
[Federal Register Volume 77, Number 76 (Thursday, April 19, 2012)]
[Rules and Regulations]
[Pages 23380-23382]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-8584]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0330; Directorate Identifier 2008-NE-43-AD; 
Amendment 39-17015; AD 2012-07-09]
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 superseding an existing airworthiness directive (AD) 
for Turbomeca S.A. Arrius 2F turboshaft engines with P3 air pipe (first 
section) part number (P/N) 0 319 71 918 0, installed. That AD currently 
requires inspections of the P3 air pipe (first section) and right-hand 
(RH) rear half-wall for proper clearance and readjustment of the pipe 
if necessary. This new AD requires the same inspections for installed 
engines, eliminates readjusting of the P3 air pipe (first section), 
requires replacement of the RH rear half-wall under certain conditions, 
and adds an optional terminating action. This AD was prompted by 
Turbomeca determining that the clearance between the P3 air pipe (first 
section) and the RH rear half-wall might change during installation of 
the engine on the helicopter. We are issuing this AD to prevent an 
uncommanded power loss to flight idle, which could result in an 
emergency autorotation landing or accident.

DATES: This AD is effective May 24, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of May 24, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in the AD as of August 
19, 2009 (74 FR 34221, July 15, 2009).

ADDRESSES: For service information identified in this AD, contact

[[Page 23381]]

Turbomeca, 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; telex 570 
042; fax 33 (0)5 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 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7758; fax: 
781-238-7199; email: mark.riley@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2009-14-11, Amendment 39-15961 (74 FR 34221, 
July 15, 2009). That AD applies to the specified products. The NPRM 
published in the Federal Register on December 13, 2011 (76 FR 77446). 
That NPRM proposed to continue to require inspections of the P3 air 
pipe (first section) and right-hand (RH) rear half-wall for proper 
clearance. That NPRM also proposed to require eliminating readjusting 
of the P3 air pipe (first section), replacing the RH rear half-wall 
under certain conditions, and adding an optional terminating action.

Service Bulletin Reference

    In AD 2009-14-11 (74 FR 34221, July 15, 2009), ``Version A'' was 
inadvertently omitted from the reference to Turbomeca Mandatory Service 
Bulletin No. 319 75 4810, dated May 14, 2008. In this AD, the service 
bulletin reference reads correctly as ``Turbomeca Mandatory Service 
Bulletin No. 319 75 4810, Version A, dated May 14, 2008.''

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (76 FR 77446, December 13, 
2011).

Credit for Previous Action Added

    Since we issued the NPRM (76 FR 77446, December 13, 2011) the 
European Aviation Safety Agency (EASA) superseded AD 2011-0182, dated 
September 22, 2011, to include a credit for inspections done using 
Turbomeca Mandatory Service Bulletin (MSB) No. 319 75 4810, Version A, 
dated May 14, 2008. We added a paragraph for credit for previous 
action, which states that inspections performed on an installed engine 
before the effective date of this AD using Turbomeca MSB No. 319 75 
4810, Version A, dated May 14, 2008, satisfies the inspection 
requirements in paragraphs (e)(1)(i) and (e)(1)(ii) of this AD. We also 
changed the EASA AD reference to EASA AD 2011-0182R1, dated February 3, 
2012.

Conclusion

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

Costs of Compliance

    We estimate that this AD will affect about 120 Arrius 2F turboshaft 
engines installed on helicopters of U.S. registry. We also estimate 
that it will take about 2 work-hours per engine to comply with this AD. 
The average labor rate is $85 per work-hour. Required parts will cost 
about $2,565 per engine. Based on these figures, we estimate the cost 
of the AD on U.S. operators to be $328,200. 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 have 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 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 removing airworthiness directive (AD) 
2009-14-11, Amendment 39-15961 (74 FR 34221, July 15, 2009), and adding 
the following new AD:

2012-07-09 Turbomeca S.A: Amendment 39-17015; Docket No. FAA-2009-
0330; Directorate Identifier 2008-NE-43-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective May 24, 2012.

(b) Affected ADs

    This AD supersedes AD 2009-14-11, Amendment 39-15961 (74 FR 
34221, July 15, 2009).

(c) Applicability

    This AD applies to Turbomeca S.A. Arrius 2F turboshaft engines 
with right-hand (RH) rear half-wall, part number (P/N) 0319 99 824 
0, installed.

(d) Unsafe Condition

    The P3 air pipe (first section) and the RH rear half-wall could 
rub each other. Rubbing

[[Page 23382]]

between the pipe and the RH rear half-wall may lead to rupture of 
the P3 air pipe (first section), which could cause an uncommanded 
power loss to flight idle. We are issuing this AD to prevent an 
uncommanded power loss to flight idle, which could result in an 
emergency autorotation landing or accident.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) For installed engines, within 100 engine hours (EH) after 
the effective date of this AD:
    (i) Inspect the clearance between the P3 air pipe (first 
section) and the RH rear half-wall for sufficient clearance (0.5 mm 
or more).
    (ii) Use paragraph 2.B.(1) of Turbomeca Mandatory Service 
Bulletin (MSB) No. 319 75 4810, Version B, dated January 25, 2011 to 
do the inspection.
    (2) Thereafter, repeat the inspections in paragraphs (e)(1)(i) 
through (e)(1)(ii) of this AD as follows:
    (i) At every installation of a RH rear half-wall P/N 0 319 99 
824 0 on an installed engine, and
    (ii) After every installation or reinstallation of an engine 
with a RH rear half-wall P/N 0 319 99 824 0 installed.
    (3) If the P3 air pipe (first section) or the RH rear half-wall 
P/N 0 319 99 824 0 is found damaged, then before further flight, 
replace the damaged part(s) with parts eligible for installation.
    (4) If the P3 air pipe (first section) and the RH rear half-wall 
P/N 0 319 99 824 0 are found contacting each other but are not 
damaged, replace the RH rear half-wall with a RH rear half-wall 
eligible for installation.
    (5) If both the P3 air pipe (first section) and the RH rear 
half-wall are found not damaged during the inspections specified in 
paragraph (e)(1) or (e)(2) of this AD, and the clearance between 
them is less than 0.5 mm, but they are not contacting each other, 
then repeat the inspection in paragraphs (e)(1)(i) and (e)(1)(ii) of 
this AD within every 100 EH.
    (6) Installation of RH rear half-wall, P/N 0 319 99 008 0, is 
terminating action to the inspections required by paragraphs (e)(1), 
(e)(2), and (e)(5) of this AD.
    (7) Once a RH rear half-wall, P/N 0 319 99 008 0, is installed 
on an engine, do not install a RH rear half-wall, P/N 0 319 99 824 
0, on that engine.

(f) Definition

    For the purpose of this AD, parts eligible for installation is 
defined as:
    (1) An undamaged P3 air pipe (first section).
    (2) An undamaged RH rear half-wall P/N 0 319 99 824 0.
    (3) A new design RH rear half-wall P/N 0 319 99 008 0.

(g) Credit for Previous Action

    An inspection performed on an installed engine before the 
effective date of this AD using Turbomeca MSB No. 319 75 4810, 
Version A, dated May 14, 2008, satisfies the inspection requirement 
in paragraphs (e)(1)(i) and (e)(1)(ii) of this AD.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, may approve 
alternative methods of compliance 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 Mark Riley, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7758; fax: 781-238-7199; email: 
mark.riley@faa.gov.
    (2) European Aviation Safety Agency AD 2011-0182R1, dated 
February 3, 2012, pertains to the subject of this AD.
    (3) For service information identified in this AD, contact. 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

    You must use the following service information to do the actions 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference 
(IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the following 
service information.
    (1) Turbomeca Mandatory Service Bulletin No. 319 75 4810, 
Version A, dated May 14, 2008, approved for IBR August 19, 2009 (74 
FR 34221, July 15, 2009).
    (2) Turbomeca Mandatory Service Bulletin No. 319 75 4810, 
Version B, dated January 25, 2011, approved for IBR May 24, 2012.
    (3) For service information identified in this AD, contact 
Turbomeca, 40220 Tarnos, France; telephone 33 (0)5 59 74 40 00; 
telex 570 042; fax 33 (0)5 59 74 45 15.
    (4) 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.
    (5) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr_locations.html.

    Issued in Burlington, Massachusetts, on April 3, 2012.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2012-8584 Filed 4-18-12; 8:45 am]
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