Document ID: FAA-2010-0219-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Turbomeca Astazou XIV B and XIV H Turboshaft Engines
Posted Date: 2010-03-30T04:00Z

[Federal Register: March 30, 2010 (Volume 75, Number 60)]
[Proposed Rules]               
[Page 15627-15629]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30mr10-20]                         

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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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[[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).

-----------------------------------------------------------------------

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: 
kevin.dickert@faa.gov; 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: 
kevin.dickert@faa.gov; 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]
BILLING CODE 4910-13-P