Test No.15 - Operation Test (Dry Motor) of the FADEC System Engine Actuators [PW11]

TASK 73-21-00-710-809-A
Test No.15 - Operation Test (Dry Motor) of the FADEC System Engine Actuators

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

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: REMOVE THE PROTECTIVE COVERS FROM THE PROBES BEFORE YOU DO THIS PROCEDURE.

ZONE: 210
ZONE: 400

1. Reason for the Job
The actuator interactive test shall detect any operational faults of the control system actuators without an engine start.
This test shall also detect any operational faults of the Integrated Fuel Pump and Control (IFPC) Fuel Metering Valve (FMV).
The Full Authority Digital Engine Controls (FADEC) will perform interactive tests on the following actuators through engine crank.
(1) The Low Pressure Compressor (LPC) Variable Stator Vane Actuator (SVA).
(2) The High Pressure Compressor (HPC) Primary Variable Stator Vane Actuator (SVA).
(3) The High Pressure Compressor (HPC) Secondary Variable Stator Vane Actuator (SVA).
(4) The LPC 2.5 bleed valve actuator.
(5) The turbine Active Clearance Control (ACC) actuator.
(6) The Integrated Fuel Pump and Control (IFPC) Fuel Metering Valve (FMV).
This test is performed while the engine is dry motoring.

NOTE: During a motoring sequence on the ground, the 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, OAT and engine turbine temperature. During Motoring to Start, a "COOLING" indication is displayed on the upper 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	1	ACCESS PLATFORM 1M(3 FT)

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, ENG 1)
437AL, 438AR, 452AR
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
447AL, 448AR, 462AR

C. Referenced Information

REFERENCE	DESIGNATION
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 31-32-00-860-012-A	Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page
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 71-00-00-720-814-A	Test No. 2A - Engine Motor Leak Test (Wet Method)
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 73-21-00-710-806-A	Test No.7 - EEC Operation Test (Self Test)
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 79-00-00-610-801-A	Check and Fill the Engine Oil
Operation Test (Dry Motor) of the FADEC System Engine Actuators (Cockpit Controls and Panels)
Operation Test (Dry Motor) of the FADEC System Engine Actuators (Cockpit Controls and Panels)

3. Job Set-up
Subtask 73-21-00-941-064-B ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) Make sure that for all the engine motoring procedures, that you will do during this test, you obey the starter operation limits (Ref. AMM TASK 71-00-00-910-803).
(2) If you disconnect fuel lines or replace any of the actuators and components, do the Test No. 2A - Engine Motor Leak Test (Wet Method) (Ref. AMM TASK 71-00-00-720-814).
(3) Make sure that all the parts, tools, equipment and loose objects are removed from the engine air intake and the area around the intake.
(4) If the crank is wet, obey the wind direction and velocity operation limits (Ref. AMM TASK 71-00-00-910-803).

Subtask 73-21-00-860-083-B ** ON A/C NOT FOR ALL

B. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(2) On the center pedestal, on ENG panel 115VU:
(a) Make sure that the ENG/MODE rotary selector switch is in the NORM position.
(b) Make sure that the ENG MASTER 1(2) switch control was in the OFF position not less than five minutes before you do this procedure.
(3) 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.
(4) On overhead control and indicating panel 22VU:
(a) Make sure that the ON legend of the MAN START pushbutton switch is off.
(5) On RUD TRIM/PARKING BRK panel 110VU:
(a) Make sure that the parking-brake 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).

Subtask 73-21-00-860-077-B ** ON A/C NOT FOR ALL

C. Preparation before Procedure
(1) Do the EIS start procedure (ECAM Display Units (DU) only) (Ref. AMM TASK 31-60-00-860-001).
(2) Do the procedure to get access to the SYSTEM REPORT/TEST ENG page (Ref. AMM TASK 31-32-00-860-012).

Subtask 73-21-00-875-051-B ** ON A/C NOT FOR ALL

D. 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 73-21-00-860-078-B ** ON A/C NOT FOR ALL

E. Continue to Prepare for the Test
(1) On the FUEL section of HYD/FUEL panel 40VU:
(a) Push all the PUMPS pushbutton switches.
(b) Make sure that the OFF legend of these pushbutton switches go off.
(2) On the overhead circuit breaker panel 49VU:
(a) Open circuit breaker 1KC1(2) to open the LP valve.
(b) After a few seconds:

The single chime sounds.
The MASTER CAUT light comes on.
The ENG1(2) LP VALVE OPEN warning message comes into view on the upper ECAM DU.

(3) Supply the aircraft pneumatic system from a HP ground power unit or the APU (Ref. AMM TASK 36-12-00-860-803) or (Ref. AMM TASK 36-12-00-860-802).
(4) Make sure that the thrust lever of the engine 1(2) is set to IDLE.
(5) Get the engine page on the lower ECAM DU.

Operation Test (Dry Motor) of the FADEC System Engine Actuators (Cockpit Controls and Panels) ** ON A/C NOT FOR ALL

(a) Make sure that the fuel quantity is more than zero. Pressurized fuel is necessary in the engine fuel lines to move the actuators during the test.
(b) Make sure that there is a sufficient quantity of oil to operate the engine.
(c) If necessary, do the servicing of the engine oil system (Ref. AMM TASK 79-00-00-610-801).
(6) Check of the hydraulic reservoir
(a) On the lower ECAM DU, get the HYDRAULIC page:
1 Make sure that no LOW AIR PRESS message appears.
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 HYD/FUEL panel 40VU, the OFF legend of the ENG 1(2) PUMP pushbutton switch must be off).

CAUTION: WHEN YOU DO THE ACTUATOR INTERACTIVE TEST, MAKE SURE THAT THE "ENGXD-0019-HPSOV FAIL" MAINTENANCE MESSAGE IS NOT SHOWN ON THE MCDU. IF IT IS, THE TEST CAN GIVE AN INCORRECTLY POSITIVE RESULT.

(c) Do the test No. 7 - EEC Operation Test (Self Test) (Ref. AMM TASK 73-21-00-710-806) and check the Multipurpose Control and Display Unit (MCDU) to make sure that the maintenance message ENGXD-0019-HPSOV FAIL has not been set.
(7) Make sure that the aircraft is cleared and that there are no persons in the dangerous areas.

4. Procedure
Subtask 73-21-00-710-056-B ** ON A/C NOT FOR ALL

A. EEC Ground Test of the Engine Actuators

CAUTION: DO NOT OPERATE THE STARTER FOR MORE THAN THE FOUR MINUTES MAXIMUM STARTER TIME LIMIT. IF YOU DO, YOU CAN CAUSE DAMAGE TO THE STARTER.

(1) Do the test of the engine-control system actuators as follows:

Operation Test (Dry Motor) of the FADEC System Engine Actuators (Cockpit Controls and Panels) ** ON A/C NOT FOR ALL

NOTE: To run the test multiple times, the operator must exit the interactive mode completely and then re-enter. This feature is to help ensure that the starter is not accidentally operated for more than 15 minutes.

(a) Do not operate the starter for more than the extended starter duty-cycle given in the Engine Operation Limits and Guidelines (Ref. AMM TASK 71-00-00-910-803).
(b) If the actuator test operation is more than five minutes, abort the test by setting the ENG/MODE rotary selector switch to NORM.

ACTION	RESULT
1.On the MCDU:	On the MCDU:
Push the FADEC indication key. Push the EEC (1) or (2) channel A key.	The EEC (1) or (2) channel A page comes into view.
Push the ENGINE TESTS key.	The ENGINE TESTS menu comes into view.
Push the ACTUATORS TEST key.	The ACTUATORS TEST menu comes into view.
2.Supply starter AIR.
3.On ENG panel 115VU: Set the ENG/MODE rotary selector switch to the CRANK position.
4.Push the START TEST button.	The TEST screen comes into view.
5.Push the CONFIRM START OF TEST key.	The TEST IN PROGRESS message comes into view. When the test is completed, a TEST OK message or a list of faults comes into view.
6.On overhead control and indicator panel 22VU: Push the ENG MAN START pushbutton switch 1(2) to ON.	On the lower ECAM DU, the symbol for the starter valve opens. Make sure that the engine oil pressure increases. On the upper ECAM DU, the N2 rpm must continuously increase (accelerate) to the maximum air motor speed.
NOTE: Do not operate the starter for more than the fifteen minutes maximum starter time limit.
7.On overhead control and indicator panel 22VU: Release the ENG MAN START pushbutton switch (1) or (2) to OFF.	On the lower ECAM DU the symbol for the starter valve closes.
8.On ENG panel 115VU: Set the ENG/MODE rotary selector switch to NORM.	On the upper ECAM DU, the N2 rpm must decrease to zero rpm.
9.Release the ENG (1) or (2) FUEL PUMP pushbutton switch.	The OFF legend for this switch comes on.
10.Push the RETURN key.	The TEST CLOSE UP message comes into view.
11.Repeat this procedure for the other channel of the FADEC system.

(2) Make a record of any fault messages that you see on the MCDU screen.

NOTE: The table below shows maintenance and ECAM messages which may occasionally be set for reasons which are not necessary for the normal corrective action. The recommended actions for these messages must be done to prevent delays because of corrective actions that are incorrect or not necessary.

Table 1 - Nuisance Fault - Interactive Mode

Software Effectivity	Maintenance Message	ECAM Message	Nuisance Cause	Recommended Action
All software versions:	00000 Failure Detected	-	This message is set when no faults are present during the interactive tests.	No action required. Ignore this message.
All software versions:	ENGXD−0287−FUEL FLTR IMPENDING CLOG	ENG X FUEL FILTER DEGRAD	This message is set during interactive mode engine tests when it is not supposed to be set.	No action required. Ignore this message in the interactive mode. A run-to-idle is necessary to correctly set this fault message.
All software versions:	ENGXD−0633−OIL FLTR IMPENDING BYPASS	ENG X OIL FILTER DEGRAD	This message is set during interactive mode engine tests when it is not supposed to be set.	No action required. Ignore this message in the interactive mode. A run-to-idle is necessary to correctly set this fault message.
POST SB C−73−00−0037A (EEC Software FCS 5) and subsequent:	ENGXD−0693−STARTER SPEED SNSR DISAGREE	N/A	This message is set during this interactive mode engine test when it is not supposed to be.	Ignore this maintenance message in the interactive mode. An engine dry motor and review of the ground scanning report is necessary to confirm this fault.

(3) Use the record of the fault messages to do any maintenance that is necessary.
(4) Stop the pneumatic air supply to the aircraft.
(5) On HYD/FUEL panel 40VU, stop the hydraulic pump.
(6) On overhead circuit-breaker panel 49VU:

Close circuit breakers 1KC1 and 1KC2.

(7) Install protection covers as necessary to prevent damage to the engine.

Subtask 73-21-00-010-066-B ** 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 the ACCESS PLATFORM 1M(3 FT) in position.

Subtask 73-21-00-040-057-B ** ON A/C NOT FOR ALL

C. Deactivation of the Thrust Reverser for Ground 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 ground maintenance (Ref. AMM TASK 78-30-00-040-805).

Subtask 73-21-00-010-067-B ** 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)
452AR.
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
462AR.

Subtask 73-21-00-210-054-B ** ON A/C NOT FOR ALL

E. Examine the engine for leaks.
(1) Do a visual examination of the fuel lines, actuators and components for leaks.
(2) Repair any leaks as necessary.

Subtask 73-21-00-410-062-B ** ON A/C NOT FOR ALL

F. Close Access
(1) Close the thrust-reverser cowl-doors (Ref. AMM TASK 78-36-00-410-802):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
452AR.
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
462AR.

Subtask 73-21-00-440-057-B ** ON A/C NOT FOR ALL

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

Subtask 73-21-00-410-063-B ** ON A/C NOT FOR ALL

H. 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).

5. Close-up
Subtask 73-21-00-860-079-B ** ON A/C NOT FOR ALL

A. Put the aircraft back to its initial configuration.
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Disconnect the HP ground power unit or stop the APU (Ref. AMM TASK 36-12-00-860-803) (Ref. AMM TASK 36-12-00-860-802).
(3) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).
(4) On the upper ECAM DU:

The ENG1(2) LP VALVE OPEN warning message goes out of view.

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

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