Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France), 25589-25591 [2015-09548]
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Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Rules and Regulations
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times, in such forms, and accompanied
by such supporting data, as required by
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documents as they deem appropriate.
(b) The Award Agreement provides
that the provisions of the Act, this part,
and the Award Agreement are
enforceable under 12 U.S.C. 1818 of the
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Appropriate Federal Banking Agency, as
applicable, and that any violation of
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violation of the Federal Deposit
Insurance Act. Nothing in this
paragraph (b) precludes the CDFI Fund
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Agreement as provided for under the
terms of the Act.
(c) The CDFI Fund will notify the
Appropriate Federal Banking Agency
before imposing any sanctions on a
Recipient that is examined by or subject
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a sanction described in section
1806.500(b) if the Appropriate Federal
Banking Agency, in writing, not later
than 30 calendar days after receiving
notice from the CDFI Fund:
(1) Objects to the proposed sanction;
(2) Determines that the sanction
would:
(i) Have a material adverse effect on
the safety and soundness of the
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(ii) Impede or interfere with an
enforcement action against that
Recipient by the Appropriate Federal
Banking Agency;
(3) Proposes a comparable alternative
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documentation to support the
determination; and
(ii) How the alternative action
suggested pursuant to paragraph (c)(3)
of this section would be as effective as
the sanction proposed by the CDFI Fund
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(d) Prior to imposing any sanctions
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VerDate Sep<11>2014
15:13 May 04, 2015
Jkt 235001
the Recipient with written notice of the
proposed sanction and an opportunity
to comment. Nothing in this section,
however, shall provide a Recipient to
any formal or informal hearing or
comparable proceeding not otherwise
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§ 1806.504
Retention of records.
A Recipient must comply with all
record retention requirements as set
forth in the Uniform Administrative
Requirements.
Dated: April 30, 2015.
Mary Ann Donovan,
Director, Community Development Financial
Institutions Fund.
[FR Doc. 2015–10433 Filed 5–4–15; 8:45 am]
BILLING CODE 4810–70–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0038; Directorate
Identifier 2013–SW–023–AD; Amendment
39–18146; AD 2015–09–01]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Type Certificate
Previously Held by Eurocopter France)
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Airbus
Model EC225LP helicopters. This AD
requires repetitive visual and tap test
inspections of each main rotor blade
(blade) leading edge stainless steel
protective strip (strip) for a crack, cut,
or blind or open debonding
(debonding), and taking approved
corrective measures. If there is a crack
or if there is debonding that exceeds
acceptable limits, this AD requires,
before further flight, repairing or
replacing the blade with an airworthy
part. This AD was prompted by
suspected water seepage through a crack
in the blade strip resulting in significant
debonding. The actions of this AD are
intended to prevent loss of the blade
strip, excessive vibrations induced by
blade weight imbalance, and subsequent
loss of control of the helicopter.
DATES: This AD is effective June 9, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of June 9, 2015.
ADDRESSES: For service information
identified in this AD, contact Airbus
SUMMARY:
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Fmt 4700
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25589
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 the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137. It is also available
on the Internet at https://
www.regulations.gov in Docket No.
FAA–2014–0038.
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 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: 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:
Discussion
On January 31, 2014, at 79 FR 5321,
the Federal Register published our
notice of proposed rulemaking (NPRM),
which proposed to amend 14 CFR part
39 by adding an AD that would apply
to Airbus Helicopters. The NPRM
proposed to require repetitive visual
and tap test inspections of each blade
strip for a crack, cut, or debonding. If
there is a crack or if there is debonding
beyond acceptable limits or located
outside a specific area, the NPRM
proposed to require, before further
flight, repairing or replacing the blade
with an airworthy part. If there is a cut
in the blade root polyurethane
protective strip, the NPRM proposed to
require tap test inspecting the blade for
debonding. The proposed requirements
were intended to prevent loss of the
blade strip, excessive vibrations
induced by blade weight imbalance, and
subsequent loss of control of the
helicopter.
The NPRM was prompted by AD No.
2013–0103, dated May 2, 2013, issued
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25590
Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Rules and Regulations
by EASA, which is the Technical Agent
for the Member States of the European
Union, to correct an unsafe condition
for Eurocopter (now Airbus Helicopters)
Model EC225LP helicopters with certain
blades installed. EASA advises that an
investigation of significant debonding of
a blade strip revealed rapidly
progressing debonding caused by water
seepage through a crack in the blade
strip. EASA issued AD 2013–0103
requiring repetitive inspections of the
blade strip to correct this condition.
Comments
After our NPRM (79 FR 5321, January
31, 2014) was published, we received
comments from 2 commenters.
Request
Two commenters requested that a
helicopter be allowed to operate with a
crack in the leading edge blade strip as
long as the crack is within the limits
prescribed by the manufacturer. The
commenters stated that EASA and the
manufacturer allow for a helicopter to
fly if the blade strip has a crack that is
within limits because the blade strip is
sacrificial and nonstructural. The
commenters state that requiring
repairing or replacing the blade strip if
there is a crack results in a higher cost
and greater out-of-service time for
operators without a justifiable or
measured increase in safety.
We agree with allowing a crack in the
blade strip that is within limits and has
been properly sealed. Therefore, we
have changed paragraph (e)(5) of the AD
to require sealing the crack instead of
repairing or replacing the blade if there
is a crack within acceptable limits.
rljohnson on DSK3VPTVN1PROD with RULES
FAA’s Determination
This helicopter has been approved by
the aviation authority of France and is
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, reviewed the
relevant information, considered the
comments received, and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
this same type design and that air safety
and the public interest require adopting
the AD requirements as proposed with
the change described previously. This
change is consistent with the intent of
the proposals in the NPRM (79 FR 5321,
January 31, 2014) and will not increase
the economic burden on any operator
nor increase the scope of this AD.
VerDate Sep<11>2014
15:13 May 04, 2015
Jkt 235001
Related Service Information Under 1
CFR Part 51
Eurocopter issued Emergency Alert
Service Bulletin No. 05A010, Revision
2, dated April 22, 2013 (EASB), for the
Model EC225LP helicopter and for the
non-FAA typed certificated Model
EC725AP military helicopter. The EASB
specifies a visual check and tapping test
of the bonding of the strip on the
leading edge of the blades for cracks,
cuts, and debonding and taking
corrective actions as applicable.
Revision 1 to the EASB changed the
visual check and the tapping test so that
they can be performed without
removing the blades. Revision 2
extended the applicability to additional
part-numbered blades with a modified
blade strip installed. This information is
reasonably available at https://
www.regulations.gov in Docket No.
FAA–2014–0038. Or see ADDRESSES for
other ways to access this service
information.
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.
Costs of Compliance
We estimate that this AD affects 4
helicopters of U.S. Registry. We estimate
that operators may incur the following
costs in order to comply with this AD.
Labor costs are estimated at $85 per
work hour. We estimate 4 work hours to
inspect the helicopter for a total of $340
per helicopter and $1,360 for the U.S.
operator fleet per inspection cycle. If
necessary, it will take 4 work hours to
repair the blade and $600 for required
parts for a total of $940 per helicopter.
It will take about 5 work hours to
replace a blade at a cost of $425 for
labor. Parts will cost $315,495 to replace
part number (P/N) 332A11–0050–01 and
$403,650 to replace P/N 332A11–0055–
00, for a total cost of $315,920 and
$404,075, respectively.
■
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,
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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
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):
2015–09–01 Airbus Helicopters (Type
Certificate previously held by
Eurocopter France): Amendment 39–
18146, Docket No. FAA–2014–0038,
Directorate Identifier 2013–SW–023–AD.
(a) Applicability
This AD applies to Model EC225LP
helicopters with a main rotor blade (blade),
part number 332A11.0050.00,
332A11.0055.00, 332A11.0050.02, or
332A11.0055.02, installed, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as
loss of a blade stainless steel protective strip
(strip), which could result in excessive
vibrations induced by blade weight
imbalance and subsequent loss of control of
the helicopter.
(c) Effective Date
This AD becomes effective June 9, 2015.
(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
Within 15 hours time-in-service (TIS) and
thereafter at intervals not to exceed 85 hours
TIS, visually and tap test inspect each blade
strip for a crack, a cut, or open and blind
debonding. For purposes of this AD, open
debonding, also known as edge bond
separation, occurs when a bonded part
becomes unattached (debonded) leaving the
surface under it exposed to open air around
the periphery of the part. Blind debonding
occurs when a bonded part becomes
unattached internally yet remains bonded
around its entire periphery.
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Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Rules and Regulations
(1) If there is open or blind debonding
within acceptable limits and the debonded
area is located inside Area D of Figure 1 of
Eurocopter Emergency Alert Service Bulletin
No. 05A010, Revision 2, dated April 22, 2013
(EASB), no further action is required until
the next inspection.
(2) If there is open or blind debonding and
the debonded area is located outside Area D
of Figure 1 of the EASB, before further flight,
repair or replace the blade.
(3) If there is open or blind debonding
beyond acceptable limits, before further
flight, repair or replace the blade.
(4) If there is a cut in the blade root
polyurethane protective strip as depicted in
Area A of Figure 2 of the EASB, tap test
inspect the area.
(i) If there is no open and blind debonding,
at intervals not to exceed 15 hours TIS, tap
test inspect the blade strip in the blade root
area, in the stainless steel leading edge/
neoprene junction area for open or blind
debonding.
(ii) If there is open or blind debonding
within acceptable limits and the debonded
area is located inside Area D of Figure 1 of
the EASB, no further action is required until
the next inspection.
(iii) If there is open or blind and the
debonded area is located outside Area D of
Figure 1 of the EASB, before further flight,
repair or replace the blade.
(iv) If there is open or blind debonding
beyond acceptable limits, before further
flight, repair or replace the blade.
(5) If there is a crack within acceptable
limits, before further flight, seal the crack. If
there is a crack beyond the acceptable limits,
before further flight, repair or replace the
blade.
rljohnson on DSK3VPTVN1PROD with RULES
(f) 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.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2013–0103, dated May 2, 2013. You may
view the EASA AD on the Internet at
www.regulations.gov in Docket No. FAA–
2014–0038.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6210 Main Rotor Blades.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
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15:13 May 04, 2015
Jkt 235001
(IBR) 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) Eurocopter Emergency Alert Service
Bulletin No. 05A010, Revision 2, dated April
22, 2013.
(ii) Reserved.
(3) For service information identified in
this AD, 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.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on April 16,
2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2015–09548 Filed 5–4–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–1130; Directorate
Identifier 2015–CE–008–AD; Amendment
39–18150; AD 2015–09–04]
RIN 2120–AA64
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for comments
AGENCY:
We are adopting a new
airworthiness directive (AD) for DG
Flugzeugbau GmbH Model DG–1000T
gliders equipped with a Solo
Kleinmotoren Model 2350 C engine that
supersedes AD 2013–22–14 R1. This AD
results from mandatory continuing
airworthiness information (MCAI)
issued by the aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as engine shaft failure with
consequent propeller detachment. We
are issuing this AD to require actions to
SUMMARY:
Frm 00011
Fmt 4700
address the unsafe condition on these
products.
This AD is effective May 26,
2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of May 26, 2015.
We must receive comments on this
AD by June 19, 2015.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Solo Kleinmotoren
GmbH, Postfach 600152, 71050
Sindelfingen, Germany; telephone: +49
7031 301–0; fax: +49 7031 301–136;
email: aircraft@solo-germany.com;
Internet: https://aircraft.solo-online.com/
com. 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. It is also available on the Internet
at https://www.regulations.gov by
searching for locating Docket No. FAA–
2015–1130.
DATES:
Examining the AD Docket
Airworthiness Directives; DG
Flugzeugbau GmbH Gliders
PO 00000
25591
Sfmt 4700
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
1130 or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone (800) 647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Jim
Rutherford, Aerospace Engineer, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4165; fax: 98160 329–4090; email:
jim.rutherford@faa.gov.
E:\FR\FM\05MYR1.SGM
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Agencies
[Federal Register Volume 80, Number 86 (Tuesday, May 5, 2015)]
[Rules and Regulations]
[Pages 25589-25591]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-09548]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0038; Directorate Identifier 2013-SW-023-AD;
Amendment 39-18146; AD 2015-09-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters (Type Certificate
Previously Held by Eurocopter France)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus
Model EC225LP helicopters. This AD requires repetitive visual and tap
test inspections of each main rotor blade (blade) leading edge
stainless steel protective strip (strip) for a crack, cut, or blind or
open debonding (debonding), and taking approved corrective measures. If
there is a crack or if there is debonding that exceeds acceptable
limits, this AD requires, before further flight, repairing or replacing
the blade with an airworthy part. This AD was prompted by suspected
water seepage through a crack in the blade strip resulting in
significant debonding. The actions of this AD are intended to prevent
loss of the blade strip, excessive vibrations induced by blade weight
imbalance, and subsequent loss of control of the helicopter.
DATES: This AD is effective June 9, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of June 9, 2015.
ADDRESSES: For service information identified in this AD, 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 the referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137. It is also available on the Internet at https://www.regulations.gov in Docket No. FAA-2014-0038.
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 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: 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:
Discussion
On January 31, 2014, at 79 FR 5321, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 by adding an AD that would apply to Airbus Helicopters. The
NPRM proposed to require repetitive visual and tap test inspections of
each blade strip for a crack, cut, or debonding. If there is a crack or
if there is debonding beyond acceptable limits or located outside a
specific area, the NPRM proposed to require, before further flight,
repairing or replacing the blade with an airworthy part. If there is a
cut in the blade root polyurethane protective strip, the NPRM proposed
to require tap test inspecting the blade for debonding. The proposed
requirements were intended to prevent loss of the blade strip,
excessive vibrations induced by blade weight imbalance, and subsequent
loss of control of the helicopter.
The NPRM was prompted by AD No. 2013-0103, dated May 2, 2013,
issued
[[Page 25590]]
by EASA, which is the Technical Agent for the Member States of the
European Union, to correct an unsafe condition for Eurocopter (now
Airbus Helicopters) Model EC225LP helicopters with certain blades
installed. EASA advises that an investigation of significant debonding
of a blade strip revealed rapidly progressing debonding caused by water
seepage through a crack in the blade strip. EASA issued AD 2013-0103
requiring repetitive inspections of the blade strip to correct this
condition.
Comments
After our NPRM (79 FR 5321, January 31, 2014) was published, we
received comments from 2 commenters.
Request
Two commenters requested that a helicopter be allowed to operate
with a crack in the leading edge blade strip as long as the crack is
within the limits prescribed by the manufacturer. The commenters stated
that EASA and the manufacturer allow for a helicopter to fly if the
blade strip has a crack that is within limits because the blade strip
is sacrificial and nonstructural. The commenters state that requiring
repairing or replacing the blade strip if there is a crack results in a
higher cost and greater out-of-service time for operators without a
justifiable or measured increase in safety.
We agree with allowing a crack in the blade strip that is within
limits and has been properly sealed. Therefore, we have changed
paragraph (e)(5) of the AD to require sealing the crack instead of
repairing or replacing the blade if there is a crack within acceptable
limits.
FAA's Determination
This helicopter has been approved by the aviation authority of
France and is 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, reviewed the relevant information,
considered the comments received, and determined the unsafe condition
exists and is likely to exist or develop on other helicopters of this
same type design and that air safety and the public interest require
adopting the AD requirements as proposed with the change described
previously. This change is consistent with the intent of the proposals
in the NPRM (79 FR 5321, January 31, 2014) and will not increase the
economic burden on any operator nor increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Eurocopter issued Emergency Alert Service Bulletin No. 05A010,
Revision 2, dated April 22, 2013 (EASB), for the Model EC225LP
helicopter and for the non-FAA typed certificated Model EC725AP
military helicopter. The EASB specifies a visual check and tapping test
of the bonding of the strip on the leading edge of the blades for
cracks, cuts, and debonding and taking corrective actions as
applicable. Revision 1 to the EASB changed the visual check and the
tapping test so that they can be performed without removing the blades.
Revision 2 extended the applicability to additional part-numbered
blades with a modified blade strip installed. This information is
reasonably available at https://www.regulations.gov in Docket No. FAA-
2014-0038. Or see ADDRESSES for other ways to access this service
information.
Costs of Compliance
We estimate that this AD affects 4 helicopters of U.S. Registry. We
estimate that operators may incur the following costs in order to
comply with this AD. Labor costs are estimated at $85 per work hour. We
estimate 4 work hours to inspect the helicopter for a total of $340 per
helicopter and $1,360 for the U.S. operator fleet per inspection cycle.
If necessary, it will take 4 work hours to repair the blade and $600
for required parts for a total of $940 per helicopter. It will take
about 5 work hours to replace a blade at a cost of $425 for labor.
Parts will cost $315,495 to replace part number (P/N) 332A11-0050-01
and $403,650 to replace P/N 332A11-0055-00, for a total cost of
$315,920 and $404,075, respectively.
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 adding the following new airworthiness
directive (AD):
2015-09-01 Airbus Helicopters (Type Certificate previously held by
Eurocopter France): Amendment 39-18146, Docket No. FAA-2014-0038,
Directorate Identifier 2013-SW-023-AD.
(a) Applicability
This AD applies to Model EC225LP helicopters with a main rotor
blade (blade), part number 332A11.0050.00, 332A11.0055.00,
332A11.0050.02, or 332A11.0055.02, installed, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as loss of a blade
stainless steel protective strip (strip), which could result in
excessive vibrations induced by blade weight imbalance and
subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective June 9, 2015.
(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
Within 15 hours time-in-service (TIS) and thereafter at
intervals not to exceed 85 hours TIS, visually and tap test inspect
each blade strip for a crack, a cut, or open and blind debonding.
For purposes of this AD, open debonding, also known as edge bond
separation, occurs when a bonded part becomes unattached (debonded)
leaving the surface under it exposed to open air around the
periphery of the part. Blind debonding occurs when a bonded part
becomes unattached internally yet remains bonded around its entire
periphery.
[[Page 25591]]
(1) If there is open or blind debonding within acceptable limits
and the debonded area is located inside Area D of Figure 1 of
Eurocopter Emergency Alert Service Bulletin No. 05A010, Revision 2,
dated April 22, 2013 (EASB), no further action is required until the
next inspection.
(2) If there is open or blind debonding and the debonded area is
located outside Area D of Figure 1 of the EASB, before further
flight, repair or replace the blade.
(3) If there is open or blind debonding beyond acceptable
limits, before further flight, repair or replace the blade.
(4) If there is a cut in the blade root polyurethane protective
strip as depicted in Area A of Figure 2 of the EASB, tap test
inspect the area.
(i) If there is no open and blind debonding, at intervals not to
exceed 15 hours TIS, tap test inspect the blade strip in the blade
root area, in the stainless steel leading edge/neoprene junction
area for open or blind debonding.
(ii) If there is open or blind debonding within acceptable
limits and the debonded area is located inside Area D of Figure 1 of
the EASB, no further action is required until the next inspection.
(iii) If there is open or blind and the debonded area is located
outside Area D of Figure 1 of the EASB, before further flight,
repair or replace the blade.
(iv) If there is open or blind debonding beyond acceptable
limits, before further flight, repair or replace the blade.
(5) If there is a crack within acceptable limits, before further
flight, seal the crack. If there is a crack beyond the acceptable
limits, before further flight, repair or replace the blade.
(f) 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.
(g) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (EASA) AD No. 2013-0103, dated May 2, 2013. You may view the
EASA AD on the Internet at www.regulations.gov in Docket No. FAA-
2014-0038.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6210 Main Rotor
Blades.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) 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) Eurocopter Emergency Alert Service Bulletin No. 05A010,
Revision 2, dated April 22, 2013.
(ii) Reserved.
(3) For service information identified in this AD, 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.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on April 16, 2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2015-09548 Filed 5-4-15; 8:45 am]
BILLING CODE 4910-13-P