EASA AD No.: 2013-0290

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0290

Date: 09 December 2013

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 748/2012, 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].

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: This AD supersedes EASA AD 2012-0208 dated 05 October 2012.

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: Reports were received of in-flight fracture of rod end assembly part number (P/N)

M004-01H007-045, installed on the main rotor lag dampers on an A109LUH 

helicopter and on an AW109SP helicopter. The investigation identified two

batches of rod end assemblies P/N M004-01H007-041 and P/N M004-01H007-

045, which could be potentially affected.

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 instructions 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 fractured 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 one-time inspection to 

identify all affected rod end assemblies and replacement with serviceable parts.

Effective Date: 23 December 2013
EASA AD No.: 2013-0290

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Required Action(s) 

and Compliance 

Time(s):

Required as indicated, 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 dampers, 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 119-50 Rev A, as applicable, depending on 

helicopter model.

Table 1 – Affected parts

Helicopter 

model

Main Rotor lag 

dampers P/N

Affected rod 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 to 202 inclusive,

P/N M004-01H007-045 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 flight, replace the affected rod end assembly 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 the 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. Publications: AgustaWestland BT 109L-053 Revision A dated 03 December 2013.

AgustaWestland BT 109S-49 Revision A dated 03 December 2013.

AgustaWestland BT 109SP-052 Revision A dated 03 December 2013.

AgustaWestland BT 119-50 Revision A dated 03 December 2013.

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 substantiated, EASA can approve Alternative 

Methods of Compliance for this AD.

2. Based 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 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
EASA AD No.: 2013-0290

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Telephone + 39 0331 664600 ; Fax: + 39 0331 664684

E-mail: custserv@agustawestland.com.