Airworthiness Directives; Eurocopter France Helicopters, 5247-5249 [2014-01461]

Download as PDF 5247 Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations (2) Step #2—Convert each gross notional by its derivative adjustment factor to produce an adjusted gross notional. The derivative adjustment factor approximates the price sensitivity for each of the product groups in order to weight the notional amount by sensitivity before weighting for maturity. (i) For cap and floor options, the derivative adjustment factor is 33 percent. For example, an interest rate cap with a $1 million notional amount has an adjusted gross notional of $330,000 ($1,000,000 × 0.33 + $330,000). (ii) For interest rate swaps and Treasury futures, the derivative adjustment factor is 100 percent. For example, an interest rate swap with a $1 million notional amount has an adjusted gross notional of $1,000,000 ($1,000,000 × 1.00 = $1,000,000). (iii) The total adjusted notional for all derivatives positions is the sum of (i) and (ii) above. (3) Step #3—Produce the weighted average remaining time to maturity (WARM) for all derivatives positions. (i) For interest rate caps, interest rate floors, and interest rate swaps, the remaining maturity is the time left between the reporting date and the contracted maturity date, expressed in years (round up to two decimals); (ii) For Treasury futures, the remaining maturity is the underlying deliverable Treasury note’s maximum maturity (e.g., a five-year Treasury note future has a five-year remaining maturity); and (iii) Determine the WARM using the adjusted gross notional, as set forth in subsection (2) of this section, and the remaining time to maturity as defined for each product group above in paragraphs (b)(3)(i) and (ii) of this appendix. (4) Step #4—Produce the WARMN by converting the WARM to a percentage and then multiplying the percentage by the total adjusted gross notional. (i) Divide the WARM, as calculated in paragraph (b)(3) of this appendix, by ten to convert it to a percentage (e.g., 7.75 WARMN is translated to 77.5 percent); and (ii) Multiply the WARM converted to a percentage, as described in paragraph (c)(4)(i) of this appendix, by total adjusted gross notional, described in paragraph (c)(2) of this appendix. (5) Compare WARMN calculation to the WARNM limit for compliance. The total in step four (4) must be less than the limit in paragraph (a)(1)(ii) or (a)(2)(ii) of this appendix, as applicable. (6) Example calculations for compliance with this subpart: WARMN. The table below provides an illustrative example of the WARMN limit calculations for a sample Federal credit union that has entry level authority. The sample Federal credit union has a net worth of $100 million and total assets of $1 billion; its notional limit authority is $65 million (65 percent of net worth). TABLE 4—EXAMPLE WARMN LIMIT CALCULATION Options Gross Notional (Step #1) ................................................................. Adjustment Factor ............................................................................ Adjusted Notional (Step #2) ............................................................ Weighted Average Remaining Maturity (WARM) (Step #3) ............ Swaps $50,000,000 100% $50,000,000 8.50 Total $5,000,000 100% $5,000,000 5.00 $155,000,000 ............................ $88,000,000 7.74 Weighted Average Remaining Maturity Notional (WARMN) (Step #4): Notional Limit Authority (65% of net worth) Under/(Over) Notional Limit Authority 1 (77.4% $100,000,000 33% $33,000,000 7.00 Futures 1 $68,100,000 $65,000,000 ($3,100,000) of Step #3.) PART 715—SUPERVISORY COMMITTEE AUDITS AND VERIFICATIONS PART 741—REQUIREMENTS FOR INSURANCE DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 9. The authority citation for part 741 is revised to read as follows: 14 CFR Part 39 Authority: 12 U.S.C. 1757, 1766(a), 1781– 1790, and 1790d; 31 U.S.C. 3717. [Docket No. FAA–2013–0501; Directorate Identifier 2011–SW–036–AD; Amendment 39–17732; AD 2014–02–04] 10. Revise § 741.219 to read as follows: RIN 2120–AA64 § 741.219 Airworthiness Directives; Eurocopter France Helicopters ■ 7. The authority citation for part 715 continues to read as follows: ■ Authority: 12 U.S.C. 1757, 1766(a), and 1781–1790; 31 U.S.C. 3717. ■ 8. In § 715.5, revise paragraph (a) to read as follows: ■ emcdonald on DSK67QTVN1PROD with RULES § 715.5 Audit of Federal Credit Unions. (a) Total assets of $500 million or greater. To fulfill its Supervisory Committee audit responsibility, a Federal credit union having total assets of $500 million or greater, except as provided in § 703.106(b)(3) of this chapter, must obtain an annual audit of its financial statements performed in accordance with Generally Accepted Auditing Standards by an independent person who is licensed to do so by the State or jurisdiction in which the credit union is principally located. * * * * * VerDate Mar<15>2010 17:58 Jan 30, 2014 Jkt 232001 Investment requirements. (a) Any credit union which is insured pursuant to Title II of the Act must adhere to the requirements stated in part 703 of this chapter concerning transacting business with corporate credit unions. (b) Any credit union which is insured pursuant to Title II of the Act must notify the applicable NCUA Regional Director or the Director of the Office of National Examinations and Supervision in writing at least 30 days before it begins engaging in derivatives. [FR Doc. 2014–01703 Filed 1–30–14; 8:45 am] BILLING CODE 7535–01–P PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B and EC155B1 helicopters. This AD requires repetitively inspecting the lower and upper front and rear fittings (fittings) that attach the upper fin to the fenestron for a crack and, if there is a crack, removing all four fittings from service. This AD also requires, within a specified time, removing all fittings from service, and the fittings would not be eligible to be installed on any SUMMARY: E:\FR\FM\31JAR1.SGM 31JAR1 5248 Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations helicopter. This AD was prompted by the loss of an upper fin in flight. The actions of this AD are intended to detect a crack in the fittings to prevent loss of the upper fin and subsequent loss of control of the helicopter. DATES: This AD is effective March 7, 2014. The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of March 7, 2014. ADDRESSES: For service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 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. emcdonald on DSK67QTVN1PROD with RULES 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, the European Aviation Safety Agency (EASA) 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: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone 817–222–5110; email robert.grant@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On June 11, 2013, at 78 FR 34960, 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 Model EC 155B and EC155B1 helicopters. The NPRM proposed inspecting certain part-numbered fittings for a crack and, if there is a crack, removing the fittings from service before further flight. Also, the NPRM proposed removing certain partnumbered fittings from service within 180 hours time-in-service (TIS) and prohibiting the fittings from being VerDate Mar<15>2010 17:58 Jan 30, 2014 Jkt 232001 eligible for installation on any helicopter. The proposed requirements were intended to detect a crack in the fittings to prevent loss of the upper fin and subsequent loss of control of the helicopter. The NPRM was prompted by AD No. 2011–0108, dated June 7, 2011, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Eurocopter Model EC 155B and EC155B1 helicopters. EASA advises of an in-flight loss of a fin on a Model EC155B1 helicopter. According to EASA, a crack in the fittings attaching the upper fin to the fenestron (tail rotor assembly) was discovered during an investigation. As a result, EASA issued an emergency AD to mandate repetitive inspections of the upper fin attachment fittings. EASA states that Eurocopter developed modification (MOD) 0754B40 to increase the strength of the fuselagefin junction fittings by installing two reinforced single-piece fittings to replace the affected fittings, which is terminating action for the repetitive inspection requirements. EASA subsequently issued AD No. 2011–0108, which superseded its emergency AD, to require installation of MOD 0754B40 and to retain the repetitive inspection requirements until the MOD is installed. Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (78 FR 34960, June 11, 2013). 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 This AD does not require replacing the upper fin to fenestron fittings with reinforced fittings in accordance with MOD 0754B40 within 6 calendar months as stated in the EASA AD, but rather requires removing the affected fittings from service within the equivalent 180 hours TIS. PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 Related Service Information Eurocopter has issued Emergency Alert Service Bulletin No. 05A017, Revision 2, dated December 9, 2010, which specifies repetitively inspecting the fittings for a crack and replacing each fitting if there is a crack. Eurocopter has also issued Service Bulletin No. 53–029, Revision 1, dated March 10, 2011, which specifies replacing the fittings with reinforced fittings in accordance with MOD 0754B40. Costs of Compliance We estimate that this AD will affect 9 helicopters of U.S. Registry. We estimate that operators will incur the following costs in order to comply with this AD based on an average labor rate of $85 per work hour. It will take 1 work hour to inspect the fittings and about 3 inspections before replacement. It will take 8 work hours to replace the fittings, and required parts will cost $3,311. Based on these figures, the total cost will be $4,246 per helicopter and $38,214 for the U.S. 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 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; E:\FR\FM\31JAR1.SGM 31JAR1 Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations (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: (f) Credit for Actions Previously Completed Inspections accomplished before the effective date of this AD in accordance with the procedures specified in Eurocopter Emergency Alert Service Bulletin No. 05A017, Revision 2, dated December 9, 2010; Revision 1, dated January 27, 2010; and Revision 0, dated September 28, 2007, are considered acceptable for compliance with the initial inspection specified in paragraph (e)(1) of this AD. 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): ■ 2014–02–04 Eurocopter France Helicopters: Amendment 39–17732; Docket No. FAA–2013–0501; Directorate Identifier 2011–SW–036–AD. (a) Applicability This AD applies to Model EC 155B and EC155B1 helicopters with lower front fitting part number (P/N) 365A23–4240–01, upper front fitting P/N 365A23–4242–01, lower rear fitting P/N 365A23–4241–01, or upper rear fitting P/N 365A23–4243–01 (fittings), installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in a fitting. This condition could result in loss of the upper fin during flight and subsequent loss of control of the helicopter. emcdonald on DSK67QTVN1PROD with RULES (c) Effective Date This AD becomes effective March 7, 2014. (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) Within 15 hours time-in-service (TIS) and thereafter at intervals not to exceed 55 hours TIS: (i) Using an appropriate light source and a 10x or higher power magnifying glass, inspect each front (item c) and rear (item d) VerDate Mar<15>2010 17:58 Jan 30, 2014 Jkt 232001 upper fitting and each front (item e) and rear (item f) lower fitting for a crack as depicted in Detail A of Figure 1 of Eurocopter Emergency Alert Service Bulletin No. 05A017, Revision 2, dated December 9, 2010 (ASB). Inspect the hatched area as depicted in Details B, C, and D of Figure 2 of the ASB. A high-resolution (more than 2 million pixels) digital camera or dye-penetrant inspection may be used to facilitate the crack inspection. (ii) If there is a crack in any fitting, before further flight, remove all four fittings from service. (2) Within 180 hours TIS, remove the fittings from service. (3) Do not install lower front fitting P/N 365A23–4240–01, upper front fitting P/N 365A23–4242–01, lower rear fitting P/N 365A23–4241–01, and upper rear fitting P/N 365A23–4243–01 on any helicopter. (g) Special flight permits Special flight permits will not be issued. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone 817–222– 5110; email robert.grant@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. (i) Additional Information (1) Eurocopter Service Bulletin No. 53–029, Revision 1, dated March 10, 2011, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 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. (2) The subject of this AD is addressed in European Aviation Safety Agency AD No. 2011–0108, dated June 7, 2011, which can be found in Docket No. FAA–2013–0501 on the Internet at https://www.regulations.gov. PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 5249 (j) Subject Joint Aircraft Service Component (JASC) Code: 5530 Vertical Stabilizer Structure. (k) 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 Emergency Alert Service Bulletin No. 05A017, Revision 2, dated December 9, 2010. (ii) Reserved. (3) For Eurocopter service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 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. Issued in Fort Worth, Texas, on January 16, 2014. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2014–01461 Filed 1–30–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0525; Directorate Identifier 2011–SW–063–AD; Amendment 39–17730; AD 2014–02–02] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Limited (Bell) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Bell Model 206L, L–1, L–3, and L–4 helicopters. This AD requires measuring each main rotor (M/R) blade spar space to determine whether it is oversized and reidentifying the M/R blade and SUMMARY: E:\FR\FM\31JAR1.SGM 31JAR1

Agencies

[Federal Register Volume 79, Number 21 (Friday, January 31, 2014)]
[Rules and Regulations]
[Pages 5247-5249]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-01461]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0501; Directorate Identifier 2011-SW-036-AD; 
Amendment 39-17732; AD 2014-02-04]
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 EC 155B and EC155B1 helicopters. 
This AD requires repetitively inspecting the lower and upper front and 
rear fittings (fittings) that attach the upper fin to the fenestron for 
a crack and, if there is a crack, removing all four fittings from 
service. This AD also requires, within a specified time, removing all 
fittings from service, and the fittings would not be eligible to be 
installed on any

[[Page 5248]]

helicopter. This AD was prompted by the loss of an upper fin in flight. 
The actions of this AD are intended to detect a crack in the fittings 
to prevent loss of the upper fin and subsequent loss of control of the 
helicopter.

DATES: This AD is effective March 7, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of March 7, 2014.

ADDRESSES: For service information identified in this AD, contact 
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 
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, the European Aviation Safety 
Agency (EASA) 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: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; telephone 817-222-5110; email robert.grant@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    On June 11, 2013, at 78 FR 34960, 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 Model EC 155B and 
EC155B1 helicopters. The NPRM proposed inspecting certain part-numbered 
fittings for a crack and, if there is a crack, removing the fittings 
from service before further flight. Also, the NPRM proposed removing 
certain part-numbered fittings from service within 180 hours time-in-
service (TIS) and prohibiting the fittings from being eligible for 
installation on any helicopter. The proposed requirements were intended 
to detect a crack in the fittings to prevent loss of the upper fin and 
subsequent loss of control of the helicopter.
    The NPRM was prompted by AD No. 2011-0108, dated June 7, 2011, 
issued by EASA, which is the Technical Agent for the Member States of 
the European Union, to correct an unsafe condition for Eurocopter Model 
EC 155B and EC155B1 helicopters. EASA advises of an in-flight loss of a 
fin on a Model EC155B1 helicopter. According to EASA, a crack in the 
fittings attaching the upper fin to the fenestron (tail rotor assembly) 
was discovered during an investigation. As a result, EASA issued an 
emergency AD to mandate repetitive inspections of the upper fin 
attachment fittings. EASA states that Eurocopter developed modification 
(MOD) 0754B40 to increase the strength of the fuselage-fin junction 
fittings by installing two reinforced single-piece fittings to replace 
the affected fittings, which is terminating action for the repetitive 
inspection requirements. EASA subsequently issued AD No. 2011-0108, 
which superseded its emergency AD, to require installation of MOD 
0754B40 and to retain the repetitive inspection requirements until the 
MOD is installed.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (78 FR 34960, 
June 11, 2013).

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

    This AD does not require replacing the upper fin to fenestron 
fittings with reinforced fittings in accordance with MOD 0754B40 within 
6 calendar months as stated in the EASA AD, but rather requires 
removing the affected fittings from service within the equivalent 180 
hours TIS.

Related Service Information

    Eurocopter has issued Emergency Alert Service Bulletin No. 05A017, 
Revision 2, dated December 9, 2010, which specifies repetitively 
inspecting the fittings for a crack and replacing each fitting if there 
is a crack. Eurocopter has also issued Service Bulletin No. 53-029, 
Revision 1, dated March 10, 2011, which specifies replacing the 
fittings with reinforced fittings in accordance with MOD 0754B40.

Costs of Compliance

    We estimate that this AD will affect 9 helicopters of U.S. 
Registry. We estimate that operators will incur the following costs in 
order to comply with this AD based on an average labor rate of $85 per 
work hour. It will take 1 work hour to inspect the fittings and about 3 
inspections before replacement. It will take 8 work hours to replace 
the fittings, and required parts will cost $3,311. Based on these 
figures, the total cost will be $4,246 per helicopter and $38,214 for 
the U.S. 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 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;

[[Page 5249]]

    (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):

    2014-02-04 Eurocopter France Helicopters: Amendment 39-17732; 
Docket No. FAA-2013-0501; Directorate Identifier 2011-SW-036-AD.

(a) Applicability

    This AD applies to Model EC 155B and EC155B1 helicopters with 
lower front fitting part number (P/N) 365A23-4240-01, upper front 
fitting P/N 365A23-4242-01, lower rear fitting P/N 365A23-4241-01, 
or upper rear fitting P/N 365A23-4243-01 (fittings), installed, 
certificated in any category.

 (b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a fitting. 
This condition could result in loss of the upper fin during flight 
and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective March 7, 2014.

(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) Within 15 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 55 hours TIS:
    (i) Using an appropriate light source and a 10x or higher power 
magnifying glass, inspect each front (item c) and rear (item d) 
upper fitting and each front (item e) and rear (item f) lower 
fitting for a crack as depicted in Detail A of Figure 1 of 
Eurocopter Emergency Alert Service Bulletin No. 05A017, Revision 2, 
dated December 9, 2010 (ASB). Inspect the hatched area as depicted 
in Details B, C, and D of Figure 2 of the ASB. A high-resolution 
(more than 2 million pixels) digital camera or dye-penetrant 
inspection may be used to facilitate the crack inspection.
    (ii) If there is a crack in any fitting, before further flight, 
remove all four fittings from service.
    (2) Within 180 hours TIS, remove the fittings from service.
    (3) Do not install lower front fitting P/N 365A23-4240-01, upper 
front fitting P/N 365A23-4242-01, lower rear fitting P/N 365A23-
4241-01, and upper rear fitting P/N 365A23-4243-01 on any 
helicopter.

(f) Credit for Actions Previously Completed

    Inspections accomplished before the effective date of this AD in 
accordance with the procedures specified in Eurocopter Emergency 
Alert Service Bulletin No. 05A017, Revision 2, dated December 9, 
2010; Revision 1, dated January 27, 2010; and Revision 0, dated 
September 28, 2007, are considered acceptable for compliance with 
the initial inspection specified in paragraph (e)(1) of this AD.

(g) Special flight permits

    Special flight permits will not be issued.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort 
Worth, Texas 76137; telephone 817-222-5110; email 
robert.grant@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.

(i) Additional Information

    (1) Eurocopter Service Bulletin No. 53-029, Revision 1, dated 
March 10, 2011, which is not incorporated by reference, contains 
additional information about the subject of this AD. For service 
information identified in this AD, contact American Eurocopter 
Corporation, 2701 N. Forum Drive, Grand Prairie, TX 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.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency AD No. 2011-0108, dated June 7, 2011, which can be 
found in Docket No. FAA-2013-0501 on the Internet at https://www.regulations.gov.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 5530 Vertical 
Stabilizer Structure.

(k) 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 Emergency Alert Service Bulletin No. 05A017, 
Revision 2, dated December 9, 2010.
    (ii) Reserved.
    (3) For Eurocopter service information identified in this AD, 
contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand 
Prairie, TX 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 January 16, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-01461 Filed 1-30-14; 8:45 am]
BILLING CODE 4910-13-P
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