EASA AD No.: 2015-0240

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Airworthiness Directive

AD No.: 2015-0240

Issued: 18 December 2015

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation 

(EC) 216/2008 on behalf of the European Union, 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 Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (EU) 1321/2014 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 [Regulation (EU) 1321/2014 Annex I,

Part M.A.303] or agreed with the Authority of the State of Registry [Regulation (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

Effective Date: 04 January 2016

TCDS Number(s): EASA.E.121 and EASA.E.122

Foreign AD: Not applicable

Supersedure: None

ATA 72 – Engine – Engine Cylinder Head – Inspection / Replacement 

Manufacturer(s):

BRP-Powertrain GmbH & Co. KG (previously BRP-Rotax GmbH & Co. KG; Bombardier-Rotax GmbH & 

Co. KG; Bombardier-Rotax GmbH)

Applicability:

Rotax 912 A1, 912 A2, 912 A3 and 912 A4 engines, up to serial number (s/n) 4 411 086 inclusive, 

Rotax 912 F2, 912 F3 and 912 F4 engines, up to s/n 4 413 044 inclusive, Rotax 912 S2, 912 S3 and 

912 S4 engines, up to s/n 4 924 910 inclusive, and Rotax 914 F2, 914 F3 and 914 F4 engines, up to 

s/n 4 421 444 inclusive.

These engines are known to be installed on, but not limited to, the types and models aeroplanes as 

listed in Appendix 1 of this AD. The installation of these engines was either done by the respective 

aircraft manufacturer or through modification of the aircraft by Supplemental Type Certificate.

Reason:

A design change of the engine cylinder heads was introduced by BRP-Powertrain in March 2013 

which modifies the engine/aircraft interfaces by substituting the previous cylinder head 

temperature (CHT) measurement (limit temperature 135°C/150°C) with a coolant temperature (CT) 

measurement (limit temperature 120°C). 

The design change was communicated on 15 May 2013 by BRP-Powertrain Service Instruction (SI) 

912-020R7/914-022R7 (single document) but was not identified by a change of the engine model 
EASA AD No.: 2015-0240

TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified.

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designation or of the engine P/N, but only through the cylinder head P/N and the position of the 

temperature sensor.

Consequently, engines with the new cylinder heads (installed during production or replaced inservice during maintenance) may be installed on an aircraft without concurrent modification of that 

aircraft, instructions for which should be provided by the Type Certificate (TC) holder or 

Supplemental Type Certificate (STC) holder, as applicable. In this case, the coolant temperature with 

a maximum engine operating limit of 120°C (valid for engines operated with water diluted glycol 

coolant) is displayed on a CHT indicator with a typical limit marking (red radial/range) of more than 

120°C. 

This condition, if not detected and corrected, will prevent the pilot to identify coolant limit 

exceedances, with subsequent loss of coolant (120°C is the boiling temperature of the coolant), 

which could lead to engine in-flight shut-down, possibly resulting in a forced landing, with 

consequent damage to the aircraft and injury to occupants.

BRP-Powertrain published revised SI-912-020R8/914-022R8 to clarify that, on the new cylinder 

heads, the coolant temperature, instead of the cylinder head temperature in the aluminium, is 

measured. EASA issued SIB 2014-34 to raise awareness that installation of affected engines and 

spare parts, without concurrent incorporation of aircraft TC/STC holder approved modifications,

and even if unintended and unnoticed by production or maintenance, constitutes an unapproved 

aircraft modification.

Since EASA published the SIB, further investigation has finally determined that sufficient reason 

exists to warrant AD action.

For the reason stated above, this AD requires a one-time inspection to determine the actual engine 

configuration and, depending on findings, engine reidentification and (depending on TC or STC 

holder installation) modification of the affected aircraft. This also affects engines that are operated 

with waterless coolant.

Required Action(s) and Compliance Time(s):

Required as indicated, unless accomplished previously:

Within 6 months after the effective date of this AD, accomplish the actions as required by 

paragraphs (1) and (2) of this AD.

(1) Inspect the engine to determine whether a cylinder head, having a P/N as listed in Table 1 of 

this AD, is installed. A review of aircraft- and/or engine maintenance records is acceptable to 

make the determination as required by this paragraph, provided those records can be relied 

upon for that purpose.

Note 1: for the purpose of this AD, a “pre-mod engine” is an engine with cylinder head P/N that are 

not included in Table 1 of this AD.
EASA AD No.: 2015-0240

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Note 2: Engines listed in Table 2 of this AD were delivered as post-mod, but were not properly 

re-identified, and are therefore known to be affected. Other s/n engines may have had a 

replacement post-mod cylinder head installed in service at any time after 01 March 2013.

Table 1 – Post-mod Cylinder Head P/N and position

Engine Cylinder Head P/N

912 A, 912 F and 914 F P/N 413235 or P/N 413236 on cylinder head position 2/3

912 S P/N 413185 on cylinder head position 2/3

Table 2 – Known Affected Engines

Engine Serial Number

912 A S/N 4 410 982 up to S/N 4 411 086 inclusive

912 F S/N 4 413 020 up to S/N 4 413 044 inclusive

912 S S/N 4 924 544 up to S/N 4 924 910 inclusive

914 F S/N 4 421 178 up to S/N 4 421 444 inclusive

Table 3 – Post-mod Engines re-identified during production

Engine Serial Number

912 A S/N 4 411 087 and up

912 F S/N 4 413 045 and up

912 S S/N 4 924 911 and up

914 F S/N 4 421 445 and up

(2) If, during the inspection as required by paragraph (1) of this AD, a cylinder head is found 

installed on position 2 or 3, having a P/N listed in Table 1 of this AD, accomplish the actions 

specified in paragraphs (2.1), (2.2) or (2.3) of this AD, as applicable.

(2.1) For an engine having cylinder heads, with P/N listed in Table 1 of this AD, installed on 

both positions 2 and 3, change the designation of that engine in accordance with the 

instructions of BRP-Powertrain SB-912-068/SB-914-049.

(2.2) For an engine having one cylinder head, with P/N listed in Table 1 of this AD, installed on 

a single position (2 or 3), replace the cylinder head installed on the unchanged position 

(3 or 2, as applicable) with a cylinder head having a P/N listed in Table 1 of this AD, and 

concurrently change the designation of that engine in accordance with the instructions 

of BRP-Powertrain SB-912-068/SB-914-049.

(2.3) For an affected engine installed on an aircraft according to aircraft TC or STC, as 

applicable, contact the design (change) approval holder for approved modification 
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instructions, and accomplish those instructions accordingly. Table 4 of this AD provides a 

list of approved aircraft modification instructions that are acceptable to comply with this 

requirement.

Table 4 – Available Aircraft Service Publications

Type / model(s) SB

Aquila AT01 SB-AT01-029

TECNAM P92, P2002 and P2006T aeroplanes SB-183-CS

TECNAM P2008 JC aeroplanes SB-185-CS

Diamond H 36 “Dimona” and HK 36 “Super Dimona” aeroplanes OSB 36-111

Diamond DV 20 “Katana” aeroplanes OSB 20-066

Diamond (Canada) DA20-A1 “Katana” aeroplanes SB Da20-72-04

M&D AVO 68 “Samburo” aeroplanes TM 808-31

Scheibe SF 25 C and SF 36 R SI_02-14

(3) Modification of an aircraft by installing a post-mod engine (see Note 1 of this AD) in 

accordance with an approved STC is acceptable to comply with the requirements of paragraph 

(2.3) of this AD for that aircraft.

(4) Modification of an aircraft to limit the CHT indication to 120°C is an acceptable altenative 

method to comply with the requirements of paragraph (2.3) of this AD for that aircraft, 

provided this is accomplished by using approved aircraft modification instructions from the 

applicable design (change) approval holder (see Note 3 of this AD).

Note 3: For the purpose of this AD, a modification to limit the CHT indication to 120°C includes an 

assessment by the applicable design (change) approval holder that the CHT does not exceed 120°C 

when the aircraft is operated within its approved envelope.

(5) From the effective date of this AD, the use of waterless coolant (with a temperature limitation 

higher than 120°C) is no longer authorised for post-mod engines. The applicable 

BRP-Powertrain engine installation manual has been amended accordingly .

(6) From the effective date of this AD, it is allowed to install on a pre-mod engine (see Note 1 of 

this AD) cylinder heads having a P/N listed in Table 1 of this AD, provided such action is 

authorised by the applicable design (change) approval holder of the aircraft on which the 

engine is (to be) installed, that these cylinder heads are installed on both positions 2 and 3 

and, concurrently with that installation, the engine designation is changed in accordance with 

the instructions of BRP-Powertrain SB-912-068/SB-914-049. 

(7) From the effective date of this AD, it is allowed to install on an aircraft a post-mod engine (see 

Note 1 of this AD), provided that this is accomplished by using approved aircraft modification 

instructions from the applicable design (change) approval holder (see Note 3 of this AD).
EASA AD No.: 2015-0240

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(8) From the effective date of this AD, do not install on any post-mod engine (see Note 1 of this 

AD) a cylinder head, having a P/N not listed in Table 1 of this AD, in any position as indicated 

in Table 1 of this AD, unless that installation is accomplished in accordance with approved 

instructions provided by BRP-Powertrain.

Ref. Publications:

BRP Powertrain SB-912-068/SB-914-049, original issue, dated 16 April 2015.

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. Based This AD was posted on 09 November 2015 as PAD 15-138 for consultation until 30 November 

2015. The Comment Response Document can be found at http://ad.easa.europa.eu.

3. Enquiries regarding this AD should be referred to the EASA Safety Information Section,

Certification Directorate. E-mail: ADs@easa.europa.eu. 

4. For any question concerning the technical content 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.
EASA AD No.: 2015-0240

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Appendix 1 – List of Aeroplanes known to have Rotax engine(s) installed, either done by 

the respective aircraft manufacturer or through modification of the aircraft by 

Supplemental Type Certificate

Type Certificate Holder Type/model

Aero AT SP z.o.o. AT-3R100

Aeromot-Indústria MecânicoMetalúrgicaAMT-200 “Super Ximango” and AMT-300 “Turbo Super 

Ximango”

Aircraft Design and Certification Ltd. D4 “Fascination”

Aquila Aviation GmbH Aquila AT01

Cessna Aircraft Company 150 and A150 aeroplanes (and Reims F150 and FA150), 

modified by various STC

Costruzioni Aeronautiche TECNAM S.r.l. P92, P2002, P2006T and P2008 JC

Czech Sport Aircraft A.S. PS-28 “Cruiser”

Diamond Aircraft Industries GmbH H 36 “Dimona”, HK 36 “Super Dimona” and DV 20 “Katana”

Diamond Aircraft Industries Inc. DA20-A1 “Katana”

E.I.S. Aircraft GmbH RF 5 “Sperber”

Evektor spol. s.r.o. EV-97 VLA, SportStar RTC

Flight - Design CTLS-ELA

Grob Aircraft AG G109

Issoire Aviation APM-20 “Lionceau”

M&D Flugzeugbau GmbH & Co. KG AVO 68 aeroplanes “Samburo”

Magnaghi Aeronautica S.p.A. Sky Arrow 650 TC, 650 TCN, 650 TCNS and 710 RG

Korff Luftfahrt Taifun 17 E II

S.C. Constructii Aeronautice IAR-46, IS-28M2/GR

Scheibe Aircraft GmbH SF 25 C, SF 36 R

Skyfox Aviation CA-25N

Sportavia Puetzer RF-9 ABS

Stemme AG S10-VT, ASP S15-1, TSA-M S6