EASA AD No.: 2011-0140

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0140

Date: 20 July 2011

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, its Member States and of the European third countries that participate in th e activities of EASA under Article 66 of that Regulation. This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD unless other wise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, Article 14(4) exemption].



### Type Approval Holder’s Name : Agusta S.p.A. Type/Model designation(s) : AW139 helicopters

TCDS Number : EASA.R.006

Foreign AD : Not applicable

Supersedure : None



### ATA 23 Communications – Primus Epic Harnesses Solder Splic es –

Inspection / Replacement

Manufacturer(s): Agusta S.p.A. and Agusta Aerospace Corporation

Applicability: AW139 helicopters, serial numbers: 3 1248, 31249, 41001 to 41023 inclusive, 41201 to 41234 inclusive, 41236 to 41239 inclusive, 41241, 41243 to 41245 inclusive, 41247, 41248, 41250, 41253 to 41255 incl usive, and 41257.

Reason: Some occurrences have been reported of intermittent noise in the Co-Pilot audio system. The technical investigations carried out by Agusta show that some of the solder splices on the audio panel were the possible cause of these malfunctions. This condition, if not detected and corrected, coul d impair the Co-Pilot’s capability to react immediately to operational diff iculties. To address this potentially unsafe condition, Agust a have issued Bolletino Tecnico (BT) 139-249. For the reasons described above, this AD requires a ccomplishment of an inspection of the solder splices and related wires for checking their condition and proper installation and, depending on findings, replacement of the solder splices.

Effective Date: 03 August 2011EASA AD No.: 2011-0140

EASA Form 110 Page 2/2 Required Action(s) and Compliance Time(s): Required as indicated, unless already accomplished: (1) For helicopters equipped with connectors as det ailed in Table 1 (shortnose helicopters) or Table 2 (long-nose helicopters ) of Agusta BT 139-249, as applicable, within 600 flight hours or 6 months, whichever occurs first after the effective date of this AD, or, when an “A VIONIC FAULT” cockpit message is displayed, before next flight, inspect t he solder splices Part Number (P/N) D-110-41, for proper installation and overheating condition, in accordance with the instructions of Agusta BT 13 9-249. (2) If, during the inspection as required by paragr aph (1) of this AD, a discrepancy is found on the solder splices, before next flight, replace the solder splices with serviceable parts, in accordanc e with the instructions of Agusta BT 139-249. (3) If, during the inspection as required by paragr aph (1) of this AD, no discrepancy is found on the solder splices, before next flight, accomplish a manual pull-test of the splice, twisting the wires on each splice of the connector and, if a splice fails the pull-test, rep lace the defective splice with a serviceable part, in accordance with the ins tructions of Agusta BT 139-249. (4) From the effective date of this AD, do not inst all any solder splice P/N D-110-41 as identified in Table 1 and Table 2 of Ag usta BT 139-249 on any helicopter, unless the solder splice has passed the inspection in accordance with the instructions of Agusta BT 139-2 49.
Ref. Publications: Agusta Bollettino Tecnico 139-24 9, original issue dated 13 July 2011. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. The required actions and the risk allowance have granted the issuance of a Final AD with Request for Comments, postponing th e public consultation process after publication. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact Agusta S.p.A. E-mail: aw139.mbx@agustawestland.com

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