EASA AD No.: 2012-0262

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0262

Date: 14 December 2012

Note: This Airworthiness Directive (AD) is is sued 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 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 opera te an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agenc 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].



### Design Approval Holder’s Name:
AgustaWestland S.p.A. 

### Type/Model designation(s):
AB139 and AW139 helicopters

TCDS Number: EASA.R.006

Foreign AD: Not applicable

Supersedure: None



### ATA 32 Landing Gear – Nose Landing Gear Arm Pin Installation – Inspection

Manufacturer(s): AgustaWestland S.p.A. (f ormerly Agusta S.p.A.) and AgustaWestland Philadelphia Corporation (formerly Agusta Aerospace Corporation)

Applicability: AB139 and AW139 helicopters, with the following serial numbers:
31005, 31006, 31008 to 31157 inclusive, 31201 to 31398 inclusive, 31400 to 31412 inclusive, 31414, 31416, 31418, 31419, 31421, 31425, 31426, 31428, 31432, 31440, 41001 to 41023 inclusive, 41201 to 41275 inclusive, 41277 to 41286 inclusive, 41288, 41293, 41300, 41301, 41303, 41307, 41308 and 41310.

Reason: Incorrect installation of the nose landing gear (NLG) pin P/N 1661-0001 was verified on some aircraft in service, causing a pre-stress condition on the pin flange. The results of the subsequent te chnical investigation, carried out by AgustaWestland, concluded that this discrepancy could potentially affect a number of other helicopters.
This condition, if not detected and corr ected, could lead to NLG structural failure and consequent NLG collapse during landing or taxi, possibly resulting in damage to the helicopter and injury to the occupants.
For the reasons described above, this AD requires a one-time inspection of the NLG to verify proper installation of the affected NLG pins on both left and right arms and, depending on findings, accomplishment of applicable corrective actions.

Effective Date: 28 December 2012EASA AD No.: 2012-0262

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) For helicopters equipped with NLG assembly P/N 3G3220V00133 or P/N 3G3220V00135, within 50 flight hours or 1 month, whichever occurs first after the effective date of this AD, accomplish a visual inspection of the NLG pin installation on both left and right arms in accordance with the instructions of AgustaWestland BT 139-306. (2) If, during the inspection as require d by paragraph (1) of this AD, any discrepancy is detected, before nex t flight, accomplish the applicable corrective actions in accordance with the instructions of AgustaWestland BT 139-306.

Ref. Publications: AgustaWestland BT 139-306, dated 12 December 2012. The use of later approved revisions of this document 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 tec hnical content of the requirements in this AD, please contact AgustaWestland S.p.A.: E-mail: aw139.mbx@agustawestland.com

.