EASA AD No.: 2015-0035-E

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EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2015-0035-E

Date: 27 February 2015

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 EU 748/2012, Part 21.A.3B. In accordance with EU 1321/2014 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 [EU 

1321/2014 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: None

ATA 64 Tail Rotor – Pitch Control Link Assembly – Inspection / 

Replacement

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

Corporation (formerly Agusta Aerospace Corporation).

Applicability: A109A, A109AII, A109C, A109E, A109K2, A109LUH, A109S, AW109SP,

A119 and AW119MKII helicopters, all serial numbers.

Reason: An event was reported of in-flight breaking of the tail rotor (TR) pitch control link 

assembly Part Number (P/N) 109-0130-05-117 on an AW119MkII helicopter.

Further investigation determined excessive friction of one of the spherical 

bearings of the link as the most probable cause for the seizure. This may have 

been caused by incorrect installation when the affected bearing was replaced 

during overhaul a few flight hours (FH) before the occurrence.

This condition, if not detected and corrected, could lead to further cases of 

breaking of the TR pitch control link assembly, possibly resulting in loss of 

control of the helicopter.

To address this unsafe condition, AgustaWestland issued instructions to 

inspect of the spherical bearings installed on the TR pitch control link assembly.

For the reason described above, this AD requires two one-time inspections to 

detect freedom of movement of the spherical bearings installed on recently 

overhauled TR pitch control link assemblies P/N 109-0130-05-117 (one 

inspection with link installed on helicopter, the other with link removed) and, in 

case discrepancies are found, corrective action(s).

This AD is considered to be an interim action and further AD action may follow.

Effective Date: 03 March 2015
EASA AD No.: 2015-0035-E

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

This AD requires actions on each overhauled TR pitch control link assembly, 

identified by P/N 109-0130-05-117, having accumulated (on the effective date 

of this AD) less than 100 flight hours (FH) since overhaul, and those for which 

the accumulated FH since last overhaul cannot be determined.

(1) Before next flight after the effective date of this AD, inspect the spherical 

bearings in accordance with the instructions of Part I (link remains installed 

on helicopter) of AgustaWestland Bolletino Tecnico (BT) 109-145 Rev. A, 

BT 109EP-141 Rev. A, BT 109K-65 Rev. A, BT 109L-079 Rev. A, 

BT 109S-065 Rev. A, BT109SP-087 Rev. A or BT 119-072 Rev. A, as 

applicable to helicopter model.

(2) Within 5 FH after the effective date of this AD, re-inspect the spherical 

bearings in accordance with the instructions of Part II (link to be removed 

from helicopter) of AgustaWestland BT 109-145 Rev. A, BT 109EP-141

Rev. A, BT 109K-65 Rev. A, BT 109L-079 Rev. A, BT 109S-065 Rev. A, 

BT109SP-087 Rev. A or BT 119-072 Rev. A, as applicable to helicopter 

model.

(3) If, during an inspection as required by paragraph (1) or (2) of this AD, any 

discrepancy is found, before next flight, accomplish the applicable 

corrective action(s) in accordance with the instructions of AgustaWestland 

BT 109-145 Rev. A, BT 109EP-141 Rev. A, BT 109K-65 Rev. A, 

BT 109L-079 Rev. A, BT 109S-065 Rev. A, BT109SP-087 Rev. A or 

BT 119-072 Rev. A, as applicable to helicopter model.

(4) From the effective date of this AD, installation on a helicopter of an

overhauled TR pitch control link assembly P/N 109-0130-05-117 is 

allowed, provided that, prior to installation, the assembly has passed an 

inspection in accordance with the instructions of Part II of AgustaWestland 

BT 109-145 Rev. A, BT 109EP-141 Rev. A, BT 109K-65 Rev. A, 

BT 109L-079 Rev. A, BT 109S-065 Rev. A, BT109SP-087 Rev. A or 

BT 119-072 Rev. A, as applicable to helicopter model.

Ref. Publications: AgustaWestland BT 109-145 Rev. A, dated 27 February 2015.

AgustaWestland BT 109EP-141 Rev. A, dated 27 February 2015.

AgustaWestland BT 109K-65 Rev. A, dated 27 February 2015.

AgustaWestland BT 109L-079 Rev. A, dated 27 February 2015.

AgustaWestland BT 109S-065 Rev. A, dated 27 February 2015.

AgustaWestland BT 109SP-087 Rev. A, dated 27 February 2015.

AgustaWestland BT 119-072 Rev. A, dated 27 February 2015.

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. The results of the safety assessment have 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, Certification 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: AW109.mbx@agustawestland.com.