Airworthiness Directives; Eurocopter France Helicopters, 20234-20236 [2013-07211]

Download as PDF 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 Frm 00008 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: http:// 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 http:// 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 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 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 Frm 00009 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 E:\FR\FM\04APR1.SGM 04APR1 20236 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 http://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: http:// 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 Frm 00010 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]


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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 http://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 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 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 http://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: http://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