W DOC AIRBUS | AMM A320F

Installation of the Electronic Engine Control (EEC) [IAE]

TASK 73-22-34-400-010-A
Installation of the Electronic Engine Control (EEC)

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
CAUTION: MAKE SURE THAT THE EEC STANDARDS INSTALLED ARE CORRECT. SOME EEC STANDARDS CANNOT BE INTERMIXED ON A SAME AIRCRAFT.
FIN: 4000KS ** ON A/C NOT FOR ALL
1. Reason for the Job
Self explanatory
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
SAFETY CLIP - CIRCUIT BREAKER
No specific
AR
WARNING NOTICE(S)
No specific
Torque wrench: range to between 35.2 and 28.8 lbf.in (0.40 and 0.33 m.daN ) T
No specific
Torque wrench: range to between 105 and 85 lbf.in (1.19 and 0.96 m.daN ) T
No specific
Torque wrench: range to between 100 and 90 lbf.in (1.13 and 1.02 m.daN ) T
No specific
Torque wrench: range to between 150 and 142 lbf.in (1.70 and 1.60 m.daN ) T
No specific
Torque wrench: range to between 181 and 168 lbf.in (2.05 and 1.90 m.daN ) T
No specific
Torque wrench: range to between 220 and 180 lbf.in (2.49 and 2.03 m.daN ) T
No specific
Torque wrench: range to between 199 and 182 lbf.in (2.25 and 2.06 m.daN ) T
No specific
Torque wrench: range to between 212 and 195 lbf.in (2.40 and 2.20 m.daN ) T
No specific
Torque wrench: range to between 239 and 221 lbf.in (2.70 and 2.50 m.daN ) T
No specific
Torque wrench: range to between 265 and 248 lbf.in (2.99 and 2.80 m.daN ) T
IAE1R19416
1
WRENCH-SPECIAL 4 AND 8 SLOT CONNECTOR, LIFTING
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.V02-141)
corrosion resistant steel lockwire
(Material No.V10-077)
lubricant (engine oil)
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
FOR [1000EM1] (ENGINE-1)
437AL, 438AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR
 D. Expendable Parts
FIG.ITEM
DESIGNATION
IPC-CSN
8
SEAL RING
AIPC 73-22-34-80-020
11
SEAL RING
AIPC 73-22-34-80-040
14
SEAL RING
AIPC 73-22-34-80-060
21
SEAL RING
AIPC 73-22-34-80-060
18
SEAL RING
AIPC 73-22-34-80-090
 E. Referenced Information
REFERENCE
DESIGNATION
TASK 22-97-00-710-001-A
Operational Test of the LAND CAT III Capability
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 31-36-00-740-014-A
Update of the Engine Hours and Cycles in the Flight Data Interface and Management Unit (FDIMU)
TASK 70-23-11-911-013-A
General Torque Tightening Techniques
TASK 70-23-13-911-010-A
Procedures for the Installation of Preformed Packings
TASK 70-23-15-912-010-A
Connection of Electrical Connectors
TASK 70-40-11-911-010-A
Installation of the Tab-type Key Washers
TASK 70-40-11-911-012-A
General Instructions for the Uses of Lockwire
TASK 71-00-00-710-022-B
Test No. 6: Electronic Engine Control (EEC) System Idle Test
TASK 71-13-00-010-010-A
Opening of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 71-13-00-410-010-A
Closing of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 73-22-00-710-040-A
Operational Test of the FADEC SYSTEM on the Ground
TASK 73-22-00-860-010-A
Change of the Inhibition Status of the Thrust Reverser System
TASK 73-22-34-710-040-A
Operational Test of the EEC
F Electronic Engine Control
F Ground Cable
3. Job Set-up
Subtask 73-22-34-865-062-A ** ON A/C NOT FOR ALL
WARNING: BEFORE YOU OPEN PHC CIRCUIT BREAKERS 2DA1(2,3), OPEN PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND 5DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE: - THE PROBES WILL BECOME TOO HOT. - THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.
WARNING: OPEN THE ANTI-ICE/PROBES CIRCUIT BREAKERS 1DA1 (2), 3DA1 (2,3), 4DA1 (2,3) AND 5DA1 (2,3) BEFORE YOU OPEN CIRCUIT BREAKERS 2KS1, 2KS2 AND 4KS1, 4KS2. IF YOU DO NOT OBEY THIS SEQUENCE, THE PROBES WILL BECOME TOO HOT. THIS CAN CAUSE INJURY TO MAINTENANCE PERSONNEL AND/OR DAMAGE TO EQUIPMENT.
A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUANTI ICE/PROBES/AOA/14DA1D04
49VUANTI ICE/PROBES/PITOT/13DA1D02
122VUANTI ICE/PROBES/2/TAT1DA2Y15
122VUANTI ICE/PROBES/2/PITOT3DA2Y14
122VUANTI ICE/PROBES/2/AOA4DA2Y13
122VUANTI ICE/PROBES/2/STATIC5DA2Y11
122VUANTI ICE/PROBES/3/PITOT3DA3Z16
122VUANTI ICE/PROBES/3/AOA4DA3Z15
122VUANTI ICE/PROBES/3/STATIC5DA3Z14
122VUANTI ICE/PROBES/1/STATIC5DA1Z13
122VUANTI ICE/PROBES/1/TAT1DA1Z12
Subtask 73-22-34-865-063-A ** ON A/C NOT FOR ALL
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUANTI ICE/PROBES/PHC/12DA1D03
122VUANTI ICE/PROBES/PHC/32DA3Y16
122VUANTI ICE/PROBES/PHC/22DA2Y12
Subtask 73-22-34-865-054-A ** ON A/C NOT FOR ALL
WARNING: OPEN CIRCUIT BREAKERS 2KS1 AND 2KS2 AFTER YOU OPEN THE IGNITION CIRCUIT BREAKERS. IF NOT, THE CONTINUOUS IGNITION SYSTEM WILL BE ACTIVATED.
C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
FOR FIN: 1KS1 (EIU1)
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
121VUENGINE/IGN/ENG1/SYS B3JH1P41
121VUENGINE/IGN/ENG1/SYS A BAT2JH1P39
FOR FIN: 1KS2 (EIU2)
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
121VUENGINE/IGN/ENG2/SYS B3JH2P42
121VUENGINE/IGN/ENG2/SYS A BAT2JH2P40
Subtask 73-22-34-865-059-A ** ON A/C NOT FOR ALL
D. Open, safety and tag this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
FOR FIN: 1KS1 (EIU1)
49VUENGINE/1/FADEC A/AND EIU 12KS1A04
121VUENGINE/ENG1/FADEC B/AND EIU 14KS1R41
FOR FIN: 1KS2 (EIU2)
49VUENGINE/2/FADEC A/AND EIU 22KS2A05
121VUENGINE/ENG2/FADEC B4KS2Q40
Subtask 73-22-34-860-050-A ** ON A/C NOT FOR ALL
E. 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).
Subtask 73-22-34-010-051-A ** ON A/C NOT FOR ALL
F. Make sure that the fan cowls are open: (Ref. AMM TASK 71-13-00-010-010)
   (1) FOR [1000EM1] (ENGINE-1)
437AL 438AR
   (2) FOR [1000EM2] (ENGINE-2)
447AL 448AR
Subtask 73-22-34-420-051-A ** ON A/C NOT FOR ALL
G. Prepare the replacement Electronic Engine Control (EEC)
F Electronic Engine Control ** ON A/C NOT FOR ALL
   (1) Examine the outside and inside of unions (9), (12) and (19) as well as adapters (15) and (22) for evidence of debris. If debris is present, remove it with nitrogen or clean dry air at 75 psi.
   (2) Install each AIPC 73-22-34-80-020 SEAL RING (8), AIPC 73-22-34-80-040 SEAL RING (11), AIPC 73-22-34-80-060 SEAL RING (14), AIPC 73-22-34-80-090 SEAL RING (18) and AIPC 73-22-34-80-060 SEAL RING (21) onto its applicable adapter or union (Ref. AMM TASK 70-23-13-911-010).
NOTE: Do not apply lubricants to the seal rings (8), (11), (14), (18) and (21).
   (3) Install the adapters (15) and (22) and the unions (9), (12) and (19) into their applicable openings in the bottom of the EEC.
NOTE: Do not apply lubricants to the threads of the adapters (15) and (22) or the unions (9), (12) and (19).
   (4) TORQUE the union (9) to between 212 and 195 lbf.in (2.40 and 2.20 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
   (5) TORQUE the union (12) to between 265 and 248 lbf.in (2.99 and 2.80 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
   (6) TORQUE the adapters (15) and (22) to between 239 and 221 lbf.in (2.70 and 2.50 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
   (7) TORQUE the union (19) to between 181 and 168 lbf.in (2.05 and 1.90 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
Subtask 73-22-34-630-050-A ** ON A/C NOT FOR ALL
H. Remove caps from all openings.
4. Procedure
Subtask 73-22-34-420-050-A ** ON A/C NOT FOR ALL
A. Installation of the Electronic Engine Control (EEC)

As an alternative to the tool P/N IAE1R19416, a strap wrench with a drive hole to accommodate torque wrench can be used.
NOTE: The "Visual mating indication" is another option to ensure the matting connector and the receptacle are fully engaged. In this case, any strap wrench such as BT-BS-611, Glenair TG-70 (or similar), insulated-jawed pliers Glenair TG-69 (or similar) can be used to ensure the "witness" band located on the receptacle is fully covered (not visible) when mated with the connector.
   (1) Install the EEC
WARNING: BE CAREFUL DURING THE REMOVAL OR INSTALLATION OF THE EEC. THE EEC WEIGHS APPROXIMATELY 41LBS (18,6KG). IF IT FALLS, IT CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
     (a) Install the EEC on the mount brackets (1) and (3).
     (b) Apply V10-077lubricant (engine oil) to the threads of the bolts (2) which hold the EEC to the brackets.
     (c) Install the washers (7) on the bolts.
     (d) Install the bolts and the washers.
     (e) TORQUE the bolts to between 220 and 180 lbf.in (2.49 and 2.03 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
     (f) Apply V10-077lubricant (engine oil) to the threads of the bolt (5) which holds the ground cable to the EEC.
     (g) Install the bolt through the ground cable (6) into the EEC. Examine EEC ground strap ends to ensure strap is securely fastened at the two crimping locations.
F Ground Cable ** ON A/C NOT FOR ALL
NOTE: Replace the strap if wire crimp is found disconnected or moveable.
     (h) TORQUE the bolt to between 105 and 85 lbf.in (1.19 and 0.96 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
   (2) Install the vent plug assembly
     (a) Apply clean V10-077lubricant (engine oil), to the threads of the vent plug assembly (17).
     (b) Install the vent plug assembly (17) into the vent plug port on the EEC.
     (c) TORQUE the vent plug assembly (17) to between 100 and 90 lbf.in (1.13 and 1.02 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
     (d) Safety the vent plug assembly with corrosion resistant steel lockwire (Material No.V02-141) (Ref. AMM TASK 70-40-11-911-012).
   (3) Connect the electrical harness connectors
     (a) Remove the plastic caps from the electrical harness connectors.
     (b) Connect the 4000KS-J1 to -J5 and 4000KS-J7 to J11 connectors to their mating receptacles on the EEC (Ref. AMM TASK 70-23-15-912-010)
     (c) TORQUE the connectors to between 35.2 and 28.8 lbf.in (0.40 and 0.33 m.daN ) T. Use the IAE1R19416 WRENCH-SPECIAL 4 AND 8 SLOT CONNECTOR, LIFTING (Ref. AMM TASK 70-23-11-911-013).
     (d) For V2500-A1 engines which incorporated SBE 70-0056:
  • Close and secure the hinged fireshield access panels.
   (4) Connect the data entry plug assembly
     (a) Remove the plastic cap from the data entry plug assembly connector (24).
     (b) Connect the data entry plug assembly connector to the mating receptacle on the rear side of the EEC. (Ref. AMM TASK 70-23-15-912-010)
     (c) TORQUE the connector to between 35.2 and 28.8 lbf.in (0.40 and 0.33 m.daN ) T. Use the IAE1R19416 WRENCH-SPECIAL 4 AND 8 SLOT CONNECTOR, LIFTING (Ref. AMM TASK 70-23-11-911-013).
     (d) For V2500-A1 engines which incorporated SBE 70-0056:
  • Close and secure the hinged fireshield access panels.
   (5) Connect the hoses to the adapters and unions on the bottom of the EEC
     (a) Connect the hose nuts (10), (13), (16), (20) and (23) to their applicable adapters or unions.
     (b) TORQUE the hose nuts (10) and (13) to between 199 and 182 lbf.in (2.25 and 2.06 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
     (c) TORQUE the hose nuts (16), (20) and (23) to between 150 and 142 lbf.in (1.70 and 1.60 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
     (d) Safety the adapters, the unions and the hose nuts with corrosion resistant steel lockwire (Material No.V02-141) (Ref. AMM TASK 70-40-11-911-010).
5. Close-up
Subtask 73-22-34-410-050-A ** ON A/C NOT FOR ALL
A. Close Access
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010):
     (a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
     (b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
   (3) Remove the WARNING NOTICE(S).
Subtask 73-22-34-865-066-A ** ON A/C NOT FOR ALL
WARNING: MAKE SURE THAT YOU CLOSE CIRCUIT BREAKERS 2KS1 AND 2KS2 BEFORE YOU CLOSE THE IGNITION CIRCUIT BREAKERS. IF YOU DO NOT, THE CONTINUOUS IGNITION SYSTEM WILL BE ACTIVATED.
WARNING: CLOSE THE CIRCUIT BREAKERS 2KS1, 2KS2 AND 4KS1, 4KS2 BEFORE YOU CLOSE THE ANTI-ICE/PROBES CIRCUIT BREAKERS 1DA1 (2), 3DA1 (2,3), 4DA1 (2,3) AND 5DA1 (2,3). IF YOU DO NOT OBEY THIS SEQUENCE, THE PROBES CAN BECOME HOT. THIS CAN CAUSE INJURY TO MAINTENANCE PERSONNEL AND/OR DAMAGE TO EQUIPMENT.
B. Remove the safety clips and tags and close these circuit breakers in this sequence:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
FOR FIN: 1KS1 (EIU1)
49VUENGINE/1/FADEC A/AND EIU 12KS1A04
121VUENGINE/ENG1/FADEC B/AND EIU 14KS1R41
FOR FIN: 1KS2 (EIU2)
49VUENGINE/2/FADEC A/AND EIU 22KS2A05
121VUENGINE/ENG2/FADEC B4KS2Q40
Subtask 73-22-34-865-056-A ** ON A/C NOT FOR ALL
C. Remove the safety clips and tags and close these circuit breakers in this sequence:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
FOR FIN: 1KS1 (EIU1)
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
121VUENGINE/IGN/ENG1/SYS A BAT2JH1P39
121VUENGINE/IGN/ENG1/SYS B3JH1P41
FOR FIN: 1KS2 (EIU2)
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
121VUENGINE/IGN/ENG2/SYS A BAT2JH2P40
121VUENGINE/IGN/ENG2/SYS B3JH2P42
Subtask 73-22-34-865-064-A ** ON A/C NOT FOR ALL
WARNING: CLOSE THE PHC CIRCUIT BREAKERS 2DA1(2,3) BEFORE YOU CLOSE THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND 5DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE, THE PROBES WILL BECOME TOO HOT. THIS CAN CAUSE INJURY TO MAINTENANCE PERSONNEL AND/OR DAMAGE TO EQUIPMENT.
D. Remove the safety clips and tags and close these circuit breakers in this sequence:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUANTI ICE/PROBES/PHC/12DA1D03
122VUANTI ICE/PROBES/PHC/22DA2Y12
122VUANTI ICE/PROBES/PHC/32DA3Y16
Subtask 73-22-34-865-065-A ** ON A/C NOT FOR ALL
E. Remove the safety clips and tags and close these circuit breakers in this sequence:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
122VUANTI ICE/PROBES/1/TAT1DA1Z12
122VUANTI ICE/PROBES/2/TAT1DA2Y15
49VUANTI ICE/PROBES/PITOT/13DA1D02
122VUANTI ICE/PROBES/2/PITOT3DA2Y14
122VUANTI ICE/PROBES/3/PITOT3DA3Z16
49VUANTI ICE/PROBES/AOA/14DA1D04
122VUANTI ICE/PROBES/2/AOA4DA2Y13
122VUANTI ICE/PROBES/3/AOA4DA3Z15
122VUANTI ICE/PROBES/1/STATIC5DA1Z13
122VUANTI ICE/PROBES/2/STATIC5DA2Y11
122VUANTI ICE/PROBES/3/STATIC5DA3Z14
Subtask 73-22-34-861-050-A ** ON A/C NOT FOR ALL
F. Do these steps.
   (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
   (2) On the maintenance panel 50VU, push then release the ENG/FADEC GND PWR/1(2) pusbutton switch. The ON legend comes on.
Subtask 73-22-34-740-051-B ** ON A/C NOT FOR ALL
G. Update the engine hours and cycles (Ref. AMM TASK 31-36-00-740-014).
Subtask 73-22-34-869-050-A ** ON A/C NOT FOR ALL
H. On the left or right MCDU, get the SYSTEM REPORT/TEST page. (Ref. AMM TASK 31-32-00-860-012)
Subtask 73-22-34-710-060-A ** ON A/C NOT FOR ALL
I. For POST SBE 73-0222: If the Thrust Reverser system is deactivated as per AMM Task 78-30-00-040-013, change the inhibition status of the Thrust Reverser System (Ref. AMM TASK 73-22-00-860-010).
Subtask 73-22-34-710-050-B ** ON A/C NOT FOR ALL
J. Perform the following tests:
   (1) Do the test:
ACTION
RESULT
1.On the MCDU, push the line key adjacent to the ENG indication.
  • The SYSTEM REPORT/TEST ENG menu page comes into view.
2.Push the line key adjacent to the FADEC 1(2) A(B) indication.
  • The ENGINE 1(2) MAIN MENU page comes into view.
3.Push the line key adjacent to the TROUBLE SHOOTING indication.
  • The FADEC 1(2) A(B) TROUBLE SHOOTING MENU page comes into view.
4.Push the line key adjacent to the EEC CONFIGURATION indication.
  • The FADEC 1(2) EEC CONFIGURATION page comes into view.
5.Read the data that come on the MCDU (EEC P/N, ENGINE RATING, EPR MODIFIER and ENGINE SERIAL NUMBER) to make sure they are the same as written on the EEC, data entry plug and engine identification plates using the following engine ratings comparison table.
For SCN 16 software and below:
Make sure that the bump status shown on MCDU
(BUMP LEVEL=00: not installed; BUMP LEVEL=01: installed) is correct.
For SCN 17 software and above:
Make sure that the bump status shown on MCDU
(BUMP AVAILABLE=NO: not installed; BUMP AVAILABLE=YES: installed) is correct.
NOTE: If engine serial number displayed on MCDU is in the range between 13191 and 15000, then add 5000 to this value to get the actual engine serial number.

6.On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view.
7.Stop the MCDU.

   (2) If A/C is operated in actual CAT III conditions, perform a land test (Ref. AMM TASK 22-97-00-710-001).
   (3) Do an Operational Test of the EEC (Ref. AMM TASK 73-22-34-710-040) and Operational Test of the Fadec System on the Ground (Ref. AMM TASK 73-22-00-710-040) and Electronic Engine Control (EEC) System Idle Test (Ref. AMM TASK 71-00-00-710-022).
Subtask 73-22-34-710-050-C
J. Perform the following tests:
   (1) Do the test:
ACTION
RESULT
1.On the MCDU, push the line key adjacent to the ENG indication.
  • The SYSTEM REPORT/TEST ENG menu page comes into view.
2.Push the line key adjacent to the FADEC 1(2) A(B) indication.
  • The ENGINE 1(2) MAIN MENU page comes into view.
3.Push the line key adjacent to the TROUBLE SHOOTING indication.
  • The FADEC 1(2) A(B) TROUBLE SHOOTING MENU page comes into view.
4.Push the line key adjacent to the EEC CONFIGURATION indication.
  • The FADEC 1(2) EEC CONFIGURATION page comes into view.
5.Read the data that come on the MCDU (EEC P/N, ENGINE RATING, EPR MODIFIER and ENGINE SERIAL NUMBER) to make sure they are the same as written on the EEC, data entry plug and engine identification plates using the following engine ratings comparison table.
Make sure that the bump status shown on MCDU (BUMP AVAILABLE = NO: not installed; BUMP AVAILABLE = YES: installed) is correct.

6.On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view.
7.Stop the MCDU.

   (2) If A/C is operated in actual CAT III conditions, perform a land test (Ref. AMM TASK 22-97-00-710-001).
   (3) Do an Operational Test of the EEC (Ref. AMM TASK 73-22-34-710-040) and Operational Test of the Fadec System on the Ground (Ref. AMM TASK 73-22-00-710-040) and Electronic Engine Control (EEC) System Idle Test (Ref. AMM TASK 71-00-00-710-022).
Subtask 73-22-34-710-055-B ** ON A/C NOT FOR ALL
K. Engine Ratings Comparison Table
MCDU (EEC CONFIGURATION Menu)
ENGINE DATA PLATE (Engine Model)
22000 lbs
V2522
24000 lbs
V2524
27000 lbs
V2527
27000E lbs
V2527E
27000M lbs
V2527M
30000 lbs
V2530
33000 lbs
V2533
Subtask 73-22-34-862-050-A ** ON A/C NOT FOR ALL
L. Put the aircraft back to its initial configuration.
   (1) On the maintenance panel 50VU push the ENG/FADEC GND PWR/1(2) pushbutton switch. The ON legend goes off.
   (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).
[Rev.10 from 2021] 2026.04.01 03:00:53 UTC
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