Leonardo S.p.A.

Via Giovanni Agusta, 520

21017 Cascina Costa di Samarate (VA) Italy
Tel.: +39 0331 229111 - Fax: +39 0331 229605/222595

BOLLETTINO TECNICO N° 139-394

The technical content of this document is approved
under the authority of DOA nr. EASA.21J.005
DATE August 25, 2016
REV. /

Compliance with
this bulletin is: COMPANY MANDATORY

SUBJECT
CIRCULAR FORCE (CF) ACTIVE VIBRATION CONTROL SYSTEM (AVCS)
SOFTWARE

REASON

To perform software update on the AVCS Circular Force Generators (CFG).

HELICOPTERS AFFECTED

AW139 helicopters S/N 31580, S/N 31585 and S/N 31593.

COMPLIANCE

Within twelve (12) months or twelve hundreds (1200) flight hours since receipt of this
Bollettino Tecnico, whichever comes first.

DESCRIPTION

This Bollettino Tecnico has been issued to update the CFG monitor lane embedded
software to the last available release.

An appropriate entry should be made in the aircraft log book upon accomplishment.
If ownership of aircraft has changed, please, forward to new owner.

Page 1 of 22
B.T. 139-394

REQUIRED MANPOWER

To comply with this Bollettino Tecnico thirty-two (32) Maintenance Man-Hours (MMH)
are deemed necessary.
Maintenance Man-Hours are based on hands-on time and may vary with personnel
and facilities available.

WARRANTY

Owners/Operators who comply with the instructions of this Bollettino Tecnico no later
than the applicable date in the “Compliance” section will be eligible to receive
REQUIRED MATERIALS on free of charge basis, except for Consumable Materials &
Special Tools.

NOTE: Customers who fail to comply with the instructions in this Bollettino Tecnico
before the compliance date are not eligible for the aforementioned special
policy.

Please Issue relevant M.M.I.R. form ( (M)aintenance (M)alfunction (I)nformation

(R)eport ) to your Warranty Administration Dpt.

NOTE: WRM will also include RETURN MATERIAL AUTHORIZATION (RMA) code
and the core part must be shipped within fifteen (15) calendar days after the
shipment of the replacement part from the designated LHD facility. If the
core is not received within fifteen (15) calendar days, Customer will be
invoiced and the Customer Spare Part account will be debited for the price
of the replacement part and the action will be considered closed.

REQUIRED MATERIALS

There are no materials required to comply with this Bollettino Tecnico.

Page 2 of 22
 B.T. 139-394

In order to avoid a long AOG, the first four upgraded CFG will be supplied in advance
by LHD. The removed CFG must be returned to LHD for updating and then will be
sent back again to the Customer for installation on the next aircraft.

The last four CFG removed will be kept by LHD and not returned to the Customer (to
replace the first Shipset sent in advance).

SPECIAL TOOLS

The following special tools are required for compliance with this Bollettino Tecnico:

P/N DESCRIPTION Q.TY NOTE

Commercial DC External Power bench (28 VDC) AR Local supply

Refer also to ITEP for the special tools required to comply with the AMP DM
referenced in the compliance instructions and to Annex A and Annex B.

WEIGHT AND BALANCE CHANGES

N.A.

REFERENCES

 AW139 Aircraft Maintenance Publication (AMP)

 AW139 Illustrated Tools and Equipment Publication (ITEP)

PUBLICATIONS AFFECTED

 AW139 Aircraft Wiring Data Publication (AWDP)

Page 3 of 22
B.T. 139-394

COMPLIANCE INSTRUCTIONS
1. Prepare the helicopter for a safe ground maintenance. Disconnect the battery and all
the electrical power sources and/or the external power supply. Refer to AMP, see
DM n° 39-A-00-20-00-00A-120A-A.
2. Open/remove the access door 183AL and the access panels 141AL, 142AR, 151AL
and 152AR. Refer to AMP, see DM n° 39-A-06-41-00-00A-010A-A.
3. Remove CFG A483. Refer to AMP, see DM n° 39-A-18-33-03-00A-520A-K.
4. Remove CFG A475. Refer to AMP, see DM n° 39-A-18-33-04-00A-520A-K.
5. Remove CFG A478. Refer to AMP, see DM n° 39-A-18-33-05-00A-520A-K.
6. Remove CFG A474. Refer to AMP, see DM n° 39-A-18-33-06-00A-520A-K.

NOTE
Please refer to your usual contact point in Leonardo
Helicopters Material Services, in order to receive
relevant information for PO issuance of the
replacement items and for dispatch instructions.

7. Send the circular force generators to LHD in order to perform the software upgrade.
8. With reference to figures 1 and 2, modify AVCS control panel connections as
described in the following procedure:
8.1. Remove the AVCS control panel (1) from the interseat console (2). Refer to
AMP, see DM n° 39-U-18-33-01-00A-520A-A.
8.2. Gain access to PL163P1 connector (3) and stow cable D310B24-S
according to figure 2 wiring diagram.

NOTE
At following steps 9 thru 12 install circular force
generators with upgraded software.

NOTE
Do not perform the checks required by the AMP DM
after the installation of each circular force generator.

Page 4 of 22
 B.T. 139-394

Perform them one time only as required by steps 13

thru 18.

9. Install CFG A483. Refer to AMP, see DM n° 39-A-18-33-03-00A-720A-K.

10. Install CFG A475. Refer to AMP, see DM n° 39-A-18-33-04-00A-720A-K.
11. Install CFG A478. Refer to AMP, see DM n° 39-A-18-33-05-00A-720A-K.
12. Install CFG A474. Refer to AMP, see DM n° 39-A-18-33-06-00A-720A-K.
13. Do the bonding check of the circular-force generators. Refer to AMP, see DM n° 39-
A-18-33-00-00A-369A-K.
14. Do the continuity check of the CAN bus of the CF-AVCS. Refer to AMP, see DM n°
39-A-18-33-00-00A-365A-K.
15. Perform the following checks on AVCS connectors:
15.1. Connect the following connectors: A483P12 (CFG #0) and A473P4 (AVCS
Central Controller).
15.2. Disconnect the connector A478P12 (CFG #5).
15.3. Make sure there is:
 120±10Ω between the pins 2 and 1 of the connector A478P12;
 More than 10kΩ between the pins 2 and 15 of the connector A478P12;
 More than 10kΩ between the pins 1 and 15 of the connector A478P12.
15.4. Connect the connector A478P12 to the CFG #5 (A478).
15.5. Disconnect the connector A483P12 (CFG #0).
15.6. Make sure there is:
 120±10Ω between the pins 2 and 1 of the connector A483P12;
 More than 10kΩ between the pins 2 and 15 of the connector A483P12;
 More than 10kΩ between the pins 1 and 15 of the connector A483P12.
15.7. Disconnect the connector A473P4 (AVCS Central Controller).
15.8. Connect the connector A483P12 (CFG #0).
15.9. Make sure there is:
 120±10Ω between the pins 45 and 49 of the connector A473P4;
 More than 10kΩ between the pins 45 and 51 of the connector A473P4;
 More than 10kΩ between the pins 49 and 51 of the connector A473P4.
15.10. Connect the AVCS Central Controller mating connector A473P4.

Page 5 of 22
B.T. 139-394

15.11. Make sure there is:

 120±10Ω between the pins 11 and 12 of the connector PL163P1;
 More than 10kΩ between the pins 11 and 13 of the connector PL163P1;
 More than 10kΩ between the pins 12 and 13 of the connector PL163P1.
16. Install the AVCS control panel. Refer to AMP, see DM n° 39-A-18-33-01-00A-720A-
K.
17. Load the command lane software in the circular-force generators and perform the
software loading check of the AVCS according to annex A.
18. Do the configuration check of the circular-force generators according to annex B.
19. Close/install the access door 183AL and the access panels 141AL, 142AR, 151AL
and 152AR. Refer to AMP, see DM n° 39-A-06-41-00-00A-010A-A
20. Return the helicopter to flight configuration and record for compliance with this
Bollettino Tecnico on the helicopter logbook.
21. Send the attached compliance form to the following email box:
CSE.AW139.AW@leonardocompany.com. As an alternative, gain access to My
Communications section on Leonardo AW Customer Portal and compile the
“Technical Bulletin Application Communication”.

Page 6 of 22
 B.T. 139-394

Figure 1

Page 7 of 22
B.T. 139-394

Figure 2

Page 8 of 22
ANNEX A B.T. 139-394

ANNEX A
SOFTWARE LOADING CHECK

Page 9 of 22
B.T. 139-394 ANNEX A

REQUIRED TOOLS
The following tools are required:
 DC external power bench (28V DC);
 CAN-to-USB adaptor NI USB-8473;
 single CAN Termination Cable NI 192017-02;
 laptop with Windows 7 OS and the Maintenance / Master User Interface software
P/N SW-11081-1, Version 1.0.0.4251 or subsequent (provided on media P/N NVX-
2294-1) installed;
 AVCS Central Controller SW P/N 3G1830VA0100;
 AVCS CFG Command Lane SW P/N 3G1830VS0100.

REQUIRED CONDITIONS
Connect the external electrical power to the helicopter. Refer to AMP DM n° 39-A-12-41-
00-00A-730A-A.

PROCEDURE
1. Check that the following CBs are pushed IN:

CB Nomenclature System
MAU 1 PRI PWR MAU 1 Power Supply (Primary)
MAU 2 PRI PWR MAU 2 Power Supply (Primary)
MAU 1 AUX PWR MAU 1 Power Supply (Secondary)
MAU 2 AUX PWR MAU 2 Power Supply (Secondary)
(DISPLAY) PFD PLT Pilot PFD
(DISPLAY) PFD PLT CONTR Pilot Display Controller
(DISPLAY) MFD PLT Pilot MFD
(DISPLAY) PFD CPLT Copilot PFD
(DISPLAY) PFD CPLT CONTR Copilot Display Controller
(DISPLAY) MFD CPLT Copilot MFD
EXT PWR External Power Door
2. Ensure that the AVCS Central Controller (A473), Control Panel (PL163), CFGs and
accelerometers are connected to their relevant mating connectors.
3. Check that all the AVCS CBs installed (among those listed in the Table 3) are pulled
OUT, except for the “AVCS OMNI CONTR” CB (CB484), which shall be pushed IN.

Page 10 of 22
ANNEX A B.T. 139-394

4. Copy the content of the media for the SW P/N 3G1830VA0100 in a local folder on
your computer. Note that all the files in the media containing the SW P/N
3G1830VA0100 shall be copied into the same folder.
5. Connect a laptop (with the Maintenance User Interface software P/N SW-11081-1
Version 1.0.0.4251 or subsequent installed) to the USB port of the CAN-to-USB
adaptor.
6. Connect the Single CAN Termination Cable to the front connector (PL163P2) of the
AVCS Control Panel (PL163) on one side and to the CAN-to-USB adaptor on the
other side.
7. Launch the Maintenance SW from the Start menu as shown in the Figure A1. The
start up screen will appear as represented in the Figure A2.
8. On the Main Page select the “Connection Settings” option (Figure A3). The
Connection Settings dialog will pop up (Figure A4).
9. Ensure that the “CAN Port” field (of the connection settings pop up) corresponds to
the USB port of the laptop connected to the Single CAN Termination Cable.
10. Select 1M in the “Baud Rate” field of the connection settings pop up.
11. Select the SW-11076-1.a2l file in the “A2L Path” field of the connection settings pop-
up. Note that this file shall be located in the local folder where you have copied the
content of the media disk for the SW P/N 3G1830VA0100 (refer to the step 4).
12. Press the “SAVE” pushbutton on the connection settings pop-up.
13. Press the “Connect” button on the Main Page of the Maintenance UI. The pop up in
Figure A5 will be displayed. Press “Retry with CBL”. The Maintenance UI shall switch
to “Connected (CBL)”, as shown in Figure A6. This may take approximately 20
seconds.
14. Perform the CFG COMMAND LANE SW LOADING as follows:
14.1. Push IN all the AVCS CBs installed (among those listed in the Table 3)
except for the “AVCS OMNI PANEL” CB (CB283), which shall be pulled
OUT.
14.2. Set the “ON/OFF” switch on the AVCS Control Panel (PL163) to the ON
position.
14.3. Extract the content of the zip file provided on the same media of the SW P/N
3G1830VS0100 in a local folder on your computer.

Page 11 of 22
B.T. 139-394 ANNEX A

14.4. Select the “Upload” Option on the Main Page of the Maintenance UI and then
select “Application”.
14.5. Browse to select the file SW-11079-1.hex you have copied in a local folder.
14.6. Select all the CFGs installed (from CFG 0 to CFG 7) among “Devices to
Program” in the Upload File target selection window.
14.7. Push the PROGRAM pushbutton.
14.8. If you are programming blank units, the programming process will prompt you
if you want to connect to the CFG CBL after the Application connection fails.
In order to continue the SW load press the “Retry with CFG CBL” pushbutton.
Repeat this step for each CFG to be programmed.
14.9. Wait until the SW load is completed (the load is finished when the
Accelerometers and Actuator Peak Level statuses appear again).
14.10. On the Main Page select the “Upload” Option, then select “PDIF”.
14.11. Browse to select the file SW-11078-1.hex file you have copied in a local
folder.
14.12. Repeat the steps 14.6 and 14.7.
14.13. Wait until the SW load is completed.
15. Perform the SOFTWARE LOAD CHECK as follows:
15.1. Press the “Disconnect” button on the Main Page of the Maintenance UI.
Close the Maintenance UI.
15.2. Set the “ON/OFF” switch on the AVCS control panel (PL163) to the OFF
position.
15.3. Pull OUT the “AVCS OMNI CONTR” (CB484) Circuit Breaker. Set the
“ON/OFF” switch on the AVCS control panel (PL163) to the ON position.
15.4. Push IN the “AVCS OMNI CONTR” Circuit Breaker (CB484).
15.5. Launch the Maintenance User Interface (UI) software. If necessary, restore
the connection settings as described in steps 8 thru 13.
15.6. Press the “Connect” button on the Main Page of the Maintenance UI. Ensure
it switches to “Connected” and is highlighted in green.
15.7. On the main page of the Maintenance UI push the “System Version Check”
pushbutton.
15.8. Ensure that the following data related to the CC “App PartNo”, the CC “App
CRC” and the CC “App Version” are displayed:

Page 12 of 22
ANNEX A B.T. 139-394

 App Part No: SW-11076-1;

 App CRC: 0x204B0C73;
 App Version: 01.01.0000.
15.9. Ensure that the following data related to the CC PDIF are correctly displayed:
 SW-11077-3;
 0x728CFE1B;
 01.01.0301.
15.10. Ensure that the following data are correctly displayed for each one of the
CFGs installed and programmed according to the system configuration.
 App Part No: SW-11079-1;
 App CRC: 0xD23F85FA;
 App Version: 01.01.0000;
 PDIF PN: SW-11078-1;
 PDIF CRC: 0xDB7DEF6C;
 PDIF Ver: 01.00.0002.
15.11. Disconnect the laptop computer.

Page 13 of 22
B.T. 139-394 ANNEX A

Figure A1

Figure A2

Figure A3

Page 14 of 22
ANNEX A B.T. 139-394

Figure A4

Figure A5

Page 15 of 22
B.T. 139-394 ANNEX A

Figure A6

Page 16 of 22
ANNEX B B.T. 139-394

ANNEX B
CIRCULAR-FORCE GENERATORS CONFIGURATION CHECK

Page 17 of 22
B.T. 139-394 ANNEX B

PROCEDURE

NOTE
Print a copy of the table of figure B4. Use this copy as
a report for the configuration check.

NOTE
Tell the Manufacturer if the configuration check
results are not satisfactory.

1. Get access to the AVCS OMNI BUS panel (2, Figure B1) in the baggage
compartment through the opening of the access door 183AL.
2. Make sure all that the circuit breakers on the AVCS OMNI BUS panel (2) are closed.
3. Get access to the cockpit.
4. Make sure that on the auxiliary circuit-breaker panel:
 the circuit breaker AVCS CONTR (CB484) is closed;
 the circuit breaker AVCS PANEL (CB283) is opened;
 the circuit breaker AVCS PWR (CB282) is closed.
5. Connect the laptop computer to the AVCS control panel (1). Refer to the applicable
steps of the data module 39-C-18-33-00-00A-33AA-K.
6. Set the ON/OFF switch on the AVCS control panel (1) to ON. Then, make sure that
the PWR ON light comes on.
7. Open the Maintenance Software.
8. Make sure that the computer display shows the initial screen (Main Page) (Detail A of
Figure B2 ).
9. Push the “Connect” button on the “Link Status” window in the Main Page.
10. Make sure that “Connected” is shown in the “Link Status” window in a green
background.
11. Select the “Config Test” option on the “User Actions” window in the Main Page.
12. Wait that the Pop Up window comes on (Detail D of Figure B2 ). Do not push the OK
button.
13. Make sure that the Main Page shows the green "Valid" status symbol for the circular
force generators and accelerators installed on the helicopter. Refer to Detail B and C
of Figure B2.

Page 18 of 22
ANNEX B B.T. 139-394

14. Open the CFG0 circuit breaker (CB476).

15. Get access to the CFG0 circular-force generator (6) through the opening of the
access panel 141AL.
16. Disconnect the connector A483P11 from the CFG0 circular-force generator (6).
17. On the maintenance software main page, make sure that:
 The CFG0 status indicator shows the “CAN Error” symbol
 The other status indicators do not change
18. Connect the connector A483P11 to the CFG0 circular-force generator (6).
19. Close the CFG0 circuit breaker (CB476).
20. Make sure that the CFG0 status indicator shows the “Valid” status symbol”.
21. Do the steps 14 thru 20 for each of the other three circular force generators:
 get access to each circular force generator through the opening of the
applicable access panel shown on the table of Figure B3;
 when required, disconnect/connect the applicable AXXXP11 connector from
each circular force generator. Refer to the table of Figure B3;
 when required, close/open the applicable CFG circuit breaker. Refer to the table
of Figure B3.
22. Push the OK button on the pop up window.
23. Push the “Disconnect” button on the “Link Status” window in the maintenance
software main page.
24. Make sure that “Disconnected” is shown in the “Link Status” window.
25. Set the ON/OFF switch on the AVCS control panel (1) to OFF. Then, make sure that
the PWR ON light goes off.
26. Disconnect the laptop computer from the AVCS control panel (1). Refer to the
applicable steps of the AMP data module 39-C-18-33-00-00A-33AA-K.
27. Disconnect the external electrical power from the helicopter. Refer to AMP DM n° 39-
A-12-41-00-00A-510A-A.

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B.T. 139-394 ANNEX B

Figure B1

Page 20 of 22
ANNEX B B.T. 139-394

Figure B2

Page 21 of 22
B.T. 139-394 ANNEX B

Figure B3

Figure B4

Page 22 of 22
 Please send to the following address:
BOLLETTINO TECNICO COMPLIANCE FORM Date:

LEONARDO S.p.A.
CUSTOMER SUPPORT & SERVICES - ITALY Number:

PRODUCT SUPPORT ENGINEERING & LICENSES DEPT.

Via Giovanni Agusta, 520
21017 Cascina Costa di Samarate (VA) - ITALY Revision:
Tel.: +39 0331 225036 Fax: +39 0331 225988

Customer Name and Address: Telephone:

Fax:

B.T. Compliance Date:

Helicopter Model S/N Total Number Total Hours T.S.O.

Remarks:

Information:

We request your cooperation in filling this form, in order to keep out statistical data relevant to aircraft configuration up-to-date. The form should be filled in all
its parts and sent to the above address or you can communicate the application also via Technical Bulletin Application Communication Section placed in
Leonardo AW Customer Portal - MyCommunications Area. We thank you beforehand for the information given.