[Federal Register Volume 76, Number 11 (Tuesday, January 18, 2011)]
[Proposed Rules]
[Pages 2842-2845]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-720]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1303; Directorate Identifier 2010-SW-049-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France (Eurocopter) Model
SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 Helicopters
AGENCY: Federal Aviation Administration (FAA) 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 model helicopters. This proposed AD would require
an initial and recurring inspections of the inner angles and flanges of
the 9-degree frame on the right-hand (RH) and left-hand (LH) sides for
a crack. If a crack is found, this proposed AD would require, before
further flight, repairing the frame. This proposed AD is prompted by
the discovery of a crack in the 9-degree frame of a Eurocopter Model
AS-365N2 helicopter. These cracks could also develop on the other
specified model helicopters because they contain the same 9-degree
frame. The actions specified by this proposed AD are intended to detect
a crack in the 9-degree frame to prevent loss of structural integrity
and subsequent loss of control of the helicopter.
DATES: Comments must be received on or before March 21, 2011.
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: Gary Roach, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations and Policy Group, 2601 Meacham
Blvd, Fort Worth, Texas 76137, telephone (817) 222-5130, fax (817) 222-
5961.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the caption ADDRESSES. Include the Docket No. ``FAA-2010-
1303, Directorate Identifier 2010-SW-049-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because 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
Emergency AD No. 2010-0064-E, dated April 1, 2010, which supersedes
EASA Emergency AD No. 2009-0125-E, dated June 12, 2009, and the
correction dated June 15, 2009, to correct an unsafe condition for the
specified model helicopters. EASA advises that during a major
inspection a crack was found in the 9-degree frame of an AS-365N2
helicopter, which had logged a total of 10,786 flight hours. The crack
was located 230 millimeters above the cabin floor and had grown over a
large section of the 9-degree frame on the RH side. EASA states that
analysis shows that the time required for initiation of a crack in this
area varies according to the weight and balance data of the different
aircraft versions.
Related Service Information
Eurocopter has issued Emergency Alert Service Bulletin (EASB),
Revision 1, dated March 31, 2010, containing the following three
numbers: No. 05.00.57 for FAA type-certificated Model SA-365N, N1 and
AS-365N2 and N3 helicopters and for military, not FAA type-
certificated, Model AS365F, Fs, Fi, and K helicopters; No. 05.00.25 for
military, not FAA type-certificated, Model AS565AA, MA, MB, SA, SB, and
UB helicopters; and No. 05.39 for FAA type-certificated Model SA-366G1
helicopters and for military, not FAA type-certificated, Model SA366GA
helicopters. The EASB specifies checking at regular intervals for a
crack
[[Page 2843]]
in the areas of the inner angles and flanges of the 9[deg] frame on the
RH and LH sides, near the splice. The EASB states that Eurocopter is
currently studying an improvement (reinforcement) of the frame, which
will cancel the checks specified by the EASB. EASA classified this EASB
as mandatory and issued AD No. 2010-0064-E, dated April 1, 2010, to
ensure the continued airworthiness of these helicopters.
FAA's Evaluation and Unsafe Condition Determination
These helicopters 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
their AD. We are proposing 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 helicopters of these same type
designs. This proposed AD would require an initial and recurring
inspections of the inner angles and flanges of the 9-degree frame on
the RH and LH sides for a crack. If a crack is found, this proposed AD
would require, before further flight, repairing the frame.
Differences Between This Proposed AD and the EASA AD
We refer to ``flight hours'' as ``hours time-in-service.'' We do
not refer to the EASB for accomplishment instructions. We do not
require contacting the manufacturer for approved repair instructions.
We do not allow flight with a known crack. Therefore, we do not revise
our required action based on the length and specific location of the
crack on the 9-degree frame. We refer to the 9-degree frame rather than
the No. 9 frame.
Costs of Compliance
We estimate that this proposed AD would affect 19 helicopters of
U.S. registry. We also estimate that it would take about 3 work hours
for about 12 inspections a year per helicopter. It would take about 24
hours to repair a helicopter frame. The average labor rate is $85 per
work hour. Required parts would cost about $3,350. Based on these
figures, we estimate the total cost impact of the proposed AD on U.S.
operators to be $68,920 for the fleet, assuming 2 helicopters require
repair each year.
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 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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
(AD) to read as follows:
Eurocopter France: Docket No. FAA-2010-1303; Directorate Identifier
2010-SW-049-AD
Applicability: Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, and
SA-366G1 helicopters, certificated in any category.
Compliance: Required as indicated.
To detect a crack in the 9-degree frame to prevent loss of
structural integrity and subsequent loss of control of the
helicopter, do the following:
(a) On or before the affected model helicopters reach the hours
time-in-service (TIS) listed in Table 1 of this AD or within 10
hours TIS, whichever occurs later, unless accomplished previously,
and thereafter at intervals not to exceed 110 hours TIS, using a 10X
or higher magnifying glass, inspect the inner angles and flanges of
the 9-degree fuselage frame on the right hand and left hand sides
for a crack in the area depicted in Figure 1 and as shown in Figure
2 of this AD.
Table 1
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Helicopter model Hours TIS
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SA-365N................................................. 8,990
SA-365N1................................................ 9,990
AS-365N2................................................ 3,190
AS 365 N3............................................... 2,090
SA-366G1................................................ 9,990
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Note 1: Eurocopter Emergency Alert Service Bulletin, Revision 1,
dated March 31, 2010 (EASB), containing the following 3 numbers: No.
05.00.57 for FAA type-certificated Model SA-365N and N1 and AS-365N2
and N3 helicopters and for military, not FAA type-certificated,
Model AS365F, Fs, Fi, and K helicopters; No. 05.00.25 for military,
not FAA type-certificated, Model AS565AA, MA, MB, SA, SB, and UB
helicopters; and No. 05.39 for FAA type-certificated Model SA-366G1
helicopters and for military, not FAA type-certificated, Model
SA366GA helicopters. This EASB is not incorporated by reference but
contains additional information about the subject of this AD.
Actions previously done by following the procedures of this EASB are
considered acceptable for complying with the corresponding actions
in paragraphs (a) and (b) of this AD.
(b) If you find a crack, before further flight, repair the
frame. Repairing a frame does not constitute terminating action for
the repetitive inspection requirements of this AD.
(c) 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, FAA, ATTN: Gary Roach,
Aviation Safety Engineer, Regulations and Policy Group 2601 Meacham
Blvd, Fort Worth, Texas, 76137; telephone: (817) 222-5130 fax: 817-
222-5961, for information about previously approved alternative
methods of compliance.
(d) The Joint Aircraft System/Component (JASC) Code is 5311:
Fuselage Main, Frame.
Note 2: The subject of this AD is addressed in European Aviation
Safety Agency AD No. 2010-0064-E, dated April 1, 2010.
Issued in Fort Worth, Texas on December 16, 2010.
M. Monica Merritt,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-720 Filed 1-14-11; 8:45 am]
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