## BOLLETTINO TECNICO N° 

# 109-145

The t echnical content of this document is approved
under the authority of DOA nr EASA.21J.005. DATE February 27, 20 15

REV. A

Compliance with
this Bollettino is:

Page 1 of 5 S UBJECT: 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 A109A/AII/C 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 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

Tail Rotor Pitch Control links in stock shall perform point 3 of PART II^ before
their installation.B.T. 109-145 Rev. A

Page 2 of 5 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 a n inspection of the overhauled links P/N 109-0130- 05

- 117

, which have accumulated less than 100FH since their overhaul (e.g. spherical bearing replacement)

, 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, perform a visual inspection for corrosion of the spherical bearings and perform a visual inspection for cracks of the stem by means o f 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. 109-145 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:

Pertinent Maintenance Manual.

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 pertinent Maintenance Manual. 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. 109

- 145 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 pertinent Maintenanc e Manual

.

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 rotati on 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 beari ngs. In case a force torsion value above the
limit 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 value s 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 fo r 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 l iquid penetrant inspection of the affected area as reported in Annex 1

.

6. If no cracks are found, r ei nstall the links on the helicopter in accordance with the procedures given in the pertinent
Maintenance Manual

. 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. 109

- 145 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 inspe ction 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 Agusta Westland 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 sufficient2 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 clean ed and completely free from any residual of paint and/or paint stripper or contaminants. Remove any residual of
contaminants u sing a clean soft brush and cloth or towel paper and class 2 solvent

.

NOTE

Th i s 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 fi rstly 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 μ W/cm 2 )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 an d 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 ad apt 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 configur azione base, in relazione all’emissione de l Bollettino Tecnico, preghiamo di voler compilare il presente modulo in tutte le sue parti e sped irlo all’indirizzo sopra indicato. Si ring razia 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 **WESTLAND S.p.A.** 

CUSTOMER SUPPORT & SERVICES - ITALY

PRODUCT SUPPORT ENGINEERING DPT.

Via del Gregge, 100

2101 5 Lonate Pozzolo (VA) - I T ALY

T el

. : +39 0331 664905

Fa x : +39 0331 66468 4

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.