EASA AD No: 2010-0222-E 

EASA Form 111 Page 1/2 

 

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0222-E 

Date: 22 October 2010 

Note: This Emergency 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 1702/2003, Part 21A.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 operate an aircraft to which an AD applies, except in accordance 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 introduced 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 accordance 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 Bollettino 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 immediate publication and notification. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research 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.