ALERT

TRANSLATION OF

BOLLETTINO TECNICO N° 109-122

The technical content of this document is approved

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

DATE July 27, 2006

REV.

Compliance with

this Bollettino is:

 ALERT Page 1 of 8

SUBJECT: TAIL ROTOR PITCH CONTROL LINK ASSY P/N 109-0130-05-117 

INSPECTION.

REASON: Perform an “una tantum“ (one time) inspection of the subject link assy for 

excessive friction of the spherical bearing of the bearing ball and cracks.

HELICOPTERS AFFECTED:

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

All the tail rotor pitch control link assy P/N 109-0130-05-117 from S/N 

MO001 up to S/N MO773 (included) with less than 100 (one hundred) 

flight hours and installed on Agusta A109A/AII/C helicopters and/or in 

stock.

NOTE

The tail rotor pitch control link assy P/N 

109-0130-05-117 with S/N MOxxx and 

identified with the letter “T” after the S/N, 

do not require the compliance with this

Bollettino.

COMPLIANCE:

PART I^:

Before the next flight (one time only).

PART II^:

Within and not later than 5 (five) flight hours from compliance with PART 

I^.

PART III^:

After 4 (four) and however not later than 6 (six) flight hours from

compliance with PART II^.
B.T. 109-122

Page 2 of 8

DESCRIPTION:

A case of in flight fracture of the tail rotor pitch control link assy P/N 

109-0130-05-117 has been reported on an A109E helicopter. 

The incident did not cause harm to the occupants more damage to the 

helicopter.

From the resultant investigation the fracture occurred because of fatigue 

due to the excessive friction on the spherical bearing of the link.

The investigation has also revealed that the malfunction was caused by a 

production defect. The batch of the parts that could be affected by these 

malfunction were also identified.

This Bollettino is issued in order to provide the necessary instructions to 

perform an “una tantum“ (one time) inspection of the links P/N 109-0130-

05-117 as follows:

PART I^: Check for freedom of movement of the links installed on 

the helicopter.

PART II^: Check the torsion value force for the bearing balls of the 

links and perform a visual inspection by means of a 

magnifying glass and if dictated, an inspection with the 

liquid penetrant method.

PART III^: Repetition of the visual inspection by means of a

magnifying glass and if dictated, an inspection with the 

liquid penetrant method.

REQUIRED MANPOWER:

The following estimated manpower hours are required for compliance 

with this Bollettino:

PART I^: Negligible.

PART II^: 1,5 (one and half) hours for each link assy.

PART III^: 1 (one) hour for each link assy.

WARRANTY:

Should the inspection deem that the tail rotor pitch control link is to be 

replaced in accordance to the present Bollettino Tecnico, Agusta shall 

replace the part free of charge to the Customer.

The removed item must be returned to Agusta and will become its

property.

REQUIRED MATERIALS:

PART I^:

N.A.

PART II^ and PART III^:

The following consumable materials are necessary for the compliance:

SPECIFICATION DENOMINATION Q.TY

TT-N-95 type 2 Aliphatic naphtha A.R.

 (cod. 531055030)
B.T. 109-122

Page 3 of 8

In addition, the following materials can be necessary:

• Paint stripper sec. TT-R-2918;

• Liquid penetrant of Type 1, Method C and level 2 of sensitivity as per 

QPL-AMS-2644 latest revision;

• Class 2 solvent as per QPL-AMS-2644 latest revision;

• Developer as per QPL-AMS-2644 latest revision;

• One black light lamp conforming to the ASTM E 1417 requirements.

SPECIAL TOOLS:

N.A.

WEIGHT AND BALANCE CHANGES:

N.A.

REFERENCES:

Pertinent Maintenance Manual.

PUBLICATIONS AFFECTED:

N.A.

COMPLIANCE INSTRUCTIONS:

(See figure 1).

PART I^:

1. With the links installed on the helicopter, manually verify the links 

rotation. The links rotation on the spherical bearing of the bearing 

ball have to be possible.

2. In case, during the manual verification a rotation resistance

and/or binding has occurred, immediately perform the PART II^ 

of this Bollettino.

3. Record compliance with PART I^ of this Bollettino in the

helicopter log book.

NOTE

New links that may be stoked as a spare 

parts must perform the steps 3., 3.1., 3.2. 

and 3.3. of PART II^ of this Bollettino. If 

the result is favourable, the links must be 

marked with letter “T” after the Serial

Number using an etch pen.

Links with less than 100 (one hundred) 

flight hours, before their installation must 

apply the PART II^ and the PART III^ of 

this Bollettino.
B.T. 109-122

Page 4 of 8

PART II^:

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

disconnect any power source.

2. Remove the links from the helicopters in accordance with the 

procedures given in the pertinent Maintenance Manual.

3. Secure the larger bearing ball of the link in a bench vice

equipped with protective false jaws.

3.1. At the other end apply a dynamometer on the bearing ball and 

perform the check of the torsion value force for the bearing ball 

rotation as shown in figure 1.

3.2. In the same manner perform the check of the necessary torsion 

value force for the smaller link bearing ball rotation as shown in 

figure 1.

3.3. In case a force torsion value greater than 7.30 N is detected,

even if in only one of the spherical bearings, it is necessary to 

replace the link with a new one with the same P/N, but not

affected with the compliance of this Bollettino. Return the

helicopter in a ready to flight condition.

3.4. In case a force torsion value below 7.30 N in both spherical 

bearings is detected, it is necessary to proceed as below

reported and subsequently perform the PART III^ of this

Bollettino within the time frame prescribed in the paragraph

“COMPLIANCE”.

4. Carefully clean the link stem using aliphatic naphtha or

equivalent with a soft non metallic bristle brush, exercising care 

to protect the two spherical bearings.

5. Perform a visual inspection of the stem for cracks using a 10x 

magnifying glass (see figure 1).

CAUTION

In case of doubt for presence of cracks, it 

is necessary to perform a liquid 

penetrant inspection method as below

reported.

6. Liquid penetrant inspection:
B.T. 109-122

Page 5 of 8

CAUTION

This inspection must be performed by

personnel qualified at least at level II in 

the liquid penetrant method in conformity 

with the international standards EN4179 

or NAS410 or in accordance with the 

Agusta AQ18-02 rule. 

In case the above mentioned personnel 

is not available by the Customer, set

aside the link and send it to Agusta or to 

a Laboratory certified to perform liquid 

penetrant inspections.

6.1. Protect the two spherical bearings using only tape whose

adhesive does not absorb the solvent.

6.2. In the area suspected of cracks presence, carefully and totally 

remove the paint and the primer, for an area sufficient to reveal 

the point to be inspected. For this purpose use the paint stripper 

sec. TT-R-2918.

6.3. The paint stripper must be left to act for sufficient time. The 

chemical action shall be made easier by scrubbing with a soft 

bristle brush.

CAUTION

The use of any other mechanical tool, 

like scrapers or scotch-brite or others are 

forbidden.

6.4. The surface to be inspected must be carefully clean and

completely free from any residual of paint and/or paint stripper or 

contaminants. Using a clean soft brush and cloth or towel paper 

and class 2 solvent as per QPL-AMS-2644.

6.5. After the solvent is completely evaporated perform the liquid

penetrant inspection as follows:

NOTE

The link, the liquid penetrant and the

ambient shall be in a temperature range 

between 15 and 45 °C.

6.5.1 Apply the liquid penetrant of Type 1, Method C and level 2 of 

sensitivity as per QPL-AMS-2644 with a clean and dry hair pencil 

on all the area to be inspected and leave it for not less than 30 

minutes of penetration dwell time.
B.T. 109-122

Page 6 of 8

6.5.2. Remove the excess of penetrant firstly with a clean and dry cloth 

and then with a cloth dampend with class 2 solvent as per QPLAMS-2644.

NOTE

The cloth must not be soaked with

solvent and especially avoid to apply the 

solvent directly on the link.

6.5.3. Darken the part up to 20 lux maximum and then light it with the 

black light.

6.5.4. Repeat the removal of the penetrant excess with a clean cloth 

dampened with the with class 2 solvent as per QPL-AMS-2644 

until all background fluorescence has been completely removed.

6.5.5. After the solvent is completely evaporated, apply a thin and 

uniform layer of developer as per QPL-AMS-2644.

Before the application, vigorously shake the developer can for at 

least 1 minute.

CAUTION

In case of any developer sagging, the 

part shall be carefully cleaned and the 

whole process repeated.

6.5.6. After 10 minutes of developer dwell time, examine carefully the area.

CAUTION

Before examination, operator must adjust 

his sight to darkness for at least 1 minute 

and during examination he cannot wear 

sunglasses or photo chromatic lenses.

6.5.7. Carefully verify in the area suspected in order to confirm the 

crack presence that determines the link rejection.

6.5.8. At the end of the inspection, carefully clean the part from any 

residual of the products used with a clean cloth soaked with class 

2 solvent as per QPL-AMS-2644 and with soft brush.

6.6. Restore the primer and the finish paint in accordance with the 

procedures given in the pertinent Maintenance Manual.

6.7. Remove the protective adhesive tape from the two spherical

bearings.

7. Reinstall the links on the helicopters in accordance with the 

procedures given in the pertinent Maintenance Manual.
B.T. 109-122

Page 7 of 8

8. Return the helicopter in a ready to flight condition.

9. Record compliance with PART II^ of this Bollettino in the

helicopter log book.

PART III^:

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

disconnect any power source.

2. Remove the links from the helicopters in accordance with the 

procedures given in the pertinent Maintenance Manual.

3. Comply with the steps from 4. to 6. (included) of PART II^ of this 

Bollettino.

4. The links that have accomplished with success the compliance of 

the present part of this Bollettino, must be marked with letter “ T ” 

after the Serial Number, using an etch pen.

5. Comply with the steps from 7. to 9. (included) of PART II^ of this 

Bollettino.
B.T. 109-122

Page 8 of 8

Indicative diagram.

The force value must be verified on both

bearing balls.

LINK ASSY P/N 109-0130-05-117

FIGURE 1

End secured in a

bench vice equipped

with protective false

jaws

Force to be applied:

7.30 N

Area in which the visual

inspection must be performed on 

all 4 the faces using a magnifying 

glass.