[Federal Register Volume 75, Number 154 (Wednesday, August 11, 2010)]
[Proposed Rules]
[Pages 48618-48620]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-19823]
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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]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS-365N2, AS
365 N3, and SA-365N1 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
specified Eurocopter France model helicopters. This proposed AD would
require replacing the aluminum tail rotor (T/R) blade pitch control
shaft with a steel T/R blade pitch control shaft. This proposed AD is
prompted by an incident involving a Eurocopter France 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 proposed 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.
[[Page 48619]]
DATES: Comments must be received on or before October 12, 2010.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
You may get the service information identified in this proposed AD
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.
You may examine the comments to this proposed AD in the AD docket
on the Internet at http://www.regulations.gov.
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:
Comments Invited
We invite you to submit any written data, views, or arguments
regarding this proposed AD. Send your comments to the address listed
under the caption ADDRESSES. Include the docket number ``FAA-2010-0781,
Directorate Identifier 2007-SW-49-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of 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 rulemaking. Using the
search function of the docket Web site, you can find and read the
comments to any of our dockets, including the name of the individual
who sent or signed the comment. You may review the DOT's complete
Privacy Act Statement in the Federal Register published on April 11,
2000 (65 FR 19477-78).
Examining the Docket
You may examine the docket that contains the proposed AD, any
comments, and other information in person at the Docket Operations
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Operations office (telephone (800) 647-5527) is
located in Room W12-140 on the ground floor of the West Building at the
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
Discussion
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 Eurocopter AS 365 N2, AS 365 N3, and SA 365 N1 helicopters, all
serial numbers, equipped with an aluminum T/R blade pitch control
shaft, part number (P/N) 365A33.6161.20 or P/N 365A33.6161.21. The 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, 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. The EASA
classified this alert service bulletin as mandatory and issued EASA AD
No. 2007-0220, dated August 13, 2007, to ensure the continued
airworthiness of these helicopters.
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, the EASA, their technical
representative, has notified us of the unsafe condition described in
the EASA AD. We are proposing this AD because we evaluated all
information provided by the EASA and determined the unsafe condition
exists and is likely to exist or develop on other products of these
same type designs. This proposed AD would require, within 100 hours
time-in-service, 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 would be
required to be accomplished by following specified portions of the
alert service bulletin described previously.
Differences Between This Proposed AD and the EASA AD
Our proposed AD differs from the EASA AD in that we require
compliance within 100 hours time-in-service instead of no later than
December 31, 2007, since that date has passed.
Costs of Compliance
We estimate that this proposed AD would affect 36 helicopters of
U.S. registry and the proposed actions would take approximately 12 work
hours per helicopter to accomplish at an average labor rate of $85 per
work hour. Required parts would cost approximately $3,525. Based on
these figures, we estimate the total cost impact of the proposed 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 proposed AD would not have federalism
implications under Executive Order 13132. Additionally, 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 that the 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); 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
[[Page 48620]]
this proposed 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.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (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]
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
Eurocopter France: 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.
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 August 2, 2010.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-19823 Filed 8-10-10; 8:45 am]
BILLING CODE 4910-13-P