Airworthiness Directives; Bombardier-Rotax GmbH Type 912 F, 912 S, and 914 F Series Reciprocating Engines, 17632-17637 [2010-7831]
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17632
Federal Register / Vol. 75, No. 66 / Wednesday, April 7, 2010 / Proposed Rules
TABLE 1—LIST OF AFFECTED SHAFTS
Engine series
Trent
Trent
Trent
Trent
Trent
Trent
Trent
Trent
Trent
Trent
Trent
Trent
Trent
Trent
800
800
800
800
800
800
800
800
800
800
800
800
700
700
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Affected component
1–8
1–4
1–4
1–4
1–8
1–8
1–4
1–4
1–8
1–8
1–8
1–8
1–8
1–8
IP Compressor Shaft ......
HP Compressor Shaft .....
HP Compressor Shaft .....
HP Compressor Shaft .....
IP Compressor Shaft ......
IP Compressor Shaft ......
HP Compressor Shaft .....
HP Compressor Shaft .....
IP Compressor Shaft ......
IP Compressor Shaft ......
IP Compressor Shaft ......
IP Compressor Shaft ......
IP Compressor Shaft ......
IP Compressor Shaft ......
Other FAA AD Provisions
(f) Alternative Methods of Compliance
(AMOCs): The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Related Information
(g) Refer to MCAI EASA Airworthiness
Directive 2009–0021 (Corrected 09 February,
2009), dated February 6, 2009, for related
information.
(h) Contact James Lawrence, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: james.lawrence@faa.gov;
telephone (781) 238–7176; fax (781) 238–
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on
March 31, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0342; Directorate
Identifier 2002–NE–08–AD]
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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.
Use one of the following
addresses to comment on this proposed
AD.
• Federal eRulemaking Portal: Go to
https://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.
ADDRESSES:
BILLING CODE 4910–13–P
RIN 2120–AA64
Airworthiness Directives; BombardierRotax GmbH Type 912 F, 912 S, and
914 F Series Reciprocating Engines
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
15:16 Apr 06, 2010
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DATES: We must receive any comments
on this proposed AD by June 7, 2010.
[FR Doc. 2010–7830 Filed 4–6–10; 8:45 am]
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Shaft serial No.
MW0115238 ...........................
MW0115512 ...........................
MW0004708 ...........................
MW00063868 .........................
DN65507 ................................
DN65158 ................................
MW0125467 ...........................
DN65189 ................................
MW0091518 ...........................
MW0126365 ...........................
DN66422 ................................
MW0203314 ...........................
DN63228 ................................
MW0026046 ...........................
Compliance
period
(flight cycles in
service after
December 4,
2008.)
750
750
2000
2500
2500
2500
3500
3500
3500
3500
4750
4750
3250
4500
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 https://
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 https://
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Federal Register / Vol. 75, No. 66 / Wednesday, April 7, 2010 / Proposed Rules
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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 BombardierRotax engines in Europe.
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.
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-inservice (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.
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
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.
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.
Authority for This Rulemaking
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,
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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
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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.
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Federal Register / Vol. 75, No. 66 / Wednesday, April 7, 2010 / Proposed Rules
List of Subjects in 14 CFR Part 39
Comments Due Date
Air transportation, Aircraft, Aviation
safety, Safety.
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by June 7,
2010.
The Proposed Amendment
Affected ADs
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
proposes to amend 14 CFR part 39 as
follows:
(b) This AD supersedes AD 2002–16–26,
Amendment 39–12865.
Applicability
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–12865 (67 FR
53296, August 15, 2002) and by adding
a new airworthiness directive, to read as
follows:
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Bombardier-Rotax GmbH (formerly Rotax,
Motorenfabrik): Docket No. FAA–2010–
0342; Directorate Identifier 2002–NE–
08–AD.
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(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
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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.
BILLING CODE 4910–13–P
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EP07AP10.001
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Federal Register / Vol. 75, No. 66 / Wednesday, April 7, 2010 / Proposed Rules
Federal Register / Vol. 75, No. 66 / Wednesday, April 7, 2010 / Proposed Rules
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.
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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
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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
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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)
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17636
Federal Register / Vol. 75, No. 66 / Wednesday, April 7, 2010 / Proposed Rules
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2010–0085; Airspace
Docket No. 10–ACE–1]
Proposed Amendment of Class E
Airspace; Cherokee, IA
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: This action proposes to
amend Class E airspace at Cherokee, IA.
Decommissioning of the Pilot Rock nondirectional beacon (NDB) at Cherokee
County Regional Airport has made this
action necessary for the safety and
management of Instrument Flight Rules
(IFR) operations at the airport.
DATES: Comments must be received on
or before May 24, 2010.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, 1200
New Jersey Avenue, SE., West Building,
Ground Floor, Room W12–140,
Washington, DC 20590–0001. You must
identify the docket number FAA–2010–
0085/Airspace Docket No. 10–ACE–1, at
the beginning of your comments. You
may also submit comments through the
Internet at https://www.regulations.gov.
You may review the public docket
containing the proposal, any comments
received, and any final disposition in
person in the Dockets Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Office (telephone 1–800–647–
5527), is on the ground floor of the
building at the above address.
FOR FURTHER INFORMATION CONTACT:
Scott Enander, Central Service Center,
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15:16 Apr 06, 2010
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Operations Support Group, Federal
Aviation Administration, Southwest
Region, 2601 Meacham Blvd., Fort
Worth, TX 76137; telephone: (817) 321–
7716.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments, as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket numbers and be submitted in
triplicate to the address listed above.
Commenters wishing the FAA to
acknowledge receipt of their comments
on this notice must submit with those
comments a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket No. FAA–2010–0085/Airspace
Docket No. 10–ACE–1.’’ The postcard
will be date/time stamped and returned
to the commenter.
Availability of NPRMs
An electronic copy of this document
may be downloaded through the
Internet at https://www.regulations.gov.
Recently published rulemaking
documents can also be accessed through
the FAA’s Web page at https://
www.faa.gov/airports_airtraffic/
air_traffic/publications/airspace
amendments/.
Additionally, any person may obtain
a copy of this notice by submitting a
request to the Federal Aviation
Administration (FAA), Office of Air
Traffic Airspace Management, ATA–
400, 800 Independence Avenue, SW.,
Washington, DC 20591, or by calling
(202) 267–8783. Communications must
identify both docket numbers for this
notice. Persons interested in being
placed on a mailing list for future
NPRM’s should contact the FAA’s
Office of Rulemaking (202) 267–9677, to
request a copy of Advisory Circular No.
11–2A, Notice of Proposed Rulemaking
Distribution System, which describes
the application procedure.
The Proposal
This action proposes to amend Title
14, Code of Federal Regulations (14
CFR), Part 71, by amending Class E
airspace extending upward from 700
feet above the surface for standard
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17637
instrument approach procedures at
Cherokee County Regional Airport,
Cherokee, IA. Airspace reconfiguration
is necessary due to the
decommissioning of the Pilot Rock NDB
and the cancellation of the NDB
approach. Adjustment to the geographic
coordinates would be made in
accordance with the FAAs National
Aeronautical Charting Office. Controlled
airspace is needed for the safety and
management of IFR operations at the
airport.
Class E airspace areas are published
in Paragraph 6005 of FAA Order
7400.9T, dated August 27, 2009, and
effective September 15, 2009, which is
incorporated by reference in 14 CFR
71.1. The Class E airspace designation
listed in this document would be
published subsequently in the Order.
The FAA has determined that this
proposed regulation only involves an
established body of technical
regulations for which frequent and
routine amendments are necessary to
keep them operationally current. It,
therefore, (1) is not a ‘‘significant
regulatory action’’ under Executive
Order 12866; (2) is not a ‘‘significant
rule’’ under DOT Regulatory Policies
and Procedures (44 FR 11034; February
26, 1979); and (3) does not warrant
preparation of a Regulatory Evaluation
as the anticipated impact is so minimal.
Since this is a routine matter that will
only affect air traffic procedures and air
navigation, it is certified that this rule,
when promulgated, will not have a
significant economic impact on a
substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the U.S. Code. 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. This rulemaking is
promulgated under the authority
described in Subtitle VII, Part A,
Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it would
amend controlled airspace at Cherokee
County Regional Airport, Cherokee, IA.
List of Subjects in 14 CFR Part 71
Airspace, Incorporation by reference,
Navigation (Air).
E:\FR\FM\07APP1.SGM
07APP1
Agencies
[Federal Register Volume 75, Number 66 (Wednesday, April 7, 2010)]
[Proposed Rules]
[Pages 17632-17637]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-7831]
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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 https://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 https://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 https://
[[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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(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]
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