[Federal Register Volume 75, Number 214 (Friday, November 5, 2010)]
[Rules and Regulations]
[Pages 68169-68171]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-27972]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1082; Directorate Identifier 2009-SW-041-AD;
Amendment 39-16491; AD 2010-23-02]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France (Eurocopter) Model
SA-365N, SA-365N1, AS-365N2, and AS 365 N3 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) for
the
[[Page 68170]]
specified Eurocopter model helicopters. This action requires amending
the Limitations section of the Rotorcraft Flight Manual (RFM) to limit
the never-exceed velocity (VNE) to 150 Knots Indicated Air Speed (KIAS)
and to add a 1,500 ft/minute rate of descent (R/D) limitation beyond
140 KIAS. This action also requires installing one or more placards on
the cockpit instrument panel in full view of the pilot and co-pilot.
This amendment is prompted by failures of the horizontal stabilizers on
recently delivered Model AS 365 N3 helicopters. Tests indicate that the
failures were due to a vibration phenomenon that may arise during the
descent flight phases at high speed regardless of the stabilizer
installed. The actions specified in this AD are intended to restrict
the VNE, to prevent failure of the horizontal stabilizer, and
subsequent loss of control of the helicopter.
DATES: Effective November 22, 2010.
Comments for inclusion in the Rules Docket must be received on or
before January 4, 2011.
ADDRESSES: Use one of the following addresses to submit comments on
this 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 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.
Examining the Docket: You may examine the docket that contains the
AD, any comments, and other information on the Internet at http://www.regulations.gov, or 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.
FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations and Guidance Group, 2601
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5130, fax
(817) 222-5961.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Emergency AD No. 2008-0204-E, dated December 4, 2008, to correct an
unsafe condition for the specified Eurocopter model helicopters. EASA
advises that Eurocopter has received reports of failed horizontal
stabilizers on recently delivered AS 365 N3 helicopters. The failures
occurred during acceptance test and training flights as part of the
demonstration of the VNE and resulted in in-flight separation and loss
of the failed sections. In each case, the helicopters succeeded in
returning to base with no further problems. Tests conducted on the
helicopter and in the laboratory have revealed the reported incidents
were due to a vibration phenomenon that may arise in the descent flight
phases at high speed ``regardless of the stabilizer definition.''
Although EASA AD 2008-0110-E, dated June 6, 2008, which is superseded
by EASA AD 2008-0204-E, dated December 4, 2008, applied to the Model
SA-336G1, EASA states that the stabilizer assembly procedure on SA-
366G1 helicopters modifies the dynamic behavior of the stabilizer.
Since an unsafe condition does not exist on that helicopter, the SA-
366G1 has been deleted from the EASA AD applicability.
Related Service Information
Eurocopter has issued an Emergency Alert Service Bulletin (EASB)
with 3 numbers (01.00.60, 01.00.16, and 01.28), Revision 1, dated
December 2, 2008. EASB No. 01.00.60 applies to U.S. type-certificated
Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters and also
to military Model AS365F, Fs, Fi, and K helicopters that are not type
certificated in the United States. EASB No. 01.00.16 applies to
military Model AS565AA, MA, MB, SA, SB, and UB helicopters that are not
type certificated in the United States. EASB 01.28 applies to the Model
SA-366G1 helicopter. The EASB specifies bonding one or more locally-
produced labels to the instrument panel stating that the VNE is limited
to 150 KIAS and the R/D must not exceed 1,500 ft/min beyond 140 KIAS.
Eurocopter states in the EASB that it is working on an enhanced
definition that will be proposed as soon as possible. EASA classified
this EASB as mandatory and issued Emergency AD No. 2008-0204-E, dated
December 4, 2008, 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
the MCAI AD. We are issuing 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.
Differences Between This AD and the EASA AD
This AD uses a compliance time of before further flight rather than
before next flight after June 7, 2008, as stated in the EASA AD.
FAA's Determination and Requirements of This AD
This unsafe condition is likely to exist or develop on other
helicopters of these same type designs. Therefore, this AD is being
issued to restrict the VNE to prevent failure of the horizontal
stabilizer and subsequent loss of control of the helicopter. This AD
requires amending the Limitations section of the RFM to limit the VNE
to 150 KIAS and to add a 1,500 ft/minute R/D limitation for airspeeds
beyond 140 KIAS. This action also requires installing one or more
placards on the cockpit instrument panel in full view of the pilot and
co-pilot stating the limitations. The change to the Operating
limitation section of the RFM may be made in pen and ink or a copy of
this AD may be filed in the Limitations section of the RFM.
The short compliance time involved is required because the
previously described critical unsafe condition can adversely affect the
controllability and structural integrity of the helicopter. Amending
the Limitations section of the RFM to limit the VNE to 150 KIAS and
adding a 1,500 ft/minute R/D limitation beyond 140 KIAS are required
before further flight and installing one or more placards on the
cockpit instrument panel is required. Therefore, this AD must be issued
immediately.
Since a situation exists that requires the immediate adoption of
this
[[Page 68171]]
regulation, it is found that notice and opportunity for prior public
comment hereon are impracticable, and that good cause exists for making
this amendment effective in less than 30 days.
Costs of Compliance
We estimate that this AD will affect about 39 helicopters of U.S.
registry. We also estimate that it will take about \l/2\ work-hour per
helicopter to make copies to include in the RFM and to make and install
the placards. The average labor rate is $85 per work-hour. The parts
costs are minimal. Based on these figures, we estimate the cost of this
AD on U.S. operators is $1,658 for the fleet.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any written data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2010-1082; Directorate
Identifier 2009-041-SW-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of the AD. We will consider all
comments received by the closing date and may amend the 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 AD. 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 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).
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 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.
Adoption of the Amendment
0
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:
2010-23-02 Eurocopter France: Amendment 39-16491; Docket No. FAA-
2010-1082; Directorate Identifier 2009-SW-041-AD.
Applicability: Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3-
helicopters, with a horizontal stabilizer, part number 365A13-3030-
1901, -1902, -1903, -1904, -1905, -1906, -1908, -1909; 365A13-3036-
00, -0001, -0002, -0003; or 365A13-3038-00, installed, certificated
in any category.
Compliance: Before further flight, unless accomplished
previously.
To restrict the never-exceed velocity (VNE) to prevent failure
of the horizontal stabilizer, and subsequent loss of control of the
helicopter, do the following:
(a) Revise the airspeed operating limitation in the Limitations
section of the Rotorcraft Flight Manual (RFM) by making pen and ink
changes or by inserting a copy of this AD into the RFM stating:
``The never-exceed speed (VNE) is limited to 150 knots indicated
airspeed (KIAS),'' and ``The rate-of-descent (R/D) must not exceed
1,500 ft/min when the airspeed is beyond 140 KIAS.''
(b) Install one or more self-adhesive placards, with 6
millimeter red letters on white background, on the cockpit
instrument panel in full view of the pilot and co-pilot to read as
follows:
``VNE LIMITED TO 150 KIAS''
``R/D MUST NOT EXCEED 1,500 ft/min when airspeed is beyond 140
KIAS''
(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: ATTN: Gary Roach,
Aerospace Engineer, FAA, 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 5510:
Horizontal Stabilizer Structure.
(e) This amendment becomes effective on November 22, 2010.
Note: The subject of this AD is addressed in European Aviation
Safety Agency Emergency AD No. 2008-0204-E, dated December 4, 2008,
and in Eurocopter Emergency Alert Service Bulletin No. 01.00.60,
Revision 1, dated December 2, 2008, for the Model AS365N series
helicopters.
Issued in Fort Worth, Texas, on October 15, 2010.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-27972 Filed 11-4-10; 8:45 am]
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