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 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 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 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 [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2011-0182 superseded EASA AD 2008-0134R1 dated 17 February 2009. 

ATA 73 Engine Fuel & Control - P3 Air Pipe – Inspection / Modification 

Manufacturer(s): Turbomeca 

Applicability: ARRIUS 2F turboshaft engines, all serial 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 bulkhead 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 Engineering Department 

concluded that the tolerance of assembly established during the design 

could result in some rubbing between parts. 

This condition, if not detected and corrected, could lead to chafing 

between the pipe and the bulkhead and consequent rupture of the P3 air 

pipe, prompting the fuel control system to go to idle which could result in 

reduced control of the helicopter. 

To address this unsafe condition, EASA issued AD 2008-0134 to require 

the inspection of the P3 air pipe (first section) and 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 wording. It emphasized 

that, under some circumstances, repetitive inspections 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 installation 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 than 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 inspections have be to 

accomplished again on engines that have already been inspected and 

corrected as required by AD 2008-0134R1. In addition, 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 which a RH rear halfwall P/N 0319 99 008 0 is installed (modification TF 80), repetitive 

inspections of the clearance between the P3 air pipe 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 Turbomeca 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 previously: 

(1) For engines that are already installed on a helicopter and on which a 

RH rear half-wall P/N 0319 99 82 40 is installed, within 100 Engine 

Hours (EH) after the effective date of this AD, inspect the P3 air pipe 

and the RH rear half-wall in accordance with the instructions of MSB 

N° 319 75 4810 issue B. 

For engines that are already installed on a helicopter and on which a 

RH rear half-wall P/N 0319 99 82 40 is being installed, upon 

installation of this part, inspect the P3 air pipe and the RH rear halfwall in accordance with the instructions of Turbomeca 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 undamaged, and the 

distance between the P3 air pipe and the RH rear half-wall is less than 

0.5 mm, repeat the inspection as required by paragraph (1) of this AD 

at intervals not to exceed 100 EH. 

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

the RH rear half-wall is found damaged, or the P3 air 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 of Turbomeca MSB 

N° 319 75 4810 issue B. 

(4) If, during an inspection as required by paragraphs (1) or (2) of this AD, 

P3 air pipe is found damaged, before next flight, install 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 pipe and verification 

that the distance between P3 air pipe and RH rear half-wall P/N 0319 

99 82 40 is equal to or greater than 0.5 mm, constitutes terminating 

action for the repetitive inspections required by paragraph (2) of this 
EASA 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 the repetitive 

inspections required by paragraph (2) of this AD for 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 install 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 compliance with the 

requirements of this AD. 

(8) Engines already installed on a helicopter, that have been inspected 

and, depending on findings, corrected, before 06 October 2011 [the 

effective date of the original issue of this AD], in 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 engine has not been 

removed from that helicopter. 

Ref. Publications: TURBOMECA Mandatory Service Bulletin N°. 319 75 4810 issue B, dated 

25 January 2011. 

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. The original issue of this AD was posted on 22 July 2011 as PAD 

11-076 for consultation until 19 August 2011. The Comment 

Response Document can be found at http://ad.easa.europa.eu/. 

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 questions concerning the technical content of the 

requirements in this AD, please contact: 

Turboméca, S.A., ARRIUS Customer Support, 40220 TARNOS, 

FRANCE. Fax: +33 5 59 74 45 15; or contact your nearest technical 

representative at www.turbomeca-support.com