EASA AD No.: 2013-0117-E

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EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2013-0117-E

Date: 30 May 2013

Note: This Emergency 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 EU 748/2012, Part 21.A.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].

Design Approval Holder’s Name:

BRP-POWERTRAIN GmbH & Co. KG

Type/Model designation(s):

Rotax 912 and 914 engines

TCDS Number: EASA.E.121 and EASA E.122

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA Emergency AD 2013-0055-E dated 06 March 2013.

ATA 72 Engine – Cylinder Head Section – Inspection / Replacement

Manufacturer(s): BRP-Powertrain GmbH & Co. KG, BRP-Rotax GmbH & Co. KG; BombardierRotax GmbH & Co. KG; Bombardier-Rotax GmbH

Applicability: Rotax 912 A1, 912 A2, 912 A3 and 912 A4 engines, Rotax 912 F2, 912 F3 and 

912 F4 engines, Rotax 912 S2, 912 S3 and 912 S4 engines, and Rotax 914 F2, 

914 F3 and 914 F4 engines, all serial numbers (s/n).

These engines are known to be installed on, but not limited to, the following 

types of aeroplanes: 3-i Sky Arrow 650 TC, 650 TCN, 650 TCNS and 710 RG; 

Aeromot AMT-200 Super Ximango and AMT-300 Turbo Super Ximango; 

Aircraft Philipp (formerly Alpla-Werke; Nitsche) AVO 68 series Samburo; 

Aquila AT01; Cessna 150 and A150 series and (Reims) F150 and FA150 

series; Diamond (formerly HOAC) H 36 Dimona, HK 36 series Super Dimona, 

DV 20 Katana and DA20-A1 Katana; Evektor-Aerotechnik EV-97 VLA; Grob 

G 109; Issoire APM-20 Lionceau; Scheibe SF 36R and SF 25C; Stemme S10-

VT; Tecnam P 92-J, P 92-JS, P2002-JR, P2002-JS and P2006T; W.D. Aircraft 

D4 Fascination.

Note: The installation of these engines was either done by the respective 

aeroplane manufacturer or through modification of the aeroplane by 

Supplemental Type Certificate.

Reason: During a production test run, a non-compliance of the installed cylinder head 

assembly of cylinder no. 2 and 3 (2/3) was detected, which may result in a 

latent defect on a limited number of engines. The affected cylinder heads may 

not have been manufactured in accordance with the specification.

This condition, if not detected and corrected, could lead to an oil leak in the 

intake channel in the area of the valve guide. The affected non-conforming 
EASA AD No.: 2013-0117-E

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cylinder heads may have small machined through holes, which can increase 

the oil consumption and can lead to oil starvation, possibly resulting in engine 

stoppage or in-flight engine shutdown and forced landing, with consequent risk 

of damage to the aeroplane and injury to occupants.

To address and correct this potential unsafe condition, EASA issued 

Emergency AD 2013-0055-E to require a one-time inspection of the affected 

cylinder head assemblies, known to be installed on certain s/n engines and, 

depending on findings, replacement of the cylinder head assembly.

Since that AD was issued, it was found that more engines are likely to have an 

affected cylinder head assembly installed than initially determined. In addition, it 

has been found that some affected cylinder head assemblies, identified by Part 

Number (P/N) 623682 and P/N 623687, have inadvertently been supplied as 

spares, between 31 January 2013 and 28 May 2013.

For the reasons described above, this AD retains the requirements of EASA AD 

2013-0055-E, which is superseded, but expands the Applicability to all engines, 

as it cannot be determined in which s/n engines the affected spare cylinder 

head assemblies are installed.

This AD also prohibits installation of an affected cylinder head assembly on an 

engine, or a replacement engine on an aeroplane, unless the affected cylinder 

head assembly of that engine is inspected as required by this AD.

Effective Date: 31 May 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 5 flight hours or 20 days, whichever occurs first after the effective 

date of this AD, accomplish the following actions:

(1.1) For engines identified by s/n in BRP-Powertrain Alert Service 

Bulletin (ASB) ASB-912-062R2 or ASB-914-044R2 (published as a 

single document), inspect the cylinder head assembly of cylinder no. 

2 and 3 (2/3) in accordance with the instructions of Section 3 of 

BRP-Powertrain ASB-912-062/ASB-914-044.

(1.2) For all engines, determine whether a cylinder head assembly P/N 

623682 or P/N 623687, supplied by BRP-Powertrain between

31 January 2013 and 28 May 2013, is installed on the engine as 

replacement part. A review of engine maintenance records is 

acceptable to make the determination as specified in this paragraph, 

provided those records can be relied upon for that purpose, and the

supply date and P/N of the cylinder head assembly can be 

conclusively identified from that review.

(2) If, during the determination as required by paragraph (1.2) of this AD, an 

affected cylinder head assembly is found to be installed, before next flight, 

inspect the cylinder head assembly in accordance with the instructions of 

Section 3 of BRP-Powertrain ASB-912-062/ASB-914-044.

(3) If, during an inspection as required by paragraph (1.1) or paragraph (2) of 

this AD, as applicable, excessive deposits (oil or carbon) are found on one 

of the spark plugs, before next flight, replace the affected cylinder head 

assembly with a serviceable one in accordance with the instructions of 

Section 3 of BRP-Powertrain ASB-912-062/ASB-914-044.

(4) From the effective date of this AD, do not install any affected engine (type 

and s/n as listed in BRP-Powertrain ASB-912-062R2/ASB-914-044R2) on 

an aeroplane, unless that engine has been inspected and, depending on 

findings, corrected as required by this AD.

(5) From the effective date of this AD, installation on an engine of an affected 

spare cylinder head assembly P/N 623682 or P/N 623687, supplied 

between 31 January 2013 and 28 May 2013, is allowed, provided that, 
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within 5 FH after installation, the engine (cylinder head assembly) is 

inspected and, depending on findings, corrected as required by this AD.

Ref. Publications: BRP-Powertrain ASB-912-062R2 and ASB-914-044R2 (published as a single 

document), dated 29 May 2013.

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 results of the safety assessment have indicated the need for 

immediate publication and notification, without the full public consultation 

process.

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 aspects of the requirements in 

this AD, please contact: BRP-Powertrain GmbH & Co. KG,

Telephone: +43 7246 601 0; Fax: +43 7246 601 9130;

E-mail: airworthiness@brp.com, Website www.rotax-aircraft-engines.com.