Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France), 60292-60295 [2017-27274]

Download as PDF 60292 Federal Register / Vol. 82, No. 243 / Wednesday, December 20, 2017 / Rules and Regulations Authority: 12 U.S.C. 1752(5), 1755, 1756, 1757, 1758, 1759, 1761a, 1761b, 1766, 1767, 1782, 1784, 1786, 1787, 1789. Section 701.6 is also authorized by 15 U.S.C. 3717. Section 701.31 is also authorized by 15 U.S.C. 1601 et seq.; 42 U.S.C. 1981 and 3601–3610. Section 701.35 is also authorized by 42 U.S.C. 4311–4312. Appendix B to Part 701 [Amended] 2. In appendix B to part 701, remove the term ‘‘Office of Consumer Financial Protection and Access’’ wherever it appears and add in its place the term ‘‘Office of Credit Union Resources and Expansion’’. ■ PART 705—COMMUNITY DEVELOPMENT REVOLVING LOAN FUND FOR CREDIT UNIONS 10. In § 790.2, revise the second sentence of paragraph (b)(6), paragraph (b)(12), the third sentence of paragraph (b)(13), and paragraph (b)(15) to read as follows: Authority: 12 U.S.C. 1756, 1757, 1766, 1782, 1784, 1785, 1786. 4. In § 705.5, in paragraph (d), remove the term ‘‘Office of Small Credit Union Initiatives’’ and add in its place the term ‘‘Office of Credit Union Resources and Expansion’’. ■ PART 708a—BANK CONVERSIONS AND MERGERS 5. The authority citation for part 708a continues to read as follows: ■ Authority: 12 U.S.C. 1766, 1785(b), and 1785(c). 6. In § 708a.101, revise the first sentence of the definition of ‘‘Regional Director’’ to read as follows: ■ Definitions. * * * * * Regional Director means either the director for the NCUA Regional Office for the region where a natural person credit union’s main office is located or the director of the NCUA’s Office of Credit Union Resources and Expansion. * * * * * * * * PART 708b—MERGERS OF FEDERALLY-INSURED CREDIT UNIONS; VOLUNTARY TERMINATION OR CONVERSION OF INSURED STATUS 7. The authority citation for part 708b continues to read as follows: ■ ethrower on DSK3G9T082PROD with RULES Authority: 12 U.S.C. 1752(7), 1766, 1785, 1786, and 1789. 8. In § 708b.2, revise the definition of ‘‘Regional Director’’ to read as follows: § 708b.2 Definitions. * * * * * Regional Director means either the director for the NCUA Regional Office VerDate Sep<11>2014 16:19 Dec 19, 2017 Jkt 244001 9. The authority citation for part 790 continues to read as follows: ■ ■ 3. The authority citation for part 705 continues to read as follows: ■ PART 790—DESCRIPTION OF NCUA; REQUEST FOR AGENCY ACTION Authority: 12 U.S.C. 1766, 1789, 1795f. ■ § 708a.101 for the region where a natural person credit union’s main office is located or the director of the NCUA’s Office of Credit Union Resources and Expansion. For corporate credit unions and natural person credit unions with $10 billion or more in assets, Regional Director means the director of the NCUA’s Office of National Examinations and Supervision. * * * * * § 790.2 Central and field office organization. * * * * * (b) * * * (6) * * * The Executive Director translates the NCUA Board policy decisions into workable programs, delegates responsibility for these programs to appropriate staff members, and coordinates the activities of the senior executive staff, which includes: The General Counsel; the Regional Directors; and the Office Directors for the Asset Management and Assistance Center, Chief Economist, Chief Financial Officer, Chief Information Officer, Consumer Financial Protection, Continuity and Security Management, Credit Union Resources and Expansion, Examination and Insurance, Human Resources, Minority and Women Inclusion, National Examinations and Supervision, and Public and Congressional Affairs. * * * * * * * * (12) Credit Union Resources and Expansion. This Office is responsible for coordinating NCUA policy and actions related to credit union chartering and field of membership, low income designation, and preserving credit unions run by minorities and/or serving minorities. The Office administers the Community Development Revolving Loan Program for Credit Unions (Program). This Program is funded from congressional appropriations and serves as a source of financial support, in the form of technical assistance grants and loans to low-income credit unions serving predominantly low-income members. The Program is governed by part 705 of subchapter A of this chapter. * * * * * PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 (13) Office of Minority and Women Inclusion. * * * Specific duties of the Office include developing and implementing standards for: Equal employment opportunity and the racial, ethnic, and gender diversity of the workforce and senior management of the NCUA; increased participation of minority-owned and women-owned businesses in the programs and contracts of the NCUA, including standards for coordinating technical assistance to such businesses; and assessing the diversity policies and practices of credit unions regulated by the NCUA. * * * * * * * * (15) Office of Consumer Financial Protection. (i) The Office of Consumer Financial Protection contains two divisions: (A) The Division of Consumer Compliance Policy and Outreach; and (B) The Division of Consumer Affairs; (ii) The Office provides consumer financial services, including consumer education and complaint resolution; establishes, consolidates, and coordinates consumer financial protections within the agency; oversees the agency’s fair lending examination program; and acts as the central liaison on consumer financial protection with other federal agencies. * * * * * [FR Doc. 2017–27411 Filed 12–19–17; 8:45 am] BILLING CODE 7535–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0671; Product Identifier 2016–SW–072–AD; Amendment 39–19135; AD 2017–26–04] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2009–25– 07 for Airbus Helicopters Model EC120B helicopters. AD 2009–25–07 required amending the rotorcraft flight manual supplement (RFMS) and preflight checking the emergency flotation gear before each flight over water. Since we issued AD 2009–25–07, Airbus Helicopters developed a terminating action and identified an additional part- SUMMARY: E:\FR\FM\20DER1.SGM 20DER1 Federal Register / Vol. 82, No. 243 / Wednesday, December 20, 2017 / Rules and Regulations numbered emergency floatation gear part with the unsafe condition. This new AD retains the requirements of AD 2009–25–07, expands the applicability, and adds a terminating action for the repetitive inspections. The actions of this AD are intended to correct an unsafe condition on these helicopters. DATES: This AD is effective January 24, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/website/ technical-expert/. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. ethrower on DSK3G9T082PROD with RULES Examining the AD Docket You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0671; 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, 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: George Schwab, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email george.schwab@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2009–25–07 (74 FR 65682, December 11, 2009) (2009– 25–07), and add a new AD. AD 2009– 25–07 applied to Eurocopter France (now Airbus Helicopters) Model EC120B helicopters. AD 2009–25–07 required amending the limitations section of RFMS to prohibit flight over water if the ‘‘float arm’’ pushbutton does not remain lit, conducting a pilot check to determine whether the ‘‘float arm’’ pushbutton remains lit before any flight VerDate Sep<11>2014 16:19 Dec 19, 2017 Jkt 244001 over water, and placarding the ‘‘float arm’’ pushbutton as inoperative if the functional check is unsuccessful. The NPRM published in the Federal Register on July 14, 2017 (82 FR 32501). The NPRM was prompted by AD No. 2016–0180, dated September 13, 2016 (AD 2016–0180), issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Model EC120B helicopters. EASA advises that Airbus Helicopters has designed an improved latching pushbutton, which when installed becomes a terminating action for the repetitive functional checks of the float arm pushbuttons. EASA also states that lighting and ancillary control unit (LACU) part number (P/N) 040101BA is equipped with the same faulty pushbutton and must be included in the applicability. Accordingly, the NPRM proposed to retain the RFMS amendment and repetitive functional check requirements of AD 2009–25–07, add LACU P/N 040101BA to the applicability paragraph, require replacing the float arm pushbutton P/N 045004A111A with float arm pushbutton P/N 304–2500–00 within 300 hours time-in-service (TIS), and prohibit installing float arm pushbutton P/N 045004A111A on any helicopter. Replacing the float arm pushbutton was also proposed as a terminating action for the repetitive functional checks prior to flight overwater. An owner/operator (pilot) may perform the functional check required by this AD and must enter compliance with that paragraph into the helicopter maintenance records in accordance with 14 CFR 43.9(a)(1) through (4) and 91.417(a)(2)(v). A pilot may perform this check because it involves only a functional check to determine whether the emergency flotation gear has been armed and can be performed equally well by a pilot or a mechanic. This check is an exception to our standard maintenance regulations. The proposed requirements were intended to prohibit flight over water if a functional test indicates that the emergency flotation gear cannot be armed, which would preclude deployment of the floats in an emergency water ditching, resulting in subsequent damage to the helicopter and injury to occupants. Since the NPRM was issued, the FAA’s Aircraft Certification Service has changed its organization structure. The new structure replaces product directorates with functional divisions. We have revised some of the office titles and nomenclature throughout this Final rule to reflect the new organizational PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 60293 changes. Additional information about the new structure can be found in the Notice published on July 25, 2017 (82 FR 34564). Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM. FAA’s Determination We have reviewed the relevant information and determined that an 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 The EASA AD requires installing the LACU float arm pushbutton within 13 months; this AD requires the installation within 300 hours TIS. Related Service Information We reviewed Airbus Helicopters Emergency Alert Service Bulletin No. 04A007, Revision 1, dated June 30, 2016 (EASB), for Airbus Helicopters Model EC120B helicopters. The EASB describes procedures for a pre-flight check of the float arm pushbutton while arming the emergency flotation gear and prohibits operators from flight over water if the float arm pushbutton fails. We also reviewed Airbus Helicopters Alert Service Bulletin No. EC120– 31A008, Revision 0, dated June 30, 2016 (ASB), for Airbus Helicopters Model EC120B helicopters. The ASB describes procedures for replacing the float arm pushbutton with a new design pushbutton and for re-labeling the modified LACU with a new P/N label. Costs of Compliance We estimate this AD will affect 53 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. At an average labor rate of $85 per hour, the cost of revising the limitations section of the RFMS and of the pre-flight functional check is negligible. Replacing the float arm pushbutton will require about 2 workhours, and required parts cost about $311, for a cost per helicopter of $481 and a total cost of $25,493 to 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, E:\FR\FM\20DER1.SGM 20DER1 60294 Federal Register / Vol. 82, No. 243 / Wednesday, December 20, 2017 / Rules and Regulations 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; (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. (a) Applicability This AD applies to Airbus Helicopters (previously Eurocopter France) Model EC120B helicopters, certificated in any category, with a Lighting and Ancillary Control Unit (LACU) part-number (P/N) 040101AB or 040101BA with a float arm pushbutton P/N 045004A111A installed. (b) Unsafe Condition This AD defines the unsafe condition as failure of a ‘‘float arm’’ pushbutton, which could result in inoperative floats being used in an emergency water ditching, causing damage to the helicopter or injury to occupants. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (c) Affected ADs PART 39—AIRWORTHINESS DIRECTIVES This AD becomes effective January 24, 2018. 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] This AD supersedes AD 2009–25–07, Amendment 39–16126 (74 FR 65682, December 11, 2009). (d) Effective Date (e) 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. ■ (f) Required Actions 2017–26–04 Airbus Helicopters (Previously Eurocopter France): Amendment 39– 19135; Docket No. FAA–2017–0671; Product Identifier 2016–SW–072–AD. (1) Before further flight, amend the EC120B Rotorcraft Flight Manual Supplement (RFMS) for the Aerazur emergency flotation gear, by inserting a copy of this AD into the Limitations section of the RFMS or by making pen and ink changes to that section to add the information in Figure 1 to paragraph (f)(1) of this AD: 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2009–25–07, Amendment 39–16126 (74 FR 65682, December 11, 2009), and adding the following new AD: FIGURE 1 TO PARAGRAPH (f)(1)—AMENDMENT TO RFMS ethrower on DSK3G9T082PROD with RULES Arm the emergency flotation gear by pressing the LACU ‘‘FLOAT ARM’’ pushbutton. —If both lights of the pushbutton remain lit, flight over water is permitted. —If one or both lights of the pushbutton do not remain lit, FLIGHT OVER WATER IS PROHIBITED. (2) Before each flight over water: (i) Perform a functional check to determine whether flight over water is permitted under the Limitations section in paragraph (f)(1) of this AD. For purposes of this AD, ‘‘flight over water’’ means flight beyond the power-off gliding distance from shore. ‘‘Shore’’ is an area of land adjacent to the water and above the high water mark but does not include land area that is intermittently under water. The actions required by this paragraph may be performed by the owner/operator (pilot) holding at least a private pilot certificate, and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9(a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. (ii) If the LACU fails the functional check required by paragraph (f)(2)(i) of this AD, place a placard over the ‘‘float arm’’ pushbutton that reads ‘‘INOP.’’ VerDate Sep<11>2014 16:19 Dec 19, 2017 Jkt 244001 (3) Within 300 hours time-in-service, replace float arm pushbutton P/N 045004A111A with float arm pushbutton P/N 304–2500–00. Installing float arm pushbutton P/N 304–2500–00 is terminating action for the functional check and placard required by paragraphs (f)(2)(i) and (f)(2)(ii) of this AD. (4) Do not install float arm pushbutton P/N 045004A111A on any helicopter. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: George Schwab, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 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. (h) Additional Information (1) Airbus Helicopters Emergency Alert Service Bulletin No. 04A007, Revision 1, dated June 30, 2016, and Airbus Helicopters Alert Service Bulletin No. EC120–31A008, Revision 0, dated June 30, 2016, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/website/ technical-expert/. You may review a copy of the service information at the FAA, Office of E:\FR\FM\20DER1.SGM 20DER1 Federal Register / Vol. 82, No. 243 / Wednesday, December 20, 2017 / Rules and Regulations the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2016–0180, dated September 13, 2016. You may view the EASA AD on the internet at http://www.regulations.gov in Docket No. FAA–2017–0671. Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. (i) Subject Joint Aircraft Service Component (JASC) Code: 2560 Emergency Equipment. Examining the AD Docket Issued in Fort Worth, Texas, on December 12, 2017. Scott A. Horn, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2017–27274 Filed 12–19–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–1191; Product Identifier 2017–SW–046–AD; Amendment 39–19134; AD 2017–26–03] RIN 2120–AA64 Airworthiness Directives; The Enstrom Helicopter Corporation Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for the Enstrom Helicopter Corporation (Enstrom) Model F–28, F–28A, F–28C, F–28C–2, F–28C–2R, F–28F, F–28F–R, TH–28, 280, 280C, 280F, 280FX, 480, and 480B helicopters. This AD requires inspecting certain rod end bearing assemblies. This AD is prompted by an accident. The actions of this AD are intended to prevent an unsafe condition on these helicopters. DATES: This AD becomes effective January 4, 2018. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of January 4, 2018. We must receive comments on this AD by February 20, 2018. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket ethrower on DSK3G9T082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:19 Dec 19, 2017 Jkt 244001 You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 1191; 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-byreference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this final rule, contact Enstrom Helicopter Corporation, 2209 22nd Street, Menominee, MI; telephone (906) 863–1200; fax (906) 863–6821; or at www.enstromhelicopter.com. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. It is also available on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 1191. FOR FURTHER INFORMATION CONTACT: Manzoor Javed, Senior Aerospace Engineer, Chicago ACO Branch, Compliance and Airworthiness Division, Aircraft Certification Service, FAA, 2300 East Devon Ave., Des Plaines, IL 60018; telephone (847) 294– 8112; email manzoor.javed@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 60295 supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion We are adopting a new AD for Enstrom Model F–28, F–28A, F–28C, F– 28C–2, F–28C–2R, F–28F, F–28F–R, TH–28, 280, 280C, 280F, 280FX, 480, and 480B helicopters with a rod end bearing assembly (bearing assembly) part number (P/N) 01–824–08E–011, 09455–01–824–08E–011, ECD091–1, ASMK8T, M81935/1–08K, MS21242S8K, or MTK8 installed. We received a report of an accident involving an Enstrom Model 480B helicopter in which one of the main rotor (M/R) blades departed in-flight. The preliminary investigation indicated that failure of a rod end bearing assembly of one of the M/R hydraulic damper assemblies may have caused the M/R blade to depart from the helicopter. Based on a partially visible marking, the FAA believes the failed part is assembly P/N ECD091–1, vendor P/N 09455–01– 824–08E–011. Analysis of the failed assembly revealed corrosion in the root of the threaded portion of the rod end. Enstrom identified a potential failure mode whereby failure of the rod end bearing assembly may result in the loss of the M/R blade. Because there is no indication of a specific manufacturing or design issue that would limit the potential for this corrosion to have occurred on other similarly-designed rod ends, the FAA determined it necessary to require an inspection of all approved rod end P/Ns. Accordingly, this AD requires, within 5 hours time-in-service (TIS), a one-time inspection of the bearing assemblies for corrosion on the threaded portion of the rod end. If there is any corrosion, this AD requires replacing the bearing assembly before further flight. This AD also requires reporting information about the inspection to the FAA within 10 days. The actions specified by this AD are intended to detect corrosion in the bearing assembly to prevent failure of the rod end, loss of an M/R blade, and subsequent loss of control of the helicopter. Additional inspections at longer intervals may also be necessary. E:\FR\FM\20DER1.SGM 20DER1

Agencies

[Federal Register Volume 82, Number 243 (Wednesday, December 20, 2017)]
[Rules and Regulations]
[Pages 60292-60295]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-27274]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0671; Product Identifier 2016-SW-072-AD; Amendment 
39-19135; AD 2017-26-04]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2009-25-07 for 
Airbus Helicopters Model EC120B helicopters. AD 2009-25-07 required 
amending the rotorcraft flight manual supplement (RFMS) and pre-flight 
checking the emergency flotation gear before each flight over water. 
Since we issued AD 2009-25-07, Airbus Helicopters developed a 
terminating action and identified an additional part-

[[Page 60293]]

numbered emergency floatation gear part with the unsafe condition. This 
new AD retains the requirements of AD 2009-25-07, expands the 
applicability, and adds a terminating action for the repetitive 
inspections. The actions of this AD are intended to correct an unsafe 
condition on these helicopters.

DATES: This AD is effective January 24, 2018.

ADDRESSES: For service information identified in this final rule, 
contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; 
or at http://www.airbushelicopters.com/website/technical-expert/. You 
may review the referenced service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, 
Fort Worth, TX 76177.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0671; 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, 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: George Schwab, Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; 
email [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to remove AD 2009-25-07 (74 FR 65682, December 11, 2009) (2009-
25-07), and add a new AD. AD 2009-25-07 applied to Eurocopter France 
(now Airbus Helicopters) Model EC120B helicopters. AD 2009-25-07 
required amending the limitations section of RFMS to prohibit flight 
over water if the ``float arm'' pushbutton does not remain lit, 
conducting a pilot check to determine whether the ``float arm'' 
pushbutton remains lit before any flight over water, and placarding the 
``float arm'' pushbutton as inoperative if the functional check is 
unsuccessful.
    The NPRM published in the Federal Register on July 14, 2017 (82 FR 
32501). The NPRM was prompted by AD No. 2016-0180, dated September 13, 
2016 (AD 2016-0180), issued by EASA, which is the Technical Agent for 
the Member States of the European Union, to correct an unsafe condition 
for Model EC120B helicopters. EASA advises that Airbus Helicopters has 
designed an improved latching pushbutton, which when installed becomes 
a terminating action for the repetitive functional checks of the float 
arm pushbuttons. EASA also states that lighting and ancillary control 
unit (LACU) part number (P/N) 040101BA is equipped with the same faulty 
pushbutton and must be included in the applicability.
    Accordingly, the NPRM proposed to retain the RFMS amendment and 
repetitive functional check requirements of AD 2009-25-07, add LACU P/N 
040101BA to the applicability paragraph, require replacing the float 
arm pushbutton P/N 045004A111A with float arm pushbutton P/N 304-2500-
00 within 300 hours time-in-service (TIS), and prohibit installing 
float arm pushbutton P/N 045004A111A on any helicopter. Replacing the 
float arm pushbutton was also proposed as a terminating action for the 
repetitive functional checks prior to flight overwater. An owner/
operator (pilot) may perform the functional check required by this AD 
and must enter compliance with that paragraph into the helicopter 
maintenance records in accordance with 14 CFR 43.9(a)(1) through (4) 
and 91.417(a)(2)(v). A pilot may perform this check because it involves 
only a functional check to determine whether the emergency flotation 
gear has been armed and can be performed equally well by a pilot or a 
mechanic. This check is an exception to our standard maintenance 
regulations.
    The proposed requirements were intended to prohibit flight over 
water if a functional test indicates that the emergency flotation gear 
cannot be armed, which would preclude deployment of the floats in an 
emergency water ditching, resulting in subsequent damage to the 
helicopter and injury to occupants.
    Since the NPRM was issued, the FAA's Aircraft Certification Service 
has changed its organization structure. The new structure replaces 
product directorates with functional divisions. We have revised some of 
the office titles and nomenclature throughout this Final rule to 
reflect the new organizational changes. Additional information about 
the new structure can be found in the Notice published on July 25, 2017 
(82 FR 34564).

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM.

FAA's Determination

    We have reviewed the relevant information and determined that an 
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

    The EASA AD requires installing the LACU float arm pushbutton 
within 13 months; this AD requires the installation within 300 hours 
TIS.

Related Service Information

    We reviewed Airbus Helicopters Emergency Alert Service Bulletin No. 
04A007, Revision 1, dated June 30, 2016 (EASB), for Airbus Helicopters 
Model EC120B helicopters. The EASB describes procedures for a pre-
flight check of the float arm pushbutton while arming the emergency 
flotation gear and prohibits operators from flight over water if the 
float arm pushbutton fails.
    We also reviewed Airbus Helicopters Alert Service Bulletin No. 
EC120-31A008, Revision 0, dated June 30, 2016 (ASB), for Airbus 
Helicopters Model EC120B helicopters. The ASB describes procedures for 
replacing the float arm pushbutton with a new design pushbutton and for 
re-labeling the modified LACU with a new P/N label.

Costs of Compliance

    We estimate this AD will affect 53 helicopters of U.S. Registry.
    We estimate that operators may incur the following costs in order 
to comply with this AD. At an average labor rate of $85 per hour, the 
cost of revising the limitations section of the RFMS and of the pre-
flight functional check is negligible. Replacing the float arm 
pushbutton will require about 2 work-hours, and required parts cost 
about $311, for a cost per helicopter of $481 and a total cost of 
$25,493 to 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,

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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;
    (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 removing Airworthiness Directive (AD) 
2009-25-07, Amendment 39-16126 (74 FR 65682, December 11, 2009), and 
adding the following new AD:

2017-26-04 Airbus Helicopters (Previously Eurocopter France): 
Amendment 39-19135; Docket No. FAA-2017-0671; Product Identifier 
2016-SW-072-AD.

(a) Applicability

    This AD applies to Airbus Helicopters (previously Eurocopter 
France) Model EC120B helicopters, certificated in any category, with 
a Lighting and Ancillary Control Unit (LACU) part-number (P/N) 
040101AB or 040101BA with a float arm pushbutton P/N 045004A111A 
installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of a ``float 
arm'' pushbutton, which could result in inoperative floats being 
used in an emergency water ditching, causing damage to the 
helicopter or injury to occupants.

(c) Affected ADs

    This AD supersedes AD 2009-25-07, Amendment 39-16126 (74 FR 
65682, December 11, 2009).

(d) Effective Date

    This AD becomes effective January 24, 2018.

(e) 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.

(f) Required Actions

    (1) Before further flight, amend the EC120B Rotorcraft Flight 
Manual Supplement (RFMS) for the Aerazur emergency flotation gear, 
by inserting a copy of this AD into the Limitations section of the 
RFMS or by making pen and ink changes to that section to add the 
information in Figure 1 to paragraph (f)(1) of this AD:

             Figure 1 to Paragraph (f)(1)--Amendment to RFMS
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
Arm the emergency flotation gear by pressing the LACU ``FLOAT ARM''
 pushbutton.
    --If both lights of the pushbutton remain lit, flight over water is
     permitted.
    --If one or both lights of the pushbutton do not remain lit, FLIGHT
     OVER WATER IS PROHIBITED.
------------------------------------------------------------------------

    (2) Before each flight over water:
    (i) Perform a functional check to determine whether flight over 
water is permitted under the Limitations section in paragraph (f)(1) 
of this AD. For purposes of this AD, ``flight over water'' means 
flight beyond the power-off gliding distance from shore. ``Shore'' 
is an area of land adjacent to the water and above the high water 
mark but does not include land area that is intermittently under 
water. The actions required by this paragraph may be performed by 
the owner/operator (pilot) holding at least a private pilot 
certificate, and must be entered into the aircraft records showing 
compliance with this AD in accordance with 14 CFR 43.9(a)(1) through 
(4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as 
required by 14 CFR 91.417, 121.380, or 135.439.
    (ii) If the LACU fails the functional check required by 
paragraph (f)(2)(i) of this AD, place a placard over the ``float 
arm'' pushbutton that reads ``INOP.''
    (3) Within 300 hours time-in-service, replace float arm 
pushbutton P/N 045004A111A with float arm pushbutton P/N 304-2500-
00. Installing float arm pushbutton P/N 304-2500-00 is terminating 
action for the functional check and placard required by paragraphs 
(f)(2)(i) and (f)(2)(ii) of this AD.
    (4) Do not install float arm pushbutton P/N 045004A111A on any 
helicopter.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Rotorcraft Standards 
Branch, FAA, may approve AMOCs for this AD. Send your proposal to: 
George Schwab, Aviation Safety Engineer, Safety Management Section, 
Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, 
TX 76177; telephone (817) 222-5110; email [email protected].
    (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.

(h) Additional Information

    (1) Airbus Helicopters Emergency Alert Service Bulletin No. 
04A007, Revision 1, dated June 30, 2016, and Airbus Helicopters 
Alert Service Bulletin No. EC120-31A008, Revision 0, dated June 30, 
2016, which are not incorporated by reference, contain additional 
information about the subject of this AD. For service information 
identified in this AD, contact Airbus Helicopters, 2701 N. Forum 
Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 
232-0323; fax (972) 641-3775; or at http://www.airbushelicopters.com/website/technical-expert/. You may review 
a copy of the service information at the FAA, Office of

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the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 
6N-321, Fort Worth, TX 76177.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2016-0180, dated September 13, 2016. You 
may view the EASA AD on the internet at http://www.regulations.gov 
in Docket No. FAA-2017-0671.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 2560 Emergency 
Equipment.

    Issued in Fort Worth, Texas, on December 12, 2017.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2017-27274 Filed 12-19-17; 8:45 am]
 BILLING CODE 4910-13-P