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[Federal Register: April 7, 2010 (Volume 75, Number 66)]
[Proposed Rules]               
[Page 17632-17637]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07ap10-17]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0342; Directorate Identifier 2002-NE-08-AD]
RIN 2120-AA64

 
Airworthiness Directives; Bombardier-Rotax GmbH Type 912 F, 912 
S, and 914 F Series Reciprocating Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for certain serial numbers (S/Ns) of Bombardier-Rotax 
GmbH type 912 F and 914 F series reciprocating engines. That AD 
currently requires initial and repetitive visual inspections of the 
engine crankcase for cracks. This proposed AD would require those same 
inspections, would add the 912 S series to the affected population, add 
a test procedure to determine the engine suitability for a special 
flight permit, and would change applicability from engine S/N to 
crankcase S/N. This proposed AD results from an increase in the 
affected crankcase population. We are proposing this AD to prevent oil 
loss caused by cracks in the engine crankcase, which could lead to in-
flight failure of the engine and forced landing.

DATES: We must receive any comments on this proposed AD by June 7, 
2010.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     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.
    Contact BRP-Rotax GmbH & Co. KG, Welser Strasse 32, A-4623 
Gunskirchen, Austria, for the service information identified in this 
proposed AD.

FOR FURTHER INFORMATION CONTACT: Richard Woldan, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7136; fax (781) 238-7199.

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-2010-0342; 
Directorate Identifier 2002-NE-08-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. Using the search 
function of the Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You may review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://[[Page 17633]]www.regulations.gov; 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 AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is the same as 
the Mail address provided in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

Discussion

    On August 7, 2002, the FAA issued AD 2002-16-26, Amendment 39-12865 
(67 FR 53296, August 15, 2002). That AD requires initial visual 
inspection for cracks in the engine crankcase of certain S/N engines, 
within 50 hours time-in-service (TIS) after the effective date of that 
AD, and repetitive visual inspections at each 100-hour, annual, or 
progressive inspection, or within 110 hours TIS since last inspection, 
whichever occurs first. If any cracks are found, the engine must be 
replaced. Austro Control GmbH (ACG), which is the airworthiness 
authority for Austria, notified the FAA that an unsafe condition may 
exist on certain S/Ns of Bombardier-Rotax GmbH type 912 F and 914 F 
series reciprocating engines. Austro Control GmbH advises that they 
have received reports of about 100 engine crankcases found cracked in 
service worldwide over the past 10 years. To date, no engine failures 
due to cracks in the crankcase were reported. However, ACG has 
determined that an engine could fail due to oil loss from a cracked 
crankcase. This condition, if not corrected, could result in an 
inflight failure of the engine and forced landing.

Actions Since AD 2002-16-26 Was Issued

    Since that AD was issued, we determined that the affected crankcase 
population has increased, requiring us to expand the applicability of 
the AD. We also learned that Bombardier-Rotax has introduced a new 
design crankcase assembly that is not susceptible to the cracking 
issue. The introduction of the new crankcase design allows us to limit 
this proposed AD applicability to those crankcases with a S/N of 27811 
or below, and to provide an optional terminating action to the 
repetitive inspections required by AD 2002-16-26.

Relevant Service Information

    We have reviewed and approved the technical contents of Rotax 
Aircraft Engines Mandatory Service Bulletins (MSBs) SB-912-029, 
Revision 3, dated July 11, 2006, and SB-914-018, Revision 3, dated July 
11, 2006, that describe procedures for inspecting the crankcase for 
cracks. The European Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Community, has 
classified these service bulletins as mandatory and issued EASA 
Airworthiness Directive 2007-0025, dated February 1, 2007 to ensure the 
airworthiness of these Bombardier-Rotax engines in Europe.

Differences Between the Proposed AD and the Service Information

    Rotax Aircraft Engines MSBs specify applicability by engine S/N and 
replacement crankcase S/N. This proposed AD would specify applicability 
by crankcase S/N only.

Bilateral Agreement Information

    Bombardier-Rotax GmbH type 912 F, 912 S, and 914 F series 
reciprocating engines are manufactured in Austria, and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, ACG has kept the FAA informed of the 
situation described above. The FAA has examined the findings of ACG, 
reviewed all available information, and determined that AD action is 
necessary for products of this type design that are certificated for 
operation in the United States.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. We are proposing this AD, which would require 
initial visual inspection for cracks in the engine crankcase of certain 
S/N crankcases, within 50 hours time-in-service (TIS) after the 
effective date of this AD, and repetitive visual inspections at each 
100-hour, annual, or progressive inspection, or within 110 hours TIS 
since last inspection, whichever occurs first. If any engine crankcase 
cracks are found, replace the engine before further flight. The 
proposed AD would require that you do these actions using the service 
information described previously.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 250 products of U.S. registry. We also estimate that 
it would take about 3 work-hours per inspection and 20 work-hours to 
replace the crankcase to comply with this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $6,500 
per crankcase. Based on these figures and an estimate of one crankcase 
replaced per year, we estimate the annual cost of the proposed AD on 
U.S. operators to be $68,100. Our cost estimate is exclusive of 
possible warranty coverage.

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 have 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 that the proposed AD:
    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); and
    3. Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

[[Page 17634]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 14 
CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-12865 (67 FR 
53296, August 15, 2002) and by adding a new airworthiness directive, to 
read as follows:

Bombardier-Rotax GmbH (formerly Rotax, Motorenfabrik): Docket No. 
FAA-2010-0342; Directorate Identifier 2002-NE-08-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by June 7, 
2010.

Affected ADs

    (b) This AD supersedes AD 2002-16-26, Amendment 39-12865.

Applicability

    (c) This airworthiness directive (AD) is applicable to 
Bombardier-Rotax GmbH type 912 F series, 912 S series, and 914 F 
series reciprocating engines that have a crankcase serial-numbered 
27811 or lower, installed. These engines are installed on, but not 
limited to, Aeromot-Industria Mecanico Metalurgica Itda AMT-300; 
Aquila Technische Entwiklugen GmbH AQUILA AT01; Diamond Aircraft 
Industries DA-20A1, Diamond Aircraft Industries GmbH Models HK36TC, 
HK36TTC, HK36TTC-ECO, and HK36TTS; Iniziative Industriali Italiane 
S.p.A. Sky Arrow 650 series; SCHEIBE-Flugzeugnau GmbH SF 25C; and 
Stemme S10-VT aircraft.

Unsafe Condition

    (d) This AD results from an increase in the affected engine 
crankcase population. We are issuing this AD to prevent oil loss 
caused by cracks in the engine crankcase, which could lead to in-
flight failure of the engine and forced landing.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Determining the Crankcase Serial Number (S/N)

    (f) Determine if your crankcase is affected by looking at the S/
N in the area indicated by XXX, following ``Made in Austria,'' as 
shown on Figure 2 of this AD. The marking is on both crankcase 
halves.

Initial Inspection

    (g) Within 50 hours time-in-service (TIS) from the effective 
date of this AD, perform a visual inspection as follows:
    (1) Inspect the engine crankcase (item 1, Figure 1 of this AD) 
for cracks, especially in the area of cylinder 1 upper side (item 
2), between cylinder 1 and 3 upper side (item 3), cylinder 4 lower-
right side (item 4) and detailed inspection in the area identified 
in Figure 2 (item 5) of this AD. Information concerning this 
inspection can be found in Bombardier-Rotax Mandatory Service 
Bulletins No. SB-912-029, Revision 3, dated July 11, 2006 and No. 
SB-914-018, Revision 3, dated July 11, 2006.
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[[Page 17635]]

[GRAPHIC] [TIFF OMITTED] TP07AP10.001


[[Page 17636]]


[GRAPHIC] [TIFF OMITTED] TP07AP10.002

BILLING CODE 4910-13-C
    (2) Cracks in crankcases of engines with a ROTAX cooling air 
baffle may not be easily visible, and oil leaks may be an indication 
of cracks. Visually inspect for oil leaks in areas of (item 2, 
Figure 1 of this AD) and (item 3).
    (3) If you find oil leaks, determine the source by either using 
a borescope or removing the object blocking the view such as the air 
baffle or accessory, and perform the inspection.
    (4) If the engine crankcase is cracked, replace the engine 
before further flight.

Repetitive Inspections

    (h) Visually inspect the engine crankcase (item 1, Figure 1 of 
this AD) for cracks at each 100-hour, annual, or progressive 
inspection, or within 110 hours TIS since last inspection, whichever 
occurs first, in accordance with paragraphs (g)(1) through (g)(4) of 
this AD.

Alternative Methods of Compliance

    (i) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Special Flight Permits

    (j) Under 14 CFR part 39.23, we are limiting the special flight 
permits for this AD by the following conditions if the crankcase is 
cracked or there is evidence of oil leakage from the crankcase:
    (1) Perform a leak check as follows:
    (i) Clean the crankcase surface to remove any oil.
    (ii) Warm up the engine to a minimum oil temperature of 50 
degrees C (120 degrees F). Information about warming up the engine 
can be found in the applicable line maintenance manual.
    (iii) Accelerate the engine to full throttle and stabilize at 
full throttle speed for a time period of 5 to 10 seconds. 
Information about performing a full throttle run can be found in the 
applicable line maintenance manual.
    (iv) Shutdown after running the engine at idle only long enough 
to prevent vapor locks in the cooling system and fuel system.
    (v) Inspect the crankcase for evidence of oil leakage. Oil 
wetting is permitted, but oil leakage of more than one drip in 3 
minutes after engine shutdown is not allowed.
    (2) Check the crankcase mean pressure to confirm that it is 1.46 
pounds-per-square inch gage (psig) (0.1 bar) or higher when checked 
at takeoff power to ensure proper return of oil from the crankcase 
to the oil tank. Information about checking crankcase mean pressure 
is available in the Lubrication System section of the applicable 
engine installation manual.
    (3) A ferry flight is not allowed if oil leakage exceeds one 
drip in 3 minutes or if crankcase mean pressure is below 1.46 psig.

Optional Terminating Action

    (k) Installing a crankcase that has a S/N above 27811 terminates 
the inspection requirements of paragraphs (g)(1) through (g)(4) and 
(h) of this AD.

Related Information

    (l) Contact Richard Woldan, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; telephone (781) 238-
7136; fax (781)

[[Page 17637]]

238-7199, for more information about this AD.
    (m) EASA airworthiness directive 2007-0025, dated February 1, 
2007, also addresses the subject of this AD.
    (n) Bombardier-Rotax Mandatory Service Bulletins No. SB-912-029, 
Revision 3, dated July 11, 2006 and No. SB-914-018, Revision 3, 
dated July 11, 2006, pertain to the subject of this AD. Contact BRP-
Rotax GmbH & Co. KG, Welser Strasse 32, A-4623 Gunskirchen, Austria, 
or go to rotax-aircraft-engines.com for a copy of this service 
information.

    Issued in Burlington, Massachusetts, on April 1, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-7831 Filed 4-6-10; 8:45 am]
BILLING CODE 4910-13-P
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