Airworthiness Directives; Airbus Helicopters, 46862-46864 [2018-19750]

Download as PDF 46862 Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Rules and Regulations Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (l)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Fokker Services B.V.’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: 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 1 hour per 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. daltland on DSKBBV9HB2PROD with RULES (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0163, dated September 4, 2017; corrected September 5, 2017, for related information. This MCAI may be found in the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018–0448. (2) For more information about this AD, contact Tom Rodriquez, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and fax 206–231– 3226. (m) 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 this AD specifies otherwise. (i) Fokker Service Bulletin SBF100–32– 169, dated August 23, 2017. (ii) Reserved. (3) For service information identified in this AD, contact Fokker Services B.V., VerDate Sep<11>2014 16:03 Sep 14, 2018 Jkt 244001 Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; phone: +31 (0)88–6280–350; fax: +31 (0)88–6280– 111; email: technicalservices@fokker.com; internet: http://www.myfokkerfleet.com. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (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. Issued in Des Moines, Washington, on August 30, 2018. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–19754 Filed 9–14–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0384; Product Identifier 2017–SW–061–AD; Amendment 39–19401; AD 2018–19–01] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS–365N2, AS 365 N3, EC 155B, EC155B1, SA–365N1, and SA–366G1 helicopters. This AD requires repetitive inspections of the aft fuselage outer skin. This AD was prompted by several reports of aft fuselage outer skin disbonding. The actions of this AD are intended to address an unsafe condition on these products. DATES: This AD is effective October 22, 2018. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of October 22, 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.helicopters.airbus.com/website/ en/ref/Technical-Support_73.html. You may review the referenced service SUMMARY: PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. 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–2018–0384. 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–2018– 0384; or in person at Docket Operations 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-byreference service information, the economic evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email matthew.fuller@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On May 9, 2018, at 83 FR 21194, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Airbus Helicopters Model AS–365N2, AS 365 N3, EC 155B, EC155B1, SA– 365N1, and SA–366G1 helicopters. The NPRM proposed to require a repetitive tap inspection of the aft fuselage outer skin for disbonding. Depending on the inspection results, the NPRM proposed to require reducing the compliance time interval of the tap inspections or repairing or replacing the panel to terminate the shorter compliance time interval. The NPRM also proposed to require a repetitive cleaning of the aft fuselage outer skin to visually inspect for distortion, wrinkling, and corrosion. Depending on the visual inspection results, the NPRM proposed to require an additional tap inspection of the area. The proposed E:\FR\FM\17SER1.SGM 17SER1 Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Rules and Regulations requirements were intended to detect disbonding of the aft fuselage outer skin, which could result in loss of aft fuselage structural integrity and subsequent loss of control of the helicopter. The NPRM was prompted by AD No. 2017–0165, dated September 5, 2017 (EASA AD 2017–0165), issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for the Airbus Helicopters Model SA 365 N1, AS 365 N2, AS 365 N3, SA 366 G1, EC 155 B and EC 155 B1 helicopters. EASA advises of several reports of aft fuselage (baggage compartment area) outer skin disbonding found during a 600-hour inspection. EASA advises that most of the reports of disbonding occurred on Model EC 155 helicopters and may occur in the same area on Model AS 365, SA 365, and SA 366 helicopters due to design similarity. According to EASA, the cause of the disbonding has not yet been determined and the investigation is continuing. Airbus Helicopters states possible causes that are being considered include exhaust gas heat from the exhaust pipes and environmental conditions. EASA states that this condition, if not detected and corrected, could reduce the structural integrity of the aft fuselage, possibly affecting safe flight and landing. To address this unsafe condition, EASA AD 2017–0165 requires a repetitive tap inspection of the aft fuselage outer skin for disbonding, a repetitive visual inspection of the aft fuselage outer skin for distortion, wrinkling, and corrosion, and contacting Airbus Helicopters if there is any disbonding. Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM. daltland on DSKBBV9HB2PROD with RULES 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. VerDate Sep<11>2014 16:03 Sep 14, 2018 Jkt 244001 Interim Action We consider this AD to be an interim action. If final action is later identified, we might consider further rulemaking then. Differences Between This AD and the EASA AD If there is disbonding within the allowable limit, the EASA AD specifies reporting the inspection results to Airbus Helicopters, whereas this AD does not. If there is disbonding that exceeds the allowable limit, the EASA AD specifies contacting Airbus Helicopters for approved skin panel repair or replacement instructions, whereas this AD requires repairing or replacing the panel instead. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Helicopters Alert Service Bulletin (ASB) No. AS365– 05.00.77 for Model AS365 N, N1, N2, and N3 and non-FAA-certificated Model AS365 F, Fs, Fi, K, and K2 helicopters; ASB No. SA366–05.48 for Model SA366 G1 and non-FAA-certificated Model SA366 GA helicopters; and ASB No. EC155–05A033 for Model EC155 B and B1 helicopters, all Revision 0 and all dated July 21, 2017. This service information specifies repetitive tap and visual inspections between aft fuselage outer skin frames X4630 and X6630 and defines the allowable limit of disbonding for this area. If there is distortion, wrinkling, or corrosion, this service information specifies performing a tap inspection. If there is disbonding within the allowable limit, this service information specifies reporting the inspection results to Airbus Helicopters and performing the recurring tap inspection at a shorter compliance time interval. If there is disbonding that exceeds the allowable limit, this service information specifies contacting Airbus Helicopters for repair before further flight. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 46 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Tap inspecting the aft fuselage outer skin takes about 3 work-hours for an estimated cost of $255 per helicopter and $11,730 for the U.S. fleet per inspection cycle. Visually inspecting the aft fuselage outer skin takes about 0.3 work-hour for an estimated cost of $26 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 46863 per helicopter and $1,196 for the U.S. fleet per inspection cycle. Repairing a panel takes about 5 work-hours and parts cost about $500 for an estimated cost of $925. Replacing a panel takes about 10 work-hours and parts cost about $20,000 for an estimated cost of $20,850. 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; (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. E:\FR\FM\17SER1.SGM 17SER1 46864 Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Rules and Regulations 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 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): ■ 2018–19–01 Airbus Helicopters: Amendment 39–19401; Docket No. FAA–2018–0384; Product Identifier 2017–SW–061–AD. (a) Applicability This AD applies to Model AS–365N2, AS 365 N3, EC 155B, EC155B1, SA–365N1, and SA–366G1 helicopters, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as disbonding of the aft fuselage outer skin. This condition could result in loss of aft fuselage structural integrity and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective October 22, 2018. daltland on DSKBBV9HB2PROD with RULES (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 110 hours time-in-service (TIS), tap inspect the aft fuselage outer skin for disbonding between frames X4630 and X6630 in the areas depicted in Figure 1 of Airbus Helicopters Alert Service Bulletin (ASB) No. AS365–05.00.77, ASB No. SA366– 05.48, or ASB No. EC155–05A033, all Revision 0 and dated July 21, 2017 (ASB AS365–05.00.77, ASB SA366–05.48, or ASB EC155–05A033), as applicable for your model helicopter. Examples of acceptable and unacceptable disbonding areas are depicted in Figure 2 of ASB AS365–05.00.77, ASB SA366–05.48, and ASB EC155–05A033, as applicable for your model helicopter. (i) If there is no disbonding, repeat the tap inspection at intervals not to exceed 660 hours TIS. (ii) If there is disbonding within one square-shaped area measuring 3.94 in. x 3.94 in. (10 cm x 10 cm) that does not cross two skin panels, repeat the tap inspection at intervals not to exceed 110 hours TIS. (iii) If there is disbonding that exceeds one square-shaped area measuring 3.94 in. x 3.94 in. (10 cm x 10 cm) or crosses two skin panels, before further flight, repair or replace the panel. Thereafter, tap inspect the panel at intervals not to exceed 660 hours TIS. VerDate Sep<11>2014 16:03 Sep 14, 2018 Jkt 244001 (2) Within 220 hours TIS, and thereafter at intervals not to exceed 110 hours TIS, clean the aft fuselage outer skin and using a light, visually inspect for distortion, wrinkling, and corrosion between frames X4630 and X6630 as depicted in Figure 1 of ASB AS365– 05.00.77, ASB SA366–05.48, or ASB EC155– 05A033, as applicable for your model helicopter. If there is any distortion, wrinkling, or corrosion, before further flight, tap inspect the area for disbonding by following the inspection instructions in paragraph (e)(1) of this AD. (f) 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: Matt Fuller, Senior 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 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 (EASA) AD No. 2017–0165, dated September 5, 2017. You may view the EASA AD on the internet at http://www.regulations.gov in Docket No. FAA–2018–0384. (h) Subject Joint Aircraft Service Component (JASC) Code: 5302, Rotorcraft tail boom. (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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) Airbus Helicopters Alert Service Bulletin (ASB) No. AS365–05.00.77, Revision 0, dated July 21, 2017. (ii) Airbus Helicopters ASB No. SA366– 05.48, Revision 0, dated July 21, 2017. (iii) Airbus Helicopters ASB No. EC155– 05A033, Revision 0, dated July 21, 2017. (3) For Airbus Helicopters 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.helicopters.airbus. com/website/en/ref/Technical-Support_ 73.html. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 (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. Issued in Fort Worth, Texas, on September 4, 2018. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2018–19750 Filed 9–14–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2018–0139; Airspace Docket No. 18–ACE–1] RIN 2120–AA66 Amendment of Class E Airspace; Lyons, KS Federal Aviation Administration (FAA), DOT. ACTION: Final rule, correction. AGENCY: This action corrects a final rule published in the Federal Register of August 1, 2018, that amends Class E airspace at Lyons-Rice County Municipal Airport, Lyons, KS. The word ‘‘County’’ was inadvertently omitted from the airport name in the Summary, History, and Rules section of the document, as well as in the header of the legal description. DATES: Effective date 0901 UTC, November 8, 2018. The Director of the Federal Register approves this incorporation by reference action under Title 1, Code of Federal Regulations, part 51, subject to the annual revision of FAA Order 7400.11 and publication of conforming amendments. FOR FURTHER INFORMATION CONTACT: Rebecca Shelby, Federal Aviation Administration, Operations Support Group, Central Service Center, 10101 Hillwood Parkway, Fort Worth, TX 76177; telephone (817) 222–5857. SUPPLEMENTARY INFORMATION: SUMMARY: History The FAA published a final rule in the Federal Register for Docket No. FAA– 2018–0139 (83 FR 37422, August 1, 2018), amending Class E airspace at Lyons-Rice County Municipal Airport, Lyons, KS. Subsequent to publication, the FAA identified a clerical error that the word ‘‘County’’ was omitted from E:\FR\FM\17SER1.SGM 17SER1

Agencies

[Federal Register Volume 83, Number 180 (Monday, September 17, 2018)]
[Rules and Regulations]
[Pages 46862-46864]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-19750]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0384; Product Identifier 2017-SW-061-AD; Amendment 
39-19401; AD 2018-19-01]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus 
Helicopters Model AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365N1, and 
SA-366G1 helicopters. This AD requires repetitive inspections of the 
aft fuselage outer skin. This AD was prompted by several reports of aft 
fuselage outer skin disbonding. The actions of this AD are intended to 
address an unsafe condition on these products.

DATES: This AD is effective October 22, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of October 22, 
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.helicopters.airbus.com/website/en/ref/Technical-
Support_73.html. 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. 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-2018-
0384.

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-2018-
0384; or in person at Docket Operations 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 
Docket Operations (phone: 800-647-5527) is U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior 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

    On May 9, 2018, at 83 FR 21194, the Federal Register published our 
notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR 
part 39 by adding an AD that would apply to Airbus Helicopters Model 
AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365N1, and SA-366G1 
helicopters.
    The NPRM proposed to require a repetitive tap inspection of the aft 
fuselage outer skin for disbonding. Depending on the inspection 
results, the NPRM proposed to require reducing the compliance time 
interval of the tap inspections or repairing or replacing the panel to 
terminate the shorter compliance time interval. The NPRM also proposed 
to require a repetitive cleaning of the aft fuselage outer skin to 
visually inspect for distortion, wrinkling, and corrosion. Depending on 
the visual inspection results, the NPRM proposed to require an 
additional tap inspection of the area. The proposed

[[Page 46863]]

requirements were intended to detect disbonding of the aft fuselage 
outer skin, which could result in loss of aft fuselage structural 
integrity and subsequent loss of control of the helicopter.
    The NPRM was prompted by AD No. 2017-0165, dated September 5, 2017 
(EASA AD 2017-0165), issued by EASA, which is the Technical Agent for 
the Member States of the European Union, to correct an unsafe condition 
for the Airbus Helicopters Model SA 365 N1, AS 365 N2, AS 365 N3, SA 
366 G1, EC 155 B and EC 155 B1 helicopters. EASA advises of several 
reports of aft fuselage (baggage compartment area) outer skin 
disbonding found during a 600-hour inspection. EASA advises that most 
of the reports of disbonding occurred on Model EC 155 helicopters and 
may occur in the same area on Model AS 365, SA 365, and SA 366 
helicopters due to design similarity. According to EASA, the cause of 
the disbonding has not yet been determined and the investigation is 
continuing. Airbus Helicopters states possible causes that are being 
considered include exhaust gas heat from the exhaust pipes and 
environmental conditions. EASA states that this condition, if not 
detected and corrected, could reduce the structural integrity of the 
aft fuselage, possibly affecting safe flight and landing.
    To address this unsafe condition, EASA AD 2017-0165 requires a 
repetitive tap inspection of the aft fuselage outer skin for 
disbonding, a repetitive visual inspection of the aft fuselage outer 
skin for distortion, wrinkling, and corrosion, and contacting Airbus 
Helicopters if there is any disbonding.

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

    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.

Interim Action

    We consider this AD to be an interim action. If final action is 
later identified, we might consider further rulemaking then.

Differences Between This AD and the EASA AD

    If there is disbonding within the allowable limit, the EASA AD 
specifies reporting the inspection results to Airbus Helicopters, 
whereas this AD does not. If there is disbonding that exceeds the 
allowable limit, the EASA AD specifies contacting Airbus Helicopters 
for approved skin panel repair or replacement instructions, whereas 
this AD requires repairing or replacing the panel instead.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Helicopters Alert Service Bulletin (ASB) No. 
AS365-05.00.77 for Model AS365 N, N1, N2, and N3 and non-FAA-
certificated Model AS365 F, Fs, Fi, K, and K2 helicopters; ASB No. 
SA366-05.48 for Model SA366 G1 and non-FAA-certificated Model SA366 GA 
helicopters; and ASB No. EC155-05A033 for Model EC155 B and B1 
helicopters, all Revision 0 and all dated July 21, 2017. This service 
information specifies repetitive tap and visual inspections between aft 
fuselage outer skin frames X4630 and X6630 and defines the allowable 
limit of disbonding for this area. If there is distortion, wrinkling, 
or corrosion, this service information specifies performing a tap 
inspection. If there is disbonding within the allowable limit, this 
service information specifies reporting the inspection results to 
Airbus Helicopters and performing the recurring tap inspection at a 
shorter compliance time interval. If there is disbonding that exceeds 
the allowable limit, this service information specifies contacting 
Airbus Helicopters for repair before further flight.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

 Costs of Compliance

    We estimate that this AD affects 46 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD.
    Tap inspecting the aft fuselage outer skin takes about 3 work-hours 
for an estimated cost of $255 per helicopter and $11,730 for the U.S. 
fleet per inspection cycle. Visually inspecting the aft fuselage outer 
skin takes about 0.3 work-hour for an estimated cost of $26 per 
helicopter and $1,196 for the U.S. fleet per inspection cycle. 
Repairing a panel takes about 5 work-hours and parts cost about $500 
for an estimated cost of $925. Replacing a panel takes about 10 work-
hours and parts cost about $20,000 for an estimated cost of $20,850.

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;
    (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.

[[Page 46864]]

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):

2018-19-01 Airbus Helicopters: Amendment 39-19401; Docket No. FAA-
2018-0384; Product Identifier 2017-SW-061-AD.

(a) Applicability

    This AD applies to Model AS-365N2, AS 365 N3, EC 155B, EC155B1, 
SA-365N1, and SA-366G1 helicopters, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as disbonding of the aft 
fuselage outer skin. This condition could result in loss of aft 
fuselage structural integrity and subsequent loss of control of the 
helicopter.

(c) Effective Date

    This AD becomes effective October 22, 2018.

(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 110 hours time-in-service (TIS), tap inspect the aft 
fuselage outer skin for disbonding between frames X4630 and X6630 in 
the areas depicted in Figure 1 of Airbus Helicopters Alert Service 
Bulletin (ASB) No. AS365-05.00.77, ASB No. SA366-05.48, or ASB No. 
EC155-05A033, all Revision 0 and dated July 21, 2017 (ASB AS365-
05.00.77, ASB SA366-05.48, or ASB EC155-05A033), as applicable for 
your model helicopter. Examples of acceptable and unacceptable 
disbonding areas are depicted in Figure 2 of ASB AS365-05.00.77, ASB 
SA366-05.48, and ASB EC155-05A033, as applicable for your model 
helicopter.
    (i) If there is no disbonding, repeat the tap inspection at 
intervals not to exceed 660 hours TIS.
    (ii) If there is disbonding within one square-shaped area 
measuring 3.94 in. x 3.94 in. (10 cm x 10 cm) that does not cross 
two skin panels, repeat the tap inspection at intervals not to 
exceed 110 hours TIS.
    (iii) If there is disbonding that exceeds one square-shaped area 
measuring 3.94 in. x 3.94 in. (10 cm x 10 cm) or crosses two skin 
panels, before further flight, repair or replace the panel. 
Thereafter, tap inspect the panel at intervals not to exceed 660 
hours TIS.
    (2) Within 220 hours TIS, and thereafter at intervals not to 
exceed 110 hours TIS, clean the aft fuselage outer skin and using a 
light, visually inspect for distortion, wrinkling, and corrosion 
between frames X4630 and X6630 as depicted in Figure 1 of ASB AS365-
05.00.77, ASB SA366-05.48, or ASB EC155-05A033, as applicable for 
your model helicopter. If there is any distortion, wrinkling, or 
corrosion, before further flight, tap inspect the area for 
disbonding by following the inspection instructions in paragraph 
(e)(1) of this AD.

(f) 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: 
Matt Fuller, Senior 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.

(g) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2017-0165, dated September 5, 2017. You may 
view the EASA AD on the internet at http://www.regulations.gov in 
Docket No. FAA-2018-0384.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 5302, Rotorcraft 
tail boom.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference 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) Airbus Helicopters Alert Service Bulletin (ASB) No. AS365-
05.00.77, Revision 0, dated July 21, 2017.
    (ii) Airbus Helicopters ASB No. SA366-05.48, Revision 0, dated 
July 21, 2017.
    (iii) Airbus Helicopters ASB No. EC155-05A033, Revision 0, dated 
July 21, 2017.
    (3) For Airbus Helicopters 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.helicopters.airbus. com/website/en/
ref/Technical-Support_73.html.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. 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 September 4, 2018.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2018-19750 Filed 9-14-18; 8:45 am]
 BILLING CODE 4910-13-P