EASA AD No.: 2 013

- 0185

TE. CAP.00110

- 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

. : 2 013

- 0185

Date: 1 4 A ugust 2 013

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 E U 748/2012 , 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].



### Design Approval Holder’s Name : AGUSTAWESTLAND S.p.A. 

### Type/Model designation(s) :

AB 205 , AB 212 and AB 412 helicopters

TCDS Number: ENAC Italy A 370 and A 157

F oreign AD: Not applicable

Supersedure: None



### ATA 64 Tail Rotor

– Tail Rotor Blades

– Inspection / Repair / Replacement

Manufacturer(s): AgustaWestland S.p.A

. (formerly Agusta S.p.A.)

Applicability: AB 205A1, AB 212, AB 412 and AB 412EP helicopters, all manufacturer serial numbers

Reason: Some cases of tail rotor (T/R) blade failures have been reported by Bell Helicopter for T/R blade Part Numbers (P/N) 212

- 010

- 750

- ALL (where “ALL” represents a placeholder for any number). Investigations conducted by Bell determined that the failure originated from a fatigue crack deriving from surface damages.

No similar failure has been reported for T/R blades installed on A gusta Westland helicopters, but the affected T/R blade P/N 212

- 010

- 750

- ALL may also be installed on AB 205A1, AB 212, AB 412 and AB 412EP helicopters.
This condition, if not detected and corrected, could potentially lead to a T/R structural failure, resulting in loss of control of the helicopter.
To address this unsafe condition, A gustaWestland issued Bollettino Tecnico (BT) 205A1

- 134 , BT 212

- 203 and BT 412

- 136 providing instructions for detailed visual inspection s of the tail rotor blade surface and, in case of findings, corrective actions.
For the reasons described above, this AD requires detailed visual inspection s of the tail rotor b lade surface for nicks, dents, scratches, corrosion or cracks and, in case of findings, repair or replacement of affected T/R blades.EASA AD No.: 2 013

- 0185

TE. CAP.00110

- 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. Effective Date: 2 1 August 2013

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously:
(1) For helicopters on which T/R blade P/N 212

- 010

- 750

- ALL is installed,

w ithin 25 flight hours (FH) or 30 days after the effective date of this AD, whichever occurs first, and, thereafter, at intervals not to exceed 25 FH or 30 days

, whichever occurs first, accomplish a detailed visual inspection of the affected T/R entire blade surface for cracks, corrosion, nicks, dents and scratches in accordance with the instructions of AgustaWestland BT 205A1

- 134, BT 212

- 203 or BT 412

- 136, as applicable to helicopter model.
(2) If, during any inspection as required by paragraph (1) of this AD, any paint damage is detected on the T/R blade surface , before next flight, remove the paint from the affected area and accomplish a detailed visual inspection of the affected area in accordance with the instructions of AgustaWestland BT 205A1

- 134, BT 212

- 203 or BT 412

- 136, as applicable to helicopter model.
(3) If, during any inspection as required by par agraph (1) of this AD, any nick, scratch or dent is detected, before next flight, accomplish a detailed visual inspection of the affected area and measure the depth of the damage in accordance with the instructions of AgustaWestland BT 205A1

- 134, BT 212

- 2 03 or BT 412

- 136, as applicable to helicopter model.
(4) If, during any inspection as required by paragraph (1), (2) or (3) of this AD, any crack is detected or any damage or corrosion is found which is outside the limits defined in the applicable Maintenance Manual (MM)

, before next flight, remove the T/R blade and replace it with a serviceable blade.
(5) If, during any inspection as required by paragraph ( 2 ) or ( 3 ) of this AD

, any damage or corrosion is found which is inside the limits defined in the applicable MM , before next flight, repair the damage or remove the corrosion in accordance with the instructions of the applicable MM.
(6) Repair and replacement of affected T/R blades as required by paragraph (4) and (5) of this AD does not constitute terminating action for the repetitive inspections as required by paragraph (1) of this AD.
(7) From the effective date of this AD, do not install on any helicopter a T/R blade P/N 212

- 010

- 750

- ALL unless the T/R blade is in compliance with the requirements of this AD.

Ref. Public ations: AgustaWestland BT 205A1

- 134 original issue dated 13 August 2013. AgustaWestland BT 212

- 203 original issue dated 13 August 2013

. AgustaWestland BT 412

- 136 original issue dated 13 August 2013.

BHT

- 205A1

- MM Rev ision 7 dated 08 Jul y 2013

. BHT

- 212

- MM issue Rev ision 13 dated 16 Sept ember 2010

. AB412

- MM issue Rev ision 3 dated 0 6 June 2012

. The u se of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated

, EASA can approve Alternative Methods of Compliance for this AD.

2. Based on t he required actions and the compliance time, EASA have decided to issue a Final AD with Request for Comments

, postponing the public consul tation process until after publication

. 3. Enquiries regarding this A D should be referred to the Safety Information Section, Executive Directorate , EASA. E

- mail : ADs@easa.europa.eu

.EASA AD No.: 2 013

- 0185

TE. CAP.00110

- 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. 4. For any question concerning the technical content of the requirements in this AD, please contact: 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