[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
[email protected].
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 [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office before operating any aircraft
complying with this AD through an AMOC.
(h) Additional Information
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