EASA AD No.: 201 3

- 0 225

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TE. CAP.0011 1

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Pro prietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No

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Date: 20 September 201 2

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 Me mber 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 EU 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 aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Age nc y [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, AW109

, A119 and AW119 helicopter s

TCDS Number: EASA. R .0 05

F oreign AD : Not applicable

Supersedure: None



### ATA 64 Tail Rotor

– Tail Rotor Drive Shaft Line Nut

– Inspection

Manufacturer(s): AgustaWestland S.p.A (formerly Agusta S.p.A.).

Applicability: A109 A, A109AII and A109C heli copters, all serial numbers (S/N);

A109 E helicopters , all S/N up to S/N 11832 inclusive, except S/N 11796, from 11808 to S/N 11810 inclusive and from S/N 11812 to 11829 inclusive ;

A109 K2 helicopters , all S/N;
A109LUH helicopters

, all S/N ; A109S helicopters , all S/N ; AW109SP helicopters, all S/N up to S/N 22316 inclusive, except S/ N 22284, 22286, 22307 and 22308;

A119 and AW119MKII helicopters, all S/N up to AW119MKI I S/N 14811 inclusive , except 14805 and 14807

.

Reason: Occurrences were reported of two in

- s ervice AW109SP helicopters, where during scheduled inspection on the tail rotor drive shaft line, one nut Part Number (P/N) MS21042L4 that connect s the Thomas coupling with the splined adapter was found cracked

. The subsequent technical investigation ident ified that the reported cracks of the nuts are the results of a production defi ci ency (causing hydrogen embrittlement) at the nut supplier.
This condition, if not detected and corrected, could lead to failure of the tail rotor function, resulting in loss o f control of the helicopter

.EASA AD No.: 201 3

- 0 225

- E

TE. CAP.0011 1

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

- Internet/Intranet. To address this unsafe condition, AgustaWestland issued s even Bollettino Tecnico (BT), BT 109EP

- 130

, BT 109

- 13 6 , BT 109K

- 58, BT 109L

- 066, BT 109S

- 055, BT 109SP

- 069 and BT 119

- 61 for all helicopters that are potentially affected

. For the reasons described above, this AD requires a one

- time inspection of each P/N MS21042L4 nut installed on the tail rotor drive shaft line and replacement of each affected nut with a serviceable part having a different P/N

.

Effective Date: 21 Septem ber 201 3

Required A ction(s) and Compliance Time(s): Required as indicated, unless accomplished previously:
( 1 ) Before next flight after the effective date of this AD, inspect each nut P/N MS21042L4 and, within the compliance time specified in Table 1 of t his AD, depending on findings, as applicable, replace each nut P/N MS21042L4 with a serviceable part in accordance with the instructions of the applicable BT

. Note: For the purpose of this AD, the applicable BT is the one mentioned in Ref. Publications of this AD for the affected helicopter model.

Table 1

– N ut replacement

Finding Compliance time

Nut is cracked Before next flight

Nut is not cracked Within 10 flight hours or 30 days, whichever occurs first aft er the effective date of this AD

( 2 ) From the effective date of this AD, do not install a nut having a P/N MS21042L4 on the tail rotor drive shaft line of any helicopter

.

Ref. Public ations: AgustaWestland BT 109EP

- 130 dated 2 0 September 201 3

. AgustaWestland BT 109

- 136 dated 2 0 September 201 3

. AgustaWestland BT 109K

- 58 dated 2 0 September 201 3

. AgustaWestland BT 109L

- 066 dated 2 0 September 201 3

. AgustaWestland BT 109S

- 055 dated 2 0 September 201 3

. AgustaWestland BT 109SP

- 069 dated 2 0 September 201 3

. AgustaWestland BT 119

- 61 dated 2 0 September 201 3.

The use of late r approved revisions of the s e document s 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 results of the safety assess ment ha ve indicated the need for immediate publication and notification , without the full public consultation process

. 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

.