[Federal Register Volume 75, Number 60 (Tuesday, March 30, 2010)]
[Proposed Rules]
[Pages 15627-15629]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-7055]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 75, No. 60 / Tuesday, March 30, 2010 /
Proposed Rules
[[Page 15627]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0219; Directorate Identifier 2010-NE-14-AD]
RIN 2120-AA64
Airworthiness Directives; Turbomeca Astazou XIV B and XIV H
Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed 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: Investigation of an uncommanded in-flight shutdown (IFSD)
revealed that a third stage turbine wheel rupture was not contained by
the turbine casings. The released portion consisted of a turbine blade
together with the rim piece immediately below the blade. The rim piece
was bounded by two adjacent axial slots and a fatigue crack that had
developed between the holes in which the slots terminate. The slots and
holes, which are closed by riveted plugs, were introduced by
modification AB 173 in order to improve the vibration characteristics
of the turbine wheel. Modification AB 208 brings an improvement to
modification AB 173 by changing only the riveting detail. SN 283 72
0805 provides instructions for re-boring the holes at overhaul or
repair in order to improve their surface condition. A manufacturing
process modification has been introduced to improve the surface
condition of these holes in third stage turbine wheels. Wheels subject
to the improved manufacturing process have S/Ns outside the range
specified in Table 1. Although there is only one known event, and
although it resulted only in an uncommanded IFSD, with no damage to the
aircraft, the possibility exists that additional events may occur,
potentially involving damage to the aircraft.
We are proposing this AD to prevent uncontained failures of the
third stage turbine wheel, which could result in damage to the
helicopter.
DATES: We must receive comments on this proposed AD by April 29, 2010.
ADDRESSES: You may send comments by any of the following methods:
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 Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40
00, fax (33) 05 59 74 45 15, for the service information identified in
this proposed AD.
Examining the AD Docket
You may examine the AD docket on the Internet at http://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 proposed 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.
FOR FURTHER INFORMATION CONTACT: Kevin Dickert, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; telephone (781) 238-7117, 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-2010-0219;
Directorate Identifier 2010-NE-14-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).
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2010-0004, dated January 5, 2010 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
Investigation of an uncommanded IFSD revealed that a third stage
turbine wheel rupture was not contained by the turbine casings. The
released portion consisted of a turbine blade together with the rim
piece immediately below the blade. The rim piece was bounded by two
adjacent axial slots and a fatigue crack that had developed between
the holes in which the slots terminate. The slots and holes, which
are closed by riveted plugs, were introduced by modification AB 173
in order to improve the vibration characteristics of the turbine
wheel. Modification AB 208 brings an improvement to modification AB
173 by changing only the riveting detail. SB 283 72 0805 provides
instructions for re-boring the holes at overhaul or repair in order
to improve their surface condition. A manufacturing process
modification has been introduced to improve
[[Page 15628]]
the surface condition of these holes in third stage turbine wheels.
Wheels subject to the improved manufacturing process have S/Ns
outside the range specified in Table 1. Although there is only one
known event, and although it resulted only in an uncommanded IFSD,
with no damage to the aircraft, the possibility exists that
additional events may occur, potentially involving damage to the
aircraft.
To address the unsafe condition, EASA issued AD 2009-0136,
mandating inspection of certain third stage turbine wheels and
removal of any damaged wheel. The wheels to be inspected were those
whose cycles since new (CSN) would exceed 2,000 by February 1, 2011.
Following additional research by Turbomeca on crack initiation and
growth, this AD mandates inspections based on new criteria and
removal of any damaged wheel.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Turbomeca has issued Mandatory Service Bulletin No. 283 72 0804,
Version C, dated October 23, 2009. The actions described in this
service information are intended to correct the unsafe condition
identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of France
and is approved for operation in the United States. Pursuant to our
bilateral agreement with France, 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
provided by EASA and determined the unsafe condition exists and is
likely to exist or develop on other products of the same type design.
This proposed AD would require performing dye penetrant inspections for
cracks on the rear face of certain third stage turbine wheels with
fewer than 1,200 cycles-since-last-overhaul or repair, or since-new if
the engine has never been overhauled, on the effective date of the AD,
and removal of the third stage turbine wheel before further flight if
found cracked.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about three Astazou engines installed on products of U.S.
registry. We also estimate that it would take about 5 work-hours per
engine to comply with this proposed AD. The average labor rate is $85
per work-hour. We anticipate no parts to be required. Based on these
figures, we estimate the cost of the proposed AD on U.S. operators to
be $1,275.
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); 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 proposed AD and placed it in the AD docket.
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
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 adding the following new AD:
Turbomeca: Docket No. FAA-2010-0219; Directorate Identifier 2010-NE-
14-AD.
Comments Due Date
(a) We must receive comments by April 29, 2010.
Affected Airworthiness Directives (ADs)
(b) None.
Applicability
(c) This AD applies to Turbomeca Astazou XIV B and XIV H
turboshaft engines with the following part number (P/N) third stage
turbine wheels that incorporate modification AB 173 (Turbomeca
Service Bulletin (SB) No. 283 72 0091) or modification AB 208
(Turbomeca SB No. 283 72 0117), but that do not incorporate
Turbomeca SB No. 283 72 805:
(1) Third stage turbine wheels P/N 0265257000, all serial
numbers (S/Ns);
(2) Third stage turbine wheels P/N 0265257020, all S/Ns;
(3) Third stage turbine wheels P/N 0265257060, all S/Ns;
(4) Third stage turbine wheels P/N 0265257050, of the S/Ns
listed in Appendix 1 of Turbomeca Mandatory Service Bulletin No. 283
72 0804, Version C, dated October 23, 2009.
(5) These engines are installed on, but not limited to, single-
engine Aerospatiale AS319B ``Alouette III'' and AS342J ``Gazelle''
helicopters.
Reason
(d) European Aviation Safety Agency (EASA) AD No. 2010-0004,
dated January 5, 2010, states:
Investigation of an uncommanded in-flight shutdown (IFSD)
revealed that a third stage turbine wheel rupture was not contained
by the turbine casings. The released portion consisted of a turbine
blade together with the rim piece immediately below the blade. The
rim piece was bounded by two adjacent axial slots and a fatigue
crack that had developed between the holes in which the slots
terminate. The slots and holes, which are closed by riveted plugs,
were introduced by modification AB 173 in order to improve the
vibration characteristics of the turbine wheel. Modification AB 208
brings an improvement to modification AB 173 by changing only the
riveting detail. SN 283 72 0805 provides instructions for re-boring
the holes at overhaul or repair in order to improve their surface
condition. A manufacturing process modification has been introduced
to improve the surface condition of these holes in third stage
turbine wheels. Wheels subject to the improved manufacturing process
have S/Ns outside the range specified in Table 1. Although there is
only one known event, and
[[Page 15629]]
although it resulted only in an uncommanded IFSD, with no damage to
the aircraft, the possibility exists that additional events may
occur, potentially involving damage to the aircraft.
To address the unsafe condition, EASA issued AD 2009-0136,
mandating inspection of certain third stage turbine wheels and
removal of any damaged wheel. The wheels to be inspected were those
whose cycles since new (CSN) would exceed 2,000 by February 1, 2011.
Following additional research by Turbomeca on crack initiation and
growth, this AD mandates inspections based on new criteria and
removal of any damaged wheel.
We are issuing this AD to prevent uncontained failures of the
third stage turbine wheel, which could result in damage to the
helicopter.
Actions and Compliance
(e) Unless already done, do the following actions.
(1) For any affected third stage turbine wheel that on the
effective date of this AD has accumulated fewer than 500 cycles-
since-last-overhaul or repair, or since-new if the engine has never
been overhauled or repaired:
(i) Within 300 additional cycles, perform a dye penetrant
inspection on the rear face of the third stage turbine wheel.
(ii) Use Section 2, Instructions to Be Incorporated, of
Turbomeca Mandatory Service Bulletin (MSB) No. 283 72 0804, Version
C, dated October 23, 2009, to do the inspection.
(iii) Perform a second dye penetrant inspection when the engine
has accumulated between 450 and 550 cycles from the first
inspection.
(2) For any affected third stage turbine wheel that on the
effective date of this AD, has accumulated 500 or more but fewer
than 700 cycles-since-last-overhaul or repair, or since-new if the
engine has never been overhauled or repaired:
(i) Within 200 additional cycles, perform a dye penetrant
inspection on the rear face of the third stage turbine wheel.
(ii) Use Section 2, Instructions to Be Incorporated, of
Turbomeca Mandatory Service Bulletin (MSB) No. 283 72 0804, Version
C, dated October 23, 2009, to do the inspection.
(3) For any affected third stage turbine wheel that on the
effective date of this AD, has accumulated 700 or more but fewer
than 1,200 cycles-since-last-overhaul or repair, or since-new if the
engine has never been overhauled or repaired:
(i) Within 150 additional cycles, perform a dye penetrant
inspection on the rear face of the third stage turbine wheel.
(ii) Use Section 2, Instructions to Be Incorporated, of
Turbomeca Mandatory Service Bulletin (MSB) No. 283 72 0804, Version
C, dated October 23, 2009, to do the inspection.
(4) If any crack indication is found, then before further
flight, remove the third stage turbine wheel from service.
(5) For any affected third stage turbine wheel that on the
effective date of this AD has accumulated 1,200 or more cycles-
since-last-overhaul or repair, or since-new if the engine has never
been overhauled or repaired, no action is required.
FAA AD Differences
(f) This AD differs from the Mandatory Continuing Airworthiness
Information (MCAI) and or service information as follows:
(1) EASA AD 2010-0004, dated January 5, 2010, requires removing
the engine from service before further flight if a third stage
turbine wheel is found cracked.
(2) This AD requires removing the third stage turbine wheel from
service before further flight if a third stage turbine wheel is
found cracked.
Alternative Methods of Compliance
(g) 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
(h) Refer to MCAI EASA AD 2010-0004, dated January 5, 2010, and
Turbomeca Mandatory Service Bulletin No. 283 72 0804, Version C,
dated October 23, 2009, for related information. Contact Turbomeca,
40220 Tarnos, France; telephone (33) 05 59 74 40 00, fax (33) 05 59
74 45 15, for a copy of this service information.
(i) Contact Kevin Dickert, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; telephone (781) 238-7117, fax (781) 238-7199,
for more information about this AD.
Issued in Burlington, Massachusetts, on March 23, 2010.
Robert Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-7055 Filed 3-29-10; 8:45 am]
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