Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France), 79274-79276 [2015-31847]

Download as PDF 79274 Proposed Rules Federal Register Vol. 80, No. 244 Monday, December 21, 2015 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–3741; Directorate Identifier 2014–SW–040–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede airworthiness directive (AD) 2013–08– 17 for Airbus Helicopters Model SA– 365N, SA–365–N1, AS–365N2, AS 365 N3, and SA–366G1 helicopters. AD 2013–08–17 currently requires an initial and recurring inspections of the 9degree fuselage frame for a crack and a repair of the frame if a crack exists. Since we issued AD 2013–08–17, additional information has prompted us to propose modifying the compliance times and expanding the inspection area of the 9-inch frame. These proposed actions are intended to detect a crack in the 9-degree frame to prevent loss of structural integrity and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by February 19, 2016. 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 Lhorne on DSK5TPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 15:25 Dec 18, 2015 Jkt 238001 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–2015– 3741; 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 proposed 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 (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, Inc., 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/techpub. You may review service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, Texas 76177. FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort Worth, Texas 76177; telephone (817) 222–5110; email robert.grant@faa.gov. SUPPLEMENTARY INFORMATION: 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 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 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 On April 12, 2013, we issued AD 2013–08–17, Amendment 39–17434 (78 FR 25380, May 1, 2013), for Eurocopter France (now Airbus Helicopters) Model SA–365N, SA–365–N1, AS–365N2, AS 365 N3, and SA–366G1 helicopters. AD 2013–08–17 requires an initial and recurring inspection of the 9-degree fuselage frame for a crack and a repair of the frame if a crack exists. AD 2013– 08–17 was prompted by the discovery of a crack in the 9-degree frame of a Model AS–365N2 helicopter. This type of crack could develop on the other specified model helicopters because they contain the same 9-degree frame. Those actions are intended to detect a crack in the 9degree frame to prevent loss of structural integrity and subsequent loss of control of the helicopter. AD 2013–08–17 was prompted by Emergency AD No. 2010–0064–E, dated April 6, 2010, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Model SA– 365N, SA–365–N1, AS–365N2, AS 365 N3, and SA–366G1 helicopters. EASA advises that a crack was found in the 9degree frame of an AS–365N2 helicopter during an inspection. The helicopter had logged 10,786 flight hours. The crack was located 230 millimeters above the cabin floor and had grown over a large section of the 9-degree frame on the right-hand (RH) side. EASA states that the time required for initiation of a crack in the area varies according to the weight and balance data of the different aircraft versions. Actions Since AD 2013–08–17 Was Issued Since we issued AD 2013–08–17, Amendment 39–17434 (78 FR 25380, May 1, 2013), EASA issued AD No. 2014–0159, dated July 7, 2014, which supersedes EASA Emergency AD No. 2010–0064–E. Further analysis on the strength of the 9-degree frame by Airbus E:\FR\FM\21DEP1.SGM 21DEP1 Federal Register / Vol. 80, No. 244 / Monday, December 21, 2015 / Proposed Rules Helicopters indicated that compliance times should be modified and the inspection area expanded. Consequently, we propose issuing this AD, which would supersede AD 2013– 08–17, and reflect the modified compliance times and inspection areas. 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. Lhorne on DSK5TPTVN1PROD with PROPOSALS Related Service Information Under 1 CFR Part 51 Airbus Helicopters has issued an Emergency Alert Service Bulletin (EASB), Revision 2, dated April 7, 2014, containing the following three numbers: No. 05.00.57 for the Model SA–365N and N1, and AS–365N2 and N3 and for military Model AS365F, Fs, Fi, and K helicopters; No. 05.39 for Model SA 366–G1 and military Model SA 366–GA helicopters; and No. 05.00.25 for military Model AS565MA, MB, SA, SB, and UB helicopter. The EASB specifies checking at regular intervals for a crack in the areas of the inner angles and flanges of the 9degree frame on the RH and left hand (LH) sides, near the splice. Revision 2 of the EASB modifies the compliance times, adds a compliance time based on take-off/landing cycles, and expands the inspection areas up to the junction with the upper part of the frame. EASA classified this service information as mandatory and issued EASA AD No. 2014–0159 to ensure the continued airworthiness of these helicopters. 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 inspecting the 9-degree fuselage frame on the RH and LH sides for a crack, using a 10x or higher magnifying glass and a light source, in the areas depicted in specified portions of the EASB applicable to your helicopter. If there is a crack, this proposed AD would require repairing the frame before further flight. For helicopters that have not reached a certain hours time-in-service (TIS) or VerDate Sep<11>2014 15:25 Dec 18, 2015 Jkt 238001 landing threshold, the inspection would be required within 110 hours TIS after reaching whichever threshold occurs first, and thereafter at intervals not to exceed 110 hours TIS. For helicopters that have reached or exceeded the hours TIS or landing threshold, the inspection would be required within 110 hours TIS since the effective date of the AD and thereafter at intervals not to exceed 110 hours TIS. Differences Between This Proposed AD and the EASA AD We would not require contacting the manufacturer for approved repair instructions. We also would not allow flight with a known crack. Costs of Compliance We estimate that this proposed AD would affect 40 helicopters of U.S. Registry and that labor costs average $85 a work hour. Based on these estimates, we expect the following costs: • Inspecting the 9-degree frame would require 3 work-hours per inspection for a cost of $255 per helicopter and $10,200 for the fleet per inspection cycle. • Repairing the 9-degree frame would require 24 work-hours for a labor cost of $2,040. Parts would cost $3,350 for a total cost of $5,390 per helicopter. 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 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 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 79275 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: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2013–08–17, Amendment 39–17434 (78 FR 25380, May 1, 2013) and adding the following new AD: ■ Airbus Helicopters (Previously Eurocopter France): Docket No. FAA–2015–3741; Directorate Identifier 2014–SW–040–AD. (a) Applicability This AD applies to Airbus Helicopters Model SA–365N, SA–365–N1, AS–365N2, AS 365 N3, and SA–366G1 helicopters, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in the 9-degree frame, which could result in the loss of structural integrity and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes AD 2013–08–17, Amendment 39–17434 (78 FR 25380, May 1, 2013). (d) Comments Due Date We must receive comments by February 19, 2016. E:\FR\FM\21DEP1.SGM 21DEP1 79276 Federal Register / Vol. 80, No. 244 / Monday, December 21, 2015 / Proposed Rules (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. Issued in Fort Worth, Texas, on December 11, 2015. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service. If you use a telecommunications device for the deaf (TDD) or text telephone (TTY), call the Federal Relay Service (FRS), toll free, at 1–800–877– 8339. (f) Required Actions (1) Within 110 hours time-in-service (TIS) after reaching the hours or landings threshold, whichever occurs first, listed in Table 1 to Paragraph (f)(1) of this AD or within 110 hours TIS from the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 110 hours TIS, using a 10X or higher magnifying glass and a light, inspect the 9-degree fuselage frame on the right-hand (RH) and left-hand (LH) sides for a crack in the areas depicted in Figures 1 and 2 of Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. AS365 05.00.57, Revision 2, dated April 7, 2014, or EASB No. SA366 05.39, Revision 2, dated April 7, 2014, as applicable to your model helicopter. For purposes of this AD, a landing would be counted anytime the helicopter lifts off into the air and then lands again regardless of the duration of the landing and regardless of whether the engine is shut down. [FR Doc. 2015–31847 Filed 12–18–15; 8:45 am] SUPPLEMENTARY INFORMATION: TABLE 1 TO PARAGRAPH (f)(1) Helicopter model SA–365N .......... SA–365N1 ........ AS–365N2 ........ AS 365 N3 ........ SA–366G1 ........ Hours TIS 11,490 10,490 9,140 8,740 8,390 Landings 22,980 20,980 18,280 17,480 16,780 (2) If there is a crack, before further flight, repair the frame. Repairing a frame does not constitute terminating actions for the repetitive inspection requirements of this AD. Lhorne on DSK5TPTVN1PROD with PROPOSALS (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort Worth, Texas 76177; telephone (817) 222– 5110; email 9-ASW-FTW-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. (h) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2014–0159, dated July 7, 2014. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA–2015–3741. (i) Subject Joint Aircraft Service Component (JASC) Code: 5311, Fuselage Main, Frame. VerDate Sep<11>2014 15:25 Dec 18, 2015 Jkt 238001 BILLING CODE 4910–13–P DEPARTMENT OF EDUCATION 34 CFR Chapter VI [Docket ID ED–2015–OPE–0103] Negotiated Rulemaking Committee; Negotiator Nominations and Schedule of Committee Meetings—Borrower Defenses Office of Postsecondary Education, Department of Education. ACTION: Intent to establish negotiated rulemaking committee. AGENCY: On October 20, 2015, we announced our intention to establish a negotiated rulemaking committee to prepare proposed regulations for the Federal Student Aid programs authorized under title IV of the Higher Education Act of 1965, as amended (HEA), and solicited nominations for individual negotiators for the committee. We are requesting additional nominations for individual negotiators who represent specific stakeholder constituencies for the issues to be negotiated to serve on the committee. DATES: We must receive your nominations for negotiators to serve on the committee on or before December 28, 2015. The dates, times, and locations of the committee meetings are set out in the Schedule for Negotiations section in the SUPPLEMENTARY INFORMATION section. ADDRESSES: Please send your nominations for negotiators to Barbara Hoblitzell, U.S. Department of Education, 1990 K Street NW., Room 8019, Washington, DC 20006. Telephone: (202) 502–7649 or by email: Barbara.Hoblitzell@ed.gov. FOR FURTHER INFORMATION CONTACT: For information about the content of this notice, including information about the negotiated rulemaking process or the nomination submission process, contact: Barbara Hoblitzell, U.S. Department of Education, 1990 K Street NW., Room 8019, Washington, DC 20006. Telephone: (202) 502–7649 or by email: Barbara.Hoblitzell@ed.gov. For information about negotiated rulemaking in general, see The Negotiated Rulemaking Process for Title IV Regulations, Frequently Asked Questions at www2.ed.gov/policy/ highered/reg/hearulemaking/hea08/negreg-faq.html. SUMMARY: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 On October 20, 2015, we published a notice in the Federal Register (80 FR 63478) announcing our intention to establish a negotiated rulemaking committee to address for loans made under the William D. Ford Federal Direct Loan (Direct Loan) Program: (1) The procedures to be used for a borrower to establish a defense to repayment; (2) the criteria that the Department will use to identify acts or omissions of an institution that constitute defenses to repayment of Direct Loans, including the creation of a Federal standard; (3) the standards and procedures that the Department will use to determine the liability of the institution for amounts based on borrower defenses; (4) the effect of borrower defenses on institutional capability assessments; and (5) other loan discharges. We noted that, in addition, the committee may also consider if and how these issues will affect the Federal Family Education Loan (FFEL) Program. In that notice, we set a schedule for the committee meetings and requested nominations for individual negotiators who represent stakeholder constituencies for the issues to be negotiated to serve on the committee. We are requesting additional nominations for individual negotiators who represent the following stakeholder constituencies for the issues to be negotiated to serve on the committee: • State higher education executive officers. • Institutions of higher education eligible to receive Federal assistance under title III, parts A, B, and F, and title V of the HEA, which include Historically Black Colleges and Universities, Hispanic-Serving Institutions, American Indian Tribally Controlled Colleges and Universities, Alaska Native and Native HawaiianServing Institutions, Predominantly Black Institutions, and other institutions with a substantial enrollment of needy students as defined in title III of the HEA. • Two-year public institutions of higher education. • Private, for-profit institutions of higher education. • National, regional, or specialized accrediting agencies. We intend to select negotiators for the committee who represent the interests significantly affected by the topics proposed for negotiations. In so doing, E:\FR\FM\21DEP1.SGM 21DEP1

Agencies

[Federal Register Volume 80, Number 244 (Monday, December 21, 2015)]
[Proposed Rules]
[Pages 79274-79276]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-31847]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 80, No. 244 / Monday, December 21, 2015 / 
Proposed Rules

[[Page 79274]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3741; Directorate Identifier 2014-SW-040-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Type Certificate 
Previously Held by Eurocopter France)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede airworthiness directive (AD) 2013-08-
17 for Airbus Helicopters Model SA-365N, SA-365-N1, AS-365N2, AS 365 
N3, and SA-366G1 helicopters. AD 2013-08-17 currently requires an 
initial and recurring inspections of the 9-degree fuselage frame for a 
crack and a repair of the frame if a crack exists. Since we issued AD 
2013-08-17, additional information has prompted us to propose modifying 
the compliance times and expanding the inspection area of the 9-inch 
frame. These proposed actions are intended to detect a crack in the 9-
degree frame to prevent loss of structural integrity and subsequent 
loss of control of the helicopter.

DATES: We must receive comments on this proposed AD by February 19, 
2016.

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-2015-
3741; 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 proposed 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 
(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, Inc., 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/techpub. You may review service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, Texas 76177.

FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort 
Worth, Texas 76177; telephone (817) 222-5110; email 
robert.grant@faa.gov.

SUPPLEMENTARY INFORMATION:

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

    On April 12, 2013, we issued AD 2013-08-17, Amendment 39-17434 (78 
FR 25380, May 1, 2013), for Eurocopter France (now Airbus Helicopters) 
Model SA-365N, SA-365-N1, AS-365N2, AS 365 N3, and SA-366G1 
helicopters. AD 2013-08-17 requires an initial and recurring inspection 
of the 9-degree fuselage frame for a crack and a repair of the frame if 
a crack exists. AD 2013-08-17 was prompted by the discovery of a crack 
in the 9-degree frame of a Model AS-365N2 helicopter. This type of 
crack could develop on the other specified model helicopters because 
they contain the same 9-degree frame. Those actions are intended to 
detect a crack in the 9-degree frame to prevent loss of structural 
integrity and subsequent loss of control of the helicopter.
    AD 2013-08-17 was prompted by Emergency AD No. 2010-0064-E, dated 
April 6, 2010, issued by EASA, which is the Technical Agent for the 
Member States of the European Union, to correct an unsafe condition for 
Model SA-365N, SA-365-N1, AS-365N2, AS 365 N3, and SA-366G1 
helicopters. EASA advises that a crack was found in the 9-degree frame 
of an AS-365N2 helicopter during an inspection. The helicopter had 
logged 10,786 flight hours. The crack was located 230 millimeters above 
the cabin floor and had grown over a large section of the 9-degree 
frame on the right-hand (RH) side. EASA states that the time required 
for initiation of a crack in the area varies according to the weight 
and balance data of the different aircraft versions.

Actions Since AD 2013-08-17 Was Issued

    Since we issued AD 2013-08-17, Amendment 39-17434 (78 FR 25380, May 
1, 2013), EASA issued AD No. 2014-0159, dated July 7, 2014, which 
supersedes EASA Emergency AD No. 2010-0064-E. Further analysis on the 
strength of the 9-degree frame by Airbus

[[Page 79275]]

Helicopters indicated that compliance times should be modified and the 
inspection area expanded. Consequently, we propose issuing this AD, 
which would supersede AD 2013-08-17, and reflect the modified 
compliance times and inspection areas.

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

    Airbus Helicopters has issued an Emergency Alert Service Bulletin 
(EASB), Revision 2, dated April 7, 2014, containing the following three 
numbers: No. 05.00.57 for the Model SA-365N and N1, and AS-365N2 and N3 
and for military Model AS365F, Fs, Fi, and K helicopters; No. 05.39 for 
Model SA 366-G1 and military Model SA 366-GA helicopters; and No. 
05.00.25 for military Model AS565MA, MB, SA, SB, and UB helicopter.
    The EASB specifies checking at regular intervals for a crack in the 
areas of the inner angles and flanges of the 9-degree frame on the RH 
and left hand (LH) sides, near the splice. Revision 2 of the EASB 
modifies the compliance times, adds a compliance time based on take-
off/landing cycles, and expands the inspection areas up to the junction 
with the upper part of the frame. EASA classified this service 
information as mandatory and issued EASA AD No. 2014-0159 to ensure the 
continued airworthiness of these helicopters.
    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 inspecting the 9-degree fuselage 
frame on the RH and LH sides for a crack, using a 10x or higher 
magnifying glass and a light source, in the areas depicted in specified 
portions of the EASB applicable to your helicopter. If there is a 
crack, this proposed AD would require repairing the frame before 
further flight. For helicopters that have not reached a certain hours 
time-in-service (TIS) or landing threshold, the inspection would be 
required within 110 hours TIS after reaching whichever threshold occurs 
first, and thereafter at intervals not to exceed 110 hours TIS. For 
helicopters that have reached or exceeded the hours TIS or landing 
threshold, the inspection would be required within 110 hours TIS since 
the effective date of the AD and thereafter at intervals not to exceed 
110 hours TIS.

Differences Between This Proposed AD and the EASA AD

    We would not require contacting the manufacturer for approved 
repair instructions. We also would not allow flight with a known crack.

Costs of Compliance

    We estimate that this proposed AD would affect 40 helicopters of 
U.S. Registry and that labor costs average $85 a work hour. Based on 
these estimates, we expect the following costs:
     Inspecting the 9-degree frame would require 3 work-hours 
per inspection for a cost of $255 per helicopter and $10,200 for the 
fleet per inspection cycle.
     Repairing the 9-degree frame would require 24 work-hours 
for a labor cost of $2,040. Parts would cost $3,350 for a total cost of 
$5,390 per helicopter.

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 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 removing Airworthiness Directive (AD) 
2013-08-17, Amendment 39-17434 (78 FR 25380, May 1, 2013) and adding 
the following new AD:

Airbus Helicopters (Previously Eurocopter France): Docket No. FAA-
2015-3741; Directorate Identifier 2014-SW-040-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model SA-365N, SA-365-N1, 
AS-365N2, AS 365 N3, and SA-366G1 helicopters, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in the 9-degree 
frame, which could result in the loss of structural integrity and 
subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2013-08-17, Amendment 39-17434 (78 FR 
25380, May 1, 2013).

(d) Comments Due Date

    We must receive comments by February 19, 2016.

[[Page 79276]]

(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) Within 110 hours time-in-service (TIS) after reaching the 
hours or landings threshold, whichever occurs first, listed in Table 
1 to Paragraph (f)(1) of this AD or within 110 hours TIS from the 
effective date of this AD, whichever occurs later, and thereafter at 
intervals not to exceed 110 hours TIS, using a 10X or higher 
magnifying glass and a light, inspect the 9-degree fuselage frame on 
the right-hand (RH) and left-hand (LH) sides for a crack in the 
areas depicted in Figures 1 and 2 of Airbus Helicopters Emergency 
Alert Service Bulletin (EASB) No. AS365 05.00.57, Revision 2, dated 
April 7, 2014, or EASB No. SA366 05.39, Revision 2, dated April 7, 
2014, as applicable to your model helicopter. For purposes of this 
AD, a landing would be counted anytime the helicopter lifts off into 
the air and then lands again regardless of the duration of the 
landing and regardless of whether the engine is shut down.

                       Table 1 to Paragraph (f)(1)
------------------------------------------------------------------------
               Helicopter model                  Hours TIS     Landings
------------------------------------------------------------------------
SA-365N.......................................       11,490       22,980
SA-365N1......................................       10,490       20,980
AS-365N2......................................        9,140       18,280
AS 365 N3.....................................        8,740       17,480
SA-366G1......................................        8,390       16,780
------------------------------------------------------------------------

    (2) If there is a crack, before further flight, repair the 
frame. Repairing a frame does not constitute terminating actions for 
the repetitive inspection requirements of this AD.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort 
Worth, Texas 76177; telephone (817) 222-5110; email 9-ASW-FTW-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.

(h) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2014-0159, dated July 7, 2014. You may view the 
EASA AD on the Internet at http://www.regulations.gov in Docket No. 
FAA-2015-3741.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 5311, Fuselage 
Main, Frame.

    Issued in Fort Worth, Texas, on December 11, 2015.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2015-31847 Filed 12-18-15; 8:45 am]
BILLING CODE 4910-13-P