Airworthiness Directives; Airbus Helicopters, 21194-21196 [2018-09742]

Download as PDF Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules (i) No Alternative Actions and Intervals After the maintenance or inspection program, as applicable, has been revised as required by paragraphs (g) and (h) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (k)(1) of this AD. (j) Terminating Action for Certain ADs Accomplishing the actions required by this AD terminates all requirements of AD 2000– 17–09, AD 2008–04–19 R1, and AD 2015–26– 09 for ATR–GIE Avions de Transport ´ Regional Model ATR42–200, –300, and –320 airplanes only. amozie on DSK3GDR082PROD with PROPOSALS (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the 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 ´ ATR–GIE Avions de Transport Regional’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017–0221R1, dated December 15, 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–2018–0391. VerDate Sep<11>2014 17:09 May 08, 2018 Jkt 244001 (2) For more information about this AD, contact Shahram Daneshmandi, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th Street, Des Moines, WA 980198; telephone and fax 206–231–3220. (3) For service information identified in this AD, contact ATR–GIE Avions de ´ ´ Transport Regional, 1 Allee Pierre Nadot, 31712 Blagnac Cedex, France; telephone +33 (0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; email continued.airworthiness@atraircraft.com; http://www.atr-aircraft.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th Street, Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on April 27, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–09746 Filed 5–8–18; 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] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Airbus Helicopters Model AS–365N2, AS 365 N3, EC 155B, EC155B1, SA–365N1, and SA–366G1 helicopters. This proposed AD would require repetitive inspections of the aft fuselage outer skin. This proposed AD is prompted by several reports of aft fuselage outer skin disbonding. The actions of this proposed AD are intended to address an unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 9, 2018. SUMMARY: PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 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 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. ADDRESSES: 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 proposed AD, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received, and other information. The street address for Docket Operations (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 proposed 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. 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: E:\FR\FM\09MYP1.SGM 09MYP1 EP09MY18.018</GPH> 21194 Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules Comments Invited 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 might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include 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 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 proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. amozie on DSK3GDR082PROD with PROPOSALS Discussion EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD No. 2017– 0165, dated September 5, 2017 (EASA AD 2017–0165), to correct an unsafe condition for 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 VerDate Sep<11>2014 17:09 May 08, 2018 Jkt 244001 fuselage outer skin for distortion, wrinkling, and corrosion, and contacting Airbus Helicopters if there is any disbonding. 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 its AD. We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition is likely to exist or develop on other products of the same type design. 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. Proposed AD Requirements This proposed AD would require, within 110 hours time-in-service (TIS), a tap inspection of the aft fuselage outer skin for disbonding. If there is no disbonding, repeating the tap inspection at intervals not to exceed 660 hours TIS would be required. If there is disbonding, either repeating the tap inspections at intervals not to exceed 110 hours TIS or repairing or replacing the panel before further flight and then PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 21195 tap inspecting the panel at intervals not to exceed 660 hours TIS would be required. This proposed AD would also require, within 220 hours TIS and thereafter at intervals not to exceed 110 hours TIS, cleaning the aft fuselage outer skin and visually inspecting for distortion, wrinkling, and corrosion. If there is any distortion, wrinkling, or corrosion, tap inspecting the area for disbonding would be required before further flight. Differences Between This Proposed 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 proposed AD would 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 proposed AD would require repairing or replacing the panel instead. Interim Action We consider this proposed AD to be an interim action. If final action is later identified, we might consider further rulemaking then. Costs of Compliance We estimate that this proposed AD would affect 46 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per work-hour. Tap inspecting the aft fuselage outer skin would take 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 would take 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 would take about 5 work-hours and parts would cost about $500 for an estimated cost of $925. Replacing a panel would take about 10 work-hours and parts would 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, E:\FR\FM\09MYP1.SGM 09MYP1 21196 Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules 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 products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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 proposed 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: amozie on DSK3GDR082PROD with PROPOSALS ■ 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): ■ Airbus Helicopters: Docket No. FAA–2018– 0384; Product Identifier 2017–SW–061– AD. VerDate Sep<11>2014 17:09 May 08, 2018 Jkt 244001 (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) Comments Due Date We must receive comments by July 9, 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 9-ASWFTW-AMOC-Requests@faa.gov. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 (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 the AD Docket. (h) Subject Joint Aircraft Service Component (JASC) Code: 5302, Rotorcraft tail boom. Issued in Fort Worth, Texas, on April 26, 2018. Lance T. Gant, Director, Compliance & Airworthiness Division,Aircraft Certification Service. [FR Doc. 2018–09742 Filed 5–8–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0395; Product Identifier 2017–NM–136–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330–200 Freighter series airplanes, Model A330–200 series airplanes, Model A330–300 series airplanes, Model A340–200 series airplanes, Model A340–300 series airplanes, Model A340–500 series airplanes, and Model A340–600 series airplanes. This proposed AD was prompted by a report of deficient fatigue performance of high strength steel used in forgings. Components made from the affected high strength steel are installed on the main landing gear (MLG), nose landing gear (NLG), and center landing gear (CLG). This proposed AD would require identifying the part number and serial number of certain components installed on the MLG, NLG, and CLG; replacing affected parts; identifying the airplane’s weight variant; and determining the applicable life limit for SUMMARY: E:\FR\FM\09MYP1.SGM 09MYP1

Agencies

[Federal Register Volume 83, Number 90 (Wednesday, May 9, 2018)]
[Proposed Rules]
[Pages 21194-21196]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-09742]


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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]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

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

DATES: We must receive comments on this proposed AD by July 9, 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 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.

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 proposed AD, the European Aviation Safety Agency (EASA) AD, the 
economic evaluation, any comments received, and other information. The 
street address for Docket Operations (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 proposed 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.

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: 

[[Page 21195]]

Comments Invited

    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 might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include 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 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 proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD No. 2017-0165, dated September 5, 
2017 (EASA AD 2017-0165), to correct an unsafe condition for 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.

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 
its AD. We are proposing this AD because we evaluated all known 
relevant information and determined that an unsafe condition is likely 
to exist or develop on other products of the same type design.

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.

Proposed AD Requirements

    This proposed AD would require, within 110 hours time-in-service 
(TIS), a tap inspection of the aft fuselage outer skin for disbonding. 
If there is no disbonding, repeating the tap inspection at intervals 
not to exceed 660 hours TIS would be required. If there is disbonding, 
either repeating the tap inspections at intervals not to exceed 110 
hours TIS or repairing or replacing the panel before further flight and 
then tap inspecting the panel at intervals not to exceed 660 hours TIS 
would be required. This proposed AD would also require, within 220 
hours TIS and thereafter at intervals not to exceed 110 hours TIS, 
cleaning the aft fuselage outer skin and visually inspecting for 
distortion, wrinkling, and corrosion. If there is any distortion, 
wrinkling, or corrosion, tap inspecting the area for disbonding would 
be required before further flight.

Differences Between This Proposed 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 proposed AD would 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 proposed AD would require repairing or replacing the panel 
instead.

Interim Action

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

Costs of Compliance

    We estimate that this proposed AD would affect 46 helicopters of 
U.S. Registry. We estimate that operators may incur the following costs 
in order to comply with this AD. Labor costs are estimated at $85 per 
work-hour.
    Tap inspecting the aft fuselage outer skin would take 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 would take 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 would take about 5 work-hours and parts would cost 
about $500 for an estimated cost of $925. Replacing a panel would take 
about 10 work-hours and parts would 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,

[[Page 21196]]

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 products identified in this rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Airbus Helicopters: 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) Comments Due Date

    We must receive comments by July 9, 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 
the AD Docket.

(h) Subject

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

    Issued in Fort Worth, Texas, on April 26, 2018.
Lance T. Gant,
Director, Compliance & Airworthiness Division,Aircraft Certification 
Service.
[FR Doc. 2018-09742 Filed 5-8-18; 8:45 am]
 BILLING CODE 4910-13-P