[Federal Register Volume 75, Number 221 (Wednesday, November 17, 2010)]
[Rules and Regulations]
[Pages 70098-70101]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-27980]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0522; Directorate Identifier 2010-CE-022-AD;
Amendment 39-16506; AD 2010-23-17]
RIN 2120-AA64
Airworthiness Directives; Various Aircraft Equipped With Rotax
Aircraft Engines 912 A Series Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) issued 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:
This Airworthiness Directive (AD) results from reports of cracks
in the engine crankcase. Austro Control GmbH (ACG) addressed the
problem by issuing AD No 107R3 which was superseded by ACG AD A-
2004-01.
The present AD supersedes the ACG AD A-2004-01. On one hand,
introduction by Rotax of an optimized crankcase assembly has
permitted to reduce applicability of the new AD, when based on
engines' serial numbers (s/n). On the other hand, applicability is
extended for some engines that may have been fitted with certain
crankcase s/n, supplied as spare parts.
In addition, accomplishment instructions given through the
relevant Service Bulletins (SB) have been detailed to better locate
engine's areas that are to be scrutinised.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective December 22, 2010.
On December 22, 2010, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in this
AD.
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at Document Management Facility, U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC
20590.
For service information identified in this AD, contact BRP-
Powertrain GMBH & Co KG, Welser Strasse 32, A-4623 Gunskirchen,
Austria; phone: (+43) (0) 7246 601-0; fax: (+43) (0) 7246 6370;
Internet: http://www.rotax.com. You may review copies of the 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.
FOR FURTHER INFORMATION CONTACT: Sarjapur Nagarajan, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329-4145; fax: (816) 329-4090 e-
mail: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on May 21, 2010 (75 FR
28504). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
This Airworthiness Directive (AD) results from reports of cracks
in the engine crankcase. Austro Control GmbH (ACG) addressed the
problem by issuing AD No 107R3 which was superseded by ACG AD A-
2004-01.
The present AD supersedes the ACG AD A-2004-01. On one hand,
introduction by Rotax of an optimized crankcase assembly has
permitted to reduce applicability of the new AD, when based on
engines' serial numbers (s/n). On the other hand, applicability is
extended for some engines that may have been fitted with certain
crankcase s/n, supplied as spare parts.
In addition, accomplishment instructions given through the
relevant Service Bulletins (SB) have been detailed to better locate
engine's areas that are to be scrutinised.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comment received.
Request To Change AD 2002-16-26
Robert Seton of Rotech Research Canada Ltd. requested information
regarding if AD 2006-16-26 would be changed to incorporate the same
terminating action specified in this AD. We infer that he wants us to
supersede
[[Page 70099]]
AD 2002-16-26 with a new AD that incorporates the same terminating
action. Mr. Seton also commented there was confusion regarding the
starting serial number range for the new crankcase.
We agree with the comment that AD 2002-16-26 should be superseded.
AD 2002-16-26 does address the same unsafe condition, but that AD
applies to a different group of products. On October 4, 2010, AD 2010-
20-23, Amendment 39-16458 (75 FR 61046, October 4, 2010) was published
and is effective on November 8, 2010. AD 2010-20-23 supersedes AD 2002-
16-26 and added the following 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.
The wording for the applicable starting S/N for the terminating action
in AD 2010-20-23 is slightly different than what was in the proposed
rulemaking for this final rule AD. To clarify the starting S/N for the
terminating action, we changed the starting S/N in this final rule AD
action to match AD 2010-20-23.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the AD.
Costs of Compliance
We estimate that this AD will affect 60 products of U.S. registry.
We also estimate that it will take about 3 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour.
Based on these figures, we estimate the cost of this AD to the U.S.
operators to be $15,300, or $255 per product.
In addition, we estimate that any necessary follow-on actions will
take about 20 work-hours and require parts costing $6,500, for a cost
of $8,200 per product. We have no way of determining the number of
products that may need these actions.
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 AD will not have federalism implications
under Executive Order 13132. This AD will 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 AD:
(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) 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD Docket.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; 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 the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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:
2010-23-17 Various Aircraft: Amendment 39-16506; Docket No. FAA-
2010-0522; Directorate Identifier 2010-CE-022-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
22, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all serial numbers (S/N) of the following
aircraft, equipped with a Rotax Aircraft Engines 912 A series engine
with a crankcase assembly S/N up to and including S/N 27811,
certificated in any category:
[[Page 70100]]
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Type certificate holder Aircraft model Engine model
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Aeromot-Industria Mecanico Metalurgica AMT-200........................ 912 A2
ltda.
Diamond Aircraft Industries............. HK 36 R ``SUPER DIMONA''....... 912 A
Diamond Aircraft Industries GmbH........ HK 36 TS....................... 912 A3
HK 36 TC....................... 912 A3
Diamond Aircraft Industries Inc......... DA20-A1........................ 912 A3
HOAC-Austria............................ DV 20 KATANA................... 912 A3
Iniziative Industriali Italiane S.p.A... Sky Arrow 650 TC............... 912 A2
SCHEIBE-Flugzeugbau GmbH................ SF 25C......................... 912 A2 or 912 A3
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Subject
(d) Air Transport Association of America (ATA) Code 72: Engine.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
This Airworthiness Directive (AD) results from reports of cracks
in the engine crankcase. Austro Control GmbH (ACG) addressed the
problem by issuing AD No 107R3 which was superseded by ACG AD A-
2004-01.
The present AD supersedes the ACG AD A-2004-01. On one hand,
introduction by Rotax of an optimized crankcase assembly has
permitted to reduce applicability of the new AD, when based on
engines' serial numbers (s/n). On the other hand, applicability is
extended for some engines that may have been fitted with certain
crankcase s/n, supplied as spare parts.
In addition, accomplishment instructions given through the
relevant Service Bulletins (SB) have been detailed to better locate
engine's areas that are to be scrutinised.
The aim of this AD is to ensure that the requested engine power
is available at any time to prevent a sudden loss of power that
could lead to a hazardous situation in a low altitude phase of
flight.
The MCAI requires inspecting certain crankcases for cracks and
replacing the crankcase if cracks are found.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) Within the next 50 hours time-in-service (TIS) after
December 22, 2010 (the effective date of this AD), inspect the
engine crankcase for cracks following Rotax Aircraft Engines Service
Bulletin SB-912-029 R3, dated July 11, 2006. Repetitively thereafter
do the inspection at each 100-hour, annual, or progressive
inspection or within 110 hours TIS since last inspection, whichever
occurs first.
(2) If cracks in the engine crankcase are found during any
inspection required by paragraph (f)(1) of this AD, before further
flight, replace the crankcase following Rotax Aircraft Engines
Service Bulletin SB-912-029 R3, dated July 11, 2006.
(3) Installing a crankcase that has a S/N above 27811 terminates
the inspection requirements of paragraph (f)(1) of this AD.
Note 1: The service information is a combined service bulletin
for both the 912 type (Service Bulletin SB-912-029 R3, dated July
11, 2006) and 914 type (Service Bulletin SB-914-018, Revision 3,
dated July 11, 2006) engines. This AD does not reference Service
Bulletin SB-914-018, Revision 3, dated July 11, 2006, because this
AD does not apply to the 914 series engines. This unsafe condition
for the 914 type engines is the subject of AD 2010-20-23.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) 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: Sarjapur Nagarajan, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4145; fax: (816) 329-4090; e-
mail: [email protected]. 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.
(3) Reporting Requirements: For any reporting requirement in
this AD, a federal agency may not conduct or sponsor, and a person
is not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
Special Flight Permit
(h) 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.
Related Information
(i) Refer to MCAI EASA AD No.: 2007-0025, dated February 1,
2007, for related information.
Material Incorporated by Reference
(j) You must use Rotax Aircraft Engines Service Bulletin SB-912-
029 R3, dated July 11, 2006, to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact BRP-
Powertrain GMBH & Co KG, Welser Strasse 32, A-4623 Gunskirchen,
Austria; phone: (+43) (0) 7246 601-0; fax: (+43) (0) 7246 6370;
Internet: http://www.rotax.com.
(3) You may review copies of the referenced service information
at the FAA, Small Airplane Directorate, 901 Locust, Kansas City,
Missouri 64106. For information
[[Page 70101]]
on the availability of this material at the FAA, call (816) 329-
4148.
(4) You may also review copies of the service information
incorporated by reference for this AD at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Kansas City, Missouri, on November 1, 2010.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-27980 Filed 11-16-10; 8:45 am]
BILLING CODE 4910-13-P