EASA AD No : 2011-0182R1

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0182R1

Date: 03 February 2012

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 participat e in the 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 accordance with the requirements of that AD, unl ess 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].



### Type Approval Holder’s Name :

TURBOMECA Type/Model designation(s) :

ARRIUS 2F turboshaft engines

TCDS Number : France n°M22

Foreign AD : Not applicable

Revision : This AD revises EASA AD 2011-0182 dated 22 September 2011. EASA AD

2011-0182 superseded EASA AD 2008-0134R1 dated 17 F ebruary 2009.



### ATA 73 Engine Fuel & Control - P3 Air Pipe – Inspec tion / Modification

Manufacturer(s): Turbomeca

Applicability: ARRIUS 2F turboshaft engines, all se rial numbers.

These engines are known to be installed on, but not limited to, Eurocopter EC120B helicopters.

Reason: On several ARRIUS 2F engines, the clearance between the P3 air pipe Part Number (P/N) 0319719180 and the rear right bul khead P/N 0319998240 has been found to be too small. Investigations have shown that both P3 air pipe and rear right bulkhead were compliant with the design. Turbomeca Engineeri ng Department concluded that the tolerance of assembly establishe d during the design could result in some rubbing between parts.
This condition, if not detected and corrected, coul d lead to chafing between the pipe and the bulkhead and consequent r upture of the P3 air pipe, prompting the fuel control system to go to id le which could result in reduced control of the helicopter.
To address this unsafe condition, EASA issued AD 20 08-0134 to require the inspection of the P3 air pipe (first section) a nd Right Hand (RH) rear half-wall and, in case it was found damaged or non- compliant, the replacement or readjustment of parts.EASA AD No : 2011-0182R1

EASA Form 110 Page 2/3 EASA AD 2008-0134R1 was issued to clarify the wordi ng. It emphasized that, under some circumstances, repetitive inspecti ons are required.
Since issuance of EASA AD 2008-0134R1, the results of investigations by Turbomeca have shown that the clearance between the P3 air pipe and the RH rear half-wall might change during installat ion of the engine on the helicopter. The same investigations have shown that , when a RH rear half-wall P/N 0319998240 is installed on an engine which is already installed on an helicopter, a clearance of more tha n 0,5 mm between the RH rear half-wall and the P3 air pipe is sufficient to prevent any chaffing between the two parts. This means that the inspecti ons have be to accomplished again on engines that have already bee n inspected and corrected as required by AD 2008-0134R1. In additio n, Turbomeca have developed a new RH rear half-wall P/N 0319 99 008 0 which prevents chafing between RH rear half-wall and P3 air pipe.
For the reasons described above, this AD supersedes EASA AD 2008-0134R1 and requires, except for engines on whi ch a RH rear halfwall P/N 0319 99 008 0 is installed (modification T F 80), repetitive inspections of the clearance between the P3 air pip e and RH rear half-wall and, in case of discrepancy, accomplishment of the applicable corrective actions. This AD is revised to address the engines that were already inspected and corrected in accordance with the instructions of Tu rbomeca Mandatory Service Bulletin (MSB) N° 319 75 4810 issue A.

Effective Date: Revision 1: 06 February 2012 Original issue: 06 October 2011

Required Action(s) and Compliance Time(s): Required as indicated unless accomplished previousl y: (1) For engines that are already installed on a hel icopter and on which a RH rear half-wall P/N 0319 99 82 40 is installed, w ithin 100 Engine Hours (EH) after the effective date of this AD, ins pect the P3 air pipe and the RH rear half-wall in accordance with the in structions of MSB N° 319 75 4810 issue B. For engines that are already installed on a helicop ter and on which a RH rear half-wall P/N 0319 99 82 40 is being instal led, upon installation of this part, inspect the P3 air pipe and the RH rear halfwall in accordance with the instructions of Turbome ca Mandatory Service Bulletin (MSB) N° 319 75 4810 issue B. (2) If, during the inspection required by paragraph (1) of this AD, both the P3 air pipe and the RH rear half-wall are found und amaged, and the distance between the P3 air pipe and the RH rear ha lf-wall is less than 0.5 mm, repeat the inspection as required by paragr aph (1) of this AD at intervals not to exceed 100 EH. (3) If, during an inspection as required by paragra phs (1) or (2) of this AD, the RH rear half-wall is found damaged, or the P3 a ir pipe interferes with RH rear half-wall, before next flight, install a RH rear half-wall P/N 0319 99 008 0 in accordance with the instructions o f Turbomeca MSB N° 319 75 4810 issue B. (4) If, during an inspection as required by paragra phs (1) or (2) of this AD, P3 air pipe is found damaged, before next flight, i nstall a serviceable P3 air pipe and verify that the distance between P3 air pipe and RH rear half-wall is equal to or greater than 0.5 mm, in accordance with the instructions of Turbomeca MSB N° 319 75 4810 is sue B. Installation on an engine of a serviceable P3 air p ipe and verification that the distance between P3 air pipe and RH rear h alf-wall P/N 0319 99 82 40 is equal to or greater than 0.5 mm, consti tutes terminating action for the repetitive inspections required by p aragraph (2) of thisEASA AD No : 2011-0182R1

EASA Form 110 Page 3/3 AD for that engine. (5) Modification of an engine by installation of a RH rear half-wall P/N 0319 99 008 0 constitutes terminating action for th e repetitive inspections required by paragraph (2) of this AD fo r that engine. (6) After modification of an engine as specified in paragraph (5) of this AD, do not install a RH rear half-wall P/N 0319 99 82 40 on that engine. (7) From the effective date of this AD, do not inst all a RH rear half-wall P/N 0319 99 82 40 on an engine or an engine with a RH rear half-wall P/N 0319 99 82 40 on a helicopter, unless in compli ance with the requirements of this AD. (8) Engines already installed on a helicopter, that have been inspected and, depending on findings, corrected, before 06 Oc tober 2011 [the effective date of the original issue of this AD], i n accordance with the instructions of Turbomeca MSB N° 319 75 4810 at iss ue A, are compliant with the requirements of paragraphs (1), (2), (3) and (4) of this AD, provided that, after the inspection, the e ngine has not been removed from that helicopter.

Ref. Publications: TURBOMECA Mandatory Service Bull etin N°. 319 75 4810 issue B, dated 25 January 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 original issue of this AD was posted on 22 J uly 2011 as PAD 11-076 for consultation until 19 August 2011. The C omment Response Document can be found at http://ad.easa.europa.eu/

. 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 questions concerning the technical conte nt of the requirements in this AD, please contact: Turboméca, S.A., ARRIUS Customer Support, 40220 TAR NOS, FRANCE. Fax: +33 5 59 74 45 15; or contact your nea rest technical representative at www.turbomeca-support.com