EASA AD No.: 2012-0019-E

EASA Form 111 Page 1/2

EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2012-0019-E

Date: 26 January 2012

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 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:

BRP-Powertrain GmbH & Co. KG

Type/Model designation(s):

Rotax 912 S2, 912 S3 and 914 F2 engines

TCDS Numbers : EASA.E.121, EASA.E.122

Foreign AD : Not applicable

Supersedure : None

ATA 78 Engine Oil – Oil Pump and Attachment Bolts – Inspection

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

Applicability: Rotax 912 S2 and 912 S3 engines, serial numbers (s/n) 4,924.287 to 4,924.295 

inclusive, 4,924.300 to 4,924.304 inclusive, 4,924.342 to 4,924.350 inclusive, 

4,924.352 and 4,924.353.

Rotax 914 F2 engines, s/n 4,421.079, 4,421.080 and 4,421.081.

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 and P2002-JF; 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 quality review, a deviation in the assembly process of the oil 

pump attachment bolts has been detected, which may have resulted in a latent 

defect on a limited number of engines. The affected bolts may not have been 

tightened to the correct torque value, i.e. not in accordance with the 

specification.
EASA AD No.: 2012-0019-E

EASA Form 111 Page 2/2

This condition, if not corrected, could lead to oil leaks and irregularities in the oil 

supply, possibly resulting in uncommanded in-flight engine shutdown and forced 

landing, damage to the aeroplane and injury to occupants.

For the reasons described above, this AD requires a one-time inspection of the 

oil pump installation and a torque check of the oil pump attachment bolts and, 

depending on findings, corrective action(s).

This AD also prohibits installation of an affected engine on an aeroplane, unless

the oil pump installation and the attachment bolts of that engine have passed 

the inspection and torque check as required by this AD.

Effective Date: 27 January 2012

Required Action(s) 

and Compliance

Time(s)

Required as indicated, unless accomplished previously:

(1) Within 4 flight hours or 30 days, whichever occurs first after the effective 

date of this AD, accomplish an engine oil system inspection and a torque 

check of the oil pump attachment bolts, in accordance with the instructions 

of Section 3 of BRP-Powertrain Alert Service Bulletin (ASB) ASB-912-060

or ASB-914-043, as applicable to engine type.

(2) If, during the inspection as required by paragraph (1) of this AD, 

discrepancies are detected, before next flight, accomplish all applicable 

(depending on findings) follow-on inspections and corrective actions in 

accordance with the instructions of Section 3 of BRP-Powertrain ASB-912-

060 or ASB-914-043, as applicable to engine type.

(3) From the effective date of this AD, do not install an engine, identified by s/n 

in the Applicability of this AD, on an aeroplane, unless that engine has been 

inspected as required by paragraph (1) of this AD and, depending on 

findings, corrected as required by paragraph (2) of this AD.

Ref. Publications: BRP-Powertrain ASB-912-060 and ASB-914-043 (same document),

dated 26 January 2012.

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 safety assessment has requested not to implement the full consultation 

process and an immediate publication and notification.

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.