Document ID: FAA-2013-0575-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Turbomeca S.A. Turboshaft Engines
Posted Date: 2013-08-06T04:00Z

[Federal Register Volume 78, Number 151 (Tuesday, August 6, 2013)]
[Proposed Rules]
[Pages 47581-47582]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-18908]

 ========================================================================
 Proposed Rules
                                                 Federal Register
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 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. 78, No. 151 / Tuesday, August 6, 2013 / 
Proposed Rules  

[[Page 47581]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0575; Directorate Identifier 2013-NE-21-AD]
RIN 2120-AA64

Airworthiness Directives; Turbomeca S.A. 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 all 
Turbomeca S.A. ASTAZOU XIV B and XIV H engines. This proposed AD was 
prompted by reports of cracks on the 2nd-stage turbine disc. This 
proposed AD would require replacement of the 2nd-stage turbine disc. We 
are proposing this AD to prevent disc cracking, uncontained 2nd-stage 
turbine blade release, damage to the engine, and damage to the 
helicopter.

DATES: We must receive comments on this proposed AD by October 7, 2013.

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.
    For service information identified in this proposed AD, contact 
Turbomeca, S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; 
telex: 570 042; fax: 33 (0)5 59 74 45 15. You may view this service 
information at the FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA. For information on the availability of 
this material at the FAA, call 781-238-7125.

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 Mandatory 
Continuing Airworthiness Information (MCAI), the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (phone: 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: Frederick Zink, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7779; 
fax: 781-238-7199; email: frederick.zink@faa.gov.

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-2013-0575; 
Directorate Identifier 2013-NE-21-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 2013-0111R1, dated June 3, 2013 (referred to 
hereinafter as ``the MCAI), to correct an unsafe condition for the 
specified products. The MCAI states:

    Some cracks have been reported on the second stage turbine disc 
of ASTAZOU XIV engines inducted into a Repair Centre. These cracks 
are located in the serrations of the disc. The results of the 
technical investigation concluded that the cracks were present on 
non-shot peened second stage turbine discs (discs on which AB 138 
modification was not incorporated), and on second stage turbine 
discs that were shot peened during their service life (discs on 
which AB 138 modification was incorporated after initial service use 
without shot peening). Until now, no crack has been reported on 
second stage turbine discs shot peened since new, these discs 
accounting for more than half of all ASTAZOU XIV flight hours. It 
was not possible to clearly identify what caused the cracks.

    This condition, if not corrected, could lead to some events of 
disc serrations rupture, possibly resulting in uncontained second 
stage turbine blade release with consequent damage to, and reduced 
control of, the helicopter.

You may obtain further information by examining the MCAI in the AD 
docket.

FAA's Determination and Requirements of This Proposed AD

    These engines have been approved by the aviation authority of 
France, and are approved for operation in the United States. Pursuant 
to our bilateral agreement with the European Community, EASA has 
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 engines of 
the same type design. This proposed AD would require replacement of the 
2nd-stage turbine disc.

Costs of Compliance

    We estimate that this proposed AD affects 6 products of U.S. 
registry. We

[[Page 47582]]

also estimate that it would take about 5 hours per product to comply 
with this proposed AD. The average labor rate is $85 per hour. Required 
parts cost about $6,560 per product. Based on these figures, we 
estimate the cost of the proposed AD on U.S. operators to be $41,910. 
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 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),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction, and
    (4) 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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

    Turbomeca S.A.: Docket No. FAA-2013-0575; Directorate Identifier 
2013-NE-21-AD.

(a) Comments Due Date

    We must receive comments by October 7, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Turbomeca S.A. ASTAZOU XIV B and XIV H 
engines.

(d) Reason

    This AD was prompted by reports of cracks on the 2nd-stage 
turbine disc. We are issuing this AD to prevent disc cracking, 
uncontained 2nd-stage turbine blade release, damage to the engine, 
and damage to the helicopter.

(e) Actions and Compliance

    Unless already done, do the following actions.
    (1) For ASTAZOU XIV B engines that have not incorporated AB 138 
modification remove 2nd-stage turbine disk part number (P/N) 
0265260270 as follows:
    (i) For engines with 1,800 or more engine cycles since new (CSN) 
or since last overhaul (CSLO), remove 2nd-stage turbine disk P/N 
0265260270 within 10 operating hours after the effective date of 
this AD.
    (ii) For engines with less than 1,800 CSN or CSLO, remove 2nd-
stage turbine disk P/N 0265260270 within 300 operating hours after 
the effective date of this AD or before 1800 CSN or CSLO, whichever 
comes first.
    (2) For ASTAZOU XIV B engines that have incorporated AB 138 
modification, remove 2nd-stage turbine disk P/N 0283270200 with P/N 
0265260270 written or scratched onto the disk within 1,800 CSN or 
CSLO, or within 10 operating hours after the effective date of this 
AD, whichever occurs later.
    (3) For ASTAZOU XIV H engines, remove 2nd-stage turbine disk P/N 
0265260270 within 300 operating hours after the effective date of 
this AD.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
to this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(h) Related Information

    (1) For more information about this AD, contact Frederick Zink, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7779; fax: 781-238-7199; email: 
frederick.zink@faa.gov.
    (2) Refer to European Aviation Safety Agency Airworthiness 
Directive 2013-0111R1, dated June 3, 2013, for more information. You 
may examine the AD on the Internet at http://www.regulations.gov.
    (3) Turbomeca S.A. Alert Mandatory Service Bulletin (MSB) No. 
A283 72 0809, Version A, dated May 16, 2013, and Turbomeca S.A. 
Alert MSB No. A283 72 0808, Version A, dated May 16, 2013, which are 
not incorporated by reference in this AD, can be obtained from 
Turbomeca S.A. using the contact information in paragraph (h)(4) of 
this AD.
    (4) For service information identified in this AD, contact 
Turbomeca, S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; 
telex: 570 042; fax: 33 (0)5 59 74 45 15. You may view this service 
information at the FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA. For information on the 
availability of this material at the FAA, call 781-238-7125.

    Issued in Burlington, Massachusetts, on July 19, 2013.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-18908 Filed 8-5-13; 8:45 am]
BILLING CODE 4910-13-P