E ASA AD No.: 20 13

- 0205

TE.CAP.0011 0

- 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

. : 20 1 3

- 0205

Date: 09 September 201 3

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 E U 748/2012 , Part 21

. A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness o f 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].


### Design Approval Holder’s Name:

EUROCOPTER Type/Model designation(s):

A S 355 helicopters

TCDS Number: EASA. R. 146

F oreign AD: Not applicable

Su persedure: None



### ATA 28 Fuel

– FUELTRON Flowmeter Installation

– Removal

Manufacturer(s): Eurocopter (formerly Eurocopter France

, Aerospatiale )

Applicability: ECUREUIL AS355 E

, AS355 F

, AS355 F1

, AS355 F2 helicopters, all serial numbers with modifica tion 350A070791 embodied in production (installation of the FUELTRON flowmeter) , except those with modification 355A085801 embodied in production



### .

Reason: An occurrence has been reported where, a fter landing of an AS355 helicopter,

an uncontrolled flame

- o ut of engine No. 1 occurred . A nalysis results revealed that a particle contamination ha d obstructed the FUELTRON flowmeter

. This contamination may have been introduced during refuelling of the helicopter

. Th e obstruction was due to the cross

- section of the passage area of the flowmeter being smaller than the meshes in the upstream fuel pump strainer. Consequently , the particles could pass through the strainer and then created the obstruction in the FUELTRON flowmeter. The affected FUELTRON flowmeter installa tion is identical on the two engines.

This condition ( simultaneous obstruction of both flowmeters for both engines )

, if not detected and corrected

, could lead to the flame

- out of both engines in flight , possibly resulting in reduced control of the helicop ter

. For the reasons described above, this AD requires to remove and disable the FUELTRON flowmeter installation

. This AD is considered an interim action, pending the development of a modification

.

Effective Date: 23 September 2013E ASA AD No.: 20 13

- 0205

TE.CAP.0011 0

- 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 A ction(s)

an d Compliance Time(s) : Required as indicated, unless previously accomplished: (1) Within 5 month or 750 Flight Hours , whichever occurs first a fter the effective date of this AD

, accomplish the following actions concurrently in accordance with the instructio ns of Eurocopter Alert Service Bulletin (ASB) AS355

- 28.00.20 : (1.1) Remove the FUELTRON flowmeter Part N umber (P/N) 704A37

- 670

- 001 and modify the fuel system ; and (1.2) Disable the electrical wiring connections related to the flowmeter installation. (2 ) From the effective date of this AD, do not install a FUELTRON flowmeter P/N 704A37

- 670

- 001 on any helicopter.

Note: Precautions to prevent fuel contamination during refuelling can be found in Eurocopter Information Notice No. 2145

- I

- 28 and work card 20.0 7.02.208.

Ref. Publications: Eurocopter ASB AS355

- 28.00.20 dated 06 June 2013. The use of later approved revisions of th i s 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. This AD was posted on 20 June 2013 as PAD 13

- 085 for consultation until 18 July 2013

. No comments were received during the consultation period

. 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 technical conte nt of the requirements in this AD, please contact: EUROCOPTER (STDI)

– Aéroport d e Marseille Provence , 13725 Marignane Cedex, France ; t e l ephone +33 (4) 12 85 97 97 ; facsimile +33 (4) 85 99 66; E

- mail: Directive.technical

- support@eurocopter.com

.