ALERT 

TRANSLATION OF 

BOLLETTINO TECNICO

 N° 119-39

The technical content of this document is approved 

under the authority of DOA nr EASA.21J.005. 

 DATE July 02, 2010

 REV. A May 23, 2011 

Compliance with 

this bulletin is: 

 ALERT Page 1 of 17

THE REVISION A OF THIS BOLLETTINO TECNICO CANCELS AND

SUPERSEDES THE BASIC ISSUE DATED JULY 02, 2010.

- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

SUBJECT: INSPECTION AND MODIFICATION OF THE PILOT CONTROL BOX 

ASSY P/N 109-0010-81-103 AND CO-PILOT CONTROL BOX ASSY 

P/N 109-0010-81-107 OF THE COLLECTIVE PITCH CONTROL 

INSTALLATION.

REASON: Perform an inspection of the subject pilot and co-pilot control boxes to 

verify for the correct installation of the engine RVDT control gear locking 

pin and provide the necessary instructions to modify the subject pilot and 

copilot control boxes.

HELICOPTERS AFFECTED:

PART I^, PART II^ and PART III^:

All the pilot control box assy P/N 109-0010-81-103 and the co-pilot 

control box assy P/N 109-0010-81-107, installed on the Agusta A119 and 

AW119MKII helicopters and/or in stock. 

NOTE

The pilot control box assy P/N 109-0010-

81-103 and the co-pilot control box assy 

P/N 109-0010-81-107 reporting the mark 

B.T. 119-39 REV.A (ref. figure 7), are not 

interested in the compliance with this 

Bollettino Tecnico.

COMPLIANCE:

PART I^:

Within the next 5 flight hours after the receipt of this Bollettino and 

however within and not later than June 15, 2011. 

ALERT

ALERT

MANDATORY

An appropriate entry should be made in the aircraft log book upon accomplishment.

If ownership of aircraft has changed, please, forward to new owner.

An Company

Via GiovanniAgusta, 520

21017 Cascina Costa di Samarate (VA) Italy

Tel.: +39 0331-229111 - Fax: +39 0331-229605/222595
B.T. 119-39

Page 2 of 17

PART II^:

Every 50 flight hours after compliance with PART I^ of this Bollettino until 

PART III^ compliance. 

PART III^:

Within and not later than January 31, 2012. 

DESCRIPTION:

On an AW119MKII helicopter it has been reported that the two throttle 

handles, installed on the pilot and co-pilot collective control levers were 

not moving synchronously and moreover that both the IDLE and FLIGHT 

were missing on the co-pilot throttle. 

The investigation has revealed that the engine RVDT control gear locking 

pin, inside the pilot control box assy P/N 109-0010-81-103, fell out of its 

seat that lead to the loss of the pilot and co-pilot engine throttles 

synchronicity. 

The actions of Agusta and Triumph Controls LLC, pilot control box assy 

P/N 109-0010-81-103 and the copilot control box assy 

P/N 109-0010-81-107 supplier; have found the definitive solution at the 

malfunction, modifying the boxes internal configuration in order to 

guarantee the lock of the engine RVDT control gear locking pin. 

This Bollettino is issued in order to provide:

PART I^: the necessary instructions to perform a one-time inspection to 

verify for the correct installation of the engine RVDT pilot control box 

assy P/N 109-0010-81-103 and co-pilot control box P/N 109-0010-81-107 

gear locking pin. 

PART II^: the necessary instructions to perform a periodic inspection to 

verify the fixing strength of the engine RVDT pilot control box assy 

P/N 109-0010-81-103 and co-pilot control box P/N 109-0010-81-107 gear 

locking pin. 

PART III^: the necessary instructions to install two lockwired half clamps 

on the RVDT control gear of the pilot control box assy 

P/N 109-0010-81-103 and copilot control box assy P/N 109-0010-81-107

in order to avoid any possible movement of the locking pin. 

After the compliance with PART III^, the periodic inspection to verify the 

fixing strength of the engine RVDT pilot control box assy 

P/N 109-0010-81-103 and co-pilot control box P/N 109-0010-81-107 gear 

locking pin described in PART II^ is no longer applicable. 

REQUIRED MANPOWER:

The following estimated manpower hours are required for compliance 

with this Bollettino: 

PART I^: 1.5 (one and a half hours);

PART II^: 1.5 (one and a half hours); 

PART III^: 8 (eight hours).
B.T. 119-39

Page 3 of 17

WARRANTY:

Within the calendar terms mentioned at point “Compliance”, the parts 

required to apply the present Bollettino shall be supplied on a free of 

charge basis by Agusta upon Customer’s request. 

Upon application of this Bollettino, Customers are requested to submit to 

Agusta Warranty Administration the Technical Bulletin Compliance form 

attached to this Bollettino duly completed in all its parts, and relevant 

M.M.I.R. (Maintenance Malfunction Information Report).

REQUIRED MATERIALS:

PART I^ and PART II^:

The following materials could be required for compliance with PART I^ 

and PART II^ of this Bollettino: 

P/N DENOMINATION Q.TY NOTES

109-0010-81-103 Pilot control box assy 1 (1)

109-0010-81-107 Co-pilot control box assy 1 (1)

PART III^:

The following materials are required for compliance with PART III^ of this 

Bollettino:

P/N DENOMINATION Q.TY NOTES

109G7606R01-101 Clamp assy kit 2 (2)

Consisting of:

68165-1 Upper half clamp .1

68167-1 Lower half clamp .1

68169-1 Threaded stud .1 (3)

NAS1352C04H8 Screw .2

MS20995C20 Lockwire .CR

68172-1 Foam cube .4 (3)

NOTES:

(1) Component modified in accordance with PART III^ of this Bollettino. 

(2) Alternatively could be provided the P/N 68168-1.

(3) Special tools to remove from the helicopter after this Bollettino 

compliance. 

SPECIAL TOOLS:

N.A. 

WEIGHT AND BALANCE CHANGES:

PART I^ and PART II^: N.A. 

PART III^: Negligible. 

REFERENCES:

A119 / AW119 MKII Maintenance Manual. 
B.T. 119-39

Page 4 of 17

PUBLICATIONS AFFECTED:

N.A. 

COMPLIANCE INSTRCTIONS:

PART I^ and PART II^:

(See figures 1÷2) 

1. Prepare the helicopter on ground for a safe maintenance, 

disconnect any power supply.

2. Gain access to the pilot control box assy P/N 109-0010-81-103 

removing the guard assy P/N 109-0703-07 in accordance with 

the instructions given in the A119 / AW119 MKII Maintenance 

Manual.

3. With reference to figure 1, acting on the four fixing screws open 

the pilot control box assy P/N 109-0010-81-103 cover.

CAUTION

Do not remove the cover until all the four 

fixing screws are removed, in order to avoid 

that the screws may fall into the pilot control 

box assy P/N 109-0010-81-103. If a screw 

falls into the box assy, must be removed to 

prevent damage to the aircraft.

4. With reference to figure 2, verify that the gear locking pin is 

correctly installed in its seat as follows:

4.1 If necessary act on the pilot collective stick engine throttle to set 

the locking pin in central position, in order to have a perfect view 

of it.

 

4.2 If the locking pin is not present or partially out of its seat or 

recessed for more than 2.00 mm, immediately replace the pilot 

control box assy P/N 109-0010-81-103 with a new assy of the 

same P/N already modified with PART III^ of this Bollettino, in

accordance with the instructions given in the A119 / AW119 MKII 

Maintenance Manual applying however the PART I^ of this 

Bollettino. 

NOTE

The removed pilot control box assy 

P/N 109-0010-81-103 must be returned to 

Agusta for repair. 

4.3 If the inspection at previous step has been performed with 

favourable exit proceed with step 5 and followings.
B.T. 119-39

Page 5 of 17

5. Gain access to the co-pilot control box assy 

P/N 109-0010-81-107 removing the fairing assy 

P/N 109-0011-88 (or the fairing assy P/N 109-0703-11-101 if the 

Kit P/N 109-0810-01 is installed) in accordance with the 

instructions given in the A119 / AW119 MKII Maintenance 

Manual.

6. With reference to figure 1, acting on the four fixing screws open 

the co-pilot control box assy P/N 109-0010-81-107 cover.

CAUTION

Do not remove the cover until all the four 

fixing screws are removed, in order to avoid 

that the screws may fall into the co-pilot 

control box assy P/N 109-0010-81-107. If a 

screw falls into the box assy, must be 

removed to prevent damage to the aircraft. 

7. With reference to figure 2, verify that the gear locking pin is 

correctly installed in its seat as follows:

7.1 If necessary act on the co-pilot collective stick engine throttle to 

set the locking pin in central position, in order to have a perfect 

view of it.

 

7.2 If the locking pin is not present or partially out of its seat or 

recessed for more than 2.00 mm, immediately replace the 

co-pilot control box assy P/N 109-0010-81-107 with a new assy 

of the same P/N already modified with PART III^ of this 

Bollettino, in accordance with the instructions given in the A119 / 

AW119 MKII Maintenance Manual applying however the PART I^ 

of this Bollettino. Perform step 8 and followings.

NOTE

The removed co-pilot control box assy 

P/N 109-0010-81-107 must be returned to 

Agusta for repair. 

7.3 If the inspection at previous step has been performed with 

favourable exit proceed with step 8 and followings.

8. With reference to figure 1, acting on the fixing hardware close the 

pilot control box assy P/N 109-0010-81-103 and the co-pilot 

control box assy P/N 109-0010-81-107 covers.

9. Reinstall the guard assy P/N 109-0703-07 and the fairing assy 

P/N 109-0011-88 (or the fairing assy

P/N 109-0703-11-101 if the Kit P/N 109-0810-01 is installed) in
B.T. 119-39

Page 6 of 17

accordance with the instructions given in the A119 / AW119 MKII 

Maintenance Manual.

10. Return the helicopter to a ready to flight condition.

11. Record compliance with PART I^ or PART II^ of this Bollettino in 

the helicopter log book.

PART III^:

(See figures 3÷7) 

1. Prepare the helicopter on ground for a safe maintenance, 

disconnect any power supply.

2. Gain access to the copilot control box assy P/N 109-0010-81-107 

removing the fairing assy P/N 109-0011-88 (or, if installed the 

dual control kit P/N 109-0810-01, the guard assy P/N 109-0703-

11) in accordance with the instructions given in the A119 / 

AW119 MKII Maintenance Manual.

3. Modify the copilot control box assy P/N 109-0010-81-107 in 

accordance with the following instructions:

3.1. Remove the four MS51957-2 screws fixing the cover P/N 64709-

1 to the box assy P/N 64703-2.

3.2. Remove the cover P/N 64709-1 from the box assy P/N 64703-2 

to expose gear.

CAUTION

Remove the cover only after the four fixing 

screws removal, in order to avoid that the 

screws may fall into the box assy. If a screw 

falls into the box assy, must be removed to 

prevent damage to the aircraft. 

3.3. Place the copilot control box assy in approximate midstroke 

position rotating the copilot collective stick engine handle to end 

to travel. Locate the holes in the gear and rotate the engine 

handle in the opposite direction two holes.

3.4. Using needle-nose pliers, place four foam cubes P/N 68172-1

into the box assy to protect open spaces in the housing interior 

(see figure 3).

3.5. Insert the lower half clamp P/N 68167-1 with lockwire 

MS20995C20 already installed in the box assy and position 

around the hub of the gear. The counterbore of the lower half 

clamp must mate with the radius of the gear.
B.T. 119-39

Page 7 of 17

3.6. Thread the threaded stud P/N 68169-1 in one hole of the lower 

half clamp P/N 68167-1 until the stud is securely engaged with 

the lower half clamp.

NOTE

The stud is a tool to be used for assembly the 

clamp assy kit. It is not a permanent part of the 

copilot control box assy. 

3.7. Slide one hole of the upper half clamp P/N 68165-1 down the 

threaded stud P/N 68169-1 to mate with the lower half clamp P/N 

68167-1. The counterbore of the upper half clamp must mate 

with the radius of the gear (see figure 4).

3.8. Rotate the upper half clamp P/N 68165-1 slightly to insert the tab 

through a hole in the gear.

NOTE

Ensure the upper half clamp tab is engaged in 

gear hole. 

3.9. Fix the upper half clamp P/N 68165-1 to the lower half clamp 

P/N 68167-1 using one NAS1352C04H8 screw. Fingertight the 

screw.

3.10. Remove the threaded stud P/N 68169-1 and install the second 

NAS1352C04H8 screw fixing the upper half clamp P/N 68165-1 

to the lower half clamp P/N 68167-1. Fingertight the screw.

3.11. Torque the two NAS1352C04H8 screws to 0.45÷0.62 Nm (4÷5,5 

inch-pounds) and secure the lower half clamp P/N 68167-1 using 

lockwire MS20995C20 (see figures 5 and 6).

3.12. Remove all loose pieces of lockwire and any other debris that 

may have fallen into the box assy.

CAUTION

If lockwire or other debris falls into the box 

assy, must be removed to prevent damage to 

the aircraft. 

3.13. Using needle-nose pliers, remove the four foam cubes 

P/N 68172-1 from the box assy.

3.14. Place the cover P/N 64709-1 in its position on the box assy 

P/N 64703-2 to align screw holes.

3.15. Secure the cover P/N 64709-1 to the box assy P/N 64703-2 

using the four MS51957-2 screws.
B.T. 119-39

Page 8 of 17

3.16. In the area shown in figure 7, using an etch pen, on the copilot 

control box assy P/N 109-0010-81-107 mark B.T. 119-39 REV.A.

4. Gain access to the pilot control box assy P/N 109-0010-81-103 

removing the pilot seat P/N 109-0702-98, the guard assy 

P/N 109-0703-07 and the central cover assy P/N 109-0313-54 in 

accordance with the instructions given in the A119 / AW119 MKII 

Maintenance Manual.

5. Modify the pilot control box assy P/N 109-0010-81-103 in 

accordance with the following instructions:

5.1. Remove the four MS51957-2 screws fixing the cover P/N 64737-

1 to the box assy P/N 64734-2.

5.2. Remove the cover P/N 64737-1 from the box assy P/N 64734-2 

to expose gear.

CAUTION

Remove the cover only after the four fixing 

screws removal, in order to avoid that the 

screws may fall into the box assy. If a screw 

falls into the box assy, must be removed to 

prevent damage to the aircraft. 

5.3. Place the pilot control box assy in approximate midstroke 

position rotating the pilot collective stick engine handle to end to 

travel. Locate the holes in the gear and rotate the engine handle 

in the opposite direction two holes.

5.4. Using needle-nose pliers, place four foam cubes P/N 68172-1

into the box assy to protect open spaces in the housing interior 

(see figure 3).

5.5. Insert the lower half clamp P/N 68167-1 with lockwire 

MS20995C20 already installed in the box assy and position 

around the hub of the gear. The counterbore of the lower half 

clamp must mate with the radius of the gear.

5.6. Thread the threaded stud P/N 68169-1 in one hole of the lower 

half clamp P/N 68167-1 until the stud is securely engaged with 

the lower half clamp.

NOTE

The stud is a tool to be used for assembly the 

clamp assy kit. It is not a permanent part of the 

pilot control box assy. 
B.T. 119-39

Page 9 of 17

5.7. Slide one hole of the upper half clamp P/N 68165-1 down the 

threaded stud P/N 68169-1 to mate with the lower half clamp 

P/N 68167-1. The counterbore of the upper half clamp must mate 

with the radius of the gear (see figure 4).

5.8. Rotate the upper half clamp P/N 68165-1 slightly to insert the tab 

through a hole in the gear.

NOTE

Ensure the upper half clamp tab is engaged in 

gear hole. 

5.9. Fix the upper half clamp P/N 68165-1 to the lower half clamp 

P/N 68167-1 using one NAS1352C04H8 screw. Fingertight the 

screw.

5.10. Remove the threaded stud P/N 68169-1 and install the second 

NAS1352C04H8 screw fixing the upper half clamp P/N 68165-1 

to the lower half clamp P/N 68167-1. Fingertight the screw.

5.11. Torque the two NAS1352C04H8 screws to 0.45÷0.62 Nm (4÷5,5 

inch-pounds) and secure the lower half clamp P/N 68167-1 using 

lockwire MS20995C20 (see figures 5 and 6).

5.12. Remove all loose pieces of lockwire and any other debris that 

may have fallen into the box assy.

CAUTION

If lockwire or other debris falls into the box 

assy, must be removed to prevent damage to 

the aircraft.

5.13. Using needle-nose pliers, remove the four foam cubes 

P/N 68172-1 from the box assy.

5.14. Place the cover P/N 64737-1 in its position on the box assy 

P/N 64734-2 to align screw holes.

5.15. Secure the cover P/N 64737-1 to the box assy P/N 64734-2 

using the four MS51957-2 screws.

5.16. In the area shown in figure 7, using an etch pen, on the pilot 

control box assy P/N 109-0010-81-103 mark B.T. 119-39 REV.A.

6. Reinstall the guard assy P/N 109-0703-07, the cover assy 

P/N 109-0313-54, the fairing assy P/N 109-0011-88 (or, if 

installed the dual control kit P/N 109-0810-01, the guard assy 

P/N 109-0703-11) and the pilot seat P/N 109-0702-98 in 
B.T. 119-39

Page 10 of 17

accordance with the instructions given in the A119 / AW119 MKII 

Maintenance Manual.

7. Return the helicopter to a ready to flight condition.

8. Record compliance with PART III^ of this Bollettino in the 

helicopter log book.
B.T. 119-39

Page 11 of 17

Pilot control box assy P/N 109-0010-81-103

Co-pilot control box assy P/N 109-0010-81-107

FIGURE 1

Open the cover acting on the four 

fixing screws

Open the cover acting on the four 

fixing screws
B.T. 119-39

Page 12 of 17

Pilot control box assy P/N 109-0010-81-103

Co-pilot control box assy P/N 109-0010-81-107

 FIGURE 2

Verify that the gear 

locking pin is correctly 

installed in its seat

Verify that the gear locking pin is 

correctly installed in its seat
B.T. 119-39

Page 13 of 17

N. 4 FOAM CUBES P/N 68172-1 TO PROTECT THE BOX ASSY 

INTERIOR

FIGURE 3
B.T. 119-39

Page 14 of 17

THREADED STUD P/N 68169-1 USED FOR CLAMP ASSY KIT

P/N 109G7606R01-101 INSTALLATION

FIGURE 4
B.T. 119-39

Page 15 of 17

CLAMP ASSY KIT P/N 109G7606R01-101 INSTALLED AND LOCKWIRED

FIGURE 5
B.T. 119-39

Page 16 of 17

109G7606R01-101 CLAMP ASSY KIT

FIGURE 6

68167-1

LOWER HALF CLAMP

68165-1

UPPER HALF CLAMP

NAS1352C04H8

SCREW (2 OFF)

TAB MUST INSERT

IN A GEAR HOLE
B.T. 119-39

Page 17 of 17

FIGURE 7

IDENTIFICATION AREA MARK: BT 

119-39 REV.A WITH ETCH PEN

IDENTIFICATION AREA MARK: 

BT 119-39 REV.A WITH ETCH 

PEN 

109-0010-81-107 COPILOT CONTROL BOX ASSY

109-0010-81-103 PILOT CONTROL BOX ASSY

Note: 

Remarks:

Informazioni: 

Information:

Al fine di gestire le varianti alla configurazione base, in relazione all’emissione del Bollettino Tecnico, preghiamo di voler compilare il presente modulo in tutte le sue parti e spedirlo all’indirizzo sopra indicato. Si ringrazia per la gentile collaborazione data. 

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. We thank you beforehand for the information given.

MODULO APPLICAZIONE BOLLETTINO TECNICO

TECHNICAL BULLETIN COMPLIANCE FORM

Data: 

Date:

Numero: 

Number:

Revisione: 

Revision:

Prego spedire a questo indirizzo: 

Please send to the following address: 

AGUSTA S.p.A. 

CUSTOMER SUPPORT & SERVICES - ITALY

PRODUCT SUPPORT ENGINEERING DPT.

Via del Gregge, 100

21015 Lonate Pozzolo (VA) - ITALY 

Tel.: +39 0331 664600

Fax: +39 0331 664684

Telefono: 

Telephone:

Fax:

Data Applicazione B.T.: 

B.T. Compliance Date:

Denominazione Cliente ed Indirizzo: 

Customer Name and Address:

Modello Elicottero 

Helicopter Model S/N Matricola Tail Number

Ore Totali 

Total Hours

Ore D.U.R. 

T.S.O.