On-Wing Reprogramming of the Electronic Control Unit (ECU) [CFMB]

TASK 73-21-60-740-002-A
On-Wing Reprogramming of the Electronic Control Unit (ECU)

ZONE: 400

1. Reason for the Job
To upgrade the ECU software version.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	CAP - PROTECTION
No specific	1	WARNING NOTICE(S)
ALT45200001	1	PORTABLE DATA LOADER
YV68A110	1	PORTABLE DATA LOADER

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
400	POWER PLANT, NACELLES AND PYLONS
FOR [1000EM1] (ENGINE-1)
437AL, 438AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR

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 31-36-00-740-014-A	Update of the Engine Hours and Cycles in the Flight Data Interface and Management Unit (FDIMU)
TASK 31-36-00-740-015-A	Printout of the Engine/APU Hours and Cycles Stored in the Flight Data Interface and Management Unit (FDIMU)
TASK 71-13-00-010-040-B	Opening of the Fan Cowl Doors
TASK 71-13-00-410-040-B	Closing of the Fan Cowl Doors
TASK 73-21-60-740-006-A	Read the LRU Identification Report and the Thrust Reverser Shut-off Valve Status
TASK 73-21-60-740-008-A	Entry of the Engine Serial Number Through MCDU
TASK 73-29-00-710-040-B-02	Operational Test of the FADEC on the Ground (with Engine Non motoring)

3. Job Set-up
Subtask 73-21-60-740-076-A ** ON A/C NOT FOR ALL

A. Do a print-out of the engine hours and cycles (Ref. AMM TASK 31-36-00-740-006) or (Ref. AMM TASK 31-36-00-740-015) and of the LRU IDENTIFICATION page of the MCDU (Ref. AMM TASK 73-21-60-740-006) and keep the print-out with the engine for follow-up.

NOTE: Some tasks will possibly not be applicable depending on whether a Data Management Unit (DMU) or a Flight Data Interface and Management Unit (FDIMU) is installed on the aircraft.

Subtask 73-21-60-840-050-A ** ON A/C NOT FOR ALL

B. Before you reprogram the ECU with new software, verify with Airbus the latest version of ECU/software interchangeability requirements.

Subtask 73-21-60-941-053-A ** ON A/C NOT FOR ALL

C. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) in position to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is OFF.
(b) Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 73-21-60-010-056-A ** ON A/C NOT FOR ALL

D. Open the fan cowl doors (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 73-21-60-740-077-A ** ON A/C NOT FOR ALL

A. On-Wing Reprogramming:

NOTE: For PDL users, refer to paragraph 4.A.(1) and for PMAT users, refer to paragraph 4.A.(2).

(1) When you use a Sundstrand or Demo System PDL like YV68A110 PORTABLE DATA LOADER, do the steps that follow:
(a) Disconnect the engine rating and identification plug from the J14 connector of the ECU.
(b) Disconnect the aircraft cables from the J2, J3 and J4 connectors on the ECU.
(c) Remove the CAP - PROTECTION from the J15 connector. Keep the cap.
(d) You can temporarily disconnect the cable connecting to the J1 connector to get access to the J3 connector.

NOTE: J1 cable must be reconnected to the ECU before programming.

(e) Connect ECU/PDL adapter cable 856A1700 to the receptacle of the PDL.
(f) Before you connect adapter cable 856A1700 to the FADEC:
1 Touch the connector coupling nut of PDL adapter cable 856A1700, checking cables and connectors for accuracy.
2 Hold for one second to dissipate any potential electrical charge in the PDL.
(g) Connect the ECU adapter cable 856A1700 P2, P3, P4, P14 and P15 receptacles to the J2, J3, J4, J14 and J15 receptacles respectively on the ECU to be reprogrammed. You must connect the PC2 to the aircraft harness W2 (J2 harness cable).

NOTE: The ECU/PDL will be powered by aircraft (A/C) 28 volts direct current (VDC) supply via the J1 and J2 connectors.

(h) Connect the ECU/PDL adapter connector PC2 to the disconnected W2 A/C cable (J2 harness cable).
(i) Make sure that the diskette is not installed in the PDL.
(j) Apply power to the FADEC system (push FADEC GND PWR ENG X pushbutton switch to ON).

NOTE: After the ECU is initially powered, there is a five-minute time limit during which the reprogramming procedure can be initiated. Steps 4.A.(1)(j) through 4.A.(1)(l) must be completed within the five-minute time period. After the five-minute time limit has been reached, reprogramming is disabled. After this, power must be cycled on the ECU to re-enable the reprogramming mode.

(k) Turn the PDL on (PDL may also turn on automatically once power is applied to ECU).

NOTE: After the PDL is initialized, the Demo Systems PDL display will read DISK NOT INSERTED. The Sundstrand PDL will display RDY indication.

(l) Identify the new ECU hardware part number per the CFM software Service Bulletin and insert the working copy of the reprogramming software disk, into the PDL. It takes approximately twenty five minutes per channel to reprogram each ECU.

NOTE: The PDL display messages shown in the procedures that follow are from a Demo Systems PDL. If you have a Sundstrand PDL, the display messages will be different in some cases. Below are the Demo Systems messages and their Sundstrand equivalents.

DEMO SYSTEMS	SUNDSTRAND EQUIVALENT
LOAD COMPLETE	COMP (illuminated in green)
TRANSFER FAIL	XFER (illuminated in red)
READ/WRITE FAIL	R/W (illuminated in red)

NOTE: The PDL will automatically install the Operating Program and Non-Volatile Memory (NVM) Software to both channels of the ECU. If successful, the PDL will display LOAD COMPLETE.

NOTE: It takes approximately twenty five minutes per channel to reprogram an ECU. If the reprogramming fails initially, the PDL will attempt to reprogram two more times. It may take an additional three to five minutes before the TRANSFER FAIL lamp illuminates.

NOTE: During the installation procedure, the Demo Systems PDL display will show a numeric value that will count down from 256 to zero for the operation software and from 1150 to zero for the NVM. The countdown sequence will occur twice, first for Channel A and again for Channel B.

(m) If a reprogramming error occurs, the Demo Systems PDL UNIT FAIL READ/WRITE FAIL or TRANSFER FAIL lamp illuminates. Also, the Sundstrand PDL No Load Complete indication will occur after ten minutes. Remove the power from both channels of the ECU. Make sure the cable connections are correct, cycle power OFF to the ECU and PDL, then do paragraph 4.A.(2)(j) through 4.A.(2)(l) again. If additional attempts are made with the same disk, the original NVM removed from the ECU during the first attempt and stored on the disk will be overwritten. To save the original NVM, use a new disk when additional attempts are made (or back-up diskette to separate location).
(n) If LOAD COMPLETE is displayed on the PDL, remove power from the ECU (FADEC GND PWR ENG X pushbutton switches ON legend is out).
(o) Remove the working copy disk from the PDL and keep retrieved data for archive.
(p) After making sure all power is OFF, remove ECU/PDL adapter cable 856A1700 from the W2 (J2 harness cable), J2, J3, J4, J14 and J15 connectors.
(q) Remove the PDL adapter cable from the PDL.
(r) Continue with paragraph 4.A.(3).
(2) When using a Demo Systems PMAT like ALT45200001 PORTABLE DATA LOADER, do the steps that follow:
(a) Disconnect the engine rating and identification plug from the J14 connector of the ECU.
(b) Disconnect the aircraft cables from J2, J3 and J4 on the ECU.
(c) Remove the CAP - PROTECTION from the J15 connector. Keep the cap.
(d) You can temporarily disconnect the cable connecting to J1 to get access to connector J3.

NOTE: J1 cable must be reconnected to the ECU before reprogramming.

(e) Connect ECU/PMAT adapter cable 856A1700 to the receptacle on the PMAT.
(f) Before you connect adapter cable 856A1700 to the FADEC:
1 Touch the connector coupling nut of the PMAT adapter, checking cables and connectors for accuracy.
2 Hold for one second to dissipate any potential electrical charge in the PMAT.
(g) Connect the ECU adapter cable 856A1700 P2, P3, P4, P14 and P15 receptacles to the J2, J3, J4, J14 and J15 receptacles respectively on the ECU to be reprogrammed. You must connect PC2 to aircraft harness W2 (J2 harness cable).

NOTE: With the PMAT there are two ways you can load software to the ECU. The software reprogramming can be accomplished by the use of a floppy disk or the PMAT hard drive. To install software with a floppy disk, follow procedure 4.A.(2).(h). To install software by use of the PMAT hard drive, follow procedure 4.A.(2).(i).

(h) The procedure that follows, must be used when the software installation is accomplished with a floppy disk. Turn on the PMAT with the floppy disk not inserted in the drive:

NOTE: The reprogramming process must be started within five minutes of restoring power to the ECU. After the five-minute limit has been reached, reprogramming is disabled. After this, power must be cycled on the ECU to re-enable the reprogramming mode.

1 Restore power to the FADEC system. Apply power to the FADEC system (push FADEC GND PWR X pushbutton switch to ON).
2 On the PMAT, from the main menu, click the PDL615 DATALOADING button.
3 Insert the floppy disk in the disk drive and select Floppy Drive.
4 Complete the requested information, TYPE, LRU, Part Number, Operator and Tail No. Select START LOAD only after you make sure all of the information is correct.
5 On this screen, if the block count is not decreasing to zero, then the software is not loading. One possible reason for this would be the five-minute window that the ECU allows could have elapsed. If this is the case, select the GO BACK tab to abort the process. When you do this, the program will return to step 1_. The ECU must then be recycled by pressing the FADEC button OFF and ON again. Select the Floppy Drive button as in step 3_ and continue.
6 The PMAT will automatically install the ECU software on the ECU. This can be verified on the PMAT screen when the PWR ON and READY indicators are shown green. This loading process will take approximately twenty five minutes. While loading, as each file is loaded, the block count will decrease accordingly. When the block count reaches zero, loading of the current file is complete. After a successful software load, the PMAT will indicate LOAD COMPLETE:

If the software load is unsuccessful, FADEC GND PWR ENG X push-button switches ON legend is out, check that the cables between the PMAT and the ECU are correctly installed. Do the programming procedure again.

7 After a successful software load, remove power from the ECU (FADEC GND PWR ENG X pushbutton switch ON legend is out).
8 Disconnect the PMAT from the ECU and re-install the rating identification plug in the J14 receptacle of the ECU.
9 Connect the harness cables to the J2, J3 and J4 ECU receptacles.
10 Install the CAP - PROTECTION on the J15 ECU receptacle.
11 Continue with paragraph 4.A.(3).
(i) The procedure that follows must be done when the software installation is done with the PMAT hard drive. Turn the PMAT on with the floppy disk not inserted in the drive:
1 On the PMAT, from the Main Menu, click the PDL615 DATALOADING button.
2 Click the PMAT Mass Storage button.
3 Select the correct TYPE, LRU and Part Number. Make sure that the SELECT BY: MODEL option is chosen. Make sure the correct selections have been made and click on SELECT. Then click on START 615 LOAD.
4 Make sure the information on the screen is correct and fill in the Operator and Tail No. Do not click "START LOAD".

NOTE: The reprogramming process must be started within five minutes of restoring power to the ECU. After the five-minute time limit has been reached, reprogramming is disabled. After this, power must be cycled on the ECU to re-enable reprogramming mode.

5 Restore power to the FADEC system.
6 Click on START LOAD on the PMAT.
7 The PMAT will automatically install the operating system on the ECU. This process will take approximately thirty to fifty minutes. The PMAT will display whether the load was complete or unsuccessful at the end of this time. If the software load is unsuccessful, FADEC GND PWR ENG X push-button switches ON legend is out, make sure that the cables between the PMAT and ECU are correctly installed, then do the programming procedure again.
8 After the software loads successfully, remove power from the ECU (FADEC GND PWR ENG X pushbutton switch ON legend is out).
9 Disconnect the PMAT from the ECU and re-install the rating identification plug in the J14 receptacle of the ECU. Reconnect the cables to the receptacles J3, J4 and J15 ports.
10 Connect the harness cables to the J2, J3 and J4 ECU receptacles.
11 Install the CAP - PROTECTION on the J15 ECU receptacle.
12 Continue with paragraph 4.A.(3).
(3) Restore power to the FADEC system.
(4) Test after reprogramming of the ECU:
(a) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
(b) At the flight deck, generate the LRU IDENTIFICATION FADEC REPORT for the engine you just reprogrammed. Make sure that the ECU software part number corresponds to the new software P/N 2044M38PXX or 2459M16PXX (Ref. AMM TASK 73-21-60-740-006). Before, a combined hardware and software part number was shown on the ECU. Beginning with 5.B.M and for all future software upgrades for the CFM56-5B engine, the ECU hardware part number will remain the same and the software part number is displayed in the LRU Ident report.
(c) Enter the Engine Serial Number (ESN) through the MCDU (Ref. AMM TASK 73-21-60-740-008).
(d) Enter the thrust-reverser hydraulic isolation-valve status through the MCDU (Ref. AMM TASK 73-21-60-740-006).

NOTE: This step must be done only if the Thrust Reverser Shut-Off Valve (T/R SOV) is installed on the aircraft. The ECU default status is:
T/R SOV not installed on the MCDU screen.

NOTE: This procedure must be completed only on one ECU channel (A or B) per engine.

(e) Re-load the engine hours and cycles (Ref. AMM TASK 31-36-00-740-005).

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

(5) Do an operational test of the FADEC system using the non-motoring FADEC system test (Ref. AMM TASK 73-29-00-710-040).
(6) After the FADEC system test, if a fault is present, get access to the troubleshooting report via the menu mode. Make sure that none of the faults below exists and then print the test report:
(a) Fault message: Fault description:

ECU (CPU FAULT): ECU-CPU fault.
ECU (NVM FAULT): ECU-NVM fault.

(7) After reprogramming, re-identify on software label. Or, if upgrading from software version before the software version 5.B.M, install a new ECU hardware identification plate and software label with current ECU software version loaded. The new ECU hardware part number should correspond to the part number specified in the CFM Service Bulletin.

NOTE: Starting with software version 5.B.M, the software changes will change only the software part number, not the ECU hardware part number.

(8) Mark the Service Bulletin identification plate with the number of the CFM software Service Bulletin using a ballpoint pen.

NOTE: Do not remove the old Service Bulletin ID plate. If an old ECU part number appears on the Service Bulletin ID plate, mark a line through the part number with a ballpoint pen and write the new ECU hardware part number per the CFM Service Bulletin, as necessary.

Subtask 73-21-60-860-081-A ** ON A/C NOT FOR ALL

B. Put the aircraft back to its initial configuration.
(1) On the overhead maintenance panel 50VU:
(a) Push the FADEC GND PWR 1(2) pushbutton switch. The ON legend goes off.

Subtask 73-21-60-862-074-A ** ON A/C NOT FOR ALL

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

5. Close-up
Subtask 73-21-60-410-053-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 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 02:59:27 UTC