EASA AD No.: 201 3

- 0 290

TE. CAP.0011 0

- 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
. : 20 1 3 - 0 290

Date: 09 Decem ber 201 3

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 EC 7 48 /20 12 , 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 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]

. 

### D e sign Approval Holder’s Name : AGUSTA

WESTLAND S.p.A. Type/Model designation(s) : A109 , AW109, A119 and A W 119 helicopters
TCDS Number: EASA. R .0 05
F oreign AD : Not applicable Supersedure: This AD supersedes EASA AD 2012

- 0208 dated 05 October 2012.



### ATA 6 2 Rotor
– Main Rotor Lag Damper
– Identification / Replacement

Manufacturer(s): AgustaWestland S.p.A (formerly Agusta S.p.A.), AgustaWestla nd Philadelphia Corporation (formerly Agusta Aerospace Corporation). Applicability: A109LUH , A109S , AW109SP , A 119 , and A W 1 1 9 M K II helicopters, all serial numbers ( s / n )

. Reason: Reports were received of i n - flight f r acture of rod end assembly part number (P /N) M004

- 01H007

- 045 , installed on the main rotor lag dampers o n an A109LUH helicopter and on an AW109SP helicopter. The investigation identif ied two batch es of rod end assemblies P/N M004

- 01H007

- 041 and P/N M004

- 01H007

- 045 , which could be potentially affec ted. This condition, if not detected and corrected, could ultimately lead to main rotor damage , possibly resulting in loss of control of the helicopter

. To address this condition, AgustaWesland S.p.A. issued 4 Bollettino Tecnico (BT) to provide instruction s for a one - time inspection of the affected rod end assemblies to identify the relevant s/n’s and replacement of the affected parts

. EASA issued EASA AD 2012

- 0208 to require accomplishment of those actions. Since that AD was issued , a new case of fracture d rod end assembly has been reported. The related investigation concluded that further batches of the two previously identified P/N rod end assemblies , as well as some batches of P/N 109

- 0112

- 11

- 101 and P/N 109

- 0112

- 11

- 105 , are also potentially affected by cracks. For the reasons described above, this AD requires a o n e - time inspection to identify all affected rod end assemblies and replacement with serviceable parts.
Effective Date: 23 December 2013EASA AD No.: 201 3

- 0 290

TE. CAP.0011 0

- 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. Required A ction(s) and Compliance Time(s): Required as in dicated, unless accomplished previously: (1) Within 25 flight hours or 2 months , or at the next maintenance of the helicopter involving removal of a rod end assembly , whichever occurs first after the effective date of this AD , inspect the main rotor lag da mpers , as identified by P/N in Table 1 of this AD, depending on helicopter model , to identify the P/N and s/n of each rod end assembly in accordance with the instructions of AgustaWestland BT 109L

- 053 Rev A , BT 109S

- 49 Rev A , BT 109SP

- 052 Rev A or BT 119

- 5 0 Rev A , as applicable , depending on helicopter model

. Table 1

– Affected parts Helicopter model Main Rotor lag

dampers P/N Affected r od end assemblies P/N and s/n
A109S , A109LUH and AW109SP 109

- 0112

- 39

- 103

109

- 0112

- 39

- 105 P/N M004

- 01H007

- 041 s/n from

1 t o 202 inclusive, P/N M004

- 01H007

- 04 5 s/n from 1RW to 202 RW inclusive and from 4964 to 5011 inclusive

.

A119 and AW119MKII 109

- 0112

- 05

- 105

109

- 0112

- 05

- 107 P/N 109

- 0112

- 11

- 101 s/n from 1

to 78 inclusive; P/N 109

- 0112

- 11

- 105 s/n from 1RW to 78RW inclusive P/ N M004

- 01H007

- 045 s/n from 1RW to 202 RW inclusive and from 4964 to 5011 inclusive (2) If , during the inspection as required by paragraph (1) of this AD, the identified rod end assembly has a P/N and s/n as identified in Table 1 of this AD , before next fl ight , replace the affected rod end a ssembly with a serviceable part in accordance with the instructions of AgustaWestland BT 109L

- 053 Rev A , BT 109S

- 49 Rev A , BT 109SP

- 052 Rev A or BT 119

- 50 Rev A , as applicable , depending on helicopter model. Note: For th e purpose of this AD , a serviceable rod end assembly is a part having a P/N and s/n not listed in Table 1 of this AD

. ( 3 ) From the effective date of this AD, do not install on any helicopter a rod end assembly having a P/N and s/n listed in Table 1 of this AD

. Ref. Public ations: AgustaWestland BT 109L

- 05 3 Revision A dated 03 December 201 3

. AgustaWestland BT 109S

- 49 Revision A dated 03 December 201 3

. AgustaWestland BT 109SP

- 052 Revision A dated 03 December 201 3

. AgustaWestland BT 119

- 50 Revision A dated 03 December 201 3

. The use of later approved revisions of th e 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. Ba sed on the required 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 Informati on 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)

– ItalyEASA AD No.: 201 3

- 0 290

TE. CAP.0011 0

- 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. Telephone + 39 0331 664600 ; Fax: + 39 0331 664684 E

- mail: custserv@agustawestland.com

.