Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France), 79274-79276 [2015-31847]
Download as PDF
<![CDATA[
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
https://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 https://
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 https://
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
https://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 https://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 https://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
https://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 https://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
