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[Federal Register Volume 81, Number 59 (Monday, March 28, 2016)]
[Proposed Rules]
[Pages 17109-17111]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-06279]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-4878; Directorate Identifier 2016-CE-001-AD]
RIN 2120-AA64

Airworthiness Directives; Various Aircraft Equipped With BRP-
Powertrain GmbH & Co KG 912 A Series Engine

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
various aircraft equipped with a BRP-Powertrain GmbH & Co KG (formerly 
Rotax Aircraft Engines) 912 A series engine. This proposed AD results 
from mandatory continuing airworthiness information (MCAI) originated 
by an aviation authority of another country to identify and correct an 
unsafe condition on an aviation product. The MCAI describes the unsafe 
condition as a design change of the engine cylinder head temperature 
sensor without a concurrent revision of the engine model designation, 
the engine part number, or the cockpit indication to the pilot. We are 
issuing this proposed AD to require actions to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by May 12, 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.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
BRP-Powertrain GmbH & Co. KG, Welser Strasse 32, A-4623 Gunskirchen, 
Austria; phone: +43 7246 601 0; fax: +43 7246 601 9130; Internet: 
www.rotax-aircraft-engines.com. You may review this referenced service 
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas 
City, Missouri 64106. For information on the availability of this 
material at the FAA, call (816) 329-4148.

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-
4878; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (telephone (800) 647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Jim Rutherford, Aerospace Engineer, 
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4165; fax: (816) 329-4090; email: 
jim.rutherford@faa.gov.

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-2016-4878; 
Directorate Identifier 2016-CE-001-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 because of those comments.
    We will post all comments we receive, without change, to http://regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about 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 AD 
No.: 2015-0240, dated December 18, 2015, 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

[[Page 17110]]

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 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.
    This condition, if not detected and corrected, will prevent the 
pilot to identify coolant limit exceedances, with subsequent loss of 
coolant (120 [deg]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.

You may examine the MCAI on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2016-4878.

Related Service Information Under 1 CFR Part 51

    BRP-Powertrain GmbH & CO KG has issued Rotax Aircraft Engines BRP 
Service Bulletin SB-912-068 and SB-914-049 (co-published as one 
document), dated April 16, 2015. The service information describes 
procedures for re-identifying the engine that has new cylinder heads, 
part numbers 413235 and 413236 installed. 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 the Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have 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 and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design.

Costs of Compliance

    We estimate that this proposed AD would affect 65 products of U.S. 
registry.
    We also estimate that it would take about 1 work-hour per product 
to comply with the engine re-identification requirement of this 
proposed AD. The average labor rate is $85 per work-hour.
    Based on these figures, we estimate the cost of this portion of 
this proposed AD on U.S. operators to be $5,525, or $85 per product.
    We also estimate that it would take about 1 work-hour per product 
to comply with the engine installation modification to indicate a 
Maximum Coolant Temperature requirement of this proposed AD. The 
average labor rate is $85 per work-hour.
    Based on these figures, we estimate the cost of this portion of 
this proposed AD on U.S. operators to be $5,525, or $85 per product.
    We also estimate that it would take about 1.5 work-hours per 
product to comply with the cylinder head replacement option of this 
proposed AD. The average labor rate is $85 per work-hour. Required 
parts would cost about $2,500 to replace a single engine cylinder head.
    Based on these figures, we estimate the cost of this portion of 
this proposed AD on U.S. operators to be $2,627.50 per engine cylinder 
head.

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, 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 AD:

Various Aircraft: Docket No. FAA-2016-4878; Directorate Identifier 
2016-CE-001-AD.

[[Page 17111]]

(a) Comments Due Date

    We must receive comments by May 12, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all serial numbers of the airplanes listed in 
table 1 of paragraph (c) of this AD, that are:
    (1) Equipped with a BRP-Powertrain GmbH & Co KG (formerly Rotax 
Aircraft Engines) 912 A series engine with a part number (P/N) 
413235 or 413236 cylinder head installed in position 2 or 3; and
    (2) certificated in any category.

              Table 1 of Paragraph (c)--Affected Airplanes
------------------------------------------------------------------------
   Type certificate holder         Aircraft model        Engine model
------------------------------------------------------------------------
Aeromot-Ind[uacute]stria       AMT-200..............              912 A2
 Mec[acirc]nico-
 Metal[uacute]rgica Ltda.
Diamond Aircraft Industries..  HK 36 R ``SUPER                     912 A
                                DIMONA''.
DIAMOND AIRCRAFT INDUSTRIES    HK 36 TS and HK 36 TC              912 A3
 GmbH.
Diamond Aircraft Industries    DA20-A1..............              912 A3
 Inc.
HOAC-Austria.................  DV 20 KATANA.........              912 A3
Iniziative Industriali         Sky Arrow 650 TC.....              912 A2
 Italiane S.p.A.
SCHEIBE-Flugzeugbau GmbH.....  SF 25C...............      912 A2, 912 A3
------------------------------------------------------------------------

(d) Subject

    Air Transport Association of America (ATA) Code 72: Engine--
Reciprocating.

(e) Reason

    This AD was prompted by design change of the engine cylinder 
head temperature sensor without a concurrent revision of the engine 
model designation, the engine part number, or the cockpit indication 
to the pilot. The sensor now measures the coolant temperature rather 
than the cylinder head temperature. If the engine coolant 
temperature with a maximum engine operating limit of 120 [deg]C is 
displayed on a Cylinder Head Temperature indicator with a typical 
limit marking greater than 120 [deg]C, the pilot will be unable to 
identify coolant temperature limit exceedances. This could result in 
loss of coolant, which could cause an inflight engine shutdown and 
forced landing.

(f) Actions and Compliance

    Unless already done, do the following actions:
    (1) Within 6 months after the effective date of this AD, for 
engines with cylinder heads listed in paragraph (c)(1) 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 following paragraph 3.1.1) of the Accomplishment/Instructions 
in Rotax Aircraft Engines BRP Service Bulletin SB-912-068 and SB-
914-049 (co-published as one document), dated April 16, 2015.
    (2) Within 6 months after the effective date of this AD, for 
engines with only one cylinder head listed paragraph (c)(1) of this 
AD installed in a position 2 or 3, in order to keep such cylinder 
installed, you must replace the cylinder head installed on the 
unchanged position (2 or 3, as applicable) with a cylinder head 
having a P/N listed in paragraph (c)(1) of this AD, and change the 
engine model designation on the engine type data plate to include a 
``-01'' suffix following paragraph 3.1.1) of the Accomplishment/
Instructions in Rotax Aircraft Engines BRP Service Bulletin SB-912-
068 and SB-914-049 (co-published as one document), dated April 16, 
2015.
    (3) Before further flight after doing the required actions in 
paragraphs (f)(1) or (f)(2) of this AD as applicable, modify the 
aircraft and related documentation to indicate a Maximum Coolant 
Temperature limit of 120 [deg]C using FAA-approved procedures.
    (i) Such procedures can be found by contacting your aircraft 
type certificate holder or the FAA contact specified in paragraph 
(g)(1) of this AD. The service documents referenced in paragraph (h) 
of this AD are examples of FAA-approved procedures for the 
applicable aircraft.
    (ii) These re-identified engines remain eligible for 
installation on approved aircraft-engine combinations.
    (4) As of the effective date of this AD, do not install any 
other P/N cylinder head unless that installation is done following 
approved instructions provided by BRP-Powertrain at the address 
provided in paragraph (h) of this AD.

(g) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, FAA, has the authority to approve AMOCs for this 
AD, if requested using the procedures found in 14 CFR 39.19. Send 
information to ATTN: Jim Rutherford, Aerospace Engineer, FAA, Small 
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4165; fax: (816) 329-4090; email: 
jim.rutherford@faa.gov. Before using any approved AMOC on any 
airplane to which the AMOC applies, notify your appropriate 
principal inspector (PI) in the FAA Flight Standards District Office 
(FSDO), or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(h) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 
2015-0240, dated December 18, 2015; Rotax Aircraft Engines BRP 
Service Bulletin SB-912-066 R1/SB-914-047 R1 (published as one 
document), Revision 1, dated April 23, 2015; Diamond Aircraft 
Industries GmbH Optional Service Bulletin OSB 36-111, dated 
September 17, 2015; Diamond Aircraft Industries GmbH Work 
Instruction WI-OSB 36-111, dated September 17, 2015; Diamond 
Aircraft Service Bulletin No.: DA20-72-04, dated January 22, 2015; 
Diamond Aircraft Industries GmbH Optional Service Bulletin OSB 20-
066, dated September 17, 2015; Diamond Aircraft Industries GmbH Work 
Instruction WI-OSB 20-066, dated September 17, 2015; and Scheibe 
Aircraft GmbH Service Information 02/14-1, dated December 15, 2014, 
for related information. You may examine the MCAI on the Internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2016-4878. For service information related to this AD, contact 
BRP-Powertrain GmbH & Co. KG, Welser Strasse 32, A-4623 Gunskirchen, 
Austria; phone: +43 7246 601 0; fax: +43 7246 601 9130; Internet: 
http://www.rotax-aircraft-engines.com. You may review this 
referenced service information at the FAA, Small Airplane 
Directorate, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
(816) 329-4148.

    Issued in Kansas City, Missouri, on March 10, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-06279 Filed 3-25-16; 8:45 am]
 BILLING CODE 4910-13-P
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