EASA AD No.: 2015

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TE. CAP.0011 1

- 00 4 © European Aviation Safety Agency. A ll rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## 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 Mem ber 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 E U 748/2012 , Part 21

. A.3B. In accordance with EU 1321/2014 Annex I, Part M.A.301, the conti nuing 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

T CDS Number: EASA.R.005

F oreign AD: Not applicable Supersedure: None



### ATA 64 Tail Rotor
– Pitch Control Link Ass embl y – 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: A n event was reported of in

- flight br e aking of the tail rotor (TR) pitch con trol link assembly Part Number ( P/N ) 109

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- 117 on an A W 119MkII 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 incor rect 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 br e aking of the TR pitch control link ass embl y, possibly r esulting 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 ass embl y

. For the reason described above, this AD requires two o ne - time inspections to detect freedom of movement of the spherical bearings installed on recently overhauled TR pitch control link assemblie s P/N 109

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- 117 (one inspection with link installed on helicopter, the other with link removed) and , in case d iscrepancies are found, corrective action(s). This AD is considered to be an interim action and further AD action may follow.
Effective Date: 03 March 2015EASA AD No.: 2015

- 0035

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TE. CAP.0011 1

- 00 4 © European Aviation Safety Agency. A ll rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(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

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- 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 sinc e 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

- 1 45 Rev. A , BT 109EP

- 141 Rev. A , BT 109K

- 65 Rev. A , BT 109L

- 079 Rev. A , BT 109S

- 065 Rev. A , BT 109SP

- 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 a ccordance with the instructions of Part I I (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 h elicopter 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 a n overhauled TR pitch control link ass embl y P/N 109

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- 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. Public ations: AgustaWestland BT 109

- 145 Rev. A , dated 27 February 2015

. AgustaWestland BT 109EP

- 141 Rev. A , dated 27 February 2015

. AgustaWes tland 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 2 7 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 fo r this AD. 2. The results of the safety assessment ha ve indicated the need for immediate publication and notification , without the full public consultation process

. 3. Enquiries regarding this A D should be referred to the Safety Information Section, Certificatio n 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. Custom er Support, Via del Gregge, 100, 21015 Lonate P ozzolo (VA)

– Italy Telephone: +39 0331 664600; Fax: +39 0331 664684 E

- mail: AW109.mbx@agustawestland.com

.