Actuators Test (Menu Mode) [CFML]

TASK 73-29-00-740-802-A
Actuators Test (Menu Mode)

WARNING: MAKE SURE THAT ALL ENGINE OPERATING AREAS ARE AS CLEAN AS POSSIBLE. ALL RAMPS, TAXIWAYS, RUNWAYS AND OTHER OPERATING AREAS MUST BE VERY CLEAN TO PREVENT BAD DAMAGE TO THE ENGINE, AIRCRAFT AND PERSONS IN THE AREA.

WARNING: DO NOT TRY TO STOP THE FAN FROM TURNING BY HAND. THIS CAN CAUSE INJURY TO THE PERSONS AND DAMAGE TO THE EQUIPMENT.

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

WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

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

ZONE: 400

1. Reason for the Job
The actuators test will verify the operation of the fuel driven actuator servo loops. This includes electrical and position faults. The actuators and servo-valves tested are the FMV, PMV, VSV, VBV, TBV, FRV and SBV BAI Valve. The motoring test will slew the electro-hydraulic controlled actuators fully open and fully closed while the engine is dry-motoring. Upon completion of the test, the test results screen is displayed on the MCDU showing any faults detected during the test.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
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 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 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 36-12-00-860-805-A	Pressurization of the Bleed System with the APU
TASK 36-12-00-860-806-A	Pressurization of the Bleed System through the HP Ground Connector
TASK 71-00-00-790-805-A	Fuel or Hydraulic or Oil Leakage Limits
TASK 71-00-00-869-802-A	Wind Limitations During Engine Ground Operations
TASK 71-00-00-869-803-A	Safety Precautions During Engine Ground Operations
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 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
Actuators Test (Menu Mode)

3. Job Set-up
Subtask 73-29-00-869-079-A

A. Preparation for Test
(1) Obey the wind limitations and safety precautions during engine ground operations (Ref. AMM TASK 71-00-00-869-802) and (Ref. AMM TASK 71-00-00-869-803).
(2) Make sure that the engine inlet and exhaust covers are removed. Make sure that these areas are clear of unwanted objects.
(3) Do a visual check of the fan inlet, temperature sensor and exhaust areas.

NOTE: Make sure that the engine inlet, inlet lip, fan, spinner and fan exhaust duct are clear of ice or snow. Melt the ice or snow if the fan does not turn freely.

(4) Look at the general condition of the fan spinner and fan blades, core exhaust nozzle, LPT and external surfaces of the cowls.
(5) Do a check of the oil quantity (Ref. AMM TASK 12-13-79-610-805).
(6) Do a check of the drain ports for fuel, oil and hydraulic leaks (Ref. AMM TASK 71-00-00-790-805).
(7) Remove covers from TAT, AOA, and PITOT probes.

Subtask 73-29-00-941-081-A

B. 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.

Subtask 73-29-00-010-076-A

C. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-803) if required:
(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 2M (6 FT) - ADJUSTABLE in position.

Subtask 73-29-00-040-063-A

D. Deactivation of the Thrust Reverser System for Maintenance if required:

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 maintenance (Ref. AMM TASK 78-30-00-040-809).

Subtask 73-29-00-010-077-A

E. Open the thrust reverser cowl-doors (Ref. AMM TASK 78-36-00-010-806) if required:
(1) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
451AL 452AR
(2) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
461AL 462AR

Subtask 73-29-00-861-091-A

F. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).

Subtask 73-29-00-865-071-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
49VU	ENGINE/1 AND 2/IGN/SYS A	1JH	A03
49VU	L/G/LGCIU/SYS1/NORM	1GA	C09
121VU	HYDRAULIC/LGCIU/SYS2	2GA	Q35
121VU	HYDRAULIC/LGCIU/SYS1/GRND SPLY	52GA	Q34
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENGINE 1)
49VU	ENGINE/1/FADEC A/AND EIU 1	2KS1	A04
121VU	ENGINE/IGN/ENG1/SYS B	3JH1	P41
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R40
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENGINE 2)
49VU	ENGINE/2/FADEC A/AND EIU 2	2KS2	A05
121VU	ENGINE/IGN/ENG2/SYS B	3JH2	P42
121VU	ENGINE/ENG2/FADEC B/AND EIU2	4KS2	R41

Subtask 73-29-00-865-099-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENGINE 1)
49VU	ENGINE/1/HP FUEL SOV	1KC1	A01
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENGINE 2)
49VU	ENGINE/2/HP FUEL SOV	1KC2	A02

Subtask 73-29-00-869-080-A

I. Continue to Prepare for Test

CAUTION: MAKE SURE THAT THE HYDRAULIC RESERVOIR PRESSURE IS IN THE CORRECT OPERATION RANGE BEFORE YOU START THE ENGINE. THE HYDRAULIC FLUID IS NECESSARY TO LUBRICATE THE HYDRAULIC PUMPS THAT THE ENGINE OPERATES.

(1) Supply the aircraft pneumatic system from the HP ground power unit or the APU (Ref. AMM TASK 36-12-00-860-806) or (Ref. AMM TASK 36-12-00-860-805).
(2) On the lower ECAM display unit:
(a) Get the HYDRAULIC page.
(b) Make sure that the pressure of the Green reservoir for engine 1 (Yellow reservoir for engine 2) is correct.
(c) Make sure that the reservoir fluid level is correct.
(3) Make sure that the engine 1(2) pump is serviceable (on the HYD/FUEL panel 40VU, the OFF legend of the ENG 1(2) PUMP pushbutton switch must be off).
(4) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).
(5) On the ENG section of maintenance panel 50VU:
(a) Release the FADEC GND PWR 1(2) pushbutton switch (the ON legend comes on).

4. Procedure

CAUTION: DO NOT RUN THE ENGINE IF THE FUEL INLET PRESSURE IS NOT POSITIVE (THE FUEL IS NECESSARY TO LUBRICATE THE ENGINE FUEL PUMP AND THE FMU AND THUS PREVENT DAMAGE).

CAUTION: MAKE SURE THAT THE ENG/MASTER 1(2) CONTROL SWITCH (ON THE PANEL 115VU) IS SET TO OFF BEFORE YOU START THE FUEL PUMPS.

Subtask 73-29-00-740-051-A

WARNING: MAKE SURE THAT THE ENGINE IS CLEAN AND CLEAR OF PERSONS AND TOOLS OR OTHER ITEMS. THE ENGINE WILL CRANK AND ENGINE ACTUATORS WILL MOVE DURING THE TEST. IF YOU DO NOT OBEY THIS PRECAUTION, INJURY OR DAMAGE CAN OCCUR.

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

A. Actuators Test (Menu Mode)

NOTE: During the test, obey the instructions shown on the MCDU.

NOTE: The Trouble Shooting Manual (TSM) procedures for the applicable faults will tell you which EEC channel to set during this test.

NOTE: The actuators test takes approximately four minutes to complete.

NOTE: The EEC will not enter the menu mode (interactive mode) after an enquire command from the CFDS (Centralized Fault Display System) when any of the following conditions are set:

N2 more than ten percent or invalid
Rotary selector on CRANK or IGN/START or invalid
Manual Start Button on ON or invalid
TLA (Throttle Lever Angle) not at idle or invalid
Aircraft in the air
MASTER lever ON or invalid
BITE command code input label invalid.

NOTE: The EEC will abort a running test or special function when any of the following conditions becomes set:

N2 more than 45 percent or invalid
Engine state not starting or off
Engine not in default or dry motor start state
TLA (Throttle Lever Angle) not at idle or invalid
Aircraft in the air
MASTER lever ON or invalid
N2 drops below 20 percent after going above 20 percent
N2 more than 20 percent for two minutes during crank or start phase
You enter in the interactive mode of the other channel.

ACTION	RESULT
1.On the MCDU ENG page: Push the key adjacent to the ACTUATORS TEST. NOTE: If the RETURN key is selected on the MCDU during a running test or N2 more than 55 percent or invalid or engine state not off or engine not in default start state or EGT more than 250 deg.C (482.00 deg.F) or invalid or TLA not at idle or invalid or aircraft in the air or MASTER lever ON or invalid or cross channel has been set to channel switch request flag, the EEC will abort the test, and display the FUNCTION TERMINATED screen. The test will need to be started again.	The Actuators Test Start page is shown.
2.Do the dry crank: A.Make sure the LP valve is open. Select the "FUEL" SD page for confirmation. B.On the ENG panel 115VU: Set the ENG/MODE/CRANK/NORM/IGN/START selector switch to CRANK. C.On the lower ECAM display unit: The ENGINE page comes into view. Make sure that the available air pressure is between 25 psi (1.72 bar) 55 psi (3.79 bar). D.On the overhead CTL & IND panel 22VU: Push the ENG/MAN START 1(2) pushbutton switch. NOTE: During cold weather, large oil pressure surges can occur. The ON legend of this pushbutton switch comes on. E.On the lower ECAM display unit, on the ENGINE page: The symbol for the starter valve is in the open position. NOTE: Make sure that: The engine rotates The oil pressure indication is positive.
3.Start the actuators test on the MCDU:
Select: PUSH BUTTON TO START THE TEST.	The Actuators Test in Progress page is displayed.
	The EEC slews the actuators to verify proper feedback through full range of operation. If no faults are recorded, the MCDU screen will display TEST OK (screen 3) or, if faults are detected, the MCDU screen will display FAULT REPORT page containing the engine number, channel letter, flight leg number (00), date, time, ATA number and description of the fault (screen 4). NOTE: A maximum of three faults per page will be displayed and a maximum of 12 faults will be saved.
Select the RETURN key.	TEST COMPLETE will be displayed on.
4.Stop the dry-crank. A.On the ENG panel 115VU: Set the ENG/MODE/CRANK/IGN/START selector switch to NORM. B.On the overhead CTL & IND panel 22VU: Release the ENG/MAN START 1(2) pushbutton switch.	The ON legend of this pushbutton switch goes off. On the lower ECAM display unit, on the ENGINE page: The symbol for the starter valve is in the closed position. Engine motoring stops and engine coast-down begins.
Select the RETURN key again to exit the Engine Tests Main Screen	The MCDU home page comes into view.

Subtask 73-29-00-865-100-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENGINE 1)
49VU	ENGINE/1/HP FUEL SOV	1KC1	A01
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENGINE 2)
49VU	ENGINE/2/HP FUEL SOV	1KC2	A02

5. Close-up
Subtask 73-29-00-862-089-A

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

Subtask 73-29-00-869-081-A

B. Put the aircraft back to its initial configuration.
(1) Stop the pneumatic supply to the aircraft.
(a) Disconnect the HP ground power unit or stop the APU.
(2) If necessary, make sure that the probes are cold and install the covers that you removed from the TAT, AOA and PITOT probes.
(3) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(4) On the ENG section of maintenance panel 50VU:
(a) Push the FADEC GND PWR 1(2) pushbutton switch (the ON legend goes off).

Subtask 73-29-00-410-079-A

C. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust-reverser cowl-doors (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 73-29-00-440-062-A

D. Do the reactivation of the thrust reverser after maintenance (Ref. AMM TASK 78-30-00-440-809).

Subtask 73-29-00-410-080-A

E. Close Access
(1) Remove the access platform(s).
(2) 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
(3) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 03:06:01 UTC