E ASA AD No.: 2013
- 0117
- E

TE. CAP.00 11 1
- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. 

## 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 S tates 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 7 48 /20 12 , 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: E ASA.E.121 and EASA E.122
F oreign 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, B RP
- Rotax GmbH & Co. KG; Bombardier
Rotax 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 91 4 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; Ai rcraft 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 - Aerote chnik 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 a eroplane 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 ass embl y of cylinder no. 2 and 3 (2/3) w as 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
- conformingE ASA AD No.: 2013
- 0117
- E

TE. CAP.00 11 1
- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. cylinder heads may have small machined through holes, which can increase the oil consumption an d 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 inspect ion of the affected cylinder head ass emblies , known to be in stalled 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 engine s are likely to hav e an affected cylinder head assembly installed than initially determined. In add ition, 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 spare s , between 31 January 2013 and 28 May 2013. For the reasons described above, this AD retai ns 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 ass embl y on an engine , or a replacement engine on an aeroplane , unless the affected cylinder head ass embly of that engine is inspected as required by this AD. Effective Date: 31 May 2013 Required A ction(s) and Compliance Time(s ) : Required as indicated, unless accomplished previously: (1) W ithin 5 flight hours or 20 days, whichever occurs first after the effective date of this AD, accomplish the following action s: (1.1) F or engines identified by s/n in BRP
- Powertrain Alert Servic e Bulletin (ASB) ASB
- 912
- 062R2 or ASB
- 914
- 044R2 (published as a single document), inspect the cylinder head ass embl y of cylinder no. 2 and 3 (2/3) in accordance wi th the instructions of Section 3 of BRP
- Powertrain ASB
- 912
- 062 / ASB
- 914
- 044. (1.2) For all eng ines, 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 , i s 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 require d 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 require d 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 accor dance 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 an y affected engine (type and s/n as listed in BRP
- Powertrain ASB
- 912
- 062R2/ASB
- 914
- 044R2 ) on an aeroplane , unless th at engine has been inspected and, depending on findings, corrected as required by this AD. (5) From the effective date of this AD, install ation on an engine of an affected spare cylinder head assembly P/N 623682 or P/N 623687, supplied between 31 January 2 013 and 28 May 2013 , is allowed, provided that,E ASA AD No.: 2013
- 0117
- E

TE. CAP.00 11 1
- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. within 5 FH after installation, the engine (cylinder head assembly) is inspected and, depending on findings, corrected as required by this AD

. Ref. Public ations: BRP
- Powertrain ASB
- 912
- 062 R2 and ASB
- 914
- 044 R 2 (published as a single document) , dated 29 May 2013

. The u se of later approved revisions of th i s docume nt 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 A D should be referred to the Safety Informati on 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 7 246 601 0; Fax: +43 7246 601 9130; E
- mail: airworthiness@brp.com , Website www.rotax
- aircraft
- engines.com

.