Airworthiness Directives; Airbus Helicopters, 23778-23780 [2018-10921]
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Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations
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 Des Moines, Washington, on May
11, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–10920 Filed 5–22–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–3883; Product
Identifier 2014–SW–029–AD; Amendment
39–19289; AD 2018–11–01]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Airbus
Helicopters Model AS332L2 and
EC225LP helicopters. This AD requires
installing a cut-out for the left-hand
(LH) and right-hand (RH) rail support
junction profiles and inspecting splices,
frame 5295, and related equipment for
a crack. This AD was prompted by
reports of cracks on frame 5295 and on
splices installed to prevent those cracks.
The actions of this AD are intended to
prevent an unsafe condition on these
products.
SUMMARY:
This AD is effective June 27,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of June 27, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Airbus Helicopters, Inc., 2701 N Forum
Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–
0323; fax (972) 641–3775; or at https://
www.airbushelicopters.com/techpub.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177. It is also
available on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
3883.
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DATES:
VerDate Sep<11>2014
16:18 May 22, 2018
Jkt 244001
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–
3883; or in person at Docket Operations
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-byreference service information, the
economic evaluation, any comments
received, and other information. The
street address for Docket Operations
(phone: 800–647–5527) is U.S.
Department of Transportation, Docket
Operations, 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 & Policy Section, Rotorcraft
Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email
gary.b.roach@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On January 5, 2016, at 81 FR 191, 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
Model AS332L2 and Model EC225LP
helicopters with an extended aluminum
splice installed on frame 5295. The
NPRM proposed to require installing a
cut-out for the LH and RH rail support
junction profiles and inspecting splices,
frame 5295, and related equipment for
a crack. The proposed requirements
were intended to detect a crack in frame
5295, which could lead to structural
failure of the frame and loss of control
of the helicopter.
The NPRM was prompted by AD No.
2014–0098–E, dated April 25, 2014,
issued by EASA, which is the Technical
Agent for the Member States of the
European Union, to correct an unsafe
condition for Model AS332L2 and
EC225LP helicopters. EASA AD No.
2014–0098–E applies to helicopters
with a frame 5295 that have been
reinforced by installing aluminium
splices on the RH and LH fuselage
external skins. EASA advises of a report
of a crack that initiated on a splice in
an area hidden by the overlapping
junction profile of the cabin sliding door
rail support and then spread to the
frame.
EASA states that a crack in frame
5295, if not detected and corrected,
could lead to loss of structural integrity
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of the helicopter frame and subsequent
loss of control of the helicopter. To
address this condition, EASA issued AD
No. 2014–0098–E to require repetitive
inspections of the splices for a crack, as
well as cutting out the rail support
junction profiles to provide a
convenient access to identify cracks in
a splice.
Since the NPRM was issued, the
FAA’s Aircraft Certification Service has
changed its organizational structure.
The new structure replaces product
directorates with functional divisions.
We have revised some of the office titles
and nomenclature throughout this Final
rule to reflect the new organizational
changes. Additional information about
the new structure can be found in the
Notice published on July 25, 2017 (82
FR 34564).
Comments
After our NPRM was published, we
received comments from a commenter
who raised three issues.
Request
The commenter requested that we
revise the applicability of the AD to
exempt helicopters that are ‘‘post mod
07 26493 or RDAS 332–1284–13.’’
We partially agree. Modification
(MOD) 0726493 or repair design
approval sheet (RDAS) 332–1284–13
specify installing a stainless steel
doubler to reduce stress in the splice
and frame, thereby eliminating the
unsafe condition. We disagree with
exempting ‘‘post mod’’ helicopters,
however, as the stainless steel doubler
could be removed (subjecting the
helicopter again to the unsafe condition)
and the helicopter would still be in a
‘‘post mod’’ configuration. Instead, we
have changed the applicability to
exempt helicopters with the steel splice
kit installed that pertains to MOD
0726493.
The commenter requested that we
revise the compliance time of the AD to
include the flow charts from the Airbus
Helicopters service information. The
commenter states that this information
would explain the steps involved to
operators to eliminate the unsafe
condition. The commenter also
requested that we clarify the compliance
times as discussed in the preamble of
the NPRM, because they appear
different from those in the service
information and the EASA AD.
We disagree. The commenter is
correct that the compliance times in our
AD are different, in some measure, to
those in the EASA AD. But the
compliance times in the AD are clear as
written. The requested change is
unnecessary.
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Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations
The commenter requested that we
withdraw the AD because all helicopters
in the U.S. fleet have either installed the
cut-out or are scheduled for installation
of the cut-out.
We disagree. The FAA has
determined that an unsafe condition
exists. AD action is required to mandate
corrective action for this unsafe
condition. In addition, if additional
helicopters are imported into the United
States, AD action is necessary to require
that those helicopters accomplish the
corrective actions before operating in
this country.
accomplished on the aircraft to allow for
a visual check of the splice for frame
5295, it would have revealed the crack
in the splice, prompting its repair and
consequently limiting the damage to
frame 5295. As a result, the ASBs call
for the rail support cut-out on the RH
and LH side of the frame as well as
periodic visual inspections of frame
5295 and related equipment.
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.
FAA’s Determination
These helicopters have been approved
by the aviation authority of France and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with France, EASA, its
technical representative, has notified us
of the unsafe condition described in the
EASA AD. We are issuing this AD
because we evaluated all information
provided by EASA, 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
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed with the change described
previously and with a revision to the
estimated costs of complying with this
AD. These changes are consistent with
the intent of the proposals in the NPRM
and will not increase the economic
burden on any operator nor increase the
scope of the AD.
Other Related Service Information
We reviewed Eurocopter Helicopters
(now Airbus Helicopters) Service
Bulletin (SB) No. 53–003, Revision 4, for
Model EC225LP helicopters and SB No.
53.01.52, Revision 5, for Model
AS332L2 helicopters, both dated July
23, 2010. The SBs specify procedures to
reinforce frame 5295 by installing a new
titanium plate underneath the fitting
and a new widened aluminum splice
below the upper corner of the door. We
also reviewed Airbus Helicopters SB
No. 05–019, Revision 4, dated
September 22, 2014, for Model EC225LP
helicopters, which proposes that you
cut out the junction profiles to perform
periodic visual inspections.
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Differences Between This AD and the
EASA AD
The EASA AD requires contacting
Airbus Helicopters if there is a crack in
the affected parts. This AD makes no
such requirement.
The EASA AD sets various timelines
for repairing affected parts if a crack
exists. This AD requires repairing
affected parts before further flight if a
crack exists.
Related Service Information Under 1
CFR Part 51
We reviewed Airbus Helicopters Alert
Service Bulletin (ASB) No. EC225–
05A038 for Model EC225LP helicopters
and ASB No. AS332–05.00.97 for Model
AS332L2 helicopters. The ASBs, both
Revision 0 and both dated April 15,
2014, report cracks were found in the
splice and frame 5295 on a Model
AS332L2 helicopter during a major
inspection. The splice had been added
in compliance with MOD 0726517. Had
an optional rail support cut-out been
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16:18 May 22, 2018
Jkt 244001
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 average $85 a work-hour.
Based on these estimates, we expect the
following costs:
Installing the cut-outs on frame 5295
requires 40 work-hours for a labor cost
of $3,400. Parts cost $5,000 for total cost
per helicopter of $8,400 and $33,600 for
the U.S. fleet.
Inspecting helicopter frame 5295
requires 2 work-hours for a labor cost of
$170 per helicopter. No parts are needed
for a total U.S. fleet cost of $680 per
inspection cycle.
Repairing a splice requires 40 workhours and a parts cost of $5,000 for a
total cost of $8,400 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:
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23779
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
helicopters identified in this rulemaking
action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation
in Alaska to the extent that it justifies
making a regulatory distinction; and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared an economic evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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):
■
2018–11–01 Airbus Helicopters:
Amendment 39–19289; Docket No.
FAA–2015–3883; Product Identifier
2014–SW–029–AD.
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23780
Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations
(a) Applicability
This AD applies to Model AS332L2 and
Model EC225LP helicopters, certificated in
any category, with an extended aluminum
splice installed on frame 5295, except
helicopters with steel splice kit part number
332A08–2649–3072 installed.
Note 1 to paragraph (a) of this AD:
Helicopters with Modification (MOD)
0726517 have an extended aluminum splice
installed.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack on helicopter frame 5295. This
condition could result in structural failure of
the frame and subsequent loss of control of
the helicopter.
(c) Effective Date
This AD becomes effective June 27, 2018.
(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) Before a splice reaches 1,700 hours
time-in-service (TIS), within 50 hours TIS, or
before the helicopter reaches 11,950 hours
TIS, whichever occurs later, do the following:
(i) Install the rail support cut-out and
identify the right-hand and left-hand junction
profile in accordance with the
Accomplishment Instructions, paragraph
3.B.2, of Airbus Helicopters Alert Service
Bulletin (ASB) No. EC225–05A038, Revision
0, dated April 15, 2014 (ASB EC225–
05A038), or ASB No. AS332–05.00.97,
Revision 0, dated April 15, 2014 (ASB
AS332–05.00.97), whichever is applicable to
your helicopter.
(ii) Inspect each splice for a crack in the
area depicted as Area Y in Figure 3 of ASB
EC225–05A038 or ASB AS332–05.00.97,
whichever is applicable to your helicopter. If
a crack exists, repair or replace the splice
before further flight.
(2) Thereafter at intervals not to exceed 110
hours TIS, inspect each splice for a crack in
the area depicted as Area Y in Figure 3 of
ASB EC225–05A038 or ASB AS332–05.00.97.
If a crack exists, repair or replace the splice
before further flight.
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(f) Credit for Actions Previously Completed
Installing rail support cut-outs in
accordance with MOD 0728090 or Airbus
Helicopters Service Bulletin No. 05–019,
Revision 4, dated September 22, 2014, before
the effective date of this AD is considered
acceptable for compliance with the
corresponding actions specified in paragraph
(e)(1)(i) of this AD.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Section, Rotorcraft Standards Branch, FAA,
may approve AMOCs for this AD. Send your
proposal to: Gary Roach, Aviation Safety
Engineer, Regulations & Policy Section,
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
VerDate Sep<11>2014
16:18 May 22, 2018
Jkt 244001
telephone (817) 222–5110; email 9-ASWFTW-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
(1) Airbus Helicopters Service Bulletin
(SB) No. 05–019, Revision 4, dated
September 22, 2014, and Eurocopter
Helicopters (now Airbus Helicopters) SB No.
53–003, Revision 4, and SB No. 53.01.52,
Revision 5, both dated July 23, 2010, which
are not incorporated by reference, contain
additional information about the subject of
this AD. 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 view the referenced service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2014–0098–E, dated April 25, 2014. You
may view the EASA AD on the internet at
https://www.regulations.gov in Docket No.
FAA–2015–3883.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 5310, Fuselage Main, Structure.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Helicopters Alert Service
Bulletin No. EC225–05A038, Revision 0,
dated April 15, 2014.
(ii) Airbus Helicopters Alert Service
Bulletin No. AS332–05.00.97, Revision 0,
dated April 15, 2014.
(3) For Airbus Helicopters 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 the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
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www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on May 16,
2018.
Scott A. Horn,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2018–10921 Filed 5–22–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0188; Product
Identifier 2018–CE–002–AD; Amendment
39–19285; AD 2018–10–10]
RIN 2120–AA64
Airworthiness Directives; Diamond
Aircraft Industries GmbH Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for comments
AGENCY:
We are superseding
Airworthiness Directive (AD) 2017–01–
12, AD 2017–11–08, and AD 2017–15–
09 for certain Diamond Aircraft
Industries GmbH Model DA 42
airplanes. This AD results from
mandatory continuing airworthiness
information (MCAI) issued by the
aviation authority of another country to
identify and address an unsafe
condition on an aviation product. The
MCAI describes the unsafe condition as
uncommanded engine shutdown during
flight due to failure of the propellerregulating valve caused by hot exhaust
gases coming from fractured engine
exhaust pipes. We are issuing this AD
to require actions to address the unsafe
condition on these products.
DATES: This AD is effective June 12,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 12, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of May 31, 2017 (82 FR
24843, May 31, 2017) and August 1,
2017 (82 FR 35630, August 1, 2017).
We must receive comments on this
AD by July 9, 2018.
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.
SUMMARY:
E:\FR\FM\23MYR1.SGM
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]]>Agencies
[Federal Register Volume 83, Number 100 (Wednesday, May 23, 2018)]
[Rules and Regulations]
[Pages 23778-23780]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-10921]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-3883; Product Identifier 2014-SW-029-AD; Amendment
39-19289; AD 2018-11-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus
Helicopters Model AS332L2 and EC225LP helicopters. This AD requires
installing a cut-out for the left-hand (LH) and right-hand (RH) rail
support junction profiles and inspecting splices, frame 5295, and
related equipment for a crack. This AD was prompted by reports of
cracks on frame 5295 and on splices installed to prevent those cracks.
The actions of this AD are intended to prevent an unsafe condition on
these products.
DATES: This AD is effective June 27, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of June 27, 2018.
ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, Inc., 2701 N Forum Drive, Grand Prairie, TX
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775;
or at https://www.airbushelicopters.com/techpub. You may review the
referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort
Worth, TX 76177. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3883.
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-
3883; or in person at Docket Operations 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
Docket Operations (phone: 800-647-5527) is U.S. Department of
Transportation, Docket Operations, 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 & Policy Section, Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email
[email protected].
SUPPLEMENTARY INFORMATION:
Discussion
On January 5, 2016, at 81 FR 191, 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 Model AS332L2 and Model
EC225LP helicopters with an extended aluminum splice installed on frame
5295. The NPRM proposed to require installing a cut-out for the LH and
RH rail support junction profiles and inspecting splices, frame 5295,
and related equipment for a crack. The proposed requirements were
intended to detect a crack in frame 5295, which could lead to
structural failure of the frame and loss of control of the helicopter.
The NPRM was prompted by AD No. 2014-0098-E, dated April 25, 2014,
issued by EASA, which is the Technical Agent for the Member States of
the European Union, to correct an unsafe condition for Model AS332L2
and EC225LP helicopters. EASA AD No. 2014-0098-E applies to helicopters
with a frame 5295 that have been reinforced by installing aluminium
splices on the RH and LH fuselage external skins. EASA advises of a
report of a crack that initiated on a splice in an area hidden by the
overlapping junction profile of the cabin sliding door rail support and
then spread to the frame.
EASA states that a crack in frame 5295, if not detected and
corrected, could lead to loss of structural integrity of the helicopter
frame and subsequent loss of control of the helicopter. To address this
condition, EASA issued AD No. 2014-0098-E to require repetitive
inspections of the splices for a crack, as well as cutting out the rail
support junction profiles to provide a convenient access to identify
cracks in a splice.
Since the NPRM was issued, the FAA's Aircraft Certification Service
has changed its organizational structure. The new structure replaces
product directorates with functional divisions. We have revised some of
the office titles and nomenclature throughout this Final rule to
reflect the new organizational changes. Additional information about
the new structure can be found in the Notice published on July 25, 2017
(82 FR 34564).
Comments
After our NPRM was published, we received comments from a commenter
who raised three issues.
Request
The commenter requested that we revise the applicability of the AD
to exempt helicopters that are ``post mod 07 26493 or RDAS 332-1284-
13.''
We partially agree. Modification (MOD) 0726493 or repair design
approval sheet (RDAS) 332-1284-13 specify installing a stainless steel
doubler to reduce stress in the splice and frame, thereby eliminating
the unsafe condition. We disagree with exempting ``post mod''
helicopters, however, as the stainless steel doubler could be removed
(subjecting the helicopter again to the unsafe condition) and the
helicopter would still be in a ``post mod'' configuration. Instead, we
have changed the applicability to exempt helicopters with the steel
splice kit installed that pertains to MOD 0726493.
The commenter requested that we revise the compliance time of the
AD to include the flow charts from the Airbus Helicopters service
information. The commenter states that this information would explain
the steps involved to operators to eliminate the unsafe condition. The
commenter also requested that we clarify the compliance times as
discussed in the preamble of the NPRM, because they appear different
from those in the service information and the EASA AD.
We disagree. The commenter is correct that the compliance times in
our AD are different, in some measure, to those in the EASA AD. But the
compliance times in the AD are clear as written. The requested change
is unnecessary.
[[Page 23779]]
The commenter requested that we withdraw the AD because all
helicopters in the U.S. fleet have either installed the cut-out or are
scheduled for installation of the cut-out.
We disagree. The FAA has determined that an unsafe condition
exists. AD action is required to mandate corrective action for this
unsafe condition. In addition, if additional helicopters are imported
into the United States, AD action is necessary to require that those
helicopters accomplish the corrective actions before operating in this
country.
FAA's Determination
These helicopters have been approved by the aviation authority of
France and are approved for operation in the United States. Pursuant to
our bilateral agreement with France, EASA, its technical
representative, has notified us of the unsafe condition described in
the EASA AD. We are issuing this AD because we evaluated all
information provided by EASA, 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 these
same type designs and that air safety and the public interest require
adopting the AD requirements as proposed with the change described
previously and with a revision to the estimated costs of complying with
this AD. These changes are consistent with the intent of the proposals
in the NPRM and will not increase the economic burden on any operator
nor increase the scope of the AD.
Differences Between This AD and the EASA AD
The EASA AD requires contacting Airbus Helicopters if there is a
crack in the affected parts. This AD makes no such requirement.
The EASA AD sets various timelines for repairing affected parts if
a crack exists. This AD requires repairing affected parts before
further flight if a crack exists.
Related Service Information Under 1 CFR Part 51
We reviewed Airbus Helicopters Alert Service Bulletin (ASB) No.
EC225-05A038 for Model EC225LP helicopters and ASB No. AS332-05.00.97
for Model AS332L2 helicopters. The ASBs, both Revision 0 and both dated
April 15, 2014, report cracks were found in the splice and frame 5295
on a Model AS332L2 helicopter during a major inspection. The splice had
been added in compliance with MOD 0726517. Had an optional rail support
cut-out been accomplished on the aircraft to allow for a visual check
of the splice for frame 5295, it would have revealed the crack in the
splice, prompting its repair and consequently limiting the damage to
frame 5295. As a result, the ASBs call for the rail support cut-out on
the RH and LH side of the frame as well as periodic visual inspections
of frame 5295 and related equipment.
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.
Other Related Service Information
We reviewed Eurocopter Helicopters (now Airbus Helicopters) Service
Bulletin (SB) No. 53-003, Revision 4, for Model EC225LP helicopters and
SB No. 53.01.52, Revision 5, for Model AS332L2 helicopters, both dated
July 23, 2010. The SBs specify procedures to reinforce frame 5295 by
installing a new titanium plate underneath the fitting and a new
widened aluminum splice below the upper corner of the door. We also
reviewed Airbus Helicopters SB No. 05-019, Revision 4, dated September
22, 2014, for Model EC225LP helicopters, which proposes that you cut
out the junction profiles to perform periodic visual inspections.
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 average $85 a work-hour. Based on
these estimates, we expect the following costs:
Installing the cut-outs on frame 5295 requires 40 work-hours for a
labor cost of $3,400. Parts cost $5,000 for total cost per helicopter
of $8,400 and $33,600 for the U.S. fleet.
Inspecting helicopter frame 5295 requires 2 work-hours for a labor
cost of $170 per helicopter. No parts are needed for a total U.S. fleet
cost of $680 per inspection cycle.
Repairing a splice requires 40 work-hours and a parts cost of
$5,000 for a total cost of $8,400 per helicopter.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on helicopters identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2018-11-01 Airbus Helicopters: Amendment 39-19289; Docket No. FAA-
2015-3883; Product Identifier 2014-SW-029-AD.
[[Page 23780]]
(a) Applicability
This AD applies to Model AS332L2 and Model EC225LP helicopters,
certificated in any category, with an extended aluminum splice
installed on frame 5295, except helicopters with steel splice kit
part number 332A08-2649-3072 installed.
Note 1 to paragraph (a) of this AD: Helicopters with
Modification (MOD) 0726517 have an extended aluminum splice
installed.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack on helicopter
frame 5295. This condition could result in structural failure of the
frame and subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective June 27, 2018.
(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) Before a splice reaches 1,700 hours time-in-service (TIS),
within 50 hours TIS, or before the helicopter reaches 11,950 hours
TIS, whichever occurs later, do the following:
(i) Install the rail support cut-out and identify the right-hand
and left-hand junction profile in accordance with the Accomplishment
Instructions, paragraph 3.B.2, of Airbus Helicopters Alert Service
Bulletin (ASB) No. EC225-05A038, Revision 0, dated April 15, 2014
(ASB EC225-05A038), or ASB No. AS332-05.00.97, Revision 0, dated
April 15, 2014 (ASB AS332-05.00.97), whichever is applicable to your
helicopter.
(ii) Inspect each splice for a crack in the area depicted as
Area Y in Figure 3 of ASB EC225-05A038 or ASB AS332-05.00.97,
whichever is applicable to your helicopter. If a crack exists,
repair or replace the splice before further flight.
(2) Thereafter at intervals not to exceed 110 hours TIS, inspect
each splice for a crack in the area depicted as Area Y in Figure 3
of ASB EC225-05A038 or ASB AS332-05.00.97. If a crack exists, repair
or replace the splice before further flight.
(f) Credit for Actions Previously Completed
Installing rail support cut-outs in accordance with MOD 0728090
or Airbus Helicopters Service Bulletin No. 05-019, Revision 4, dated
September 22, 2014, before the effective date of this AD is
considered acceptable for compliance with the corresponding actions
specified in paragraph (e)(1)(i) of this AD.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Section, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this AD. Send your proposal to:
Gary Roach, Aviation Safety Engineer, Regulations & Policy Section,
Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth,
TX 76177; telephone (817) 222-5110; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office, before operating any aircraft
complying with this AD through an AMOC.
(h) Additional Information
(1) Airbus Helicopters Service Bulletin (SB) No. 05-019,
Revision 4, dated September 22, 2014, and Eurocopter Helicopters
(now Airbus Helicopters) SB No. 53-003, Revision 4, and SB No.
53.01.52, Revision 5, both dated July 23, 2010, which are not
incorporated by reference, contain additional information about the
subject of this AD. 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 view the referenced service information at the FAA, Office of
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room
6N-321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2014-0098-E, dated April 25, 2014. You
may view the EASA AD on the internet at https://www.regulations.gov
in Docket No. FAA-2015-3883.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 5310, Fuselage
Main, Structure.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Helicopters Alert Service Bulletin No. EC225-05A038,
Revision 0, dated April 15, 2014.
(ii) Airbus Helicopters Alert Service Bulletin No. AS332-
05.00.97, Revision 0, dated April 15, 2014.
(3) For Airbus Helicopters 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 the FAA, Office of
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room
6N-321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on May 16, 2018.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2018-10921 Filed 5-22-18; 8:45 am]
BILLING CODE 4910-13-P
