Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France), 39007-39009 [2018-16494]
Download as PDF
Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules
(i) Additional Information
(1) Bell Alert Service Bulletin No. 429–15–
16, Revision B, dated June 15, 2016, which
is not incorporated by reference, contains
additional information about the subject of
this AD. For service information identified in
this AD, contact Bell Helicopter Textron
Canada Limited, 12,800 Rue de l’Avenir,
Mirabel, Quebec J7J1R4; telephone (450)
437–2862 or (800) 363–8023; fax (450) 433–
0272; or at https://www.bellcustomer.com/
files/. You may review a copy of the 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
Transport Canada AD No. CF–2015–16R2,
dated April 17, 2017. You may view the
Transport Canada AD on the internet at
https://www.regulations.gov in the AD Docket.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 6720 Tail Rotor Control System.
Issued in Fort Worth, Texas, on July 23,
2018.
Scott A. Horn,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2018–16637 Filed 8–7–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0669; Product
Identifier 2017–SW–041–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Previously Eurocopter
France)
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2016–25–
19 for Airbus Helicopters (previously
Eurocopter France) Model AS350B3 and
EC130B4 helicopters. AD 2016–25–19
requires inspecting the pilot’s and copilot’s throttle twist for proper
operation. This proposed AD would
retain the requirements of AD 2016–25–
19 and add certain model helicopters to
the applicability. The actions of this
proposed AD are intended to address
the unsafe condition on these
helicopters.
DATES: We must receive comments on
this proposed AD by October 9, 2018.
ADDRESSES: You may send comments by
any of the following methods:
amozie on DSK3GDR082PROD with PROPOSALS
SUMMARY:
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• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0669; 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 proposed
AD, the European Aviation Safety
Agency (EASA) AD, the economic
evaluation, any comments received and
other information. The street address for
Docket Operations (telephone 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
For service information identified in
this proposed rule, contact Airbus
Helicopters, 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax
(972) 641–3775; or at https://
www.helicopters.airbus.com/website/
en/ref/Technical-Support_73.html. You
may review service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy, Room 6N–321, Fort Worth, TX
76177.
FOR FURTHER INFORMATION CONTACT:
George Schwab, Aviation Safety
Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
george.schwab@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
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39007
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
We issued AD 2016–25–19,
Amendment 39–18745 (81 FR 95854,
December 29, 2016) (AD 2016–25–19),
for Airbus Helicopters Model AS350B3
and EC130B4 helicopters with the
ARRIEL 2B1 engine with the twochannel Full Authority Digital Engine
Control (FADEC) and with new twist
grip modification (MOD) 073254 (for the
Model AS350B3 helicopter) or MOD
073773 (for the Model EC130B4
helicopter). AD 2016–25–19 requires
repetitively inspecting the wiring,
performing an insulation test, inspecting
the pilot and copilot throttle twist grip
controls, and testing the pilot and
copilot throttle twist grip controls for
proper functioning. AD 2016–25–19 was
prompted by AD No. 2013–0191–E,
dated August 22, 2013 (EASA AD 2013–
0191–E), issued by EASA, which is the
Technical Agent for the Member States
of the European Union. EASA advised
that the switches in the engine ‘‘IDLE’’
or ‘‘FLIGHT’’ control system could be
affected by the corrosive effects of a saltladen atmosphere, which could lead to
engine power loss. EASA AD 2013–
0191–E required repetitive inspections
for corrosion, application of corrosion
protection on the switches, and testing
of the insulation and switches of the
engine idle and flight control system.
The actions required in AD 2016–25–19
are intended to prevent unintended
touchdown to the ground at a flight-idle
power setting during a practice
autorotation, damage to the helicopter,
and injury to occupants.
Actions Since AD 2016–25–19 Was
Issued
Since we issued AD 2016–25–19,
EASA issued AD No. 2017–0052, dated
March 24, 2017, which superseded
EASA AD No. 2013–0191–E, dated
August 22, 2013. EASA advised that
Airbus Helicopters had added
E:\FR\FM\08AUP1.SGM
08AUP1
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Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules
clarifications to the operational
procedure, introduced a modification to
apply water-tight protection to the
microswitch connectors, and extended
the applicability to helicopters with a
Turbomecca ARRIEL 2D engine
installed.
EASA subsequently issued AD No.
2017–0059, dated April 6, 2017, which
superseded EASA AD No. 2017–0052 to
correct the applicability by including
Model EC130T2 helicopters.
amozie on DSK3GDR082PROD with PROPOSALS
FAA’s Determination
These helicopters have been approved
by the aviation authority of France and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with France, EASA, its
technical representative, has notified us
of the unsafe condition described in its
AD. We are proposing this AD because
we evaluated all known relevant
information and determined that an
unsafe condition is likely to exist or
develop on other products of the same
type design.
Related Service Information Under
1 CFR Part 51
We reviewed one document that copublishes three Emergency Alert Service
Bulletin (EASB) identification numbers:
No. 05.00.61, Revision 3, dated June 15,
2015, for Model AS350B3 helicopters;
No. 05.00.41, Revision 2, dated June 15,
2015, for the non-FAA type certificated
Model AS550C3 helicopter; and No.
05A009, Revision 3, dated June 15,
2015, for Model EC130B4 helicopters.
EASB Nos. 05.00.61 and 05A009 are
incorporated by reference in AD 2016–
25–19 and will be retained for the
requirements of this proposed AD.
EASB No. 05.00.41 is not incorporated
by reference in AD 2016–25–19 and will
not be incorporated by reference in this
proposed AD. This service information
applies to helicopters with an Arriel
2B1 engine installed and describes
procedures for a functional check and
installation of protection for microcontacts (microswitches) 53Ka, 53Kb,
and 65K (IDLE/FLIGHT mode).
We also reviewed one document that
co-publishes three EASB identification
numbers: No. 05.00.77, Revision 1,
dated June 15, 2015, for Model AS350B3
helicopters; No. 05.00.52, Revision 1,
dated June 15, 2015, for the non-FAA
type certificated Model AS550C3
helicopter; and No. 05A014, Revision 1,
dated June 15, 2015, for Model EC130T2
helicopters. EASB Nos. 05.00.77 and
05A014 will be incorporated by
reference in this proposed AD. EASB
No. 05.00.52 will not be incorporated by
reference in this proposed AD. This
service information applies to
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18:59 Aug 07, 2018
Jkt 244001
helicopters with an Arriel 2D engine
installed and describes procedures for a
check of the protection for microcontacts (microswitches) 53Ka, 53Kb,
and 65K (IDLE/FLIGHT mode).
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Proposed AD Requirements
This proposed AD would retain the
inspection requirements of AD 2016–
25–19 but would add Model AS350B3
helicopters with an Arriel 2D engine
installed and Model EC130T2
helicopters.
Differences Between This Proposed AD
and the EASA AD
The EASA AD requires the initial
inspections within 10 flight hours or 7
days; this proposed AD requires
compliance before the next autorotation
training flight or before 100 hours timein-service, whichever occurs earlier, as
the unsafe condition only occurs when
transitioning the throttle in flight from
flight to idle and back to flight, such as
during a practice autorotation.
Additionally, the EASA AD requires
installing Airbus Helicopters
modification 074263; this proposed AD
does not as it does not correct the unsafe
condition.
Interim Action
We consider this proposed AD to be
an interim action. If final action is later
identified, we might consider further
rulemaking then.
Costs of Compliance
We estimate that this proposed AD
would affect 692 helicopters of U.S.
Registry.
We estimate that operators will incur
the following costs in order to comply
with this proposed AD. At an average
labor rate of $85 per work hour, it
would take about 4 work hours for the
inspections and any necessary
maintenance, for a total cost of $340 per
helicopter and $235,280 for the U.S.
fleet per inspection cycle.
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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General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed, I certify
this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska to the extent that it justifies
making a regulatory distinction; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared an economic evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2016–25–19, Amendment 39–18745 (81
FR 95854, December 29, 2016), and
adding the following new AD:
■
E:\FR\FM\08AUP1.SGM
08AUP1
Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules
Airbus Helicopters (Previously Eurocopter
France): Docket No. FAA–2018–0669;
Product Identifier 2017–SW–041–AD.
(a) Applicability
This AD applies to the following
helicopters, certificated in any category:
(1) Model AS350B3 helicopters with an
ARRIEL 2B1 engine with the two-channel
Full Authority Digital Engine Control
(FADEC) and with new twist grip
modification (MOD) 073254 or with an
ARRIEL 2D engine installed;
(2) Model EC130B4 helicopters with an
ARRIEL 2B1 engine with the two-channel
FADEC and with new twist grip MOD 073773
installed; and
(3) Model EC130T2 helicopters with an
ARRIEL 2D engine installed.
(b) Unsafe Condition
This AD defines the unsafe condition as
failure of one of the two contactors, 53Ka or
53Kb, which can prevent switching from
‘‘IDLE’’ mode to ‘‘FLIGHT’’ mode during
autorotation training making it impossible to
recover from a practice autorotation and
compelling the pilot to continue the
autorotation to the ground. This condition
could result in unintended touchdown to the
ground at a flight-idle power setting during
a practice autorotation, damage to the
helicopter, and injury to occupants.
(c) Affected ADs
This AD replaces AD 2016–25–19,
Amendment 39–18745 (81 FR 95854,
December 29, 2016).
(d) Comments Due Date
We must receive comments by October 9,
2018.
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(e) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(f) Required Actions
(1) Before the next practice autorotation or
within 100 hours time-in-service (TIS),
whichever occurs first, inspect the wiring,
perform an insulation test, inspect the pilot
and copilot throttle twist grip controls, and
test the pilot and copilot throttle twist grip
controls for proper functioning by following
the Accomplishment Instructions, paragraph
3.B.1 through 3.B.6, of Airbus Helicopters
Emergency Alert Service Bulletin (EASB) No.
05.00.61, Revision 3, dated June 15, 2015, for
Model AS350B3 helicopters with an ARRIEL
2B1 engine; EASB No. 05.00.77, Revision 1,
dated June 15, 2015, for Model AS350B3
helicopters with an ARRIEL 2D engine; EASB
No. 05A009, Revision 3, dated June 15, 2015,
for Model EC130B4 helicopters; or EASB No.
05A014, Revision 1, dated June 15, 2015, for
Model EC130T2 helicopters, as appropriate
for your model helicopter.
(2) Repeat the inspections in paragraph
(f)(1) of this AD at intervals not to exceed the
following compliance times. For purposes of
this AD, salt laden conditions exist when a
helicopter performs a flight from a takeoff
and landing area, heliport, or airport less
than 0.5 statute mile from salt water or
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19:48 Aug 07, 2018
Jkt 244001
performs a flight within 0.5 statute mile from
salt water below an altitude of 1,000 ft. above
ground or sea level.
(i) For helicopters that have operated in
salt laden conditions since the previous
inspection required by this AD, at intervals
not to exceed 330 hours TIS.
(ii) For helicopters that have not operated
in salt laden conditions since the previous
inspection required by this AD, at intervals
not to exceed 660 hours TIS.
(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: George Schwab, Aviation Safety
Engineer, Safety Management Group,
Rotorcraft Directorate, 10101 Hillwood
Parkway, Fort Worth, Texas 76177; telephone
(817) 222–5110; email 9-ASW-FTW-AMOCRequests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(h) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2017–0059, dated April 6, 2017. You may
view the EASA AD on the internet at https://
www.regulations.gov in the AD Docket.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 7697 Engine Control System Wiring.
Issued in Fort Worth, Texas, on July 11,
2018.
Scott A. Horn,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2018–16494 Filed 8–7–18; 8:45 am]
BILLING CODE 4910–13–P
ENVIRONMENTAL PROTECTION
AGENCY
40 CFR Part 52
[EPA–R03–OAR–2018–0153; FRL–9981–
76—Region 3]
Approval and Promulgation of Air
Quality Implementation Plans;
Maryland; Amendment to Control of
Emissions of Volatile Organic
Compounds From Consumer Products
Environmental Protection
Agency (EPA).
ACTION: Proposed rule.
AGENCY:
The Environmental Protection
Agency (EPA) is proposing to approve a
state implementation plan (SIP) revision
SUMMARY:
PO 00000
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39009
submitted by the State of Maryland.
This revision pertains to Code of
Maryland Regulations (COMAR)
26.11.32—Control of Emissions of
Volatile Organic Compounds (VOCs)
from Consumer Products. This action is
being taken under the Clean Air Act
(CAA).
DATES: Written comments must be
received on or before September 7,
2018.
ADDRESSES: Submit your comments,
identified by Docket ID No. EPA–R03–
OAR–2018–0153 at https://
www.regulations.gov, or via email to
Susan Spielberger, Associate Director,
Office of Air Planning and Programs,
Spielberger.Susan@epa.gov. For
comments submitted at Regulations.gov,
follow the online instructions for
submitting comments. Once submitted,
comments cannot be edited or removed
from Regulations.gov. For either manner
of submission, EPA may publish any
comment received to its public docket.
Do not submit electronically any
information you consider to be
confidential business information (CBI)
or other information whose disclosure is
restricted by statute. Multimedia
submissions (audio, video, etc.) must be
accompanied by a written comment.
The written comment is considered the
official comment and should include
discussion of all points you wish to
make. EPA will generally not consider
comments or comment contents located
outside of the primary submission (i.e.
on the web, cloud, or other file sharing
system). For additional submission
methods, please contact the person
identified in the FOR FURTHER
INFORMATION CONTACT section. For the
full EPA public comment policy,
information about CBI or multimedia
submissions, and general guidance on
making effective comments, please visit
https://www2.epa.gov/dockets/
commenting-epa-dockets.
FOR FURTHER INFORMATION CONTACT:
Gregory Becoat (215) 814–2036, or by
email at becoat.gregory@epa.gov.
SUPPLEMENTARY INFORMATION: On
November 16, 2017, the Maryland
Department of Environment (MDE)
submitted a revision to its SIP for
COMAR 26.11.32—Control of Emissions
of Volatile Organic Compounds from
Consumer Products. The amendment is
part of Maryland’s strategy to achieve
and maintain the 8-hour ozone national
ambient air quality standards (NAAQS)
throughout the State.
I. Background
EPA has designated certain areas
within Maryland as nonattainment for
the 2008 ozone NAAQS. See 40 CFR
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08AUP1
Agencies
[Federal Register Volume 83, Number 153 (Wednesday, August 8, 2018)]
[Proposed Rules]
[Pages 39007-39009]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16494]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0669; Product Identifier 2017-SW-041-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters (Previously
Eurocopter France)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2016-25-
19 for Airbus Helicopters (previously Eurocopter France) Model AS350B3
and EC130B4 helicopters. AD 2016-25-19 requires inspecting the pilot's
and co-pilot's throttle twist for proper operation. This proposed AD
would retain the requirements of AD 2016-25-19 and add certain model
helicopters to the applicability. The actions of this proposed AD are
intended to address the unsafe condition on these helicopters.
DATES: We must receive comments on this proposed AD by October 9, 2018.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0669; 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 proposed AD, the European Aviation Safety Agency (EASA) AD, the
economic evaluation, any comments received and other information. The
street address for Docket Operations (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
For service information identified in this proposed rule, contact
Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at
https://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may review service information at the FAA, Office
of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room
6N-321, Fort Worth, TX 76177.
FOR FURTHER INFORMATION CONTACT: George Schwab, Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110;
email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this rulemaking by submitting
written comments, data, or views. We also invite comments relating to
the economic, environmental, energy, or federalism impacts that might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. To
ensure the docket does not contain duplicate comments, commenters
should send only one copy of written comments, or if comments are filed
electronically, commenters should submit only one time.
We will file in the docket all comments that we receive, as well as
a report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
Discussion
We issued AD 2016-25-19, Amendment 39-18745 (81 FR 95854, December
29, 2016) (AD 2016-25-19), for Airbus Helicopters Model AS350B3 and
EC130B4 helicopters with the ARRIEL 2B1 engine with the two-channel
Full Authority Digital Engine Control (FADEC) and with new twist grip
modification (MOD) 073254 (for the Model AS350B3 helicopter) or MOD
073773 (for the Model EC130B4 helicopter). AD 2016-25-19 requires
repetitively inspecting the wiring, performing an insulation test,
inspecting the pilot and copilot throttle twist grip controls, and
testing the pilot and copilot throttle twist grip controls for proper
functioning. AD 2016-25-19 was prompted by AD No. 2013-0191-E, dated
August 22, 2013 (EASA AD 2013-0191-E), issued by EASA, which is the
Technical Agent for the Member States of the European Union. EASA
advised that the switches in the engine ``IDLE'' or ``FLIGHT'' control
system could be affected by the corrosive effects of a salt-laden
atmosphere, which could lead to engine power loss. EASA AD 2013-0191-E
required repetitive inspections for corrosion, application of corrosion
protection on the switches, and testing of the insulation and switches
of the engine idle and flight control system. The actions required in
AD 2016-25-19 are intended to prevent unintended touchdown to the
ground at a flight-idle power setting during a practice autorotation,
damage to the helicopter, and injury to occupants.
Actions Since AD 2016-25-19 Was Issued
Since we issued AD 2016-25-19, EASA issued AD No. 2017-0052, dated
March 24, 2017, which superseded EASA AD No. 2013-0191-E, dated August
22, 2013. EASA advised that Airbus Helicopters had added
[[Page 39008]]
clarifications to the operational procedure, introduced a modification
to apply water-tight protection to the microswitch connectors, and
extended the applicability to helicopters with a Turbomecca ARRIEL 2D
engine installed.
EASA subsequently issued AD No. 2017-0059, dated April 6, 2017,
which superseded EASA AD No. 2017-0052 to correct the applicability by
including Model EC130T2 helicopters.
FAA's Determination
These helicopters have been approved by the aviation authority of
France and are approved for operation in the United States. Pursuant to
our bilateral agreement with France, EASA, its technical
representative, has notified us of the unsafe condition described in
its AD. We are proposing this AD because we evaluated all known
relevant information and determined that an unsafe condition is likely
to exist or develop on other products of the same type design.
Related Service Information Under 1 CFR Part 51
We reviewed one document that co-publishes three Emergency Alert
Service Bulletin (EASB) identification numbers: No. 05.00.61, Revision
3, dated June 15, 2015, for Model AS350B3 helicopters; No. 05.00.41,
Revision 2, dated June 15, 2015, for the non-FAA type certificated
Model AS550C3 helicopter; and No. 05A009, Revision 3, dated June 15,
2015, for Model EC130B4 helicopters. EASB Nos. 05.00.61 and 05A009 are
incorporated by reference in AD 2016-25-19 and will be retained for the
requirements of this proposed AD. EASB No. 05.00.41 is not incorporated
by reference in AD 2016-25-19 and will not be incorporated by reference
in this proposed AD. This service information applies to helicopters
with an Arriel 2B1 engine installed and describes procedures for a
functional check and installation of protection for micro-contacts
(microswitches) 53Ka, 53Kb, and 65K (IDLE/FLIGHT mode).
We also reviewed one document that co-publishes three EASB
identification numbers: No. 05.00.77, Revision 1, dated June 15, 2015,
for Model AS350B3 helicopters; No. 05.00.52, Revision 1, dated June 15,
2015, for the non-FAA type certificated Model AS550C3 helicopter; and
No. 05A014, Revision 1, dated June 15, 2015, for Model EC130T2
helicopters. EASB Nos. 05.00.77 and 05A014 will be incorporated by
reference in this proposed AD. EASB No. 05.00.52 will not be
incorporated by reference in this proposed AD. This service information
applies to helicopters with an Arriel 2D engine installed and describes
procedures for a check of the protection for micro-contacts
(microswitches) 53Ka, 53Kb, and 65K (IDLE/FLIGHT mode).
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Proposed AD Requirements
This proposed AD would retain the inspection requirements of AD
2016-25-19 but would add Model AS350B3 helicopters with an Arriel 2D
engine installed and Model EC130T2 helicopters.
Differences Between This Proposed AD and the EASA AD
The EASA AD requires the initial inspections within 10 flight hours
or 7 days; this proposed AD requires compliance before the next
autorotation training flight or before 100 hours time-in-service,
whichever occurs earlier, as the unsafe condition only occurs when
transitioning the throttle in flight from flight to idle and back to
flight, such as during a practice autorotation.
Additionally, the EASA AD requires installing Airbus Helicopters
modification 074263; this proposed AD does not as it does not correct
the unsafe condition.
Interim Action
We consider this proposed AD to be an interim action. If final
action is later identified, we might consider further rulemaking then.
Costs of Compliance
We estimate that this proposed AD would affect 692 helicopters of
U.S. Registry.
We estimate that operators will incur the following costs in order
to comply with this proposed AD. At an average labor rate of $85 per
work hour, it would take about 4 work hours for the inspections and any
necessary maintenance, for a total cost of $340 per helicopter and
$235,280 for the U.S. fleet per inspection cycle.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed, I certify this proposed regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska to the extent that
it justifies making a regulatory distinction; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2016-25-19, Amendment 39-18745 (81 FR 95854, December 29, 2016), and
adding the following new AD:
[[Page 39009]]
Airbus Helicopters (Previously Eurocopter France): Docket No. FAA-
2018-0669; Product Identifier 2017-SW-041-AD.
(a) Applicability
This AD applies to the following helicopters, certificated in
any category:
(1) Model AS350B3 helicopters with an ARRIEL 2B1 engine with the
two-channel Full Authority Digital Engine Control (FADEC) and with
new twist grip modification (MOD) 073254 or with an ARRIEL 2D engine
installed;
(2) Model EC130B4 helicopters with an ARRIEL 2B1 engine with the
two-channel FADEC and with new twist grip MOD 073773 installed; and
(3) Model EC130T2 helicopters with an ARRIEL 2D engine
installed.
(b) Unsafe Condition
This AD defines the unsafe condition as failure of one of the
two contactors, 53Ka or 53Kb, which can prevent switching from
``IDLE'' mode to ``FLIGHT'' mode during autorotation training making
it impossible to recover from a practice autorotation and compelling
the pilot to continue the autorotation to the ground. This condition
could result in unintended touchdown to the ground at a flight-idle
power setting during a practice autorotation, damage to the
helicopter, and injury to occupants.
(c) Affected ADs
This AD replaces AD 2016-25-19, Amendment 39-18745 (81 FR 95854,
December 29, 2016).
(d) Comments Due Date
We must receive comments by October 9, 2018.
(e) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(f) Required Actions
(1) Before the next practice autorotation or within 100 hours
time-in-service (TIS), whichever occurs first, inspect the wiring,
perform an insulation test, inspect the pilot and copilot throttle
twist grip controls, and test the pilot and copilot throttle twist
grip controls for proper functioning by following the Accomplishment
Instructions, paragraph 3.B.1 through 3.B.6, of Airbus Helicopters
Emergency Alert Service Bulletin (EASB) No. 05.00.61, Revision 3,
dated June 15, 2015, for Model AS350B3 helicopters with an ARRIEL
2B1 engine; EASB No. 05.00.77, Revision 1, dated June 15, 2015, for
Model AS350B3 helicopters with an ARRIEL 2D engine; EASB No. 05A009,
Revision 3, dated June 15, 2015, for Model EC130B4 helicopters; or
EASB No. 05A014, Revision 1, dated June 15, 2015, for Model EC130T2
helicopters, as appropriate for your model helicopter.
(2) Repeat the inspections in paragraph (f)(1) of this AD at
intervals not to exceed the following compliance times. For purposes
of this AD, salt laden conditions exist when a helicopter performs a
flight from a takeoff and landing area, heliport, or airport less
than 0.5 statute mile from salt water or performs a flight within
0.5 statute mile from salt water below an altitude of 1,000 ft.
above ground or sea level.
(i) For helicopters that have operated in salt laden conditions
since the previous inspection required by this AD, at intervals not
to exceed 330 hours TIS.
(ii) For helicopters that have not operated in salt laden
conditions since the previous inspection required by this AD, at
intervals not to exceed 660 hours TIS.
(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:
George Schwab, Aviation Safety Engineer, Safety Management Group,
Rotorcraft Directorate, 10101 Hillwood Parkway, Fort Worth, Texas
76177; telephone (817) 222-5110; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office before operating any aircraft
complying with this AD through an AMOC.
(h) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (EASA) AD No. 2017-0059, dated April 6, 2017. You may view
the EASA AD on the internet at https://www.regulations.gov in the AD
Docket.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 7697 Engine
Control System Wiring.
Issued in Fort Worth, Texas, on July 11, 2018.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2018-16494 Filed 8-7-18; 8:45 am]
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