# ALERT

TRANSLATION OF



## BOLLETTINO TECNICO N° 

# 109S

- 5

The technical content of this document is approved

under the authority of DOA nr EASA.21J.005. DATE July 26, 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 AFFEC TED:

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 A109S helicopters and/or in stock.

NOTE

Th e 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. 109S

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Page 2 of 8 DESCRIPTION:

A case of in flight fracture of the tail rotor pitch control link as sy 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 t he 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 pr ovide 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 ins pection 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 lever 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. 109S

- 5

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:

A109S Air Vehicle Maintenance Publication n°0B

- A/AMP

- 00

- P

.

PUBLICATIONS A FFECTED:

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, befor e their installation must apply the PART II^ and the PART III^ of

this Bollettino.B.T. 109S

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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 procedu res given in the A109S Air Vehicle Maintenance

Publication n°0B

- A/AMP

- 00

- P

.

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 c heck 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 torsi on 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 flig ht 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 l iquid penetrant inspection method as below reported

.

6. Liquid penetrant inspection:B.T. 109S

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Page 5 of 8 CAUTION
This inspection must be performed by personnel qualified a

t 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 an d 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 sc rubbing 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 stripp er 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 l

iquid 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 t han 30 minutes of penetration dwell time.B.T. 109S

- 5

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 QPL

AMS

- 2644.

NOTE

The cloth must not be soaked with solvent and especially avoi d 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

- 26 44 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 A109S Air Vehicle Maintenance

Publication n°0B

- A/AMP

- 00

- P.

6.7. Remove the protective adhesive tape from the two spherical bearings.B.T. 109S

- 5

Page 7 of 8 7. Reinstall the links on the helicopters in accordance with the procedures given in the A109S Air Vehicle Maintenance Publicatio n n°0B

- A/AMP

- 00

- P.

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 so urce.

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

- P

.

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. 109S

- 5

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.