Installation of the Electronic Engine Control (EEC) Channel A (upper) [CFML]

TASK 73-21-55-400-802-A
Installation of the Electronic Engine Control (EEC) Channel A (upper)

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

ZONE: 400
FIN: 4601KS1

1. Reason for the Job
A. A two-person alternative method is available for the EEC installation/removal procedures.
(1) A minimum of two persons are necessary to handle the EEC during installation/removal procedures if the jack stand and the EEC adapter support equipment are not used.
B. The weight of the EEC is approximately 37 lb (16.8 kg).
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	WARNING NOTICE(S)
No specific	Torque wrench: range to between 120.75 and 109.25 lbf.in (1.36 and 1.23 m.daN )
No specific	Torque wrench: range to between 250 and 228 lbf.in (2.83 and 2.58 m.daN )
9471M17	3	STAND, JACK - LRU INSTALL/REMOVE
956A1616G01	3	ADAPTER, INSTALL/REMOVE - EEC

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.CP2101)	graphite grease

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
400	POWER PLANT, NACELLES AND PYLONS
FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
437AL, 438AR
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL, 448AR

D. 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 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
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 73-21-50-860-801-A	Programming of the Data Entry Plug (DEP)
TASK 73-29-00-710-802-A	FADEC Test (Menu Mode)
TASK 73-29-00-710-804-A	Weight Configuration (Menu Mode)
TASK 73-29-00-710-808-A	Nacelle Anti-Icing (NAI) Valve Lock Open (Menu Mode)
TASK 73-29-00-740-809-A	Read the LRU Identification Report (Menu Mode)
TASK 73-29-00-740-810-A	Entry of the Engine Serial Number (ESN) (Menu Mode)
EEC Channel A (upper) (PRE CFM SB 73-00-0010)
EEC Channel A (upper) (POST CFM SB 73-00-0010)
EEC Channel A (upper) (POST CFM SB 73-00-0024)

3. Job Set-up
Subtask 73-21-55-941-053-A

A. 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) Make sure that the WARNING NOTICE(S) are 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) Make sure that the WARNING NOTICE(S) is in position to tell persons not to energize FADEC 1(2).

Subtask 73-21-55-010-053-A

B. Get Access
(1) Make sure that the fan cowl doors are open (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) Make sure that the ACCESS PLATFORM 1M(3 FT) is in position.

Subtask 73-21-55-210-050-A

C. Verify the Software Compatibility
(1) Check if the software part number listed on the EEC software label of the EEC to be installed matches the software part number on the EEC software label of the other EEC channel.

NOTE: If the EEC software part numbers are not the same, this will require an EEC on-wing reprogramming after the installation.

4. Procedure
Subtask 73-21-55-420-051-A

WARNING: USE PERSONAL PROTECTION EQUIPMENT. USE THE ENGINE OIL IN A WELL-VENTILATED AREA. ENGINE OIL IS TOXIC.

A. Installation of EEC Channel A

EEC Channel A (upper) (PRE CFM SB 73-00-0010)

PRE CFM SB 73-00-0010 and PRE CFM SB 73-00-0024

NOTE: If the two-person alternative method is used, Para. 4.A.(3), Para. 4.A.(4), Para. 4.A(8) and Para. 4.A.(9) must not be done.

(1) Remove all COVER - PROTECTION and CAP - PROTECTION from the openings, tubes, hoses and connectors.
(2) Make sure that the mating surfaces are clean and clear of unwanted materials.
(3) Install the 956A1616G01 ADAPTER, INSTALL/REMOVE - EEC on EEC channel A (1).
(4) Install the 956A1616G01 ADAPTER, INSTALL/REMOVE - EEC on the 9471M17 STAND, JACK - LRU INSTALL/REMOVE.
(5) Install EEC channel A (1) in the correct position on the mounting brackets (13).
(6) Apply a layer of graphite grease (Material No.CP2101) to the threads of the four bolts (12).
(7) Install the four bolts (12) on the mounting brackets (13) and tighten them with your hand.
(8) Remove the 956A1616G01 ADAPTER, INSTALL/REMOVE - EEC from the 9471M17 STAND, JACK - LRU INSTALL/REMOVE.
(9) Remove the 956A1616G01 ADAPTER, INSTALL/REMOVE - EEC from EEC channel A (1).
(10) TORQUE the four bolts (12) to between 120.75 and 109.25 lbf.in (1.36 and 1.23 m.daN )

.
(11) Install the EEC cooling duct (2) on EEC channel A (1):
(a) Make sure that the mating surfaces are clean and clear of unwanted materials.
(b) Connect the EEC cooling duct (2) to EEC channel A (1).
(c) Install the clamp (11) on the EEC cooling duct (2).
(d) Tighten the screw (10) to attach the EEC cooling duct (2) to the EEC channel A (1).
(12) Connect the electrical connectors to EEC channel A (1):

CAUTION: MAKE SURE THAT THE ELECTRICAL CONNECTORS ARE CLEAN BEFORE YOU DISCONNECT OR CONNECT THEM. CONTAMINATION ON THE ELECTRICAL CONNECTORS CAN CAUSE DAMAGE TO EQUIPMENT.

(a) Connect HJ2A harness electrical connector P2A (9) to EEC channel A (1) receptacle J2.
(b) Connect HJ3A harness electrical connector P3A (8) to EEC channel A (1) receptacle J3.
(c) Connect HJ4A harness electrical connector P4A (7) to EEC channel A (1) receptacle J4.
(d) Connect HJ5A harness electrical connector P5A (6) to EEC channel A (1) receptacle J5.
(e) Connect HJ6A harness electrical connector P6A (5) to EEC channel A (1) receptacle J6.
(f) Connect HJ7 harness electrical connector P7A (4) to EEC channel A (1) receptacle J7.
(g) Connect HJ8A harness electrical connector P8A (3) to EEC channel A (1) receptacle J8.

END OF PRE CFM SB 73-00-0010 and PRE CFM SB 73-00-0024

Subtask 73-21-55-420-053-A

WARNING: USE PERSONAL PROTECTION EQUIPMENT. USE THE ENGINE OIL IN A WELL-VENTILATED AREA. ENGINE OIL IS TOXIC.

B. Installation of EEC Channel A

EEC Channel A (upper) (POST CFM SB 73-00-0010)

POST CFM SB 73-00-0010 and PRE CFM SB 73-00-0024

NOTE: SB 73-0024 introduces the blower-less EEC P08 configuration (PN: 2500M34P08). However, for an EEC P06 (PN: 2500M34P06), the accomplishment of SB 73-0034 for EEC software FCS 6.0 or applicable procedure for a later FCS software version installation along with accomplishment of either of SB 72-0071/SB 72-0191 to remove EEC blowers permits two-way interchangeability between P06 and P08 EECs and makes sure that SB 73-0024 is followed. In other words, if the EEC is of a P06 configuration with FCS 6.0 software upgrade or higher versions installed and blower removal done through either of SB 72-0191/SB 72-0071, the operators can still follow the post SB 73-0024 instructions in section 4.C regardless of if the P08 EEC is installed or not.

NOTE: If the two-person alternative method is used, Para. 4.B.(3), Para. 4.B.(4), Para. 4.B(8) and Para. 4.B.(9) must not be done.

(1) Remove all the COVER - PROTECTION and the CAP - PROTECTION from the openings, tubes, hoses and connectors.
(2) Make sure that the mating surfaces are clean and clear of unwanted materials.
(3) Install the 956A1616G01 ADAPTER, INSTALL/REMOVE - EEC on EEC channel A (1).
(4) Install the 956A1616G01 ADAPTER, INSTALL/REMOVE - EEC on the 9471M17 STAND, JACK - LRU INSTALL/REMOVE.
(5) Install EEC channel A (1) in the correct position on the mounting brackets (13).
(6) Apply a layer of graphite grease (Material No.CP2101) to the threads of the four bolts (12).
(7) Install the four bolts (12) on the mounting brackets (13) and tighten them with your hand.
(8) Remove the 956A1616G01 ADAPTER, INSTALL/REMOVE - EEC from the 9471M17 STAND, JACK - LRU INSTALL/REMOVE.
(9) Remove the 956A1616G01 ADAPTER, INSTALL/REMOVE - EEC from the EEC channel A (1).
(10) TORQUE the four bolts (12) to between 120.75 and 109.25 lbf.in (1.36 and 1.23 m.daN )

.
(11) Install the bolt (14) and the nut (15) that attach the retaining cables (16) and (17) and hand tight.
(12) Install the bolt (14) and the nut (15) that attach the retaining cable (18) and tighten with your hand.
(13) TORQUE the two bolts (14) to between 250 and 228 lbf.in (2.83 and 2.58 m.daN )

.
(14) Install the cap on the J9 connector of the EEC.

NOTE: The cap is attached to the engine.

(15) Install the EEC cooling duct (2) on EEC channel A (1):
(a) Make sure that the mating surfaces are clean and clear of unwanted materials.
(b) Connect the EEC cooling duct (2) to EEC channel A (1).
(c) Install the clamp (11) on the EEC cooling duct (2).
(d) Tighten the screw (10) to attach EEC cooling duct (2) to EEC channel A (1).
(16) Connect the electrical connectors to EEC channel A (1):

CAUTION: MAKE SURE THAT THE ELECTRICAL CONNECTORS ARE CLEAN BEFORE YOU DISCONNECT OR CONNECT THEM. CONTAMINATION ON THE ELECTRICAL CONNECTORS CAN CAUSE DAMAGE TO EQUIPMENT.

Subtask 73-21-55-420-055-A

WARNING: USE PERSONAL PROTECTION EQUIPMENT. USE THE ENGINE OIL IN A WELL-VENTILATED AREA. ENGINE OIL IS TOXIC.

C. Installation of EEC Channel A

EEC Channel A (upper) (POST CFM SB 73-00-0024)

POST CFM SB 73-00-0024

NOTE: SB 73-0024 introduces the blower-less EEC P08 configuration (PN: 2500M34P08). However, for an EEC P06 (PN: 2500M34P06), the accomplishment of SB 73-0034 for EEC software FCS 6.0 or applicable procedure for a later FCS software version installation along with accomplishment of either of SB 72-0071/SB 72-0191 to remove EEC blowers permits two-way interchangeability between P06 and P08 EECs and thereby makes sure that SB 73-0024 is followed. In other words, if the EEC is of a P06 configuration with FCS 6.0 software upgrade or higher versions installed and blower removal done through either of SB 72-0191/SB 72-0071, the operators can still follow the post SB 73-0024 instructions in section 4.C regardless of if the P08 EEC is installed or not.

NOTE: If the two-person alternative method is used, Para. 4.C.(3), Para. 4.C.(4), Para. 4.C.(8) and Para. 4.C.(9) must not be done.

(1) Remove all the COVER - PROTECTION and the CAP - PROTECTION from the openings, tubes, hoses and connectors.
(2) Make sure that the mating surfaces are clean and clear of unwanted materials.
(3) Install the 956A1616G01 ADAPTER, INSTALL/REMOVE - EEC on EEC channel A (1).
(4) Install the 956A1616G01 ADAPTER, INSTALL/REMOVE - EEC on the 9471M17 STAND, JACK - LRU INSTALL/REMOVE.
(5) Install EEC channel A (1) in the correct position on the mounting brackets (13).
(6) Apply a layer of graphite grease (Material No.CP2101) to the threads of the four bolts (12).
(7) Install the four bolts (12) on the mounting brackets (13) and tighten them with your hand.
(8) Remove the 956A1616G01 ADAPTER, INSTALL/REMOVE - EEC from the 9471M17 STAND, JACK - LRU INSTALL/REMOVE.
(9) Remove the 956A1616G01 ADAPTER, INSTALL/REMOVE - EEC from EEC channel A (1).
(10) TORQUE the four bolts (12) to between 120.75 and 109.25 lbf.in (1.36 and 1.23 m.daN )

.
(11) Install the bolt (14) and the nut (15) that connect the retaining cables (16) and (17), and tighten them with your hand.
(12) Install the bolt (14) and the nut (15) that connects the retaining cable (18), and tighten them with your hand.
(13) TORQUE the two bolts (14) to between 250 and 228 lbf.in (2.83 and 2.58 m.daN )

.
(14) Connect the cap on connector J9 of the EEC which is tied to the engine.
(15) Connect the electrical connectors to the EEC channel A (1):

CAUTION: MAKE SURE THAT THE ELECTRICAL CONNECTORS ARE CLEAN BEFORE YOU DISCONNECT OR CONNECT THEM. CONTAMINATION ON THE ELECTRICAL CONNECTORS CAN CAUSE DAMAGE TO EQUIPMENT.

Subtask 73-21-55-861-050-A

D. Energize the aircraft electrical circuits

CAUTION: FAILURE TO POWER CYCLE THE EEC TWICE AFTER EEC INSTALLATION, EEC SOFTWARE LOADING, DATA ENTRY PLUG REPLACEMENT, OR DATA ENTRY PLUG PROGRAMMING CAN RESULT IN AN EGT INCREASE DURING THE NEXT ENGINE CYCLE.

(1) The EEC has to be cycle powered twice (Ref. AMM TASK 24-41-00-861-002).

Subtask 73-21-55-869-055-A

E. Do the EIS start procedure (upper and lower ECAM DU) (Ref. AMM TASK 31-60-00-860-001).

Subtask 73-21-55-740-051-A

F. Enter the Engine Parameters:

CAUTION: IF YOU REPROGRAM THE TWO CHANNELS, PRINT THE INSTALLED FAN-BALANCE WEIGHTS AND ENTER THEM AGAIN IN THE EEC. IF YOU DO NOT OBEY THIS INSTRUCTION, THE ENGINE FAN-BALANCE WEIGHTS WILL NOT AGREE WITH THE WEIGHTS SAVED IN THE EEC MEMORY. THIS CAN CAUSE INCORRECT FAN-TRIM-BALANCE CALCULATION AND A FAN UNBALANCE.

(1) Enter the engine serial number via the menu mode (Ref. AMM TASK 73-29-00-740-810) on the EEC channel you just installed.

NOTE: Make sure that the "ENGINE" SN displayed on the screen is the same as the one written on the engine data plate.

(2) Enter the Nacelle Anti-Icing (NAI) lockout configuration via the menu mode (Ref. AMM TASK 73-29-00-710-808) only if the print-out from the removed EEC indicates that the Pressure Regulating and Shut-Off Valve (PRSOV) 1 was locked open.
(3) If the EEC A installation is part of a dual channel replacement, meaning both EEC A and EEC B are replaced, enter the fan balance weights configuration via the menu mode (Ref. AMM TASK 73-29-00-710-804). To be done on any one channel after both channels have been installed.

Subtask 73-21-55-710-051-A

G. Do these tests and tasks:
(1) Do the operational FADEC test on channel A with the engine non-motoring (Ref. AMM TASK 73-29-00-710-802).
(2) Read the Line Replaceable Unit (LRU) identification report (menu mode) on both channels to confirm that the data matches on both channels (Ref. AMM TASK 73-29-00-740-809). Read the data that comes on the Multipurpose Control and Display Unit (MCDU) screen and check for consistency with the actual engine configuration, with the LRU identification report print-out of the removed channel and with the other EEC channel:
(a) Engine thrust rating:
1 This input is available on the engine data plate.

NOTE: The engine data plate is located on the left side of the fan frame.

(b) Verify the EEC Control software part number (SW1):
1 The Part Number (PN) is available on the EEC software identification plate located on the EEC.
2 Make sure that the Control software PN is the same on the other channel. If the Control software PNs are not the same, an on-wing reprogramming will be required.

NOTE: Make sure that the interchangeability of the engines EEC Control software standards is correct. Refer to the applicable service bulletin/Power Plant IPC (PPIPC).

(c) Verify the OMAP software part number (SW2):
1 Make sure that the OMAP Software PN (SW2) is the same on both EEC channels. In some cases, the OMAP SW part numbers between channels can differ by a trailing "0". If the only difference is the trailing "0", it is permitted.
(d) Verify N1 trim configuration:
1 The N1 trim level (0 through 7) is available on the engine data plate.
(e) Verify the BUMP option: must read "Y or N".
(f) Verify the ENG CONFIG: Refer to Table 2 - "Hardware Configuration by Pin Configuration" (Ref. AMM TASK 73-21-50-860-801). The ENG CONFIG value should read the same as the value mentioned in the column "Hardware Configuration" depending on the engine configuration mentioned on the engine data plate located on the left side of the fan frame.
(g) Verify High Pressure Turbine (HPT) deterioration: must read "Y or "N" based on the LRU identification report print-out of the removed EEC. If the print-out is not available, refer to the criteria defined in the Data Entry Plug (DEP) reprogramming task (Ref. AMM TASK 73-21-50-860-801).
(h) Make sure that the PHM software part number (SW3) is correct.
1 Make sure that the PHM software PN (SW3) is the same on both EEC channels.
(i) Aircraft Type

Subtask 73-21-55-869-050-A

H. Do the EIS stop procedure (upper and lower ECAM DUs) (Ref. AMM TASK 31-60-00-860-002).

Subtask 73-21-55-862-052-A

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

5. Close-up
Subtask 73-21-55-410-051-A

A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(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 access platform(s).
(4) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 03:05:03 UTC