Document ID: FAA-2013-0575-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Turbomeca S.A. Turboshaft Engines
Posted Date: 2014-01-10T05:00Z

[Federal Register Volume 79, Number 7 (Friday, January 10, 2014)]
[Rules and Regulations]
[Pages 1733-1734]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-00166]

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  Federal Register / Vol. 79, No. 7 / Friday, January 10, 2014 / Rules 
and Regulations  

[[Page 1733]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0575; Directorate Identifier 2013-NE-21-AD; 
Amendment 39-17718; AD 2013-26-09]
RIN 2120-AA64

Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Turbomeca S.A. ASTAZOU XIV B and XIV H engines. This AD was prompted by 
reports of cracks on the 2nd-stage turbine disk. This AD requires 
replacement of the 2nd-stage turbine disk. We are issuing this AD to 
prevent disk cracking, uncontained 2nd-stage turbine blade release, 
damage to the engine, and damage to the helicopter.

DATES: This AD becomes effective February 14, 2014.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0575; 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 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 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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on August 6, 2013 (78 FR 
47581). The NPRM proposed 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 examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0575-0002.
    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (78 FR 47581, August 6, 
2013). However, we did make an editorial change to the preamble of this 
AD.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this 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 this AD.

Costs of Compliance

    We estimate that this AD will affect about 6 engines of U.S. 
registry. We also estimate that it will take about 5 hours per engine 
to comply with this AD. The average labor rate is $85 per hour. 
Required parts will cost about $6,560 per engine. Based on these 
figures, we estimate the cost of this AD on U.S. operators to be 
$41,910.

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 the DOT Regulatory Policies 
and

[[Page 1734]]

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 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.

Adoption of the Amendment

    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 airworthiness 
directive (AD):

2013-26-09 Turbomeca S.A.: Amendment 39-17718; Docket No. FAA-2013-
0575; Directorate Identifier 2013-NE-21-AD.

(a) Effective Date

    This AD becomes effective February 14, 2014.

(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 disk. We are issuing this AD to prevent disk 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 the 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 cycles since last overhaul (CSLO), remove the 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 the 
2nd-stage turbine disk, P/N 0265260270, within 300 operating hours 
after the effective date of this AD or before 1,800 CSN or CSLO, 
whichever comes first.
    (2) For ASTAZOU XIV B engines that have incorporated AB 138 
modification, remove the 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 the 2nd-stage turbine 
disk, P/N 0265260270, within 300 operating hours after the effective 
date of this AD.

(f) 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.

(g) 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 MCAI European Aviation Safety Agency airworthiness 
directive 2013-0111R1, dated June 3, 2013, for more information. You 
may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0575-0002.
    (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 (g)(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.
    (5) 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.

(h) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on January 6, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-00166 Filed 1-9-14; 8:45 am]
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