BOLLETTINO TECNICO N° 109S-065

The technical content of this document is approved 

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

DATE February 27, 2015

REV. A

Compliance with

this Bollettino is:

Page 1 of 5

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

REASON: Perform an inspection of the subject link assy for excessive friction of the 

spherical bearing. 

HELICOPTERS AFFECTED: 

PART I^ and PART II^:

All Agusta A109S helicopters that install the tail rotor pitch control link 

assy P/N 109-0130-05-117 which have accumulated less than 100 (one 

hundred) FH since their overhaul and all tail rotor pitch control link assy 

P/N 109-0130-05-117 which have accumulated less than 100 (one 

hundred) FH since their overhaul (e.g. spherical bearing replacement) 

and present in stock. 

NOTE 

If it is not possible to determine if or 

when the link has been overhauled, the 

link is affected by this Bollettino Tecnico. 

COMPLIANCE: 

PART I^: 

Before the next flight. 

PART II^: 

Within and not later than 5 (five) flight hours from the date of issuance of 

this Bollettino Tecnico. 

NOTE 

AgustaWestland S.p.A

Via Giovanni Agusta, 520

21017 Cascina Costa di Samarate (VA) Italy

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

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.

ALERT

ALERT
B.T. 109S-065 Rev. A

Page 2 of 5

Tail Rotor Pitch Control links in stock 

shall perform point 3 of PART II^ before 

their installation.

DESCRIPTION:

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

109-0130-05-117 has been reported on an A119MkII helicopter. 

The incident did not cause harm to the occupants nor damage to the 

helicopter.

The most probable cause of the seizure has been identified in an

excessive friction of one of the spherical bearings of the link; that

spherical bearing was replaced on the link during the overhaul performed 

few flight hours before by a Maintenance Organization.

The possibility that other overhauled links install spherical bearings with 

excessive friction cannot be excluded; the speed at which the link fails in 

such conditions is so to require an action on the in-service fleet to grant 

the continued airworthiness.

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

perform an inspection of the overhauled links P/N 109-0130-05-117,

which have accumulated less than 100FH since their overhaul, as 

follows:

PART I^: Check the spherical bearings of the links installed on the 

helicopter for presence of corrosion and freedom of 

movement.

PART II^: Check the torsion value force of the spherical bearings of 

the links and perform a visual inspection for cracks of the 

stem by means of a magnifying glass. Perform, if 

dictated, an inspection of the stem for cracks 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.

WARRANTY:

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

replaced in accordance to the present Bollettino Tecnico, Customer will 

be eligible to receive replacement part on a “free of charge basis”, with 

the exception of Consumable Materials.

Issue relevant (M)aintenance (M)alfunction (I)nformation (R)eport to your 

Warranty Administration Dpt., which shall provide the (R)eturn (M)aterial 

(A)uthorization to return removed part to AgustaWestland, as AW 

property.

REQUIRED MATERIALS:

PART I^:

N. A.
B.T. 109S-065 Rev. A

Page 3 of 5

PART II^:

The following consumable materials are necessary for the compliance:

SPECIFICATION DENOMINATION Q.TY

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

(cod. 531055030)

In case the required inspection gives negative results, the following material 

are necessary for the compliance:

P/N DENOMINATION Q.TY

109-0130-05-117 TR Pitch Control Link Assy A.R.

SPECIAL TOOLS:

Description Part Number

Dynamometer Local Supply

10x Magnifying Glass Local Supply

WEIGHT AND BALANCE CHANGES:

N. A.

REFERENCES:

A109S Air Vehicle Maintenance Publication n° 0B-A-AMP-00-X.

PUBLICATIONS AFFECTED:

N. A.

COMPLIANCE INSTRUCTIONS:

(See figure 1).

PART I^:

1. With the links installed on the helicopter, inspect around 

attaching points of pitch links for evidence of corrosion in 

accordance with the procedures given in the A109S Air Vehicle 

Maintenance Publication n. 0B-A-AMP-00-X. In case corrosion is 

found, replace the link with a serviceable one with the same P/N.

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

rotation. The links rotation on the spherical bearings have to be 

possible.

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

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

of this Bollettino.

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

helicopter log book.
B.T. 109S-065 Rev. A

Page 4 of 5

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 A109S Air Vehicle Maintenance 

Publication n. 0B-A-AMP-00-X.

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

equipped with protective false jaws.

3.1. At the other end apply a dynamometer on the spherical bearing

and perform the check of the torsion value force for the spherical 

bearing 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 spherical bearing rotation as 

shown in figure 1.

3.3. Check that the force torsion value is lower than 7.30 N for both 

the spherical bearings. In case a force torsion value above the 

limits is detected, even if in only one of the spherical bearings, it 

is necessary to replace the link with a serviceable one with the 

same P/N. Proceed with point 7.

3.4. In case both force torsion values are inside the limits at point 

3.3., proceed with point 4.

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 for the affected area).

CAUTION

In case of doubt for presence of cracks, it 

is necessary to perform a liquid 

penetrant inspection of the affected area 

as reported in Annex 1.

6. If no cracks are found, reinstall the links on the helicopter in 

accordance with the procedures given in the A109S Air Vehicle 

Maintenance Publication n. 0B-A-AMP-00-X. Otherwise, replace 

the link with a serviceable one with the same P/N.

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

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

helicopter log book.
B.T. 109S-065 Rev. A

Page 5 of 5

Indicative picture.

The force value must be verified on both

spherical bearings.

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 faces using a 10x magnifying 

glass.
1 of 3

ANNEX 1

Liquid penetrant inspection:

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.

In case the above mentioned 

personnel is not available by the 

Customer, set aside the link and 

send it to AgustaWestland S.p.A.

or to a Laboratory certified to 

perform liquid penetrant 

inspections.

Required Material

All following materials shall comply with SAE-AMS2644 

requirements and shall be listed in the relevant QPL:

 Liquid penetrant of Type 1, Method C and level 2 of 

sensitivity,

 Class 2 solvent,

 Developer form “d”.

 Aluminum adhesive tape;

 Paint stripper I.A.W. TT-R-2918 spec., Type I;

 Some clean, dry cloth;

 A clean and dry hair pencil.

NDT Process

For lighting conditions and other penetrant process requirements, 

the inspection shall comply with the requirements of ASTM E 

1417.

Compliance Instructions

1. Protect the two spherical bearings using Aluminum adhesive 

tape.

2. In the area suspected of cracks presence, carefully and 

totally remove the paint and the primer, for an area sufficient 
2 of 3

to reveal the point to be inspected. For this purpose use the 

paint stripper.

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.

4. The surface to be inspected must be carefully cleaned and

completely free from any residual of paint and/or paint 

stripper or contaminants. Remove any residual of 

contaminants using a clean soft brush and cloth or towel 

paper and class 2 solvent.

NOTE

This operation shall be 

performed very carefully; any 

contaminant left on the surface 

can prevent the penetrant to 

detect cracks.

5. After the solvent is completely evaporated perform the 

penetrant inspection as follows:

NOTE

The link, the penetrant and the 

ambient shall be in a 

temperature range between 15 

and 45 °C.

5.1. Apply the penetrant with a clean and dry hair pencil on the 

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

minutes of penetration dwell time.

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

cloth and then with a cloth dampened with class 2 solvent.

NOTE

The cloth must not be soaked 

with solvent and especially avoid 

to apply the solvent directly on 

the link.

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

the black light. (1,200 μW/cm2)
3 of 3

5.4. Repeat the removal of the penetrant excess with a clean 

cloth dampened with class 2 solvent until all background 

fluorescence has been completely removed.

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

uniform layer of the developer. 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.

5.6. After 10 minutes of developer dwell time, examine carefully 

the area.

CAUTION

Before starting the examination, 

the operator must adapt his sight 

to darkness for at least 1 minute 

and during examination he 

cannot wear sunglasses or photo 

chromatic lenses.

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

crack presence.

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 and with soft brush.

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

the procedures given in the applicable Maintenance Manual.

7. Remove the Aluminum adhesive tape from the two spherical 

bearings.
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: 

AGUSTAWESTLAND S.p.A. 

CUSTOMER SUPPORT & SERVICES - ITALY

PRODUCT SUPPORT ENGINEERING DPT.

Via del Gregge, 100

21015 Lonate Pozzolo (VA) - ITALY 

Tel.: +39 0331 664905

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.