EASA AD No.: 2012-0208

TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0208

Date: 05 October 2012

Note: This Airworthiness Directive (AD) is iss ued 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 748/2012, Part 21.A. 3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the cont inuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircr aft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [EC 2042/2 003 Annex I, Part M.A.303] or agreed with the Authority of t he State of Registry [EC 216/2008, Article 14(4) exemption].



### Design Approval Holder’s Name : AGUSTAWESTLAND S.p.A. Type/Model designation(s) : A109, AW109, A119 and AW119 helicopters

TCDS Number: EASA.R.005

Foreign AD: Not applicable

Supersedure: None



### ATA 62 Rotor – Main Rotor Lag Damper – Identification / Replacement

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

Applicability: A109LUH, A109S, AW109SP, A119, and AW119MKII helicopters, all serial numbers (s/n).

Reason: Cases of in-flight fracture of rod end assembly part number (P/N) M004-01H007-045, installed on the main rotor lag dampers, have been reported on an A109LUH helicopter and on an AW109SP helicopter. The investigation of these occurrences has led AgustaWestland to identify two batches of rod end assemblies P/N M004-01H007-041 and P/N M004-01H007- 045 which could be potentially affected by cracks.
This condition, if not detected and correct ed, could ultimately lead to main rotor damage, possibly resulting in loss of control of the helicopter.
For the reasons described above, this AD requires a one-time inspection of the rod end assemblies P/N M004-01H007-041 and P/N M004-01H007-045 to identify the relevant s/n’s and r eplacement of the affected parts.

Effective Date: 12 October 2012EASA AD No.: 2012-0208

TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Within 25 flight hours or 3 months, wh ichever occurs first after the effective date of this AD, inspect the rod end assemblies P/N M004-01H007-041 and P/N M004-01H007-045 of the four lag dampers, P/N 109-0112-39-103 or P/N 109-0112-39-105 or P/N 109-0112-05-105 or P/N 109-0112-05-107, to identify the s/n of each rod end assembly in accordance with the instructions of AgustaWestland Bollettino Tecnico (BT) 109L-053, BT 109S-49, BT 109SP-052 or BT 119-50, as applicable, depending on helicopter model. (2) If, during the inspection as required by paragraph (1) of this AD, the identified s/n is between 84 and s/n 132 (inclusive) or between s/n 4964 and s/n 5011 (inclusive), before next flight replace the affected rod end assembly with a serviceable part in accordance with the instructions of AgustaWestland BT 109L-053, BT 109S-49, BT 109SP-052 or BT 119-50, as applicable, depending on helicopter model. Note: For the purpose of this AD, a serviceable part is a rod end assembly P/N M004-01H007-041 or P/N M004-01H007-045, whose s/n is not between 84 and 132 (inclusive) and not between 4964 and 5011 (inclusive). (3) From the effective date of this AD , do not install on any helicopter a rod end assembly P/N M004-01H007-041 or P/N M004-01H007-045 with a s/n that is between 84 and 132 (inclusive) or between 4964 and 5011 (inclusive).
Ref. Publications: AgustaWestland BT 109L-053 dated 03 October 2012. AgustaWestland BT 109S-49 dated 03 October 2012. AgustaWestland BT 109SP-052 dated 03 October 2012. AgustaWestland BT 119-50 dated 03 October 2012. The use of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately subs tantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. Based on the requir ed actions and the compliance time, EASA have decided to issue a Final AD with Request for Comments, postponing the public consultation 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 technica l 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.