Airworthiness Directives; Eurocopter France (Eurocopter) Helicopters, 66668-66670 [2013-26568]
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Federal Register / Vol. 78, No. 215 / Wednesday, November 6, 2013 / Proposed Rules
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 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, 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.
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 adding
the following new AD:
■
Diamond Aircraft Industries GmbH: Docket
No. FAA–2013–0937; Directorate
Identifier 2013–CE–029–AD.
(a) Comments Due Date
We must receive comments by December
23, 2013.
pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
(b) Affected ADs
None.
(c) Applicability
This AD applies to Diamond Aircraft
Industries GmbH Models DA 42 NG and DA
42 M–NG airplanes, all serial numbers
certificated in any category, except those that
have Supplemental Type Certificate (STC)
SA02725NY (https://rgl.faa.gov/Regulatory_
and_Guidance_Library/rgstc.nsf/0/286A2
9A0C46D66048625764900624649?Open
Document&Highlight=sa02725ny)
incorporated.
Note 1 to paragraph (c) of this AD: STC
SA02725NY uses a different electrical system
architecture and the unsafe condition
addressed in this AD does not apply to that
system.
(d) Subject
Air Transport Association of America
(ATA) Code 24: Electric Power.
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15:07 Nov 05, 2013
Jkt 232001
(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
originated by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as failure of
the alternator indication system to indicate
warning when one alternator is inoperative.
We are issuing this proposed AD to prevent
the undetected loss of one engine alternator,
which could result in reduced capability of
the electrical generating power system.
(f) Actions and Compliance
Unless already done, do the following
actions as specified in paragraphs (f)(1)
through (f)(3) of this AD, including all
subparagraphs:
(1) For all DA 42 NG airplanes: Within 12
months after the effective date of this AD,
install Secondary Configuration Card part
number (P/N) 010–12074–02 ‘‘Additional
ALTN FAIL trigger’’ and System Software P/
N 010–00670–10 following the
Accomplishment/Instructions section of
Diamond Aircraft Industries GmbH
Mandatory Service Bulletin No. MSB 42NG–
003/13, dated October 11, 2013; or the
Accomplishment/Instructions section of
Diamond Aircraft Industries GmbH
Mandatory Service Bulletin No. MSB 42NG–
003/12, dated July 8, 2013.
(2) For DA 42 M–NG airplanes, serial
numbers (S/Ns) 42.339, 42.MN001 through
42.MN0026, and all S/Ns modified through
Optional Service Bulletin (OSB) 42–081,
using Work Instruction (WI) OSB–42–081 up
to Revision 1 inclusive: Within 100 hours
time-in-service after the effective date of this
AD or within 12 months after the effective
date of this AD, whichever occurs first:
(i) Install GEA Alternator fail control cable
P/N D62–2510–97–00–SB following the
Instructions section of Diamond Aircraft
Industries GmbH Work Instruction WI–MSB
42MNG–006, dated July 8, 2013, as specified
in the Accomplishments/Instructions section
of Diamond Aircraft Industries GmbH
Mandatory Service Bulletin No. MSB
42MNG–006, July 8, 2013; and
(ii) Install Secondary Configuration Card P/
N 010–12074–02 ‘‘Additional ALTN FAIL
trigger’’ and System Software P/N 010–
00670–10 following the Accomplishment/
Instructions section of Diamond Aircraft
Industries GmbH Mandatory Service Bulletin
No. MSB 42NG–003/13, dated October 11,
2013; or the Accomplishment/Instructions
section of Diamond Aircraft Industries GmbH
Mandatory Service Bulletin No. MSB 42NG–
003/12, dated July 8, 2013.
(3) For all airplanes: As of the effective
date of this AD, do not install on any airplane
System Software prior to P/N 010–00670–10.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Mike Kiesov, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4144; fax: (816) 329–
4090; email: mike.kiesov@faa.gov. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(h) Related Information
Refer to MCAI European Aviation Safety
Agency (EASA) AD No.: 2013–0224, dated
September 19, 2013; Diamond Aircraft
Industries GmbH Optional Service Bulletin
OSB 42–081/1; Diamond Aircraft Industries
GmbH Work Instruction WI–OSB 42–081,
Rev. 1, both dated December 23, 2010;
Diamond Aircraft Industries GmbH Optional
Service Bulletin OSB 42–081; and Diamond
Aircraft Industries GmbH Work Instruction
WI–OSB 42–081, Rev. 0, both dated March
17, 2010, for related information. You may
examine the MCAI on the Internet at
https://www.regulations.gov by searching for
and locating it in Docket No. FAA–2013–
0937. For service information related to this
AD, contact Diamond Aircraft Industries
GmbH, N.A. Otto-Stra+e 5, A–2700 Wiener
Neustadt, Austria, telephone: +43 2622
26700; fax: +43 2622 26700 1369; email:
airworthiness@diamond-air.at; Internet:
https://www.diamond-air.at. You may review
copies of the referenced service information
at the FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
Issued in Kansas City, Missouri, on
October 30, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2013–26571 Filed 11–5–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0938; Directorate
Identifier 2012–SW–057–AD]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France (Eurocopter) Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for
SUMMARY:
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Federal Register / Vol. 78, No. 215 / Wednesday, November 6, 2013 / Proposed Rules
Eurocopter Model SA–365N, SA–
365N1, AS–365N2, and AS 365 N3
helicopters. This proposed AD would
require repetitively inspecting frame
number (No.) 9 for a crack. This
proposed AD is prompted by a report of
a crack in frame No. 9 on an AS365
helicopter. The proposed actions are
intended to detect a crack and prevent
loss of structural integrity and
subsequent loss of control of the
helicopter.
We must receive comments on
this proposed AD by January 6, 2014.
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.
DATES:
pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov 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
foreign authority’s 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 AD, contact American
Eurocopter Corporation, 2701 N. Forum
Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–
0323; fax (972) 641–3775; or at https://
www.eurocopter.com/techpub. You may
review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Gary
Roach, Aviation Safety Engineer,
Regulations and Policy Group,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
gary.b.roach@faa.gov.
SUPPLEMENTARY INFORMATION:
VerDate Mar<15>2010
15:07 Nov 05, 2013
Jkt 232001
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
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD No. 2012–
0108–E, dated June 15, 2012 (AD 2012–
0108–E), to correct an unsafe condition
for Eurocopter Model SA 365 N, SA 365
N1, AS 365 N2, and AS 365 N3
helicopters with a frame No. 9 installed,
if certain ‘‘doublers or repairs have been
installed.’’ EASA advises that a crack
was discovered during the ‘‘T’’
inspection of an AS365 helicopter. The
crack started at a rivet hole of a doubler
that was installed on the frame No. 9 in
accordance with Eurocopter Alert
Service Bulletin (ASB) 53.00.42, dated
January 31, 2001. EASA further states
that structural alteration of frame No. 9
by modifications or repairs can result in
fatigue crack initiation under normal
operational loads. According to EASA,
this condition, if not corrected, could
lead to crack propagation and failure of
frame No. 9, which would adversely
affect the structural integrity of the
helicopter. For these reasons, AD 2012–
0108–E requires repetitive inspections
of frame No. 9 for a crack in the area of
the doubler or any repair performed in
the area of the latch support and
stretcher support.
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66669
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
Eurocopter has issued one Emergency
ASB (EASB) with two numbers: EASB
No. 05.00.63, Revision 1, dated June 18,
2012, for Model AS365 helicopters and
EASB No. 05.00.30, Revision 1, dated
June 18, 2012, for Model AS565
helicopters. The EASB applies to
helicopters with a frame No. 9 that has
not been modified by modification
(MOD) 07 53C17 or MOD 07 53D02, and
that has had doublers installed or
repairs performed in accordance with
certain service instructions. The EASB
describes procedures to inspect the
frame No. 9 for a crack, and for
contacting Eurocopter for further
procedures if there is a crack.
Proposed AD Requirements
This proposed AD would require, for
helicopters that have a No. 9 frame that
has had any repair or alteration made,
within 10 hours time-in-service (TIS)
and every 110 hours TIS thereafter,
inspecting the left-hand (LH) and righthand (RH) frame No. 9 for a crack in the
areas of the latch support and stretcher
support with a 10X or higher power
magnifying glass. For all other
helicopters, this proposed AD would
require this inspection within 110 hours
TIS and every 110 hours TIS thereafter.
If there is a crack, the proposed AD
would require, before further flight,
repairing the crack.
Differences Between This Proposed AD
and the EASA AD
The EASA AD requires contacting
Eurocopter for repair instructions if
there is a crack, and the proposed AD
does not. The proposed AD would apply
to all Eurocopter 365 helicopters, not
just those that were altered or repaired
in accordance with specific Eurocopter
MODs.
Costs of Compliance
We estimate that this proposed AD
would affect 37 helicopters of U.S.
Registry. We estimate that operators
may incur the following costs in order
to comply with this AD. At an average
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Federal Register / Vol. 78, No. 215 / Wednesday, November 6, 2013 / Proposed Rules
labor rate of $85 per hour, inspecting LH
and RH frame No. 9 would require about
3 work-hours, for a cost per helicopter
of $255 and a total cost to U.S. operators
of $9,435 per inspection cycle.
Repairing a cracked frame No. 9 would
require about 20 work-hours, and
required parts would cost about
$10,000, for a cost per helicopter of
$11,700.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Authority for This Rulemaking
PART 39—AIRWORTHINESS
DIRECTIVES
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 proposed
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.
pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
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.
VerDate Mar<15>2010
15:07 Nov 05, 2013
Jkt 232001
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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 adding
the following new airworthiness
directive (AD):
■
Eurocopter France Helicopters: Docket No.
FAA–2013–0938; Directorate Identifier
2012–SW–057–AD.
(a) Applicability
This AD applies to Eurocopter France
(Eurocopter) Model SA–365N, SA–365N1,
AS–365N2, and AS 365 N3 helicopters,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in frame number (No.) 9, which could
result in failure of frame No. 9, loss of
structural integrity, and subsequent loss of
control of the helicopter.
(c) Comments Due Date
We must receive comments by January 6,
2014.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) For helicopters that have any repair or
alteration to the frame No. 9, within 10 hours
time-in-service (TIS) and thereafter at
intervals not to exceed 110 hours TIS, using
a 10X or higher power magnifying glass,
inspect the left-hand (LH) and right-hand
(RH) frame No. 9 for a crack in the area of
the latch support and stretcher support, as
depicted in Figure 1 of Eurocopter AS365
Emergency Alert Service Bulletin No.
05.00.63, Revision 1, dated June 18, 2012.
(2) For all other helicopters, within 110
hours TIS and thereafter at intervals not to
exceed 110 hours TIS, perform the inspection
in paragraph (e)(1) of this AD.
(3) If there is a crack, before further flight,
repair the frame No. 9. Repairing a frame is
not terminating action for the repetitive
inspections required by paragraphs (e)(1) and
(e)(2) of this AD.
(f) Special flight permit
Special flight permits may be issued for up
to 10 hours TIS and a maximum crack length
of 80 mm.
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Fmt 4702
Sfmt 4702
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Gary Roach,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
gary.b.roach@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
(1) The subject of this AD is addressed in
European Aviation Safety Agency (EASA)
Emergency AD No. 2012–0108–E, dated June
15, 2012. You may view the EASA AD on the
Internet at https://www.regulations.gov in
Docket number FAA–2013–0938.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 5300: Fuselage Structure (General).
Issued in Fort Worth, Texas, on October 30,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–26568 Filed 11–5–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HOUSING AND
URBAN DEVELOPMENT
24 CFR Part 214
[Docket No. FR–5339–N–02]
Housing Counseling Program: New
Certification Requirements; Extension
of Public Comment Period
Office of the Assistant
Secretary for Housing—Federal Housing
Commissioner, HUD.
ACTION: Proposed rule; extension of
public comment period.
AGENCY:
On September 13, 2013, HUD
published a rule in the Federal Register
inviting public comment on proposed
changes to the Housing Counseling
Program regulations for the purpose of
implementing the Dodd-Frank Wall
Street Reform and Consumer Protection
Act amendments to the housing
counseling statute. This document
announces that HUD is extending the
public comment period, for an
additional 30-day period, to December
12, 2013.
DATES: Comment Due Date: For the
proposed rule published on September
SUMMARY:
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06NOP1
]]>Agencies
[Federal Register Volume 78, Number 215 (Wednesday, November 6, 2013)]
[Proposed Rules]
[Pages 66668-66670]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-26568]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0938; Directorate Identifier 2012-SW-057-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France (Eurocopter)
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
[[Page 66669]]
Eurocopter Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3
helicopters. This proposed AD would require repetitively inspecting
frame number (No.) 9 for a crack. This proposed AD is prompted by a
report of a crack in frame No. 9 on an AS365 helicopter. The proposed
actions are intended to detect a crack and prevent loss of structural
integrity and subsequent loss of control of the helicopter.
DATES: We must receive comments on this proposed AD by January 6, 2014.
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 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 foreign
authority's 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 AD, contact
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775;
or at https://www.eurocopter.com/techpub. You may review the referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.
FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer,
Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham
Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email
gary.b.roach@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
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
No. 2012-0108-E, dated June 15, 2012 (AD 2012-0108-E), to correct an
unsafe condition for Eurocopter Model SA 365 N, SA 365 N1, AS 365 N2,
and AS 365 N3 helicopters with a frame No. 9 installed, if certain
``doublers or repairs have been installed.'' EASA advises that a crack
was discovered during the ``T'' inspection of an AS365 helicopter. The
crack started at a rivet hole of a doubler that was installed on the
frame No. 9 in accordance with Eurocopter Alert Service Bulletin (ASB)
53.00.42, dated January 31, 2001. EASA further states that structural
alteration of frame No. 9 by modifications or repairs can result in
fatigue crack initiation under normal operational loads. According to
EASA, this condition, if not corrected, could lead to crack propagation
and failure of frame No. 9, which would adversely affect the structural
integrity of the helicopter. For these reasons, AD 2012-0108-E requires
repetitive inspections of frame No. 9 for a crack in the area of the
doubler or any repair performed in the area of the latch support and
stretcher support.
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
Eurocopter has issued one Emergency ASB (EASB) with two numbers:
EASB No. 05.00.63, Revision 1, dated June 18, 2012, for Model AS365
helicopters and EASB No. 05.00.30, Revision 1, dated June 18, 2012, for
Model AS565 helicopters. The EASB applies to helicopters with a frame
No. 9 that has not been modified by modification (MOD) 07 53C17 or MOD
07 53D02, and that has had doublers installed or repairs performed in
accordance with certain service instructions. The EASB describes
procedures to inspect the frame No. 9 for a crack, and for contacting
Eurocopter for further procedures if there is a crack.
Proposed AD Requirements
This proposed AD would require, for helicopters that have a No. 9
frame that has had any repair or alteration made, within 10 hours time-
in-service (TIS) and every 110 hours TIS thereafter, inspecting the
left-hand (LH) and right-hand (RH) frame No. 9 for a crack in the areas
of the latch support and stretcher support with a 10X or higher power
magnifying glass. For all other helicopters, this proposed AD would
require this inspection within 110 hours TIS and every 110 hours TIS
thereafter. If there is a crack, the proposed AD would require, before
further flight, repairing the crack.
Differences Between This Proposed AD and the EASA AD
The EASA AD requires contacting Eurocopter for repair instructions
if there is a crack, and the proposed AD does not. The proposed AD
would apply to all Eurocopter 365 helicopters, not just those that were
altered or repaired in accordance with specific Eurocopter MODs.
Costs of Compliance
We estimate that this proposed AD would affect 37 helicopters of
U.S. Registry. We estimate that operators may incur the following costs
in order to comply with this AD. At an average
[[Page 66670]]
labor rate of $85 per hour, inspecting LH and RH frame No. 9 would
require about 3 work-hours, for a cost per helicopter of $255 and a
total cost to U.S. operators of $9,435 per inspection cycle. Repairing
a cracked frame No. 9 would require about 20 work-hours, and required
parts would cost about $10,000, for a cost per helicopter of $11,700.
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 proposed regulation is
within the scope of that authority because it addresses an unsafe
condition that is likely to exist or develop on products identified in
this rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed, I certify this proposed regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska to the extent that
it justifies making a regulatory distinction; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Eurocopter France Helicopters: Docket No. FAA-2013-0938; Directorate
Identifier 2012-SW-057-AD.
(a) Applicability
This AD applies to Eurocopter France (Eurocopter) Model SA-365N,
SA-365N1, AS-365N2, and AS 365 N3 helicopters, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in frame number
(No.) 9, which could result in failure of frame No. 9, loss of
structural integrity, and subsequent loss of control of the
helicopter.
(c) Comments Due Date
We must receive comments by January 6, 2014.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
(1) For helicopters that have any repair or alteration to the
frame No. 9, within 10 hours time-in-service (TIS) and thereafter at
intervals not to exceed 110 hours TIS, using a 10X or higher power
magnifying glass, inspect the left-hand (LH) and right-hand (RH)
frame No. 9 for a crack in the area of the latch support and
stretcher support, as depicted in Figure 1 of Eurocopter AS365
Emergency Alert Service Bulletin No. 05.00.63, Revision 1, dated
June 18, 2012.
(2) For all other helicopters, within 110 hours TIS and
thereafter at intervals not to exceed 110 hours TIS, perform the
inspection in paragraph (e)(1) of this AD.
(3) If there is a crack, before further flight, repair the frame
No. 9. Repairing a frame is not terminating action for the
repetitive inspections required by paragraphs (e)(1) and (e)(2) of
this AD.
(f) Special flight permit
Special flight permits may be issued for up to 10 hours TIS and
a maximum crack length of 80 mm.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Gary Roach, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email gary.b.roach@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
(1) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) Emergency AD No. 2012-0108-E, dated June 15,
2012. You may view the EASA AD on the Internet at https://www.regulations.gov in Docket number FAA-2013-0938.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 5300: Fuselage
Structure (General).
Issued in Fort Worth, Texas, on October 30, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-26568 Filed 11-5-13; 8:45 am]
BILLING CODE 4910-13-P
