentially trapped in the High Pressure (HP) bleed ducts and the HP engine bleed chambers.

6 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 the wing slats overheat. However, the ON legend remains illuminated until the switch is deselected.

7 Make sure that the Pressure Regulating Valve (PRV) and the High Pressure Valve (HPV) are open on the ECAM BLEED page with the engine running at this speed while the WAI valve is open.
8 Once the WAI valve is closed, let the engine run at idle for five minutes.

NOTE: Do not actuate WAI systems before the 5-minute period at idle is over in order to avoid the WAI system overheat.

9 Increase and stabilize the engine thrust to at least 60 percent Fan (N1) for ten minutes.
10 Press the ANTI ICE/WING pushbutton switch two times to operate the WAI system once more.

NOTE: The aim is to purge water potentially trapped in the IP bleed ducts and the IP engine bleed chambers.

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

NOTE: Do not perform more than two attempts with a minimum of five minutes between the two attempts, in order to avoid the WAI system overheat.

11 Make sure that the ON legend of the ANTI ICE/WING pushbutton switch comes on when the WAI system operates.
12 Make sure that the PRV is open and the HPV is closed on the ECAM BLEED page with the engine running at this speed while the WAI valve is open.
(b) Once the WAI valve is closed, pull the throttle to stabilize the engine thrust at idle for five minutes and after, do the following:
1 Press the ANTI ICE/WING pushbutton switch and make sure that the ON legend of the ANTI ICE/WING pushbutton switch goes OFF.
2 Turn the crossbleed valve selector switch to the AUTO position.
3 Press the PACK 1 (2) pushbutton switch to operate the air conditioning pack.
4 Make sure that the OFF legend of the PACK 1 (2) pushbutton switch goes off.
5 Check for evidence of anti-freeze mixture odor/smoke in the cabin.

If evidence is found, continue to operate the engine at idle until no odor/smoke remains in the cabin.
After ten minutes of engine running, if continuous odor/smoke remains in the cabin, shut down the engine (Ref. AMM TASK 71-00-00-710-028) and decontaminate the Environmental Control System (ECS) (Ref. AMM TASK 21-00-00-615-803).
Note that the APU Bleed valve must be open before the engine shutdown.
If no evidence is found, shut the engine down (Ref. AMM TASK 71-00-00-710-028).

Subtask 72-00-00-620-070-A ** ON A/C NOT FOR ALL

CAUTION: DO NOT USE THIS ALTERNATIVE PROCEDURE IF THE TEMPERATURE IS LESS THAN +5 DEG. C.

I. Alternative procedure. Post Engine Wash Test

NOTE: The aim of this post engine wash test is:

To purge water from oil system in order to prevent potential bearing/sump corrosion/deterioration
To prevent fumes in the cockpit and in the cabin when the airplane is put back into service.

(1) On the AIR COND panel 30VU, make sure that:

PACK 1 and PACK 2 are OFF prior to the start of the procedure that follows.
The crossbleed valve selector switch is in the OPEN position.
ENG 1 BLEED and ENG 2 BLEED are OFF.

(2) On the VENTILATION panel 22VU, make sure that:

CAB FANS pushbutton switch is in the OFF position.

(3) Start the engine within 2 hours (or 30 minutes in icing condition) of the last wash cycle to purge the lube/sump system of any water ingestion (Ref. AMM TASK 71-00-00-710-003).

NOTE: This engine run is done to ensure that the bleed system is free from contaminant. Smoke/Smell in the cabin and Starter Air Valve (SAV) contamination can result if contaminant enters the bleed system.

(4) After engine start, push the APU BLEED pushbutton switch to the OFF position. The APU bleed valve must be closed, to avoid the supply of air to the wing anti-ice systems from the APU.
(5) Let the engine run at idle for 5 minutes.
(6) Press the ANTI ICE/ENG pushbutton switch to operate the engine anti-ice system.
(7) After 5 minutes put the ANTI ICE/ENG pushbutton switch to OFF.
(8) Do the following:
(a) Press the ENG 1(2) BLEED pushbutton switch to ON. Make sure that the OFF legend goes off when the engine bleed system operates.
(b) Press the ANTI ICE/WING pushbutton switch to ON. Make sure that the ON legend goes on when the wing anti ice system operates.

NOTE: The aim is to purge water potentially trapped in High Pressure (HP) bleed ducts and HP engine bleed chambers.

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

(c) Make sure that Pressure Regulating Valve (PRV) and High Pressure Valve (HPV) are open on ECAM BLEED page with engine running at this speed while WAI valves are open.
(9) Once WAI valves are closed, let the engine run at idle for 5 minutes.

NOTE: Do not actuate WAI system before the 5-minute period at idle is over in order to avoid WAI system overheat.

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

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

NOTE: Do not perform more than two attempts with a minimum of 5 minutes between the two attempts, in order to avoid WAI systems overheat.

(a) Make sure that the ON legend goes on when the wing anti ice system operates.
(b) Make sure that Pressure Regulating Valve (PRV) and High Pressure Valve (HPV) are open on ECAM BLEED page with engine running at this speed while WAI valves are open.
(11) Once the WAI valves are closed, stabilize the engine thrust at idle for 5 minutes.
(12) Press once the ANTI ICE/WING pushbutton switch and make sure that the ON legend goes off.

NOTE: Do not press the WAI pushbutton switch twice. If the WAI pushbutton switch ON legend is still on, pressing twice the WAI pushbutton switch enables a second WAI cycle of 30 seconds to be started.

(13) Push the APU BLEED pushbutton switch to the ON position.
(14) Turn the crossbleed valve selector switch to the AUTO position.
(15) Press the PACK 1 (2) pushbutton switch to operate the air conditioning pack.
(16) Make sure that the OFF legend of the PACK 1 (2) pushbutton switch goes off.
(17) Press the CAB FANS pushbutton switch.
(18) Make sure that the OFF legend of the CAB FANS pushbutton switch goes off.
(19) Shut down the engine (Ref. AMM TASK 71-00-00-710-028).

5. Close-up
Subtask 72-00-00-869-065-A ** ON A/C NOT FOR ALL

A. Make sure that the work area is clean and clear of tools and other items.

Subtask 72-00-00-862-051-A ** ON A/C NOT FOR ALL

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

Subtask 72-00-00-942-053-A ** ON A/C NOT FOR ALL

C. Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 02:40:53 UTC