Motor the Engine (Wet Method) [PW11]

TASK 71-00-00-860-825-A
Motor the Engine (Wet Method)

WARNING: WHEN YOU GO NEAR A JET ENGINE, BE CAREFUL TO STAY AWAY FROM THE INLET AREA. AN ENGINE HAS SUFFICIENT SUCTION AT THE INLET TO PULL A PERSON UP TO THE INLET OR INTO IT. THIS CAN CAUSE INJURY OR DEATH. THE INLET CAN ALSO PULL HATS, GLASSES, LOOSE CLOTHING, OR RAGS FROM POCKETS. REMOVE OR MAKE SAFE ALL LOOSE ITEMS BEFORE YOU DO WORK AROUND AN ENGINE.

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

WARNING: MAKE SURE THAT ALL ENGINE-IN-OPERATION AREAS (RAMPS, TAXIWAYS, RUNWAYS, ETC.) ARE SUFFICIENTLY CLEAN TO PREVENT INJURY TO THE PERSONS IN THE AREA AND DAMAGE TO THE ENGINE OR AIRCRAFT.

WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE CLEAR BEFORE YOU MOTOR THE ENGINE. MOVEMENT OF THE FLIGHT CONTROL SURFACES CAN BE DANGEROUS AND/OR CAUSE DAMAGE.

WARNING: DO NOT TOUCH THE PROBES DURING OR IMMEDIATELY AFTER THIS PROCEDURE. THE PROBES WILL BE HOT AND CAN BURN YOU.

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

WARNING: MAKE SURE THAT THE LANDING GEAR GROUND SAFETIES AND THE WHEEL CHOCKS ARE IN POSITION. MOVEMENT OF THE AIRCRAFT CAN BE DANGEROUS.

CAUTION: MAKE SURE THAT THERE IS NO HYDRAULIC GROUND POWER SUPPLY CONNECTED TO THE AIRCRAFT WHEN YOU DO THIS PROCEDURE. IF A GROUND POWER SUPPLY IS CONNECTED, THERE IS A RISK OF DAMAGE TO THE ENGINE PUMPS.

CAUTION: BEFORE YOU OPERATE THE ENGINE, LOOK AT THE INLET AND THE AREA AROUND IT (MAKE SURE THE AREA IS CLEAN). DIRT AND LOOSE OBJECTS CAN CAUSE DAMAGE IF THEY GET INTO THE ENGINE.

ZONE: 210
ZONE: 400

1. Reason for the Job
Use this procedure to check the complete fuel system and the oil system for leaks.
The wet motor leak test uses the engine starter only to operate the engine for a short time to check for leaks in the fuel or oil system. The ignition system is OFF for this test. The fuel goes to the Integrated Fuel Pump and Control (IFPC), the actuator fuel pressure lines, the engine fuel manifolds (primary fuel lines only) and nozzles. Fuel is then sprayed in the combustion chamber.

NOTE: During a motoring sequence on the ground, the Electronic Engine Control (EEC) automatically determines if motoring to Start is required for BOWED ROTOR PROTECTION. The EEC keeps the N2 speed at a low value (approximately 10 percent N2) for a calculated duration based on time since shutdown, Outside Air Temperature (OAT) and engine turbine temperature. During motoring to Start, a "COOLING" indication is displayed on the upper Electronic Centralized Aircraft Monitoring (ECAM) display unit. When the motoring to Start period is complete, the EEC will continue to normal engine start. If N2 exceeds the maximum speed for BOWED ROTOR PROTECTION during motoring to start, the EEC will abort the motoring and the warning ENG X START FAULT (BOWED ROTOR PROTECTION) will be displayed.

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

REFERENCE	QTY	DESIGNATION
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER

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

C. Referenced Information

REFERENCE	DESIGNATION
TASK 10-11-00-555-014-A	Removal of the Aircraft Protection Equipment
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 29-10-00-863-002-A	Pressurize the Yellow Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-30-00-200-002-A	Check of the Reservoir Quantity Indication on the ECAM Display Unit
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 36-12-00-860-802-A	Pressurization of the Bleed System with the APU
TASK 36-12-00-860-803-A	Pressurization of the Bleed System through the HP Ground Connector
TASK 71-00-00-860-833-A	Procedure to Prevent Engine Motoring
TASK 79-00-00-610-801-A	Check and Fill the Engine Oil
Cockpit Controls and Panels

3. Job Set-up
Subtask 71-00-00-941-134-A ** ON A/C NOT FOR ALL

A. Safety Precautions

CAUTION: REMOVE THE PROTECTIVE COVERS FROM THE PROBES BEFORE YOU DO THIS PROCEDURE. IF YOU DO NOT REMOVE THEM, THE PROBES AND PROTECTIVE COVERS CAN BECOME DAMAGED OR BURNED.

(1) Make sure that all the protection covers are removed from the aircraft (Ref. AMM TASK 10-11-00-555-014).
(2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
(3) Do the procedure to prevent engine motoring
(Ref. AMM TASK 71-00-00-860-833).
(4) On overhead control and indicator panel 22VU, on the ENG section:
(a) Make sure that the ON legend of the MAN START pushbutton switch is off.
(5) On rudder-trim parking-brake panel 110VU, on the PARKING BRK section:
(a) Make sure that the PARK BRK control-switch is set to ON.
(6) On right-center instrument panel 400VU, make sure that:
(a) The brake pressure indication on the Yellow brake-pressure triple-indicator is correct. If necessary, pressurize the brake accumulator with the Yellow pump (Ref. AMM TASK 29-10-00-863-002).
(7) Make sure that all the parts, tools, equipment and loose objects are removed from the engine air intake and the area around the intake.
(8) Prepare a fire extinguisher in case of fire during the procedure.

Subtask 71-00-00-860-217-A ** ON A/C NOT FOR ALL

B. Preparation before Procedure
(1) Do the Electronic Instrument System (EIS) start procedure (ECAM display units only) (Ref. AMM TASK 31-60-00-860-001).

Subtask 71-00-00-865-176-A ** ON A/C NOT FOR ALL

CAUTION: DO NOT CLOSE CIRCUIT BREAKERS 1QG/2QG/3QG/4QG IF YOU DO THE PROCEDURE "PRESERVATION OF THE ENGINE (FOR MORE THAN 60 DAYS)". IF YOU DO NOT OBEY THIS INSTRUCTION, THE LP FUEL VALVE WILL OPEN AND THERE IS A RISK THAT FUEL WILL FLOW OUT.

C. Make sure that this(these) circuit breaker(s) is(are) closed:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	ENGINE/1 AND 2/IGN/SYS A	1JH	A03
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENG 1)
49VU	FUEL/LP VALVE/MOT1/ENG1	1QG	A08
49VU	ENGINE/1/FADEC A/AND EIU 1	2KS1	A04
49VU	ENGINE/1/HP FUEL SOV	1KC1	A01
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R41
** ON A/C NOT FOR ALL
121VU	FUEL/LP VALVE/MOT2/ENG1	3QG	M25
121VU	OIL/PRESS/ENG1	10KC1	N40
121VU	ENGINE/IGN/ENG1/SYS B	3JH1	P41
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R40
** ON A/C NOT FOR ALL
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENG 2)
49VU	FUEL/LP VALVE/MOT1/ENG2	2QG	A09
49VU	ENGINE/2/FADEC A/AND EIU 2	2KS2	A05
49VU	ENGINE/2/HP FUEL SOV	1KC2	A02
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG2/FADEC B/AND EIU2	4KS2	Q40
** ON A/C NOT FOR ALL
121VU	FUEL/LP VALVE/MOT2/ENG2	4QG	M26
121VU	OIL/PRESS/ENG2	10KC2	N42
121VU	ENGINE/IGN/ENG2/SYS B	3JH2	P42
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG2/FADEC B/AND EIU2	4KS2	R41

Subtask 71-00-00-865-177-A ** ON A/C NOT FOR ALL

D. Open, safety and tag this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	ENGINE/1 AND 2/IGN/SYS A	1JH	A03
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENG 1)
121VU	ENGINE/IGN/ENG1/SYS B	3JH1	P41
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENG 2)
121VU	ENGINE/IGN/ENG2/SYS B	3JH2	P42

Subtask 71-00-00-860-218-A ** ON A/C NOT FOR ALL

E. Continue to Prepare for the Test
(1) Make sure that the thrust lever of the engine 1(2) is set to IDLE.
(2) On the lower ECAM display unit, get the ENG page:
(a) If necessary, service the engine oil system (Ref. AMM TASK 79-00-00-610-801).
(3) Check of the hydraulic reservoir
(a) On the lower ECAM display unit, get the HYDRAULIC page:
1 Make sure that the pressure of the Green reservoir for engine 1 (Yellow reservoir for engine 2) is correct.
2 Make sure that the reservoir fluid level is correct (Ref. AMM TASK 29-30-00-200-002).
(b) Make sure that the engine 1(2) pump is serviceable (on the HYD section of overhead panel 40VU, the OFF legend of the ENG 1(2) PUMP pushbutton switch must be off).
(4) Make sure that the aircraft is cleared and that there are no persons in the dangerous areas.
(5) On the FUEL section of overhead panel 40VU:
(a) Push all the PUMPS pushbutton switches.
(b) Make sure that the OFF legend of these pushbutton switches go off.
(6) Supply the aircraft pneumatic system from a High Pressure (HP) ground power unit or the Auxiliary Power Unit (APU) (Ref. AMM TASK 36-12-00-860-802) or (Ref. AMM TASK 36-12-00-860-803).

4. Procedure

CAUTION: WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.

Subtask 71-00-00-860-219-A ** ON A/C NOT FOR ALL

A. Wet-Motor the Engine
(1) Do the engine wet-motoring as follows:
(a) Set the ENG/MODE rotary selector switch to the CRANK position.
(b) Set the ENG/MAN START 1(2) pushbutton switch to the ON position.
(c) Operate the starter

CAUTION: DO NOT OPERATE THE STARTER FOR MORE THAN FIFTEEN MINUTES. IF YOU DO, YOU CAN CAUSE DAMAGE TO THE STARTER.

1 Operate the starter for as long as necessary but not for more than the starter duty cycle.
(d) The starter duty cycle is as follows:
1 Three start attempts
2 35 seconds cooling period between each start attempt
3 15 minutes cumulative cranking
4 Followed by 15 minutes minimum period when N2 speed is zero (0) Rotation Per Minute (RPM).

NOTE: The EEC will automatically command the starter air valve closed after 15 minutes to ensure the starter duty cycle is not exceed.

(e) The extended starter duty cycle is as follows:
1 15 minutes maximum continuous cranking
2 Followed by 15 minutes minimum period when N2 speed is zero (0) RPM.

NOTE: The EEC will automatically command the starter air valve closed after 15 minutes to ensure the starter duty cycle is not exceed.

(f) On the lower ECAM display unit, do a check of the main oil pressure. The pressure must be positive.
(g) On the upper ECAM display unit, do a check of the N1 and N2 speeds. Both of the rotors must turn.
(h) When the N2 rotor speed stabilizes, move the ENG MASTER 1(2) switch control to the ON position.
(i) Continue to operate the starter.

CAUTION: DO NOT OPERATE THE STARTER FOR MORE THAN ITS DUTY CYCLE. IF YOU DO, YOU CAN CAUSE DAMAGE TO THE STARTER.

1 Operate the starter for 15 seconds after a positive fuel flow indication.
(j) While the engine is motored, do a visual check for leaks at the fuel and oil system tubes, joints and manifolds.

NOTE: This procedure can be used to find a leak at any of the external fuel or oil system tubes and components.

(k) After 15 seconds, set the ENG MASTER 1(2) switch to the OFF position.
(l) Do a check of the fuel flow. The fuel flow must be zero.
(m) With the ENG MASTER 1(2) switch set to OFF, operate the starter for two minutes (do not exceed the starter duty cycle). This step will blow the unwanted fuel out of the combustion chamber and turbines.
(n) On the ENG section of the overhead control and indicating panel 22VU, set the ENG/MAN START 1(2) pushbutton switch to the OFF position.
(o) Make sure that N2 is decreasing.
(p) Set the ENG/MODE rotary selector switch to the NORM position.
(q) If you find any leaks, repair all leaks and leak test the engine again.

5. Close-up
Subtask 71-00-00-860-220-A ** ON A/C NOT FOR ALL

A. Put the aircraft back to its initial configuration.
(1) On the FUEL section of overhead panel 40VU:
(a) Release all the PUMPS pushbutton switches.
(b) Make sure that the OFF legend of these pushbutton switches comes on.
(2) Stop the pneumatic air supply to the aircraft.
(a) Disconnect the HP ground power unit or stop the APU (Ref. AMM TASK 36-12-00-860-802) or (Ref. AMM TASK 36-12-00-860-803).
(3) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(4) Make sure that the work area is clean and clear of tools and other items.

Subtask 71-00-00-865-178-A ** ON A/C NOT FOR ALL

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	ENGINE/1 AND 2/IGN/SYS A	1JH	A03
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENG 1)
121VU	ENGINE/IGN/ENG1/SYS B	3JH1	P41
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENG 2)
121VU	ENGINE/IGN/ENG2/SYS B	3JH2	P42

Subtask 71-00-00-860-238-A ** ON A/C NOT FOR ALL

C. Put the aircraft back to its initial configuration.
(1) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

[Rev.10 from 2021] 2026.04.01 12:57:05 UTC