
[Federal Register Volume 81, Number 88 (Friday, May 6, 2016)]
[Rules and Regulations]
[Pages 27303-27305]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-10286]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3741; Directorate Identifier 2014-SW-040-AD; 
Amendment 39-18507; AD 2016-09-09]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding airworthiness directive (AD) 2013-08-17 for 
Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, and 
SA-366G1 helicopters. AD 2013-08-17 required initial and recurring 
inspections of the 9-degree fuselage frame for a crack and repairing 
the frame if a crack exists. This new AD modifies the compliance times 
and expands the inspection area of the 9-inch frame. The actions of 
this AD 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: This AD is effective June 10, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of June 10, 2016.

ADDRESSES: For service information identified in this final 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 
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-2015-
3741.

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 AD, the European Aviation Safety Agency (EASA) AD, any 
incorporated-by-reference service information, the economic evaluation, 
any comments received, and other information. The street address for 
the Docket Operations Office (phone: 800-647-5527) is U.S. Department 
of Transportation, Docket Operations Office, M-30, West Building Ground 
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

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

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to remove AD 2013-08-17, Amendment 39-17434 (78 FR 25380, May 
1, 2013) and add a new AD. AD 2013-08-17 applied to Airbus Helicopters 
Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 helicopters 
and required initial and recurring inspections of the inner angles and 
flanges of the 9-degree fuselage frame on the right-hand (RH) and left-
hand (LH) sides for a crack. If a crack was found, AD 2013-08-17 
required repairing the frame. AD 2013-08-17 was prompted by EASA 
Emergency AD No. 2010-0064-E, dated April 1, 2010, to correct an unsafe 
condition for the specified model

[[Page 27304]]

helicopters. EASA, which is the Technical Agent for the Member States 
of the European Union, advises that of a crack found in the 9-degree 
frame of an AS 365 N2 helicopter that had logged a total of 10,786 
flight hours. EASA states that the time required for initiation of a 
crack in this area varies according to the weight and balance data of 
the different aircraft versions.
    The NPRM published in the Federal Register on December 21, 2015 (80 
FR 79274). The NPRM was prompted by EASA AD No. 2014-0159, dated July 
7, 2014, which supersedes EASA Emergency AD No. 2010-0064-E. EASA 
advises of further analysis on the strength of the 9-degree frame by 
Airbus Helicopters, which indicates compliance times should be modified 
and the inspection area expanded. Consequently, the NPRM proposed 
retaining the inspections of the 9-degree fuselage frame for a crack 
but in the expanded area and within the modified compliance times. 
These 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we received no comments on the NPRM (80 FR 79274, December 
21, 2015).

FAA's Determination

    These helicopters have been approved by the aviation authority of 
France and are approved for operation in the United States. Pursuant to 
our bilateral agreement with France, EASA, its technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are issuing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to exist or develop on other helicopters of these same 
type designs and that air safety and the public interest require 
adopting the AD requirements as proposed.

Differences Between This AD and the EASA AD

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

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-366G1 and military Model SA 366-GA helicopters; and No. 
05.00.25 for military Model AS565MA, MB, SA, SB, and UB helicopters.
    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 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.

Costs of Compliance

    We estimate that this AD affects 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 requires 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 requires 24 work-hours for a 
labor cost of $2,040. Parts 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 helicopters identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979);
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction; and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2013-08-17, Amendment 39-17434 (78 FR 25380, May 1, 2013) and adding 
the following new AD:

2016-09-09 Airbus Helicopters (Previously Eurocopter France): 
Amendment 39-18507; Docket No. FAA-2015-3741; Directorate Identifier 
2014-SW-040-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model SA-365N, SA-365N1, 
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.

[[Page 27305]]

(c) Affected ADs

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

(d) Effective Date

    This AD becomes effective June 10, 2016.

(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 and left-hand 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-365N3..........................................      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.

(j) 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 Emergency Alert Service Bulletin No. 
05.00.57, Revision 2, dated April 7, 2014.
    (ii) Airbus Helicopters Emergency Alert Service Bulletin No. 
05.39, Revision 2, dated April 7, 2014.

    Note 1 to paragraph (j)(2):  Airbus Helicopters Emergency Alert 
Service Bulletin No. 05.00.57 and Airbus Helicopters Emergency Alert 
Service Bulletin No. 05.39, both Revision 2, and both dated April 7, 
2014, are co-published as one document along with Airbus Helicopters 
Emergency Alert Service Bulletin No. 05.00.25, Revision 2, dated 
April 7, 2014, which is not incorporated by reference in this AD.

    (3) For Airbus Helicopters service information identified in 
this final 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.
    (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 April 22, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-10286 Filed 5-5-16; 8:45 am]
 BILLING CODE 4910-13-P


