# ALERT Via GiovanniAgusta ,520

**~~** 

# IC.T... 21017 Cascina Costa di Sama rate (VA) Italy

**~** "' Tel. : +39 0331 -229111- Fax : +39 0331-229605/222595

- ----------------------AN AGUSTAWESTLAND C OMPANY



# ~ TRANSLATION OF 

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# 109-125 BOLLETTINO TECNICO The technical content of this document is approved under the authority of DOA nr EASA.21J.005 . DATE December 13, 2007 Compliance with this bollettino is: 

# MANDATORY REV.

SUBJECT: INSPECTION OF THE TIP CAP P/N 709-0103-29-109 OF THE MAIN ROTOR BLADES P/N 709-0103-01 (ALL DASH NUMBERS). REASON: To inspect the subject tip cap for presence of cracks on the leading edge. HELICOPTERS AFFECTED: All the main rotor blades PIN 709-0103-01 installed on the Agusta A 109C helicopters (and/or stored as spare parts) equipped with tip cap P/N 709-0103-29-109.

COMPLIANCE: NOTE Main Rotor blades P/N 709-0103-01 that are not affected by the BT 109-106 Rev.B , must comply with this Bollettino.

**~** Tip Caps PIN 709-0103-29-109 that have accumulated more than 600 ( six hundred ) operating hours: • Within 5 (five) operating hours from the receipt of this Bollettino and however within and not later than January 31,2008. Subsequently every 50 ( fifty ) operating hours ( plus 5 operating hours tolerance not cumulative ).

**~** Tip Caps P/N 709-0103-29-109 that have accumulated less than 600 ( six hundred ) operating hours: • Within and not later than 600 ( six hundred ) operating hours. Subsequently every 50 ( fifty ) operating hours ( plus 5 operating hours tolerance not cumulative ).

An appropriate entry should be mode in the aircraft log book upon occornplis h rnenl. If ownership of aircraft has changed, please, forward lo new owner. 

# ALERT Page 1 of 5B.T. 109- 125 DESCRIPTION: A case of loss of a part of the tip P/N 709-0103-29-109 of the main rotor blade P/N 709-0103-01 has been reported on an A 109 series helicopter model, with subsequent increase of helicopter vibratory level. The cause of this loss is the fracture of the welded bead ( joint line of shells ) of the tip leading edge. Further investigation by AGUSTA are still ongoing . This Bollettino is issued with the purpose of providing , as a precautionary measure, a visual inspection , with the aid of a magnifying glass, for cracks of the tip cap leading edge ( welded joint line of shells ) REQUIRED MANPOWER: 0,5 estimated manpower hours are required for each blade (only visual inspection) for compliance with this Bollettino . WARRANTY: If upon implementation of this Bolletino Tecnico the tip cap is found cracked on the leading edge, please contact immediately our Customer Support Engineering REQUIRED MATERIALS: The following consumable materials will be required to accomplish this Bollettino : • abrasive paper grit No 320 or more fine • solvent (exane, or petroleum ether, or aliphatic naphtha according to TT-N-95 type 2) or solvent 9PR5 available from BRENT International ; • visible dye penetrant P6R available from BRENT International; • nonaqueous wet developer 901 B spray available from BRENT International ; • one or more white light sources able to provide an illuminance of at least 1000 lux on inspection area . Alternative products to the solvents, penetrant and developer specified above are permitted provided that: • they comply to the requirements of AMS2644 (class 2 for the solvent, type 2 and method "c" for the penetrant and form "e" for the developer); • they are listed in the pertinent QPL-AMS-2644-1 ; • the penetrant and developer are produced by the same company. SPECIAL TOOLS: N.A. WEIGHT AND BALANCE CHANGES: N.A. REFERENCES: N.A. Page 2 of 5PUBLICATIONS AFFECTED: A 109C Maintenance Manual. COMPLIANCE INSTRUCTIONS: (See figure 1) NOTE The procedures reported below are applicable to each one of the four main rotor blades, if affected by this Bollettino , and does not require to remove it from the helicopter. B.T. 109- 125

1 . Prepare the helicopter on ground for a safe maintenance, disconnect any power supply. 2. Using a 10 power magnifying glass, visually inspect on tip cap leading edge welded bead Uoint line between the two metallic shells) for presence of cracks and/or damage (see figure 1 ) . );;> If the main rotor blade does not have any presence of cracks on the tip cap, proceed to step 5 and subsequent. );;> If the main rotor blade does have presence of cracks on the tip cap , remove it from service and immediately inform AGUSTA. );;> If there are doubts on the presence of cracks, proceed with step 3 and subsequent. 3. Using the visible dye penetrant method , inspect the tip cap leading edge along the welded joint line of the shells for presence of cracks as follows (refer to figure 1 ): 3. 1. Using abrasive paper grit no320 or more fine, remove the paint from area B, on both upper and lower sides, inboard 5 to 10 mm from leading edge and starting at 30,0 mm from the trailing edge. Mask surrounding painted areas using adhesive tape . CAUTION 1 The above operation must be accomplished at the first application of the liquid penetrant inspection .

Page 3 of 5B.T. 109-125 CAUTION 2 Personnel conducting the liquid penetrant inspection must be qualified in accordance with the practice EN4179 I NAS410. The blade, the penetrant and ambient temperatures shall be between 4

# oc and 45°C. 3.2. Thoroughly degrease inspection area using a cloth soaked in solvent (refer to paragraph REQUIRED MATERIALS). Leave solvent to completely evaporate . 3.3. Using adhesive tape mask trailing edge inboard for 30,0 mm to avoid possible penetrant infiltration in the tip cap . 3.4 . Apply the penetrant in the inspection area extending approximately 5 mm inboard from trailing edge (refer to view A of figure 1 ) , on both upper and lower sides . Penetrant dwell time shall be 30 to 40 minutes. 3.5. Remove excess penetrant with a clear dry cloth followed by a cloth dampened in solvent until the background color has been completely removed . NOTE Do not directly pour the solvent on the inspection area. · 3.6 . Apply a thin and uniform layer of developer 901 B, after 10 to 15 minutes illuminate area to 1000 lux and examine it presence of cracks.

Page 4 of 53.7 . Upon completion of inspection , clean affected area with a clean dry cloth followed by a cloth dampened in solvent. 4. If the main rotor blade does not have any presence of cracks on the tip cap , proceed to step 5 and subsequent. If the main rotor blade does have presence of cracks on the tip cap, remove it from servi ce and immediately inform AGUSTA 5. Return the helicopter in ready to flight condition . 6. Record compliance with this Bollettino in the helicopter log book.View A Lap plate

Tip cap

Inspection area on the leading edge

Tip cap shell welding P/N 709-0103-29-109 marking B.T. 109- 125

Inspection area on the leading edge

AREA B (upper and lower sides) paint to remove if the liquid penetrant inspection is required

Dimensions in millimeters 

# FIGURE 1 Page 5 of 5AA AGUSTA WEs'n..ANO COMPANY 

## =tff= Prego spedire a questo indirizzo: Data: Please send to the following addr ess: MODULO APPLICAZIONE BOLLETTINO TECNICO D at

e: TECHNICAL . BULLETIN COMPLIANCE FORM 

### AGUSTA S.p.A. Numero: CUSTOMER SUPPORT Number: Via per Tornavento , 15 21019 Somma Lombardo (VA)- ITALY Tel. :+39 0331 711100 Revisione: Fax : +39 0331 711397 Revisi on: Denominazione Cliente ed lndirizzo: Telefono: Customer Name andAddress: Telephone: Fax: Data Applicazione B.T. : B. T . Compl iance Date: Modello Elicottero S /N Matricola OreTotali Ore D.U.R. Hel

i copter Model Tail Number Total Hours T.S.O.

Note: Remarks:

lnformazioni: Information: AI fine di gestire le varianti alia 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 indicate. Si ringrazia per Ia 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.