Fuel System Preservation (Menu Mode) [CFML]

TASK 73-29-00-710-803-A
Fuel System Preservation (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: DO NOT DO THE FUEL SYSTEM PRESERVATION IN A HANGAR OR IN A CLOSED AREA. A LARGE AMOUNT OF HIGHLY FLAMMABLE FUEL VAPORS COME OUT FROM THE ENGINE DURING THIS PROCEDURE AND THERE IS A RISK OF FIRE.

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: - SEE THE APPLICABLE FIGURE FOR WIND LIMIT RESTRICTIONS WHEN THE ENGINE OPERATES.

NATURAL WINDS AND IRREGULAR FORCES FROM SUDDEN GUSTS INCREASE THE DANGEROUS AREA.
DO NOT GO ABOVE OPEN COWLING LIMITATIONS WHEN YOU DO THE TESTS.
THE OPERATOR MUST FULLY KNOW ALL THE OPERATING LIMITS AND PROCEDURES BEFORE THE ENGINE OPERATES.

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 menu mode fuel system preservation function moves the fuel system valves as preservation fluid is added to the engine fuel system as part of the process for preparing the engine for storage. Preservation fluid is supplied to the fuel system inlet instead of fuel. The engine is motored and the master lever is moved to ON for the preservation oil to flow through the fuel system. The fuel system valves are then cycled to coat the servo valves with preservation fluid. The function ends when the master lever is moved to OFF.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 1M(3 FT)
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	WARNING NOTICE(S)

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 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 31-32-00-860-012-A	Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page
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 71-00-00-869-803-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 72-00-00-620-802-A	Preservation of an Engine for a Period of 30 to 365 days
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
Special Functions Menu
Fuel System Preservation Function
Function Terminated
Engine Main Menu

3. Job Set-up
Subtask 73-29-00-620-050-A

A. Do the Operable Engine Preservation On Wing (Menu Mode) (Ref. AMM TASK 72-00-00-620-802).

Subtask 73-29-00-861-070-A

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

Subtask 73-29-00-941-066-A

C. 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.
(c) Put WARNING NOTICE(S) in position to tell persons not to operate:

The ENG/MODE selector switch, and
The ENG/MASTER 1(2) control switch.

(2) 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.
(b) Put a WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2).
(3) Obey the wind limitations and safety precautions during the engine ground operations (Ref. AMM TASK 71-00-00-869-803).
(4) Make sure that the engine inlet and exhaust covers are removed. Make sure that these areas are clear of unwanted objects.
(5) Do a visual check of the fan inlet, temperature sensors, and exhaust areas.

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

(6) Look at the general condition of the fan spinner and fan blades, core exhaust nozzle, Low Pressure Turbine (LPT) and external surfaces of the cowls.
(7) Do a check of the oil quantity. Check the drain ports for fuel, oil, and hydraulic leaks (Ref. AMM TASK 71-00-00-790-805). Make sure that the fuel drained from the engine does not cause a fire.

Subtask 73-29-00-010-064-A

D. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-803):
(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 1M(3 FT) in position.

Subtask 73-29-00-040-057-A

E. Deactivation of the Thrust Reverser System for 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 maintenance (Ref. AMM TASK 78-30-00-040-809).

Subtask 73-29-00-010-065-A

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

Subtask 73-29-00-865-083-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
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/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/ENG2/FADEC B/AND EIU2	4KS2	R41

Subtask 73-29-00-865-104-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
49VU	ENGINE/1 AND 2/IGN/SYS A	1JH	A03
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENGINE 1)
49VU	FUEL/LP VALVE/MOT1/ENG1	1QG	A08
121VU	FUEL/LP VALVE/MOT2/ENG1	3QG	M25
121VU	ENGINE/IGN/ENG1/SYS B	3JH1	P41
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENGINE 2)
49VU	FUEL/LP VALVE/MOT1/ENG2	2QG	A09
121VU	FUEL/LP VALVE/MOT2/ENG2	4QG	M26
121VU	ENGINE/IGN/ENG2/SYS B	3JH2	P42

Subtask 73-29-00-860-096-A

I. Aircraft Maintenance Configuration
(1) On the ENG section of maintenance panel 50VU:

Release the FADEC GND PWR 1(2) pushbutton switch (the ON legend comes on).

(2) After the FADEC is energized, wait ten seconds before you start the test. If you do not wait ten seconds, the interactive mode stops the EEC self-test and this can cause unwanted faults.
(3) On the left or right Multipurpose Control and Display Unit (MCDU), get the SYSTEM REPORT/TEST/ENG page (Ref. AMM TASK 31-32-00-860-012).
(4) On the AIR COND panel 30VU:
(a) Make sure that the APU BLEED pushbutton switch is released (ON legend off).
(b) Install a WARNING NOTICE(S) to tell the persons not to use it.
(5) Put a WARNING NOTICE(S) on the HP ground connector to tell the persons not to pressurize the pneumatic system.
(6) On the left or right MCDU, get the SYSTEM REPORT/TEST ENG MENU PAGE.
(7) Make sure that the landing gear system is not simulated in the flight configuration.
(8) Supply the aircraft pneumatic system from the HP Ground Power Unit (GPU) or the APU (Ref. AMM TASK 36-12-00-860-805) and (Ref. AMM TASK 36-12-00-860-806).

4. Procedure
Subtask 73-29-00-710-072-A

A. General

NOTE: Preservation fluid is supplied to the fuel system inlet instead of fuel. The engine is motored and the Master Lever is moved to ON for the preservation fluid to begin flowing through the fuel system. A period of steady flow occurs first so that fluid can fill the system. Then the fuel system valves are cycled to coat the servo valves with preservation fluid. The function ends when the Master Lever is returned to OFF. Ignitor power is disabled during this function.

(1) Do the menu mode fuel system preservation function.

NOTE: During the test, obey the instructions shown on the Multipurpose Control and Display Unit (MCDU).

NOTE: The Menu Mode Fuel System Preservation function is expected to take approximately 5 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 is set on: CRANK or IGN/START or invalid.
Manual Start Button set 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, dry motor, or wet motor start state
EGT more than 250 deg.C (482.00 deg.F) or invalid
TLA (Throttle Lever Angle) not at idle or invalid
Aircraft in the air
115 V power available to igniters
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 Menu Mode main menu, push the key adjacent to SPECIAL FUNCTIONS (2R).	The SPECIAL FUNCTIONS menu is shown (SCREEN 2).
2.On the SPECIAL FUNCTIONS page (Reference SCREEN 2), select the key adjacent to FUEL SYSTEM PREP (4L).	The FUEL SYSTEM PRESERVATION function start screen is displayed (SCREEN 3).
3.Initiate the function by selecting the settings displayed on SCREEN 3: Set the Start Switch to CRANK. Set the Manual Start button to ON. Set the Master Lever to ON. Press the key adjacent to START THE TEST (5R) to begin the FUEL SYSTEM PRESERVATION function.	The FUEL SYSTEM PRESERVATION SEQUENCE IN PROGRESS screen is displayed (SCREEN 4). Just after setting the Master Lever ON during the test, select the "FUEL" SD page and make sure that the LP valve remain closed. If the LP valve is indicated open, pull the Master Lever back to off otherwise a fuel leak will occur on the engine. NOTE: Once the engine core speed exceeds motoring speed (20%), the ECC slews fuel system valves to multiple positions to circulate preservation fluid. The function takes approximately two minutes to complete. NOTE: If the RETURN key (6L) is selected while the test is in process, or if one of the following conditions occurs, the FUEL SYSTEM PRESERVATION function is aborted and the FUNCTION TERMINATED screen is displayed (SCREEN 6): Start Switch, Manual Start button or Master Lever are changed from ACTION 3. Core speed (N2) is above 55%. Exhaust Gas Temperature (EGT) > 250°C or EGT signals invalid. Throttle Lever Angle (TLA) not at idle or TLA signals invalid. Ignitor power is available. N2 falls below 20% after being above 20%. N2 does not exceed 20% within two minutes after function is initiated. FADEC channel switch requested by standby channel. Aircraft indicates in air. After valve cycling is completed, the PROCEDURE COMPLETE screen is displayed (SCREEN 5).
4.Once the PROCEDURE COMPLETE screen is displayed, restore the cockpit setting as indicated on SCREEN 5: Set the Master Lever to OFF. Set the Manual Start button to OFF. Set the Start switch to NORM. Press the key adjacent to RETURN (6L) to return to the SPECIAL FUNCTIONS menu. If the FUNCTION TERMINATED screen is displayed, restore the cockpit settings as indicated on SCREEN 6: Set the Master Lever to OFF. Set the Manual Start button to OFF. Set the Start switch to NORM. Press the key adjacent to RETURN (6L) to return to the SPECIAL FUNCTIONS menu.	The SPECIAL FUNCTIONS menu is shown (SCREEN 2).

5. Close-up
Subtask 73-29-00-865-106-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
49VU	ENGINE/1 AND 2/IGN/SYS A	1JH	A03
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENGINE 1)
49VU	FUEL/LP VALVE/MOT1/ENG1	1QG	A08
121VU	FUEL/LP VALVE/MOT2/ENG1	3QG	M25
121VU	ENGINE/IGN/ENG1/SYS B	3JH1	P41
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENGINE 2)
49VU	FUEL/LP VALVE/MOT1/ENG2	2QG	A09
121VU	FUEL/LP VALVE/MOT2/ENG2	4QG	M26
121VU	ENGINE/IGN/ENG2/SYS B	3JH2	P42

Subtask 73-29-00-860-097-A

B. Put the aircraft back to its initial configuration.
(1) On the overhead maintenance panel 50VU:

Push the ENG/FADEC GND PWR 1(2) pushbutton switch. The ON legend goes off.

Subtask 73-29-00-862-070-A

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

Subtask 73-29-00-410-067-A

D. 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 73-29-00-440-056-A

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

Subtask 73-29-00-410-068-A

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

[Rev.10 from 2021] 2026.04.01 03:06:14 UTC