Document ID: FAA-2010-0781-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Eurocopter France Model AS-365N2, AS 365 N3, and SA 365N1 Helicopters
Posted Date: 2011-03-10T05:00Z

[Federal Register Volume 76, Number 47 (Thursday, March 10, 2011)]
[Rules and Regulations]
[Pages 13065-13066]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-4467]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0781; Directorate Identifier 2007-SW-49-AD; 
Amendment 39-16590; AD 2011-03-06]
RIN 2120-AA64

Airworthiness Directives; Eurocopter France Model AS-365N2, AS 
365 N3, and SA-365N1 Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Eurocopter France (Eurocopter) model helicopters. This AD 
requires replacing the aluminum tail rotor (T/R) blade pitch control 
shaft with a steel T/R blade pitch control shaft. This AD is prompted 
by an incident involving a Eurocopter Model AS-365N2 helicopter on 
which there was a loss of control of the T/R due to a broken shaft. The 
actions specified by this AD are intended to prevent failure of the T/R 
blade pitch control shaft, loss of T/R control, and subsequent loss of 
control of the helicopter.

DATES: Effective April 14, 2011.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 14, 2011.

ADDRESSES: You may get the service information identified in this AD 
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, 
Texas 75053-4005, telephone (800) 232-0323, fax (972) 641-3710, or at 
http://www.eurocopter.com.
    Examining the Docket: You may examine the docket that contains this 
AD, any comments, and other information on the Internet at http://www.regulations.gov or at the Docket Operations office, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: Jim Grigg, Aviation Safety Engineer, 
Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5126, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION: 

Discussion

    On August 2, 2010 we issued a Notice of Proposed Rulemaking (NPRM) 
to amend 14 CFR part 39 to include an AD that would apply to the 
Eurocopter Model AS-365N2, AS 365 N3, and SA-365N1 helicopters, all 
serial numbers, with an aluminum T/R blade pitch control shaft, part 
number (P/N) 365A33.6161.20 or P/N 365A33.6161.21. That NPRM was 
published in the Federal Register on August 11, 2010 (75 FR 48618) and 
proposed to require replacing the aluminum T/R blade pitch control 
shaft with a steel T/R blade pitch control shaft. The actions specified 
by the NPRM are intended to prevent failure of the T/R blade pitch 
control shaft, loss of T/R control, and subsequent loss of control of 
the helicopter.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD No. 2007-0220, dated August 13, 2007, to correct an unsafe condition 
for the Eurocopter Model AS-365N2, AS 365 N3, and SA-365N1 helicopters, 
all serial numbers, equipped with an aluminum T/R blade pitch control 
shaft, P/N 365A33.6161.20 or P/N 365A33.6161.21. EASA advises of an 
incident in which the pilot of a Model AS 365 N2 helicopter encountered 
a loss of control of the T/R, but executed an uneventful run-on 
landing. A subsequent investigation revealed that the T/R blade pitch 
control shaft, P/N 365A33.6161.21, had broken in the main section of 
the shaft sliding area, which appeared to be damaged by peening. The 
origin of the crack, which developed under fatigue loading, could not 
be determined. However, accidental damage (i.e., shock impact), is 
believed to have caused the initiation of a crack.

Related Service Information

    Eurocopter has issued Alert Service Bulletin No. 01.00.59, dated 
June 21, 2007 (ASB), which specifies removing any T/R blade pitch 
control shaft, P/N 365A33.6161.20 or P/N 365A33.6161.21, and replacing 
it with a steel T/R blade pitch control shaft, P/N 365A33.6214.20. EASA 
classified this ASB as mandatory and issued EASA AD No. 2007-0220, 
dated August 13, 2007, to ensure the continued airworthiness of these 
helicopters.

[[Page 13066]]

FAA's Evaluation and Unsafe Condition Determination

    These products have been approved by the aviation authority of 
France, and are approved for operation in the United States. Pursuant 
to our bilateral agreement with France, EASA, their technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are adopting 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 these same type 
designs. This AD requires, within 100 hours time-in-service (TIS), 
removing any aluminum T/R blade pitch control shaft, P/N 365A33.6161.20 
or P/N 365A33.6161.21, and replacing it with a steel T/R blade pitch 
control shaft, P/N 365A33.6214.20. The actions are required to be 
accomplished by following specified portions of the ASB described 
previously.

Differences Between This AD and the EASA AD

    Our AD differs from the EASA AD in that we require compliance 
within 100 hours TIS instead of no later than December 31, 2007, since 
that date has passed.

Comments

    By publishing the NPRM, we gave the public an opportunity to 
participate in developing this AD. However, we received no comment on 
the NPRM or on our determination of the cost to the public. Therefore, 
based on our review and evaluation of the available data, we have 
determined that air safety and the public interest require adopting the 
AD as proposed.

Costs of Compliance

    We estimate that this AD will affect 36 helicopters of U.S. 
registry and the actions will take approximately 12 work hours per 
helicopter to accomplish at an average labor rate of $85 per work hour. 
Required parts will cost approximately $3,525. Based on these figures, 
we estimate the total cost impact of the AD on U.S. operators to be 
$163,620 to replace the aluminum T/R blade pitch control shaft on the 
entire fleet, or $4,545 per helicopter.

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 the 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 an economic evaluation 
of the estimated costs to comply with this AD. See the AD docket to 
examine the economic evaluation.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2011-03-06 Eurocopter France: Amendment 39-16590; Docket No. FAA 
2010-0781; Directorate Identifier 2007-SW-49-AD.

    Applicability: Model AS-365N2, AS 365 N3, and SA-365N1 
helicopters, with an aluminum tail rotor (T/R) blade pitch control 
shaft, part number (P/N) 365A33.6161.20 or P/N 365A33.6161.21, 
installed, certificated in any category.
    Compliance: Required within 100 hours time-in-service, unless 
accomplished previously.
    To prevent failure of the T/R blade pitch control shaft, loss of 
T/R control, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Remove the aluminum T/R blade pitch control shaft, P/N 
365A33.6161.20 or P/N 365A33.6161.21, and replace it with a steel T/
R blade pitch control shaft, P/N 365A33.6214.20, in accordance with 
the Accomplishment Instructions, Operational Procedure, paragraphs 
2.B.1. through 2.B.3., of Eurocopter Alert Service Bulletin No. 
01.00.59, dated June 21, 2007.
    (b) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Safety Management Group, Rotorcraft 
Directorate, FAA, Attn: Jim Grigg, Aviation Safety Engineer, 2601 
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5126, 
fax (817) 222-5961.
    (c) The Joint Aircraft System/Component (JASC) Code is 6500: 
Tail Rotor Drive System.
    (d) Replace the T/R blade pitch control shaft in accordance with 
the specified portions of Eurocopter Alert Service Bulletin No. 
01.00.59, dated June 21, 2007. The Director of the Federal Register 
approved this incorporation by reference in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Copies may be obtained from American 
Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053-
4005, telephone (800) 232-0323, fax (972) 641-3710, or at http://www.eurocopter.com. Copies may be inspected at the FAA, Office of 
the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas, or 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/code_of_federal_regulations/ibr_locations.html.
    (e) This amendment becomes effective on April 14, 2011.

    Note:  The subject of this AD is addressed in European Aviation 
Safety Agency AD No. 2007-0220, dated August 13, 2007.

    Issued in Fort Worth, Texas, on January 24, 2011.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-4467 Filed 3-9-11; 8:45 am]
BILLING CODE 4910-13-P