EASA AD No: 2010-0222-E

EASA Form 111 Page 1/2 

## EASA EMERGENCY AIRW ORTHINESS DIRECTIVE

AD No.: 2010-0222-E

Date: 22 October 2010

Note: This Emergency Airworthiness Direct ive (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 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an ai rcraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in a ccordance with the requirements 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]. 

### Type Approval Holder’s Name : Agusta S.p.A Type/Model designation(s) :
A109A and A109AII helicopters

TCDS Number: EASA.R.005

Foreign AD: Not applicable

Supersedure: None



### ATA 65 Tail Rotor Drive – Tail Rotor Special Hub Plug - Inspection

Manufacturer(s): Agusta S.p.A

Applicability: A109A and A109AII helicopters, all serial numbers if equipped with tail rotor special hub plug part number (P/N) 109-0133-18-103.
Reason: A mistaken value of the tightening torque of the tail rotor special hub plug P/N 109-0133-18-103 has been discovered in the Maintenance Manual of A109A and A109AII helicopters. The investigation carried out by Agusta has revealed that the wrong value of the tightening torque was introduc ed with the revision 9 of the A109A and A109AII Helicopter Maintenance Manual dated 15 June 2009. This condition, if not corrected, could ultimately lead to tail rotor malfunction.

Effective Date: 25 October 2010

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: Within the next 5 flight hours after the effective date of this AD but no later than 30 November 2010, whichever occurs first, verify the tightening torque of the special tail rotor hub plug P/N 109-0133-18-103, and do the applicable corrective actions, in accordanc e with the instructions of Agusta Alert Bollettino Tecnico 109-132.EASA AD No: 2010-0222-E

EASA Form 111 Page 2/2 Ref. Publications: Agusta Alert Bolletti no Tecnico 109-132 dated 22 October 2010. The use of later approved revisions of this document 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. The safety assessment has requested not to implement the full consultation process and an immedi ate publication and notification. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any questions 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 Phone + 39 0331- 664396 Fax: + 39 0331 664680 E-mail: custserv@agustawestland.com

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