Installation of the Electronic Control Unit (ECU) [CFMI]

TASK 73-21-60-400-001-A
Installation of the Electronic Control Unit (ECU)

CAUTION: MAKE SURE THAT THE ECU STANDARDS INSTALLED ARE CORRECT. SOME ECU 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	PLIERS - NOSE, SOFT, LONG
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 37 and 33 lbf.in (0.42 and 0.37 m.daN )
No specific	Torque wrench: range to between 68.2 and 55.8 lbf.in (0.77 and 0.63 m.daN )
No specific	Torque wrench: range to between 150 and 135 lbf.in (1.70 and 1.53 m.daN )
No specific	Torque wrench: range to between 200 and 180 lbf.in (2.26 and 2.03 m.daN )
No specific	Torque wrench: range to between 300 and 270 lbf.in (3.39 and 3.05 m.daN )

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.CP2101)	graphite grease
(Material No.CP8001)	lockwire 0.032 in. (0.8 mm) dia.

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
FOR [1000EM1] (ENGINE-1)
437AL, 438AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR

D. 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 31-36-00-740-005-A	Update of the Engine Hours and Cycles in the DMU after Engine or DMU Replacement
TASK 31-36-00-740-014-A	Update of the Engine Hours and Cycles in the Flight Data Interface and Management Unit (FDIMU)
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 34-10-00-860-004-A	Inertial Reference (IR) Alignment-Procedure
TASK 34-10-00-860-004-A-02	Inertial Reference (IR) Alignment-Procedure to do a Check of the Links between each Flight Management and Guidance Computer (FMGC) and the three Air Data/Inertial Reference Units (ADIRUs)
TASK 70-21-00-918-001-A	Seals (Preformed Packings and O-rings) and Gaskets
TASK 71-13-00-010-040-A	Opening of the Fan Cowl Doors
TASK 71-13-00-410-040-A	Closing of the Fan Cowl Doors
TASK 73-21-60-720-040-A	Functional Test of the Electronic Control Unit (ECU)
TASK 73-21-60-740-009-A	Entry of the Engine Serial Number through the MCDU
TASK 73-21-60-740-025-A	Entry of the Thrust Reverser Hydraulic Shut-off Valve Status through the MCDU
ECU
ECU
ECU Removal/Installation
ECU
ECU Removal/Installation
LRU Identification ** ON A/C NOT FOR ALL
LRU Identification ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 73-21-60-860-050-A ** ON A/C NOT FOR ALL

A. Aircraft Maintenance Configuration
(1) On the center pedestal, on the ENG panel 115VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the engine.
(2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a WARNING NOTICE(S) is in position to tell persons not to energize the FADEC 1(2).

Subtask 73-21-60-010-051-A ** ON A/C NOT FOR ALL

B. Make sure that the fan cowl doors are open: (Ref. AMM TASK 71-13-00-010-040)
(1) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(2) FOR [1000EM2] (ENGINE-2)
447AL 448AR

4. Procedure
Subtask 73-21-60-420-050-A ** ON A/C NOT FOR ALL

A. Installation of the Electronic Control Unit (310)
(1) Install the ECU (310) to the fan frame mounting bracket as follows:
(a) Apply a thin layer of graphite grease (Material No.CP2101) to the bolts (80).
(b) Install the ECU (310) in the mounting brackets with electrical receptacles down and interface cooling air connections to the forward position.
(c) Tighten the bolts (80). TORQUE the bolts to between 68.2 and 55.8 lbf.in (0.77 and 0.63 m.daN )

.
(2) Install the cooling air flange (330) as follows:
(a) Remove the blanking plugs from the port of the interface cooling air on the forward side of the ECU (310).
(b) Do an inspection of the gasket (520) (Ref. AMM TASK 70-21-00-918-001).
(c) Install the air flange (330) and the gasket (520) with the bolts (320).
(d) TORQUE the bolts (320) to between 37 and 33 lbf.in (0.42 and 0.37 m.daN )

.
(3) Install the interface cooling air hoses (66) as follows:
(a) Remove the blanking caps from the interface cooling air hose (66) and the inlet (60) and outlet (70) tubes of the interface cooling air connections.
(b) Install the interface cooling hoses (66) to the air inlet (60) of the air flange (330) on the forward side of the ECU (310).
(c) Tighten clamps (65).
(4) Install the air pressure tubes as follows:

CAUTION: USE TWO WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS:

ONE WRENCH TO HOLD THE UNION, AND
ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT.

THIS PREVENTS DAMAGE TO THE PARTS.

CAUTION: DURING INSTALLATION, MAKE SURE THAT THE PS3 LINE DOES NOT TOUCH THE LOWER STARTER DUCT OR OTHER PARTS IN THIS AREA. IF IT DOES, CHAFING OF THE PS3 HOSE CAN OCCUR.

(a) Connect the PS12 hose (50) and the PS3 hose (30), and if the engine has PMUX, install the PS13 (20) and P25 (40) as follows:
1 TORQUE the PS12 (50) coupling nuts to between 150 and 135 lbf.in (1.70 and 1.53 m.daN )

.
2 TORQUE the PS3 (30) coupling nuts to between 300 and 270 lbf.in (3.39 and 3.05 m.daN )

.
3 TORQUE the P25 (40) and PS13 (20) coupling nuts to between 200 and 180 lbf.in (2.26 and 2.03 m.daN )

.
4 Safety the coupling nuts with CP8001lockwire 0.032 in. (0.8 mm) dia..
5 If the engine is Non-PMUX, make sure the PS13 (25) and the P25 (45) caps are installed.
(5) Install the electrical connectors as follows:
(a) Remove the blanking caps from the electrical connectors and J1 thru J14 receptacles.
(b) Do a visual inspection of the J1 thru J14 receptacles. Make sure they are not blocked and there are no bent pins.

CAUTION: ALIGN THE ELECTRICAL PINS AND KEYWAYS SO THEY CORRECTLY ENGAGE THE ECU RECEPTACLE. IF THE PINS AND KEYWAYS ARE NOT CORRECTLY ALIGNED, DAMAGE TO THE ECU RECEPTACLE AND/OR ECU CAN OCCUR.

CAUTION: MAKE SURE THERE IS SUFFICIENT CABLE TO ENGAGE THE ELECTRICAL CONNECTOR SO THERE IS NO FORCE PUT ON THE BACKSHELL. DO NOT PULL CABLES THROUGH CABLE CLAMPS THAT ARE TIGHT. DAMAGE TO THE CABLES AND CONNECTORS CAN OCCUR.

(c) Attach the J1 thru J13 electrical connectors to the correct receptacle of the ECU (310) as follows:
1 Start with connector J13 and end with connector J1. Align the keyway to the electrical connector with the receptacle key in the ECU (310). Carefully push the connector into the receptacle.
2 Tighten the coupling ring by hand until the connector is fully seated. if necessary, carefully center the backshell to the connector as you tighten the coupling ring.
3 Tighten the electrical connector by hand plus one-eighth of a turn. If necessary, use PLIERS - NOSE, SOFT, LONG.

PRE SB (CFM56-5) 72-169 or POST SB (CFM56-5) 75-048
(d) Make sure the J15 connector on the ECU (310) has a protective cap.

POST SB (CFM56-5) 72-169 or PRE SB (CFM56-5) 75-048
(e) Install bleed bias J15 (100) connector on the ECU (310) receptacle.

END OF SB (CFM56-5) 72-169 and SB (CFM56-5) 75-048
(f) Install the identification connector (140) into the J14 receptacle (90). Tighten with your hand plus one-eighth of a turn. If necessary, use soft-nose pliers.

Subtask 73-21-60-942-050-A ** ON A/C NOT FOR ALL

B. Remove the warning notices from the panels 115VU and 50VU.

Subtask 73-21-60-861-050-A ** ON A/C NOT FOR ALL

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

Subtask 73-21-60-860-051-A ** ON A/C NOT FOR ALL

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

Subtask 73-21-60-860-071-A ** ON A/C NOT FOR ALL

E. Prepare for Tests.
(1) On the left or right MCDU, do this check:
(a) Get access to the screen of the SYSTEM REPORT/TEST ENG (Ref. AMM TASK 31-32-00-860-012).
(b) Push the line key adjacent to the FADEC1(2) A(B): The ENGINE MAIN MENU page comes into view.
(c) Do a functional test of the ECU (Ref. AMM TASK 73-21-60-720-040).
(d) Push the line key adjacent to the LRU IDENT indication: the LRU IDENTIFICATION ENGINE 1(2) CHANNEL A(B) page comes into view

LRU Identification ** ON A/C NOT FOR ALL

NOTE: The LRU identification check is only required on one channel of the ECU A or B.

(e) Do the following tests.

Subtask 73-21-60-710-055-A ** ON A/C NOT FOR ALL

F. Test of Engine configuration.
(1) Read the data that comes on the MCDU screen and check for consistency with the actual engine configuration:
(a) "LRU PART NO" (ECU Part Number):

The P/N is available on the ECU identification plate.

(b) "ENGINE FAMILY" (Engine thrust rating and type):

These inputs are available on the engine name plate.

NOTE: The engine thrust rating must be the same as on opposite engine and consistent with the Aircraft Model.

"0" = Not installed/Not used,
"1" = Denver Bump,
"2" = General Bump,
"3" = Air France Bump (overboost).

(d) "PMUX INSTALLED" option:

PMUX engine (4 hoses connected to the ECU) must read "Y"
ECU ** ON A/C NOT FOR ALL
Non PMUX engine (2 hoses connected to the ECU) must read "N"
ECU ** ON A/C NOT FOR ALL
.

Subtask 73-21-60-710-056-B ** ON A/C NOT FOR ALL

G. Entry Engine serial number
(1) Do the entry of the "ENGINE" Serial Number through the MCDU Menu according to instructions of the procedure (Ref. AMM TASK 73-21-60-740-009).

NOTE: For CFM56-5A1 or CFM56-5A1/F or CFM56-5A3: If a pre Service Bulletin 72-518 engine identification connector is installed (P/N 320-586-XXX-0), the ESN (Engine Serial Number) is automatically entered into the ECU memory.

(a) Make sure the "ENGINE" S/N displayed on the screen is the same as the one written on the Engine name plate.

Subtask 73-21-60-740-064-A ** ON A/C NOT FOR ALL

H. Update the engine hours and cycles (Ref. AMM TASK 31-36-00-740-005) or (Ref. AMM TASK 31-36-00-740-014).

NOTE: Some tasks will possibly not be applicable depending on whether a DMU or an FDIMU is installed on the aircraft.

Subtask 73-21-60-710-057-C ** ON A/C NOT FOR ALL

I. Check TRSOV status
(1) Check that the TRSOV installation status matches the aircraft configuration.
(a) "N" must be displayed if the thrust reverser shut-off valve is not installed.
(b) Change the installation status through the MCDU menu if required according to instructions of the procedure (Ref. AMM TASK 73-21-60-740-025).

Subtask 73-21-60-710-058-A ** ON A/C NOT FOR ALL

J. Test for operate the aircraft in actual CAT III conditions.
(1) If you operate the aircraft in actual CAT III conditions, do these tests:

Make sure that there is no CAT 3 DUAL INOP message on the lower ECAM DU with FADEC GND PWR 1 & 2 pushbutton switches (maintenance panel 50VU) pushed (ON legends on) and 3 IR'S aligned (Ref. AMM TASK 34-10-00-860-004),
Do the operational test of the LAND CAT III Capability (Ref. AMM TASK 22-97-00-710-001).

Subtask 73-21-60-862-050-A ** ON A/C NOT FOR ALL

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

5. Close-up
Subtask 73-21-60-860-052-A ** ON A/C NOT FOR ALL

A. Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).

Subtask 73-21-60-410-050-A ** ON A/C NOT FOR ALL

B. 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 71-13-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(3) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 02:56:46 UTC