EASA AD No.: 2013

- 0009

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 1 3

- 0 009

Date: 11 January 201 3

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EC 7 48 /20 12 , Part 21

. A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may ope rate an aircraft to which an AD applies, except in accordance with the requ irements of that AD
, unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]

.



### D e sign Approval Holder’s Name :
AGUSTA

WESTLAND S.p.A. Type/Model designation(s) :

A109 and A119 helicopters

TCDS Number: EASA. R .0 05

F oreign AD : Not applicable

Supersedure: None



### ATA 6 4 Tail Rotor

– Blade Retaining Bolt s – In spection / Replacement

Manufacturer(s): AgustaWestland S.p.A (formerly Agusta S.p.A.), AgustaWestland Philadelphia Corporation (formerly Agusta Aerospace Corporation).

Applicability: A109 C
, A109K2, A109 E and A 1 1 9 helicopters, all serial numbers ( s / n )

.

Reason: C ase s of crack ed tail rotor (TR) blade retaining bolts
, part number (P/N) 109

- 8131

- 09

- 1 installed on an A109K2 and on an A109E helicopter
, have been reported

. The investigation of these occurrences carried out by AgustaWestland revealed that the crack s w ere in the same area of the bolt s and in correspondence with
so me corrosion pits

. This condition, if not detected and corrected, could cause damage to, or loss of, a TR blade
, possibly resulting in loss of control of the helicopter

. For the reasons described above, this AD requires a o n e
- time visual and liquid penetrant inspection TR blade retaining bolts

. Thereafter, t his AD also requires repetitive insp ections of the TR blade retaining bolts and, if any crack , corrosion or damage is found, accomplishment of the applicable corrective actions.

Effective Date: 25 January 201 3EASA AD No.: 2013

- 0009

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Within the compliance time as specified in Table 1 of this AD, depending on the time in service o f the TR blade retaining bolts on the effective date of this AD, accomplish a visual and liquid penetrant inspection of the retaining bolts P/N 109

- 8131

- 09

- 1 in accordance with the instructions of Part I of AgustaWestland Bollettino Tecnico ( BT ) 109

- 1 3 5 , BT 109 K

- 55 , BT 109 E P

125 or BT 119

- 0 5 2 , as applicable
, depending on helicopter model

. Table 1

– First inspection
Flight Hours (FH) accumulated by the TR blade retaining bolts on the effective date of this AD Compliance time

Less than 400 FH Before exceeding 5 00 FH accumulated by the retaining bolts
400 FH or more Within 100 FH or 2 months, whichever occurs first after the effective date of this AD (2) After accomplishment of the inspection as required by paragraph (1) of th is AD, within the compliance time specified in Table 2 of this AD, accomplish repetitive inspection s of the TR blade retaining bolt s P/N 109

- 8131

- 09

- 1 in accordance with the instructions of Part II of AgustaWestland BT 109

- 1 3 5
, BT 109 K

- 55 , BT 109 E P

- 125 or BT 119

- 0 5 2 , as applicable
, depending on helicopter model

. Table 2
Helicopter Model( s ) Compliance time

- Interval

A109C At each”300 FH helicopter inspection” or at intervals not to exceed 6 months, whichever occurs first

A109K2, A109 E and A 1 19 At each “200 FH helicopter inspection” or at

intervals not to exceed 6 months, whichever occurs first
(3) If, during any inspection a s required by paragraph (1) or (2) of this AD
, any crack, corrosion
, damage or removal of cadmium plating in the central part of the bolt is identified, before next flight
, replace the affected TR blade retaining bolt P/N 109

- 8131

- 09

- 1 with a serviceable part in accordance with the instructions of AgustaWestland BT 109

- 1 3 5 , BT 109 K

- 55 , BT 109 E P

125 or BT 119

- 0 5 2 , as applicable
, depending on helicopter model. (4) Replacement of TR blade retaining bolts as required by paragraph (3) of this AD does not constitute terminating action for the inspections as required by paragraphs (1) and (2) of this AD. ( 5 ) From the effective date of this AD, do not install a TR retaining bolt P/N 109

- 8131

- 09

- 1 that has accumulated more than 400 FH, on any helicopter unless it h as passed the inspections as required by paragraph (1) of this AD

.
Ref. Public ations: AgustaWestland BT 109

- 1 3 5 dated 19 Decem ber 2012

. AgustaWestland BT 109 K

- 55 dated 19 Decem ber 2012

. AgustaWestland BT 109 E P

- 1 2 5 dated 19 Decem ber 2012

. AgustaWestland BT 119

- 0 5 2 dated 19 Decem ber 2012

. The use of later approved revisions of th e s e document s is acceptable for compliance with the requirements of this AD.EASA AD No.: 2013

- 0009

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.
2. Based on the required actions and the compliance time, EASA have decided to issue a Final AD with Request for Comments, postponing the public consult ation process until after publication.
3. Enquiries regarding this AD should be referred to the Safety Information Section, Executive Directorate, EASA. E

- mail: ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirements in this AD, please contact: Agusta S.p.A. Customer Support Via del Gregge, 100

- 21015 Lonate Pozzolo (VA)

– Italy Telephone + 39 0331 664600 ; Fax: + 39 0331 664684 E

- mail: custserv@agustawestland.com

.