EASA AD No.: 2011-0039

EASA Form 111 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0039

Date: 08 March 2011

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 applic able ADs. Consequently, no person may opera te an aircraft to which an AD applies, except in accordance with th e requirements of that AD, unless otherwise specified by the Ag ency [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) exemptio n]. 

### Type Approval Holder’s Name :
Austro Engine GmbH Type/Model designation(s) :

E4 engines

TCDS Number : EASA.E.200

Foreign AD : Not applicable.

Supersedure : This AD super sedes EASA Emergency AD 2010-0206-E dated 08 October 2010.



### ATA 73 Engine Fuel & Control – High Pressure Fuel Pump – Inspection / Replacement

Manufacturer(s): Austro Engine GmbH

Applicability: Model E4 engines, all serial numbers. These engines are known to be installed on, but not limited to, Diamond Aircraft Industries DA 40 NG and DA 42 NG aeroplanes.
Reason: Several power loss events have been reported, due to rail pressure control failures. Analyses have shown that hi gh pressure (HP) fuel pumps P/N E4A30-100-000 failed as a result of pressure oscillations in the fuel supply line. This condition, if not detected and correc ted, could lead to further cases of power loss or even in-flight engine shutdown, possibly resulting in loss of control of the aeroplane. To address this situation, Austro Engine had introduced an additional inspection of the affected HP fuel pum ps. As an interim measure, pending the availability of a final solution, EASA Emergency AD 2010- 0206-E was issued to require repetitive inspections of t he HP fuel pump supply line(s) to detect fuel pressure oscillations and, if this exceeded a certain value, replacement of the affected HP fuel pump. Austro Engine has now introduced a new HP fuel pump P/N E4A-30-200-000 that is no longer affected by pressure oscillations in the fuel supply line. For the reasons described above, this AD retains the requirements of EASA AD 2010-0206-E, which is superseded, and requires replacement of all P/N E4A-30-100-000 HP fuel pumps with the new P/N E4A-30-200-000 pumps.EASA AD No.: 2011-0039

EASA Form 111 Page 2/3 Effective Date: 22 March 2011

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Initially at the time indicated in Table 1 of this AD, as applicable, and thereafter intervals not to exceed 55 f light hours (FH), inspect the HP fuel pump in accordance with the instructions of Austro Engine Mandatory Service Bulletin (MSB) MSB-E4-009 and the associated Austro Engine Work Instruction (WI) WI-MSB-E4-009.
Note : AD 2010-0206-E required the inspection to be accomplished at each scheduled 50 FH inspection. As this inspection has been removed from the engine Maintenance Manual AE 300 E4.08.04, the interval has been amended in this new AD.

Table 1
Time accumulated by the HP fuel pump [on 12 October 2010, the effective date of AD 2010- 0206-E] since new: Compliance Time:

45 FH or more Within 10 FH after 12 October 2010 [the effective date of AD 2010-0206-E]
Less than 45 FH Before accumulating 55 FH

(2) If, during any inspection as required by paragraph (1) of this AD, the fuelpressure oscillation exceeds the value as specified in Austro Engine MSBE4-009, before next flight, replace the HP fuel pump with a new unit in accordance with the instructions of Austro Engine MSB-E4-009. (3) Unless accomplished as required by paragraph (2) of this AD, within 4 months after the effective date of this AD, replace each HP fuel pump P/N E4A-30-100-000 with a new P/N E4A-30-200-000 pump, in accordance with the instructions of Austro Engine MSB MSB-E4-009/2 and the Maintenance Manual E4.08.04. (4) Modification of an engine as required by paragraph (3) of this AD constitutes terminating action for the r epetitive inspection requirements of paragraph (1) of this AD. (5) After modification of an engine as required by paragraph (3) of this AD, do not install a HP fuel pump P/N E4A-30-100-000 on that engine. (6) After the effective date of this AD, do not install an E4 engine on an aeroplane, unless it has been determi ned that a P/N E4A-30-200-000 HP fuel pump is installed on that engine.
Ref. Publications: Austro Engine GmbH MSB-E4-009/2 dated 04 March 2011 and WI-MSB-E4-009 dated 07 October 2010. Austro Engine GmbH Maintenance Manual AE 300 E4.08.04, Revision 5, dated 27 January 2011. The use of later approved revisions of these documents 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 required actions and the risk a llowance have granted the issuance ofEASA AD No.: 2011-0039

EASA Form 111 Page 3/3 a Final AD with Request for Comments, postponing the public consultation process after publication. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification 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: Austro Engine GmbH, Rudolf-Diesel-Straße 11, A-2700 Wiener Neustadt, Austria Telephone: +43 2622 23000 2525 Fax: +43 2622 23000-2711 E-mail: service@austroengine.at The referenced publications can be downloaded directly from the Austro Engine GmbH Service Bulletin webpage

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