Document ID: FAA-2012-0010-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Turbomeca S.A. Turboshaft Engines
Posted Date: 2012-04-25T04:00Z

[Federal Register Volume 77, Number 80 (Wednesday, April 25, 2012)]
[Rules and Regulations]
[Pages 24585-24587]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-9789]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0010; Directorate Identifier 2012-NE-03-AD; 
Amendment 39-17035; AD 2012-08-18]
RIN 2120-AA64

Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Turbomeca S.A. Arriel 2B and 2B1 turboshaft engines. This AD was 
prompted by the discovery of non-conformities of certain power turbine 
(PT) blade fir-tree roots. This AD requires removing the affected PT 
blades from service on or before reaching a new reduced life limit for 
those certain PT blades. We are issuing this AD to prevent PT blade 
rupture, which could result in an uncommanded in-flight engine 
shutdown, forced autorotation landing, or accident.

DATES: This AD is effective May 30, 2012.

ADDRESSES: For service information identified in this AD, contact 
Turbomeca, 40220 Tarnos, France; phone: 33 05 59 74 40 00; fax: 33 05 
59 74 45 15. You may review copies of the referenced 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 Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200

[[Page 24586]]

New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Rose Len, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7772; fax: 
781-238-7199; email: rose.len@faa.gov.

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 published in the Federal Register on January 20, 2012 (77 FR 
2930). That NPRM proposed to require removing the affected PT blades 
from service on or before reaching a new reduced life limit for those 
certain PT blades.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (77 FR 2930, January 20, 
2012).

Clarification of Compliance Time

    Since we issued the proposed AD, we determined that we need to 
clarify the compliance time. The proposed AD stated 5,000 flight 
cycles. We changed the AD to state 5,000 flight cycles-since-new.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD with the change described 
previously.

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect about 150 engines installed on helicopters of U.S. registry. We 
also estimate that it will take about 4 work-hours per product to 
comply with this AD. The average labor rate is $85 per work-hour. A 
prorated replacement M04 module will cost about $20,000 per engine. 
Based on these figures, we estimate the cost of the AD on U.S. 
operators to be $3,051,000.

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

    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 that 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),
    (3) Will not affect intrastate aviation in Alaska, 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.

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):

2012-08-18 Turbomeca S.A: Amendment 39-17035; Docket No. FAA-2012-
0010; Directorate Identifier 2012-NE-03-AD.

(a) Effective Date

    This AD is effective May 30, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Turbomeca S.A. Arriel 2B and 2B1 turboshaft 
engines with at least one installed power turbine (PT) blade part 
number (P/N) 2 292 81 A01 0, serial numbers (S/Ns) 102782 through 
120230 inclusive, or, S/Ns 120293 through 120390 inclusive.

(d) Reason

    This AD was prompted by the detection of geometric non-
conformities on PT blade fir-tree roots. We are issuing this AD to 
prevent PT blade rupture, which could result in an uncommanded in-
flight engine shutdown, forced autorotation landing, or accident.

(e) Actions and Compliance

    Unless already done, do the following actions within 5,000 
flight cycles-since-new (CSN) on the PT blades, or within one month 
after the effective date of this AD, whichever occurs later.
    (1) Replace the PT blades with PT blades eligible for 
installation; or
    (2) Replace the M04 module with an M04 module having PT blades 
eligible for installation; or
    (3) Replace the PT wheel assembly with a PT wheel assembly 
having PT blades eligible for installation.
    (4) Guidance on the replacements specified in paragraphs (e)(1) 
through (e)(3) can be found in Turbomeca S.A. Alert Mandatory 
Service Bulletin No. A292 72 2842, Version A, dated September 23, 
2011.

(f) Definition

    For the purposes of this AD, a PT blade eligible for 
installation is one not listed in paragraph (c) of this AD or, one 
listed in paragraph (c) of this AD with fewer than 5,000 flight CSN.

(g) Installation Prohibition

    From the effective date of this AD:
    (1) Do not install a PT blade as listed in paragraph (c) of this 
AD, that has 5,000 or more flight CSN, into any engine.
    (2) Do not install any engine with a PT blade as listed in 
paragraph (c) of this AD, that has 5,000 or more flight CSN, onto a 
helicopter.

(h) Alternative Methods of Compliance (AMOCs)

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

(i) Related Information

    (1) For more information about this AD, contact Rose Len, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7772; fax: 781-238-7199; email: 
rose.len@faa.gov.
    (2) Refer to MCAI EASA Airworthiness Directive 2011-0218, dated 
November 10, 2011, and Turbomeca S.A. Alert Mandatory Service 
Bulletin No. A292 72 2842, Version A, dated September 23, 2011, for 
related information.
    (3) For service information identified in this AD, contact 
Turbomeca, 40220 Tarnos, France; phone: 33 05 59 74 40 00; fax: 33 
05

[[Page 24587]]

59 74 45 15. You may review copies of the referenced 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.

(j) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on April 17, 2012.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-9789 Filed 4-24-12; 8:45 am]
BILLING CODE 4910-13-P