AMM - AVA - A330 REV DATE: Apr 01/2024
Tail Number - MSN - FSN: ALL
71-00-00-720-827-A - Wet Motoring Engine
** ON A/C FSN ALL
TASK 71-00-00-720-827-A
Wet Motoring Engine
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 DO A WET MOTORING OF THE ENGINE IN A HANGAR OR OTHER CLOSED AREA. A
LARGE QUANTITY OF VERY FLAMMABLE FUEL FUMES COMES OUT OF THE ENGINE
DURING THIS PROCEDURE AND THERE IS A HIGH RISK OF FIRE.
WARNING: IT IS PERMITTED TO MOTOR THE ENGINE WITH THE T/R COWLS OPEN BUT IT IS NOT
PERMITTED TO START/IGNITE THE ENGINE. INJURY CAN BE CAUSED TO PERSONS AND
DAMAGE CAN BE CAUSED TO EQUIPMENT.
WARNING: DO NOT TRY TO STOP FAN FROM TURNING BY HAND. INJURY CAN BE CAUSED TO
PERSONS AND DAMAGE CAN BE CAUSED TO EQUIPMENT.
WARNING: NO PERSON IS TO STAND INSIDE THE T/R COWLS OR FAN COWL DOORS WHEN YOU
MOTOR THE ENGINE. INJURY CAN BE CAUSED TO PERSONS.
WARNING: OPEN THE PROBE HEATER CIRCUIT-BREAKERS OF AOA (1, 2 AND 3), TAT (1, 2), PITOT (1, 2
AND 3), AND STAT (1, 2 AND 3), BEFORE THE PROBES BECOME TOO HOT. THIS CAN
CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.
WARNING: DO NOT TOUCH THE PROBES DURING OR IMMEDIATELY AFTER THIS PROCEDURE.
THE PROBES ARE 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.
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: MAKE SURE THAT ALL ENGINE AREAS ARE AS CLEAR AS POSSIBLE.
CAUTION: MAKE SURE THAT THE WHEEL CHOCKS ARE IN THE CORRECT POSITION. THIS WILL
PREVENT UNWANTED MOVEMENT OF THE AIRCRAFT, AND THUS POSSIBLE DAMAGE.
CAUTION: REMOVE THE PROTECTIVE COVERS FROM THE PROBES BEFORE YOU DO THE TEST.
1. Reason for the Job
A wet motor procedure is used for maintenance actions that need core engine rotation and fuel flow without
ignition. A wet motor can be used to examine the fuel system for leaks and to depreserve and prime the fuel
system after maintenance.
JCP Title: wet © AIRBUS S.A.S. ALL RIGHTS RESERVED. Page 1 of 8
CONFIDENTIAL AND PROPRIETARY DOCUMENT. PRINT DATE: Jun 04/2024
AMM - AVA - A330 REV DATE: Apr 01/2024
Tail Number - MSN - FSN: ALL
71-00-00-720-827-A - Wet Motoring Engine
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
QT
REFERENCE DESIGNATION
Y
No specific AR ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE
No specific AR SAFETY CLIP - CIRCUIT BREAKER
B. Work Zones and Access Panels
ZONE/ACCESS ZONE DESCRIPTION
811
C. Referenced Information
REFERENCE DESIGNATION
Ref. 24-41-00-861-801-A Energization of the Aircraft Electrical Circuits With External Power
A
Ref. 24-41-00-861-801-A01 Energization of the Aircraft Electrical Circuits With the APU (APU
Started With the APU Battery)
Ref. 24-41-00-861-801-A03 Energization of the Aircraft Electrical Circuits With External Power
A and B
Ref. 24-41-00-861-801-A04 Energization of the Aircraft Electrical Circuits With the APU (APU
Started With External Power A)
Ref. 24-41-00-861-801-A05 Energization of the Aircraft Electrical Circuits With External Power
B
Ref. 24-41-00-862-801-A De-energization of the Aircraft Electrical Circuits With External
Power A
Ref. 24-41-00-862-801-A01 De-energization of the Aircraft Electrical Circuits With the APU
Ref. 24-41-00-862-801-A03 De-energization of the Aircraft Electrical Circuits With External
Power A and B
Ref. 24-41-00-862-801-A04 De-energization of the Aircraft Electrical Circuits With External
Power B
Ref. 26-12-00-710-812-A Operational Test of the Engine Fire and Overheat Detection (Loop
/Squib)
Ref. 29-00-00-863-802-A01 Pressurize the Blue Hydraulic System with the Electric Pump
Ref. 31-60-00-860-801-A EIS Start Procedure
Ref. 36-12-00-860-801-A Pressurization of the Bleed System with the APU
JCP Title: wet © AIRBUS S.A.S. ALL RIGHTS RESERVED. Page 2 of 8
CONFIDENTIAL AND PROPRIETARY DOCUMENT. PRINT DATE: Jun 04/2024
AMM - AVA - A330 REV DATE: Apr 01/2024
Tail Number - MSN - FSN: ALL
71-00-00-720-827-A - Wet Motoring Engine
Ref. 36-12-00-860-802-A Pressurization of the Bleed System through the HP Ground
Connector
Ref. 71-00-00-860-828-A Prepare the Aircraft/Engine for Ground Operation
Ref. 71-00-00-860-829-A The General Procedures if an Engine Fire Occurs During Ground
Operation
Ref. 71-00-00-860-836-A The Engine Limits
Ref. 72-00-00-200-813-A Borescope Inspection of the HP Compressor Blades
Ref. 72-00-00-200-814-A Borescope Inspection of HP Turbine Blades
Ref. 72-00-00-860-803-A Turn the Engine Low Pressure System
Ref. TSM 79-31-00-810-847 High Oil Consumption and Oil Staining
Ref. 12-13-79-610-809-A To Service the Engine Oil System (for corrective action)
3. Job Set-up
SUBTASK 71-00-00-861-098-A
A. Energize A/C electrical circuits Ref. AMM TASK 24-41-00-861-801.
SUBTASK 71-00-00-010-149-A
B. Get access to the avionics compartment.
(1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the access door 811.
(2) Open the access door 811.
(3) Open the protective door of the AC/DC emergency power-center 740VU.
SUBTASK 71-00-00-865-330-A
C. Make sure that this (these) circuit breaker(s) is (are) closed:
PANEL DESIGNATION FIN LOCATION
FOR FIN 4030EM1(POWERPLANT-DEMOUNTABLE, ENG 1)
721VU EIVMU 1 14KS1 N10
722VU FADEC B ENG 1 13KS1 D44
742VU HP FUEL SOV ENG 1 1KC1 C68
742VU FADEC A ENG 1 12KS1 Q73
FOR FIN 4030EM2(POWERPLANT-DEMOUNTABLE, ENG 2)
721VU EIVMU 2 14KS2 P06
722VU FADEC B ENG 2 13KS2 K49
742VU HP FUEL SOV ENG 2 1KC2 D70
742VU FADEC A ENG 2 12KS2 Q74
SUBTASK 71-00-00-865-354-A
JCP Title: wet © AIRBUS S.A.S. ALL RIGHTS RESERVED. Page 3 of 8
CONFIDENTIAL AND PROPRIETARY DOCUMENT. PRINT DATE: Jun 04/2024
AMM - AVA - A330 REV DATE: Apr 01/2024
Tail Number - MSN - FSN: ALL
71-00-00-720-827-A - Wet Motoring Engine
D. Get access to the avionics compartment. Then open, safety and tag this(these) circuit breaker(s):
PANEL DESIGNATION FIN LOCATION
FOR FIN 4030EM1(POWERPLANT-DEMOUNTABLE, ENG 1)
721VU IGN SYS B ENG 1 2EH1 G03
742VU IGN SYS A ENG 1 1EH1 Q70
FOR FIN 4030EM2(POWERPLANT-DEMOUNTABLE, ENG 2)
722VU IGN SYS B ENG 2 2EH2 F50
742VU IGN SYS A ENG 2 1EH2 Q71
SUBTASK 71-00-00-869-147-A
E. Continue to prepare for test.
(1) Do the Electronic Instrument System (EIS) start procedure Ref. AMM TASK 31-60-00-860-801.
(2) Read the general procedures for an engine fire during ground operation Ref. AMM TASK 71-00-
00-860-829.
(3) Make sure that you obey your local fire-fighting regulations.
(4) You must do the general procedures for the engine ground operation Ref. AMM TASK 71-00-00-
860-828.
(5) Read the engine limits Ref. AMM TASK 71-00-00-860-836.
(6) On the Electronic Centralized Aircraft Monitoring (ECAM) control panel, push the HYD key to get
the hydraulic page on the System Display (SD).
- Make sure that the pressure of the hydraulic reservoir is correct
(a) FOR 4030EM1 (POWERPLANT-DEMOUNTABLE, ENG 1)
Green, Blue reservoir
(b) FOR 4030EM2 (POWERPLANT-DEMOUNTABLE, ENG 2)
Green, Yellow reservoir
- Make sure that the reservoir fluid level is correct.
(7) Make sure that the engine 1, (2) fuel pump is serviceable (on the panel 245VU, the FAULT
legend of the ENG 1, (2) PUMP pushbutton switch must be off).
(8) You must have one of these air sources to wet motor the engine:
(a) The Auxiliary Power Unit (APU) air supply Ref. AMM TASK 36-12-00-860-801.
(b) The cross-bleed air from the other engine, if it is in operation.
(c) A ground air supply Ref. AMM TASK 36-12-00-860-802.
(9) Supply air from the applicable air source. Make sure there is sufficient pressure.
SUBTASK 71-00-00-720-070-A
F. Do this test:
ACTION RESULT
1.On the panel 245VU: - Make sure that the ENG 1(2) FUEL PUMP
is ON (FAULT legend off).
JCP Title: wet © AIRBUS S.A.S. ALL RIGHTS RESERVED. Page 4 of 8
CONFIDENTIAL AND PROPRIETARY DOCUMENT. PRINT DATE: Jun 04/2024
AMM - AVA - A330 REV DATE: Apr 01/2024
Tail Number - MSN - FSN: ALL
71-00-00-720-827-A - Wet Motoring Engine
2.Make sure that the throttle control lever of the
engine 1, (2), is in the idle stop position (zero on
the graduated sector).
3.On the panel 145VU: - Make sure that the ENG MODE SEL SW is
on the NORM position
4.On the panel 212VU: - Make sure that the ENG/MAN START /1,
(2), is on the OFF position.
5.On the panel 125VU: - Make sure that the ENG MASTER 1, (2),
switch is OFF.
6.On the panel 312VU: - Make sure that brake pressure indication on
the Blue brake-pressure triple indicator is
correct. If necessary pressurize the brake
accumulator with Blue pump Ref. AMM
TASK 29-00-00-863-802.
7.On the panel 117VU: - Make sure that the Parking brake is ON.
SUBTASK 71-00-00-710-141-A
G. Do an operational test of the fire detection system Ref. AMM TASK 26-12-00-710-812.
4. Procedure
SUBTASK 71-00-00-860-114-A
A. Wet motor the engine:
CAUTION: IF THE ENGINE IS IN A COLD ENVIRONMENT THE ENGINE OIL TEMPERATURE
CAN DECREASE. IF THE ENGINE IS NOT OPERATED AND IS IN THIS
ENVIRONMENT YOU MUST CHECK THE ENGINE OIL TEMPERATURE
REGULARLY. TO MAINTAIN SATISFACTORY ENGINE OIL TEMPERATURE DO AN
ENGINE START AND OPERATE THE ENGINE AT IDLE.
CAUTION: MAKE SURE THAT THE ENG/MASTER 1 (2)SWITCH (ON ENG MASTER CONTROL
PANEL 125VU) IS SET TO OFF BEFORE YOU START THE AIRCRAFT FUEL
PUMPS. DAMAGE TO ENGINE COULD OCCUR.
CAUTION: DO NOT START, DRY MOTOR OR WET MOTOR THE ENGINE IF THE OIL
TEMPERATURE IS LESS THAN MINUS 40 DEG.C (MINUS 40 DEG.F). LOW OIL
TEMPERATURES CAN CAUSE DAMAGE TO THE ENGINE BEARINGS.
CAUTION: DO NOT START, DRY MOTOR OR WET MOTOR THE ENGINE IF THERE WAS A
LOSS OF DRIVE BETWEEN THE EXTERNAL GEARBOX AND THE ENGINE
(INTERNAL GEARBOX). THIS CAN CAUSE INTERNAL OIL LOSS AND FIRE.
IF YOU TRIED TO START OR MOTOR THE ENGINE AND THE ENGINE MAIN
SHAFTS DID NOT TURN, YOU MUST REJECT THE ENGINE.
(1) Make sure that the oil temperature is more than -40 deg.C (-40.00 deg.F).
JCP Title: wet © AIRBUS S.A.S. ALL RIGHTS RESERVED. Page 5 of 8
CONFIDENTIAL AND PROPRIETARY DOCUMENT. PRINT DATE: Jun 04/2024
AMM - AVA - A330 REV DATE: Apr 01/2024
Tail Number - MSN - FSN: ALL
71-00-00-720-827-A - Wet Motoring Engine
(2) Make sure Exhaust Gas Temperature (EGT) is less than 100 deg.C (212.00 deg.F).
NOTE: The EGT must be less than 100 deg.C (212.00 deg.F) before you let fuel flow through
the engine.
(3) Make sure that the cockpit selections are set as necessary.
(4) Do the quantity checks of the engine oil system.
(a) Do not start the engine if the cockpit indication for oil in the engine oil systems is less than
3.375 USgal (12.7759 l). (If necessary use the engine oil tank sight indicator to check the
engine oil system Ref. AMM TASK 12-13-79-610-809)
1 On the panel 145VU, set the ENGINE START rotary selector to the CRANK
position
2 On the SD, make sure that the OIL QTY of oil in the oil tank of the engine 1(2) is
correct (If necessary fill the oil tank Ref. AMM TASK 12-13-79-610-809).
(b) Do not start the engine if the engine oil system requires more than 1.25 USgal (4.7318 l)
to make it full.
(5) MANUAL START pushbutton:
CAUTION: IF YOU SET THE ENG/MAN START PUSHBUTTON SWITCH TO OFF
(DURING THE DRY MOTORING PROCEDURE), DO NOT TOUCH THE
SWITCH AGAIN UNTIL THE N3 SPEED IS LESS THAN 10 PERCENT. IF YOU
SET THE SWITCH BACK TO ON, AT AN N3 SPEED HIGHER THAN 10
PERCENT, YOU WILL CAUSE DAMAGE TO THE ENGINE/STARTER.
CAUTION: DO NOT OPERATE THE STARTER MORE THAN THE STARTER LIMITS. IF
YOU DO NOT OBEY THE STARTER LIMITS, YOU CAN CAUSE DAMAGE TO
THE STARTER.
(a) Set the relevant MANUAL START pushbutton to the ON position.
NOTE: Continuous operation of the starter motor must be limited in accordance with
one of the following cycles:
- Normal cycle
up to 3 minutes continuous operation then run down to zero N3
up to a further 3 minutes continuous operation then run down to zero N3.
up to a further 1 minute continuous operation then run down to zero N3 and
allow to cool for 30 minutes.
- Extented cycle up to 5 minutes continuous operation followed by 30
minutes for cooling.
(6) Make sure that you see an indication that the N3 rotor has turned. If the N3 rotor does not turn,
set the MANUAL START pushbutton to the OFF position. Find the cause of the problem.
NOTE: The N3 rotor max.speed during the wet motor procedure is 29 to 35 percent.
(7) Make sure that you see an oil pressure indication increase in 30 seconds after N3 starts to turn.
If the oil pressure stays at zero, stop the start. Find the cause of the problem.
(8) Make sure there is an indication that the N1 and N2 rotors have turned. If the N1 or N2 rotors
have not turned within 30 seconds (after indication that N3 has turned), abandon the start - set
the MANUAL START push button to OFF. Do the steps that follow to find the cause of the
problem.
JCP Title: wet © AIRBUS S.A.S. ALL RIGHTS RESERVED. Page 6 of 8
CONFIDENTIAL AND PROPRIETARY DOCUMENT. PRINT DATE: Jun 04/2024
AMM - AVA - A330 REV DATE: Apr 01/2024
Tail Number - MSN - FSN: ALL
71-00-00-720-827-A - Wet Motoring Engine
(a) Let the engine cool, turn the Low Pressure Compressor (LPC) Ref. AMM TASK 72-00-00-
860-803.
1 If the LP compressor does not turn, remove the engine.
2 If the LP compressor turns, check the engine oil quantity.
a If the engine oil quantity has decreased by more than 2 quarts, remove the
engine.
b If the engine oil quantity has not decreased by more than 2 quarts, do a
borescope inspection of the High Pressure Compressor (HPC) Ref. AMM
TASK 72-00-00-200-813 and Ref. AMM TASK 72-00-00-200-814.
3 If the HP compressor does not turn, remove the engine.
4 If the HP compressor does turn, try a second engine start.
a If there is an N1/N2 value and the LP compressor has turned, continue to
operate the engine.
b If there is no N1/N2 value and the LP compressor has not turned, remove the
engine.
(9) Make sure that the EGT is less than 100 deg.C (212.00 deg.F). If the EGT is more than 100 deg.
C (212.00 deg.F) you must continue to dry motor the engine to lower the EGT . Do not operate
the starter more than the starter limits.
(10) Set the ENGINE MASTER lever to the ON position to let fuel flow through the engine for one
minute maximum.
NOTE: The fuel flow indication during the wet motor procedure must be 250 kg (551.1555 lb)
to 270 kg (595.2479 lb) per hour.
(11) Stop the wet motor procedure as necessary
CAUTION: DO NOT OPERATE THE STARTER MORE THAN THE STARTER LIMITS. IF
YOU DO NOT OBEY THE STARTER LIMITS, YOU CAN CAUSE DAMAGE TO
THE STARTER.
(a) Set the ENGINE MASTER lever to the OFF position.
NOTE: When the fuel flow through the engine is stopped the engine must be dry
motored to remove remaining fuel.
(b) Continue to dry motor the engine for a minimum of 20 seconds until there is no more fuel
fog at the engine exhaust.
(12) During wet motoring you can accept: Ref. TSM 79-31-00-810-847.
(a) A large quantity of new oil from the adaptor plates of the intermediate case strut.
(b) A large quantity of new oil from the drain hole in the front bearing housing.
5. Close-up
SUBTASK 71-00-00-869-148-A
A. Put the aircraft back to its initial configuration.
JCP Title: wet © AIRBUS S.A.S. ALL RIGHTS RESERVED. Page 7 of 8
CONFIDENTIAL AND PROPRIETARY DOCUMENT. PRINT DATE: Jun 04/2024
AMM - AVA - A330 REV DATE: Apr 01/2024
Tail Number - MSN - FSN: ALL
71-00-00-720-827-A - Wet Motoring Engine
(1) Stop the pneumatic supply to the aircraft :
- Disconnect the High Pressure (HP) Ground Connector or shut down the APU.
(2) Set the MANUAL START pushbutton to the OFF position.
SUBTASK 71-00-00-865-135-A
B. Remove the SAFETY CLIP - CIRCUIT BREAKER and the tag(s) and close this (these) circuit breaker
(s):
PANEL DESIGNATION FIN LOCATION
FOR FIN 4030EM1(POWERPLANT-DEMOUNTABLE, ENG 1)
721VU IGN SYS B ENG 1 2EH1 G03
742VU IGN SYS A ENG 1 1EH1 Q70
FOR FIN 4030EM2(POWERPLANT-DEMOUNTABLE, ENG 2)
722VU IGN SYS B ENG 2 2EH2 F50
742VU IGN SYS A ENG 2 1EH2 Q71
SUBTASK 71-00-00-410-126-A
C. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the protective door of the AC/DC emergency power center 740VU.
(3) Close the access door 811.
SUBTASK 71-00-00-862-092-A
D. De-energize A/C electrical circuits Ref. AMM TASK 24-41-00-862-801.
JCP Title: wet © AIRBUS S.A.S. ALL RIGHTS RESERVED. Page 8 of 8
CONFIDENTIAL AND PROPRIETARY DOCUMENT. PRINT DATE: Jun 04/2024
