Airworthiness Directives; Eurocopter France Helicopters, 20234-20236 [2013-07211]
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20234
Federal Register / Vol. 78, No. 65 / Thursday, April 4, 2013 / Rules and Regulations
(t) Retained Parts Installation Limitations
This paragraph restates the requirements of
paragraph (t) of AD 2010–17–19, Amendment
39–16413 (75 FR 52242, August 25, 2010),
with revised limitations. As of September 9,
2010 (the effective date of AD 2010–17–19),
and until the replacement required by
paragraph (u) of this AD for airplanes with
line numbers 1 through 3909 inclusive, or
until the effective date of this new AD for
airplanes with line numbers 3910 and
subsequent, as applicable: Comply with the
conditions specified in paragraphs (t)(1) and
(t)(2) of this AD.
(1) No person may install an elevator tab
control mechanism, part number (P/N)
251A2430-(), on any airplane, unless the
mechanism has been inspected before and
after installation using the inspection
procedures specified in paragraphs (o)(1) and
(o)(2) of this AD, and no discrepancies have
been found.
(2) An elevator tab control mechanism, P/
N 251A2430-(), may be installed, provided
that the inspection specified in paragraph (n)
of this AD is done within 300 flight hours
after doing the installation, and that the
inspection specified in paragraph (n) of this
AD is repeated thereafter at intervals not to
exceed 300 flight hours.
(u) New Replacement
For airplanes having line numbers 1
through 3909 inclusive: Within 60 months
after the effective date of this AD, replace the
left and right elevator tab control
mechanisms with elevator tab control
mechanisms that have new machined aft
attach lugs, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 737–27–1300, dated April
16, 2012. This replacement terminates the
requirements of paragraphs (g) through (t) of
this AD. Although Boeing Service Bulletin
737–27–1300, dated April 16, 2012, specifies
submitting a report, there is no requirement
to report completion of the replacement
required by paragraph (u) of this AD.
wreier-aviles on DSK5TPTVN1PROD with RULES
(v) New Parts Installation Prohibition
As of the effective date of this AD, no
person may install, on any airplane identified
in paragraph (v)(1) or (v)(2) of this AD, an
elevator tab control mechanism having P/N
251A2430–13, –14, –15, –16, –17, –18, –101,
–102, –103, –104, –105, or –106.
(1) Airplanes on which the replacement in
paragraph (u) of this AD has been
accomplished.
(2) Airplanes with line numbers 3910 and
subsequent.
(w) Paperwork Reduction Act Burden
Statement
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 5 minutes per
VerDate Mar<15>2010
14:43 Apr 03, 2013
Jkt 229001
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW., Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
(x) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be emailed to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010), are approved as AMOCs for the
corresponding provisions of this AD. The
expiration of the AMOCS to AD 2010–17–19,
as specified in the service information
identified in paragraphs (x)(4)(i) and (x)(4)(ii)
of this AD, is extended to remain valid until
accomplishment of the requirements of
paragraph (u) of this AD.
(i) Boeing Alert Service Bulletin 737–
27A1299, dated July 1, 2011 (which is not
incorporated by reference in this AD).
(ii) Boeing Alert Service Bulletin 737–
27A1299, Revision 1, dated April 16, 2012
(which is not incorporated by reference in
this AD).
(y) Related Information
For more information about this AD,
contact Kelly McGuckin, Aerospace
Engineer, Systems and Equipment Branch,
ANM–130S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue
SW., Renton, Washington 98057–3356;
phone: 425–917–6490; fax: 425–917–6590;
email: kelly.mcguckin@faa.gov.
(z) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
PO 00000
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Fmt 4700
Sfmt 4700
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(3) The following service information was
approved for IBR on May 9, 2013.
(i) Boeing Service Bulletin 737–27–1300,
dated April 16, 2012.
(ii) Reserved.
(4) The following service information was
approved for IBR on September 9, 2010 (75
FR 52242, August 25, 2010).
(i) Boeing Alert Service Bulletin 737–
27A1297, Revision 1, dated August 2, 2010.
(ii) Reserved.
(5) The following service information was
approved for IBR on April 29, 2010 (75 FR
21499, April 26, 2010).
(i) Boeing Alert Service Bulletin 737–
27A1297, dated April 16, 2010.
(ii) Reserved.
(6) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com.
(7) You may view this service information
at FAA, You may review copies of the
referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
(8) You may view this 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March
20, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–07209 Filed 4–3–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1014; Directorate
Identifier 2010–SW–058–AD; Amendment
39–17404; AD 2013–06–07]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model
SA–365N1, AS–365N2, and AS 365 N3
SUMMARY:
E:\FR\FM\04APR1.SGM
04APR1
Federal Register / Vol. 78, No. 65 / Thursday, April 4, 2013 / Rules and Regulations
helicopters. This AD requires revising
the Limitations section of the Rotorcraft
Flight Manual (RFM) to prohibit flight
in instrument meteorological conditions
(IMC) or night visual flight rules (VFR)
for each helicopter with a vertical gyro
unit GV76–1 installed upon a nonreinforced shelf in the rear cargo
compartment. Also, this AD requires
modifying the GV76–1 vertical gyro unit
shelf and testing for correct function of
the navigation systems. This AD was
prompted by flight crew reports of
deviations between the displayed
attitude on the attitude display screen
and the independent electromechanical
standby attitude indicator. The actions
of this AD are intended to prevent an
undetected flight display error of a slow
drift in the roll axis, disorientation of
the pilot, and subsequent loss of control
of the helicopter.
This AD is effective May 9, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of May 9, 2013.
DATES:
For service information
identified in this AD, contact American
Eurocopter Corporation, 2701 N. Forum
Drive, Grand Prairie, Texas 75052;
telephone (972) 641–0000 or (800) 232–
0323; fax (972) 641–3775; or at https://
www.eurocopter.com/techpub. You may
review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
ADDRESSES:
Examining the AD Docket
wreier-aviles on DSK5TPTVN1PROD with RULES
You may examine the AD docket on
the Internet at https://
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 AD
docket contains this AD, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Mark F. Wiley, Aviation Safety
Engineer, Regulations and Policy Group,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
mark.wiley@faa.gov.
SUPPLEMENTARY INFORMATION:
VerDate Mar<15>2010
14:43 Apr 03, 2013
Jkt 229001
Discussion
On September 25, 2012, at 77 FR
58971, the Federal Register published
our notice of proposed rulemaking
(NPRM), which proposed to amend 14
CFR part 39 to include an AD that
would apply to certain Eurocopter
Model SA–365N1, AS–365N2, and AS
365 N3 helicopters, with the GV76–1
vertical gyro unit installed on the lefthand (LH) or right-hand (RH) shelf in
the rear cargo compartment, pre-MOD
365P081895. That NPRM proposed to
require revising the Limitations section
of the RFM to prohibit flight in IMC or
night VFR until the GV76–1 vertical
gyro unit shelf is reinforced and tested.
The proposed requirements were
intended to prevent an undetected flight
display error of a slow drift in the roll
axis, disorientation of the pilot, 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
Union, issued EASA AD No. 2010–
0100R1, dated August 4, 2010, and
corrected August 11, 2010, to correct an
unsafe condition for the specified
Eurocopter model helicopters. EASA
advises that a slow drift in the roll axis
on the pilot’s and co-pilot’s attitude
display screens occurred
simultaneously during flight on several
helicopters equipped with the GV76–1
vertical gyro unit installed in the rear
cargo compartment. EASA advises
‘‘these drifts were caused by a fault in
the vertical gyros unit installation in the
rear cargo.’’ EASA states that in certain
configurations, the GV76–1 vertical gyro
unit installation has a natural mode
close to the main rotor’s harmonic
frequency that generates rather
significant vibratory levels on the
GV76–1 unit by amplifying the intrinsic
vibration of the aircraft. The faults are
caused by these vibratory levels. EASA
also states that the critical mode is
essentially due to bending on the
horizontal cross-members, which
support the GV76–1 shelf.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (77 FR 58971, September 25,
2012).
FAA’s 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, its
technical representative, has notified us
PO 00000
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Fmt 4700
Sfmt 4700
20235
of the unsafe condition described in the
EASA 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 and that air
safety and the public interest require
adopting the AD requirements as
proposed.
Differences Between This AD and the
EASA AD
We do not use the calendar dates,
which have already passed. This AD
prohibits flight in IMC or night VFR
until MOD 365P081895 is
accomplished.
Related Service Information
Eurocopter issued Alert Service
Bulletin (ASB) No. 34.00.31, Revision 1,
dated July 28, 2010 (ASB 34.00.31), for
FAA type-certificated Model SA–365N1,
AS–365N2, and AS 365 N3 helicopters
and for military non-FAA typecertificated Model AS–365F, Fi, and K
helicopters. ASB 34.00.31 specifies
reinforcing the shelves of the vertical
gyros GV76–1 (in cargo compartment)
on the RH or LH side. EASA classified
this ASB as mandatory and issued AD
No. 2010–0100R1, dated August 4, 2010,
and corrected August 11, 2010, to
ensure the continued airworthiness of
these helicopters.
Costs of Compliance
We estimate that this AD will affect
19 helicopters of U.S. Registry. We
estimate that operators may incur the
following costs in order to comply with
this AD. It will take about 16 workhours to install a shelf reinforcement kit
per helicopter at an average labor rate of
$85 per work-hour. Required parts will
cost about $2,560 per helicopter. Based
on these figures, we estimate the total
cost of this AD on U.S. operators to be
$74,480 to reinforce the shelf of the
entire fleet.
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
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04APR1
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Federal Register / Vol. 78, No. 65 / Thursday, April 4, 2013 / Rules and Regulations
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
helicopters identified in this rulemaking
action.
Regulatory Findings
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 to the extent that it justifies
making a regulatory distinction; 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.
We prepared an economic evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
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:
(h) Subject.
Joint Aircraft Service Component (JASC)
Code: 3421, Attitude Gyro and Indicator
System.
(b) Unsafe Condition
This AD defines the unsafe condition as an
undetected flight display error of a slow drift
in the roll axis. This condition could result
in disorientation of the pilot and subsequent
loss of control of the helicopter.
(i) Material Incorporated by Reference.
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Eurocopter Alert Service Bulletin No.
34.00.31, Revision 1, dated July 28, 2010.
(ii) Reserved.
(3) For Eurocopter service information
identified in this AD, contact American
Eurocopter Corporation, 2701 N. Forum
Drive, Grand Prairie, Texas 75052; telephone
(972) 641–0000 or (800) 232–0323; fax (972)
641–3775; or at https://www.eurocopter.com/
techpub.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
(c) Effective Date.
This AD becomes effective May 9, 2013.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) Before further flight, revise the
Limitations section of the Rotorcraft Flight
Manual (RFM) by inserting a copy of this AD
into the RFM or by pen and ink changes to
the RFM that prohibits flight in instrument
meteorological conditions (IMC) or night
visual flight rules (VFR) for each helicopter
with a vertical gyro unit GV76–1 installed on
the rear cargo compartment shelf without
reinforcement per Modification 365P081895.
(2) Within 110 hours time-in-service,
modify the GV76–1 vertical gyro unit shelf as
depicted in Figures 1 through 3 and by
following the Accomplishment Instructions,
paragraphs 2.A. through 2.B.2.e., of
Eurocopter Alert Service Bulletin No.
34.00.31, Revision 1, dated July 28, 2010.
After reinforcing the shelf, operationally test
the GV76–1 vertical gyro unit and
functionally test the navigation systems.
(3) After modifying the GV76–1 vertical
gyro unit shelf, remove this AD from the
Limitations section of the RFM or remove
any changes to the Limitations section of the
RFM that prohibit flight in IMC or VFR as a
result of paragraph (e)(1) of this AD.
(4) Modifying the GV76–1 vertical gyro
unit shelf is terminating action for the
requirements of this AD.
2013–06–07 Eurocopter France Helicopters:
Amendment 39–17404; Docket No.
FAA–2012–1014; Directorate Identifier
2010–SW–058–AD.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Mark F. Wiley,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
mark.wiley@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(a) Applicability
This AD applies to Model SA–365N1, AS–
365N2, and AS 365 N3 helicopters, with the
GV76–1 vertical gyro unit installed on the
left-hand (LH) or right-hand (RH) shelf in the
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency AD No.
2010–0100R1, dated August 4, 2010, and
corrected August 11, 2010.
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
wreier-aviles on DSK5TPTVN1PROD with RULES
rear cargo compartment, pre-MOD
365P081895, certificated in any category, all
serial numbers except 6698, 6701, 6723,
6737, and 6741.
VerDate Mar<15>2010
14:43 Apr 03, 2013
Jkt 229001
PO 00000
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Fmt 4700
Sfmt 4700
Issued in Fort Worth, Texas, on March 21,
2013.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2013–07211 Filed 4–3–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF THE INTERIOR
National Indian Gaming Commission
25 CFR Part 518
RIN 3141–AA44
Self-Regulation of Class II Gaming
National Indian Gaming
Commission.
ACTION: Final rule.
AGENCY:
The National Indian Gaming
Commission (NIGC or Commission)
amends its regulation for the review and
approval of petitions seeking the
issuance of a certificate for tribal selfregulation of Class II gaming.
DATES: Effective Date: The effective date
of these regulations is September 1,
2013.
FOR FURTHER INFORMATION CONTACT: John
Hay, National Indian Gaming
SUMMARY:
E:\FR\FM\04APR1.SGM
04APR1
Agencies
[Federal Register Volume 78, Number 65 (Thursday, April 4, 2013)]
[Rules and Regulations]
[Pages 20234-20236]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-07211]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1014; Directorate Identifier 2010-SW-058-AD;
Amendment 39-17404; AD 2013-06-07]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model SA-365N1, AS-365N2, and AS 365 N3
[[Page 20235]]
helicopters. This AD requires revising the Limitations section of the
Rotorcraft Flight Manual (RFM) to prohibit flight in instrument
meteorological conditions (IMC) or night visual flight rules (VFR) for
each helicopter with a vertical gyro unit GV76-1 installed upon a non-
reinforced shelf in the rear cargo compartment. Also, this AD requires
modifying the GV76-1 vertical gyro unit shelf and testing for correct
function of the navigation systems. This AD was prompted by flight crew
reports of deviations between the displayed attitude on the attitude
display screen and the independent electromechanical standby attitude
indicator. The actions of this AD are intended to prevent an undetected
flight display error of a slow drift in the roll axis, disorientation
of the pilot, and subsequent loss of control of the helicopter.
DATES: This AD is effective May 9, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of May 9, 2013.
ADDRESSES: For service information identified in this AD, contact
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie,
Texas 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-
3775; or at https://www.eurocopter.com/techpub. You may review the
referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
Examining the AD Docket
You may examine the AD docket on the Internet at https://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 AD docket contains this AD, any incorporated-by-reference
service information, the economic evaluation, any comments received,
and other information. The street address for the Docket Operations
Office (phone: 800-647-5527) is U.S. Department of Transportation,
Docket Operations Office, M-30, West Building Ground Floor, Room W12-
140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Mark F. Wiley, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110;
email mark.wiley@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On September 25, 2012, at 77 FR 58971, the Federal Register
published our notice of proposed rulemaking (NPRM), which proposed to
amend 14 CFR part 39 to include an AD that would apply to certain
Eurocopter Model SA-365N1, AS-365N2, and AS 365 N3 helicopters, with
the GV76-1 vertical gyro unit installed on the left-hand (LH) or right-
hand (RH) shelf in the rear cargo compartment, pre-MOD 365P081895. That
NPRM proposed to require revising the Limitations section of the RFM to
prohibit flight in IMC or night VFR until the GV76-1 vertical gyro unit
shelf is reinforced and tested. The proposed requirements were intended
to prevent an undetected flight display error of a slow drift in the
roll axis, disorientation of the pilot, 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 Union, issued EASA AD No.
2010-0100R1, dated August 4, 2010, and corrected August 11, 2010, to
correct an unsafe condition for the specified Eurocopter model
helicopters. EASA advises that a slow drift in the roll axis on the
pilot's and co-pilot's attitude display screens occurred simultaneously
during flight on several helicopters equipped with the GV76-1 vertical
gyro unit installed in the rear cargo compartment. EASA advises ``these
drifts were caused by a fault in the vertical gyros unit installation
in the rear cargo.'' EASA states that in certain configurations, the
GV76-1 vertical gyro unit installation has a natural mode close to the
main rotor's harmonic frequency that generates rather significant
vibratory levels on the GV76-1 unit by amplifying the intrinsic
vibration of the aircraft. The faults are caused by these vibratory
levels. EASA also states that the critical mode is essentially due to
bending on the horizontal cross-members, which support the GV76-1
shelf.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (77 FR 58971,
September 25, 2012).
FAA's 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, its technical
representative, has notified us of the unsafe condition described in
the EASA 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 and that air safety and the public interest require
adopting the AD requirements as proposed.
Differences Between This AD and the EASA AD
We do not use the calendar dates, which have already passed. This
AD prohibits flight in IMC or night VFR until MOD 365P081895 is
accomplished.
Related Service Information
Eurocopter issued Alert Service Bulletin (ASB) No. 34.00.31,
Revision 1, dated July 28, 2010 (ASB 34.00.31), for FAA type-
certificated Model SA-365N1, AS-365N2, and AS 365 N3 helicopters and
for military non-FAA type-certificated Model AS-365F, Fi, and K
helicopters. ASB 34.00.31 specifies reinforcing the shelves of the
vertical gyros GV76-1 (in cargo compartment) on the RH or LH side. EASA
classified this ASB as mandatory and issued AD No. 2010-0100R1, dated
August 4, 2010, and corrected August 11, 2010, to ensure the continued
airworthiness of these helicopters.
Costs of Compliance
We estimate that this AD will affect 19 helicopters of U.S.
Registry. We estimate that operators may incur the following costs in
order to comply with this AD. It will take about 16 work-hours to
install a shelf reinforcement kit per helicopter at an average labor
rate of $85 per work-hour. Required parts will cost about $2,560 per
helicopter. Based on these figures, we estimate the total cost of this
AD on U.S. operators to be $74,480 to reinforce the shelf of the entire
fleet.
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
[[Page 20236]]
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 helicopters
identified in this rulemaking action.
Regulatory Findings
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 to the extent
that it justifies making a regulatory distinction; 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.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
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 adding the following new airworthiness
directive (AD):
2013-06-07 Eurocopter France Helicopters: Amendment 39-17404; Docket
No. FAA-2012-1014; Directorate Identifier 2010-SW-058-AD.
(a) Applicability
This AD applies to Model SA-365N1, AS-365N2, and AS 365 N3
helicopters, with the GV76-1 vertical gyro unit installed on the
left-hand (LH) or right-hand (RH) shelf in the rear cargo
compartment, pre-MOD 365P081895, certificated in any category, all
serial numbers except 6698, 6701, 6723, 6737, and 6741.
(b) Unsafe Condition
This AD defines the unsafe condition as an undetected flight
display error of a slow drift in the roll axis. This condition could
result in disorientation of the pilot and subsequent loss of control
of the helicopter.
(c) Effective Date.
This AD becomes effective May 9, 2013.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
(1) Before further flight, revise the Limitations section of the
Rotorcraft Flight Manual (RFM) by inserting a copy of this AD into
the RFM or by pen and ink changes to the RFM that prohibits flight
in instrument meteorological conditions (IMC) or night visual flight
rules (VFR) for each helicopter with a vertical gyro unit GV76-1
installed on the rear cargo compartment shelf without reinforcement
per Modification 365P081895.
(2) Within 110 hours time-in-service, modify the GV76-1 vertical
gyro unit shelf as depicted in Figures 1 through 3 and by following
the Accomplishment Instructions, paragraphs 2.A. through 2.B.2.e.,
of Eurocopter Alert Service Bulletin No. 34.00.31, Revision 1, dated
July 28, 2010. After reinforcing the shelf, operationally test the
GV76-1 vertical gyro unit and functionally test the navigation
systems.
(3) After modifying the GV76-1 vertical gyro unit shelf, remove
this AD from the Limitations section of the RFM or remove any
changes to the Limitations section of the RFM that prohibit flight
in IMC or VFR as a result of paragraph (e)(1) of this AD.
(4) Modifying the GV76-1 vertical gyro unit shelf is terminating
action for the requirements of this AD.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Mark F. Wiley, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email mark.wiley@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office, before operating any aircraft
complying with this AD through an AMOC.
(g) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency AD No. 2010-0100R1, dated August 4, 2010, and corrected
August 11, 2010.
(h) Subject.
Joint Aircraft Service Component (JASC) Code: 3421, Attitude
Gyro and Indicator System.
(i) Material Incorporated by Reference.
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Eurocopter Alert Service Bulletin No. 34.00.31, Revision 1,
dated July 28, 2010.
(ii) Reserved.
(3) For Eurocopter service information identified in this AD,
contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand
Prairie, Texas 75052; telephone (972) 641-0000 or (800) 232-0323;
fax (972) 641-3775; or at https://www.eurocopter.com/techpub.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. For information on the availability of this
material at the FAA, call (817) 222-5110.
(5) You may view this 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on March 21, 2013.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013-07211 Filed 4-3-13; 8:45 am]
BILLING CODE 4910-13-P