81 FR 14804 - Airworthiness Directives; BRP-Powertrain GmbH & Co KG Reciprocating Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 53 (March 18, 2016)

We propose to adopt a new airworthiness directive (AD) for certain BRP-Powertrain GmbH & Co KG Rotax 912 F2, 912 F3, 912 F4, 912 S2, 912 S3, 912 S4, 914 F2, 914 F3, and 914 F4 reciprocating engines. This proposed AD was prompted by a design change introduced by the manufacturer that relocated the engine cylinder head temperature sensor to a different location and converted it to a coolant temperature sensor. This proposed AD would require re-identification of the engine model and concurrent modification of the aircraft to indicate the maximum coolant temperature limit. We are proposing this AD to prevent exceeding engine coolant temperature limits, which could result in loss of engine coolant, damage to the engine, and loss of control of the airplane.

[Federal Register Volume 81, Number 53 (Friday, March 18, 2016)]
[Proposed Rules]
[Pages 14804-14806]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-06118]



[[Page 14804]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-2042; Directorate Identifier 2016-NE-02-AD]
RIN 2120-AA64


Airworthiness Directives; BRP-Powertrain GmbH & Co KG 
Reciprocating Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain BRP-Powertrain GmbH & Co KG Rotax 912 F2, 912 F3, 912 F4, 912 
S2, 912 S3, 912 S4, 914 F2, 914 F3, and 914 F4 reciprocating engines. 
This proposed AD was prompted by a design change introduced by the 
manufacturer that relocated the engine cylinder head temperature sensor 
to a different location and converted it to a coolant temperature 
sensor. This proposed AD would require re-identification of the engine 
model and concurrent modification of the aircraft to indicate the 
maximum coolant temperature limit. We are proposing this AD to prevent 
exceeding engine coolant temperature limits, which could result in loss 
of engine coolant, damage to the engine, and loss of control of the 
airplane.

DATES: We must receive comments on this proposed AD by May 17, 2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, 
Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: 202-493-2251.
    For service information identified in this NPRM, contact BRP-
Powertrain GmbH & Co KG, Rotaxstrasse 1, A-4623 Gunskirchen, Austria; 
Internet: http://www.FLYROTAX.com. You may view this service 
information at the FAA, Engine & Propeller Directorate, 1200 District 
Avenue, Burlington, MA. For information on the availability of this 
material at the FAA, call 781-238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
2042; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the mandatory continuing airworthiness 
information (MCAI), the regulatory evaluation, any comments received, 
and other information. The address for the Docket Office (phone: 800-
647-5527) is in the ADDRESSES section. Comments will be available in 
the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7754; fax: 781-
238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-2042; 
Directorate Identifier 2016-NE-02-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2015-0240, dated December 18, 2015 (referred to hereinafter as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    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 [deg]C/150 [deg]C) with a 
coolant temperature (CT) measurement (limit temperature 120 [deg]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 
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 in-service 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 the supplemental type certificate (STC) 
holder, as applicable. In this case, the coolant temperature with a 
maximum engine operating limit of 120 [deg]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 [deg]C.

    BRP-Powertrain GmbH & Co KG introduced a design change that 
relocated the engine cylinder head temperature sensor from the top of 
the cylinder to a new location and converted it to a coolant 
temperature sensor. The coolant temperature maximum engine operating 
limit is now less than the cylinder head temperature maximum operating 
limit. You may obtain further information by examining the MCAI in the 
AD docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-2042.

Related Service Information Under 1 CFR Part 51

    BRP-Powertrain GmbH & Co KG has issued Service Bulletin (SB) SB-
912-068/SB-914-049 (one document), dated April 16, 2015. The service 
information describes procedures for re-identification of the type 
plate for certain BRP-Powertrain GmbH & Co KG Rotax 912 and 914 
engines. This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section of this 
NPRM.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of 
Austria, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the European Community, EASA has 
notified us of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all information provided by EASA and determined the unsafe 
condition exists and is likely to exist or develop on other products of 
the same type design. This proposed AD would require re-identification 
of the engine model and

[[Page 14805]]

the concurrent modification of the aircraft to indicate maximum coolant 
temperature limit.

Costs of Compliance

    We estimate that this proposed AD affects about 40 engines 
installed on aircraft of U.S. registry. We also estimate that it would 
take about 5 hours per engine to inspect and re-identify the type 
plate. The average labor rate is $85 per hour. Based on these figures, 
we estimate the cost of this proposed AD on U.S. operators to be 
$17,000.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

BRP-Powertrain GmbH & Co KG (formerly BRP-Rotax GmbH & Co KG, 
Bombardier-Rotax GmbH & Co. KG, and Bombardier-Rotax GmbH): Docket 
No. FAA-2016-2042; Directorate Identifier 2016-NE-02-AD.

(a) Comments Due Date

    We must receive comments by May 17, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to BRP-Powertrain GmbH & Co KG Rotax model 912 
F2, 912 F3, 912 F4, 912 S2, 912 S3, 912 S4, 914 F2, 914 F3, and 914 
F4 reciprocating engines with a cylinder head that has a part number 
(P/N) listed in Figure 1 to paragraph (c) of this AD and that is 
installed in position 2 or 3.

Figure 1 to Paragraph (c) of This AD--Post-Modification Cylinder Head P/
                                    N
------------------------------------------------------------------------
          Engine model                       Cylinder head P/N
------------------------------------------------------------------------
912 F2, 912 F3, 912 F4, 914 F2,   P/N 413235 or P/N 413236.
 914 F3, and 914 F4.
912 S2, 912 S3, and 912 S4......  P/N 413185.
------------------------------------------------------------------------

(d) Reason

    This AD was prompted by a design change introduced by the 
manufacturer that relocated the engine cylinder head temperature 
sensor to a new location and converted it to a coolant temperature 
sensor. We are issuing this AD to prevent exceeding coolant 
temperature limits, which could result in loss of engine coolant, 
damage to the engine, and loss of control of the airplane.

(e) Actions and Compliance

    Comply with this AD within 6 months after the effective date of 
this AD, unless already done.
    (1) For engines with cylinder heads that have a P/N listed in 
Figure 1 to paragraph (c) of this AD installed on both position 2 
and position 3, change the engine model designation on the engine 
type data plate to include a ``-01'' suffix. Use paragraph 3.1.1 of 
BRP-Powertrain Service Bulletin (SB) SB-912-068/SB-914-049, dated 
April 16, 2015, to make this change.
    (2) For engines with only one cylinder head having a P/N listed 
in Figure 1 to paragraph (c) of this AD installed in position 2 or 
3, do one of the following:
    (i) Replace the cylinder heads having P/Ns listed in Figure 1 to 
paragraph (c) of this AD with a P/N 623682 cylinder head on Rotax 
912 F2, 912 F3, 912 F4, 914 F2, 914 F3, and 914 F4 engines and with 
a P/N 623687 cylinder head on Rotax 912 S2, 912 S3, and 912 S4 
engines. If you complete the actions in paragraph (e)(2)(i), no 
further action is required. Or,
    (ii) Install eligible cylinder heads with P/Ns identified in 
Figure 1 to paragraph (c) of this AD on both cylinder head positions 
2 and 3 and change the engine model designation of the engine type 
data plate in accordance with paragraph (e)(1) of this AD.
    (3) For engines re-identified in accordance with paragraph 
(e)(1) or (e)(2)(ii) of this AD, before further flight, modify the 
aircraft cockpit instrumentation and related documentation to 
indicate a maximum coolant temperature limit of 120 degrees Celsius 
using FAA-approved procedures. These re-identified engines remain 
eligible for installation on approved aircraft-engine combinations.

(f) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request. You may email your request to: [email protected].

(g) Related Information

    (1) For more information about this AD, contact Robert Green, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7754; fax: 781-238-7199; email: [email protected].
    (2) For more information about the installation modifications 
described in paragraph (e)(3) of this AD, contact Jim Rutherford, 
Aerospace Engineer, FAA, Small

[[Page 14806]]

Airplane Directorate, 901 Locust Ave. Room 301, Kansas City, MO; 
phone: 816-329-4165; fax: 816-329-4090; email: 
[email protected].
    (3) Refer to MCAI European Aviation Safety Agency, AD 2015-0240, 
dated December 18, 2015, for more information. You may examine the 
MCAI in the AD docket on the Internet at http://www.regulations.gov 
by searching for and locating it in Docket No. FAA-2016-2042.
    (4) BRP-Powertrain GmbH & Co KG Service Bulletin (SB) SB-912-
068/SB-914-049 (one document), dated April 16, 2015, can be obtained 
from BRP-Powertrain GmbH & Co KG, using the contact information in 
paragraph (g)(6) of this proposed AD.
    (5) The following aircraft service information contains FAA-
approved procedures for complying with paragraph (e)(3) of this AD 
and can be obtained from BRP-Powertrain GmbH & Co. KG, using the 
contact information in paragraph (g)(6) of this proposed AD:

  Figure 2 to Paragraph (g) of This AD--Aircraft Type/Model and Service
                               Information
------------------------------------------------------------------------
             Type/model(s)                              SB
------------------------------------------------------------------------
Aquila AT01............................  SB-AT01-029
TECNAM P92, P2002 and P2006T...........  SB-183-CS
TECNAM P2008 JC........................  SB-185-CS
Diamond H 36 ``Dimona'' and HK 36        OSB 36-111
 ``Super Dimona''.
Diamond DV 20 ``Katana''...............  OSB 20-066
Diamond (Canada) DA20-A1 ``Katana''....  SB Da20-72-04
M&D AVO 68 ``Samburo''.................  TM 808-31
Scheibe SF 25 C and SF 36 R............  SI_02-14
------------------------------------------------------------------------

    (6) For service information identified in this proposed AD, 
contact BRP-Powertrain GmbH & Co. KG, Rotaxstrasse 1, A-4623 
Gunskirchen, Austria; phone: +43 7246 6010; fax: +43 7246 601 9130; 
email: [email protected]; Internet: www.rotax-aircraft-engines.com.
    (7) You may view this service information at the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on March 11, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-06118 Filed 3-17-16; 8:45 am]
 BILLING CODE 4910-13-P