Airworthiness Directives; Airbus Helicopters, 35604-35606 [2020-12530]
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35604
Federal Register / Vol. 85, No. 113 / Thursday, June 11, 2020 / Proposed Rules
Flight Test Analyst, Flight Test Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5151; email 9ASW-FTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, 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.
(m) Related Information
(1) The subject of this AD is addressed in
European Aviation Safety Agency (now
European Union Aviation Safety Agency)
(EASA) AD 2018–0124, dated June 5, 2018.
This EASA AD may be found in the AD
docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2020–0468.
(2) For service information identified in
this AD, contact Leonardo S.p.A. Helicopters,
Emanuele Bufano, Head of Airworthiness,
Viale G.Agusta 520, 21017 C.Costa di
Samarate (Va) Italy; telephone +39–0331–
225074; fax +39–0331–229046; or at https://
www.leonardocompany.com/en/home. 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.
Issued on June 5, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–12586 Filed 6–10–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0570; Product
Identifier 2019–SW–121–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
2018–26–02 for Airbus Helicopters
(previously Eurocopter France) Model
AS350B3, EC130B4, and EC130T2
helicopters. AD 2018–26–02 requires
inspecting the pilot’s and co-pilot’s
throttle twist for proper operation. Since
the FAA issued AD 2018–26–02, the
FAA received a public comment that
prompted additional review. This
proposed AD would retain the
requirements of AD 2018–26–02 and
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SUMMARY:
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add calendar time compliance times for
the required actions. The actions of this
proposed AD are intended to address an
unsafe condition on these products.
DATES: The FAA must receive comments
on this proposed AD by July 27, 2020.
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–2020–
0570; 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 (now European Union Aviation
Safety Agency) (EASA) AD, any
comments received, and other
information. The street address for
Docket Operations is listed above.
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.airbus.com/
helicopters/services/technicalsupport.html. You may the view this
referenced 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
The FAA invites you to participate in
this rulemaking by submitting written
comments, data, or views. The FAA also
invites comments relating to the
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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.
The FAA will file in the docket all
comments received, as well as a report
summarizing each substantive public
contact with FAA personnel concerning
this proposed rulemaking. Before acting
on this proposal, the FAA will consider
all comments received on or before the
closing date for comments. The FAA
will consider comments filed after the
comment period has closed if it is
possible to do so without incurring
expense or delay. The FAA may change
this proposal in light of the comments
received.
Discussion
The FAA issued AD 2018–26–02,
Amendment 39–19532 (83 FR 66093,
December 26, 2018) (‘‘AD 2018–26–02’’)
for Airbus Helicopters Model AS350B3
and EC130B4 helicopters with an
ARRIEL 2B1 engine with the twochannel Full Authority Digital Engine
Control (FADEC) and with new twist
grip modification (MOD) 073254 (for
Model AS350B3 helicopters) or MOD
073773 (for Model EC130B4 helicopters)
installed, and Model AS350B3 and
EC130T2 helicopters with an ARRIEL
2D engine installed. AD 2018–26–02
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 2018–26–02 was prompted by
EASA AD No. 2017–0059, dated April 6,
2017 (EASA AD 2017–0059), 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 advised that this
condition, if not detected and corrected,
could, in case of failure of the other
switch, prevent the pilot from switching
from ‘‘IDLE’’ to ‘‘FLIGHT’’ mode during
training of autorotation landing, making
aborting the autorotation impossible,
resulting in unintended touchdown.
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Federal Register / Vol. 85, No. 113 / Thursday, June 11, 2020 / Proposed Rules
Actions Since AD 2018–26–02 Was
Issued
Since the FAA issued AD 2018–26–
02, the FAA received comments from
one commenter. The commenter
requested the FAA clarify why the
compliance time for the repetitive
inspections required in AD 2018–26–02
is given in terms of hours time-inservice (TIS) without also requiring
calendar compliance times. The
commenter stated that a lot of operators
do not operate their aircraft 660 hours
TIS in a year and asked whether the
FAA is concerned with calendar time.
The FAA agrees. Since the unsafe
condition involves corrosion, which has
a direct relationship between calendar
time and airworthiness, it is necessary
to add calendar time compliance times
for all required actions including the
repetitive inspections in this proposed
AD.
FAA’s Determination
These helicopters have been approved
by EASA and are approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the
European Union, EASA has notified the
FAA about the unsafe condition
described in its AD. The FAA is
proposing this AD after evaluating all
known relevant information and
determining that an unsafe condition is
likely to exist or develop on other
helicopters of the same type design.
jbell on DSKJLSW7X2PROD with PROPOSALS
Related Service Information Under 1
CFR Part 51
The FAA reviewed one document that
co-publishes three Airbus Helicopters
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 2018–
26–02 and are retained for the
requirements of this AD. EASB No.
05.00.41 is not incorporated by
reference in AD 2018–26–02 and is not
incorporated by reference in this 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).
The FAA also reviewed one document
that co-publishes three Airbus
Helicopters EASB identification
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16:51 Jun 10, 2020
Jkt 250001
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 are incorporated by reference in
AD 2018–26–02 and are retained for the
requirements of this AD. EASB No.
05.00.52 is not incorporated by
reference in this 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 2018–
26–02 and would include, before the
next practice autorotation, within 100
hours TIS, or 6 months, whichever
occurs first, 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. This AD would also
include calendar time requirements for
the repetitive inspections to be
completed at intervals not to exceed 330
hours TIS or 6 months, whichever
occurs first, and at intervals not to
exceed 660 hours TIS or 12 months,
whichever occurs first, depending on
operating conditions.
35605
Costs of Compliance
The FAA estimates that this proposed
AD would affect 617 helicopters of U.S.
Registry. The FAA estimates that
operators may incur the following costs
in order to comply with this proposed
AD. Labor costs are estimated at $85 per
work-hour.
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 would take about 4
work-hours, for a total estimated cost of
$340 per helicopter and $209,780 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.
The FAA is 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.
Interim Action
Regulatory Findings
The FAA 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. Will not affect intrastate aviation in
Alaska, and
3. 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.
The FAA considers this proposed AD
to be an interim action. If final action is
later identified, the FAA might consider
further rulemaking then.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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, 100 hours TIS, or 6
months, 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 MOD
074263; this proposed AD does not as it
does not correct the unsafe condition.
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35606
Federal Register / Vol. 85, No. 113 / Thursday, June 11, 2020 / Proposed Rules
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)
2018–26–02, Amendment 39–19532 (83
FR 66093, December 26, 2018), and
adding the following new AD:
■
Airbus Helicopters: Docket No. FAA–2020–
0570; Product Identifier 2019–SW–121–
AD.
(a) Applicability
This AD applies to the following Airbus
Helicopters 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 2018–26–02,
Amendment 39–19532 (83 FR 66093,
December 26, 2018).
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(d) Comments Due Date
The FAA must receive comments by July
27, 2020.
(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,
within 100 hours time-in-service (TIS), or 6
months, whichever occurs first, inspect the
wiring, perform an insulation test, inspect
VerDate Sep<11>2014
16:51 Jun 10, 2020
Jkt 250001
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 or 6 months,
whichever occurs first.
(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 or 12 months,
whichever occurs first.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this
AD. Send your proposal to: George Schwab,
Aviation Safety Engineer, Safety Management
Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Parkway, Fort Worth, Texas
76177; telephone 817–222–5110; email 9ASW-FTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
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 (now
European Union 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 on June 4, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–12530 Filed 6–10–20; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF THE TREASURY
Internal Revenue Service
26 CFR Part 1
[REG–104591–18]
RIN 1545–BO67
Denial of Deduction for Certain Fines,
Penalties, and Other Amounts;
Information With Respect to Certain
Fines, Penalties, and Other Amounts;
Correction
Internal Revenue Service (IRS),
Treasury.
ACTION: Correction to a notice of
proposed rulemaking.
AGENCY:
This document contains a
correction to a notice of proposed
rulemaking (REG–104591–18) that was
published in the Federal Register on
May 13, 2020. The guidance on section
162(f) of the Internal Revenue Code
(Code), as amended by legislation
enacted in 2017, concerning the
deduction of certain fines, penalties,
and other amounts.
DATES: Written or electronic comments
and requests for a public hearing are
still being accepted and must be
received by July 13, 2020.
ADDRESSES: Send submissions to
Internal Revenue Service, CC:PA:
LPD:PR (REG–104591–18), Room 5205,
P.O. Box 7604, Ben Franklin Station,
Washington, DC 20044. Submission of
comments electronically is strongly
suggested, as the ability to respond to
mail may be delayed. It is recommended
that comments and requests for a public
hearing be submitted electronically via
the Federal eRulemaking Portal at
https://www.regulations.gov (IRS REG–
104591–18).
FOR FURTHER INFORMATION CONTACT:
Concerning the proposed regulations,
Sharon Y. Horn (202) 317–4426;
concerning the information reporting
requirement, Nancy L. Rose (202) 317–
5147; concerning submissions of
comments and requests for a public
hearing, Regina L. Johnson, (202) 317–
5177 (not toll-free numbers).
SUPPLEMENTARY INFORMATION:
SUMMARY:
Background
The proposed regulations that are the
subject of this correction are under
section 162(f) of the Internal Revenue
Code.
Need for Correction
As published, the notice of proposed
rulemaking (REG–104591–18) contains
errors that needs to be corrected.
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]]>Agencies
[Federal Register Volume 85, Number 113 (Thursday, June 11, 2020)]
[Proposed Rules]
[Pages 35604-35606]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-12530]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0570; Product Identifier 2019-SW-121-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2018-26-02 for Airbus Helicopters (previously Eurocopter France) Model
AS350B3, EC130B4, and EC130T2 helicopters. AD 2018-26-02 requires
inspecting the pilot's and co-pilot's throttle twist for proper
operation. Since the FAA issued AD 2018-26-02, the FAA received a
public comment that prompted additional review. This proposed AD would
retain the requirements of AD 2018-26-02 and add calendar time
compliance times for the required actions. The actions of this proposed
AD are intended to address an unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by July 27,
2020.
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-2020-
0570; 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 (now European
Union Aviation Safety Agency) (EASA) AD, any comments received, and
other information. The street address for Docket Operations is listed
above. 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.airbus.com/helicopters/services/technical-support.html. You may
the view this referenced 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
The FAA invites you to participate in this rulemaking by submitting
written comments, data, or views. The FAA also invites 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.
The FAA will file in the docket all comments received, as well as a
report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal,
the FAA will consider all comments received on or before the closing
date for comments. The FAA will consider comments filed after the
comment period has closed if it is possible to do so without incurring
expense or delay. The FAA may change this proposal in light of the
comments received.
Discussion
The FAA issued AD 2018-26-02, Amendment 39-19532 (83 FR 66093,
December 26, 2018) (``AD 2018-26-02'') for Airbus Helicopters Model
AS350B3 and EC130B4 helicopters with an ARRIEL 2B1 engine with the two-
channel Full Authority Digital Engine Control (FADEC) and with new
twist grip modification (MOD) 073254 (for Model AS350B3 helicopters) or
MOD 073773 (for Model EC130B4 helicopters) installed, and Model AS350B3
and EC130T2 helicopters with an ARRIEL 2D engine installed. AD 2018-26-
02 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 2018-26-02 was prompted by EASA AD No. 2017-0059, dated April 6,
2017 (EASA AD 2017-0059), 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 advised that this condition, if
not detected and corrected, could, in case of failure of the other
switch, prevent the pilot from switching from ``IDLE'' to ``FLIGHT''
mode during training of autorotation landing, making aborting the
autorotation impossible, resulting in unintended touchdown.
[[Page 35605]]
Actions Since AD 2018-26-02 Was Issued
Since the FAA issued AD 2018-26-02, the FAA received comments from
one commenter. The commenter requested the FAA clarify why the
compliance time for the repetitive inspections required in AD 2018-26-
02 is given in terms of hours time-in-service (TIS) without also
requiring calendar compliance times. The commenter stated that a lot of
operators do not operate their aircraft 660 hours TIS in a year and
asked whether the FAA is concerned with calendar time. The FAA agrees.
Since the unsafe condition involves corrosion, which has a direct
relationship between calendar time and airworthiness, it is necessary
to add calendar time compliance times for all required actions
including the repetitive inspections in this proposed AD.
FAA's Determination
These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA about the
unsafe condition described in its AD. The FAA is proposing this AD
after evaluating all known relevant information and determining that an
unsafe condition is likely to exist or develop on other helicopters of
the same type design.
Related Service Information Under 1 CFR Part 51
The FAA reviewed one document that co-publishes three Airbus
Helicopters 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 2018-26-02
and are retained for the requirements of this AD. EASB No. 05.00.41 is
not incorporated by reference in AD 2018-26-02 and is not incorporated
by reference in this 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).
The FAA also reviewed one document that co-publishes three Airbus
Helicopters 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 are
incorporated by reference in AD 2018-26-02 and are retained for the
requirements of this AD. EASB No. 05.00.52 is not incorporated by
reference in this 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
2018-26-02 and would include, before the next practice autorotation,
within 100 hours TIS, or 6 months, whichever occurs first, 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. This AD would also
include calendar time requirements for the repetitive inspections to be
completed at intervals not to exceed 330 hours TIS or 6 months,
whichever occurs first, and at intervals not to exceed 660 hours TIS or
12 months, whichever occurs first, depending on operating conditions.
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, 100 hours TIS, or 6 months, 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
MOD 074263; this proposed AD does not as it does not correct the unsafe
condition.
Interim Action
The FAA considers this proposed AD to be an interim action. If
final action is later identified, the FAA might consider further
rulemaking then.
Costs of Compliance
The FAA estimates that this proposed AD would affect 617
helicopters of U.S. Registry. The FAA estimates that operators may
incur the following costs in order to comply with this proposed AD.
Labor costs are estimated at $85 per work-hour.
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 would take about 4 work-
hours, for a total estimated cost of $340 per helicopter and $209,780
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.
The FAA is 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
The FAA 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. Will not affect intrastate aviation in Alaska, and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 35606]]
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)
2018-26-02, Amendment 39-19532 (83 FR 66093, December 26, 2018), and
adding the following new AD:
Airbus Helicopters: Docket No. FAA-2020-0570; Product Identifier
2019-SW-121-AD.
(a) Applicability
This AD applies to the following Airbus Helicopters 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 2018-26-02, Amendment 39-19532 (83 FR 66093,
December 26, 2018).
(d) Comments Due Date
The FAA must receive comments by July 27, 2020.
(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, within 100 hours
time-in-service (TIS), or 6 months, 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 or 6 months, whichever occurs first.
(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 or 12 months, whichever occurs
first.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Standards Branch, FAA, may approve
AMOCs for this AD. Send your proposal to: George Schwab, Aviation
Safety Engineer, Safety Management Section, Rotorcraft Standards
Branch, FAA, 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, the FAA suggests
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 (now European Union 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 on June 4, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-12530 Filed 6-10-20; 8:45 am]
BILLING CODE 4910-13-P
