Airworthiness Directives; Airbus Helicopters, 81376-81378 [2020-27659]
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<![CDATA[
81376
Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations
Integrated
modified
energy factor
(cu.ft./kWh/
cycle)
Product class
(D) Front-loading, Standard (1.6 ft3 or greater capacity) ........................................................................................
khammond on DSKJM1Z7X2PROD with RULES
(ii) Top-loading, standard clothes
washers with an average cycle time of
less than 30 minutes and front-loading,
standard clothes washers with an
average cycle time of less than 45
minutes are not currently subject to
energy or water conservation standards.
(h) * * *
(3)(i) Except as provided in paragraph
(h)(3)(ii) of this section, clothes dryers
manufactured on or after January 1,
2015, shall have a combined energy
factor no less than:
The FAA is superseding
Airworthiness Directive (AD) 2014–12–
12, which applied to certain Airbus
Helicopters Model EC120B and
EC130B4 helicopters. AD 2014–12–12
required inspecting and, if necessary,
replacing parts of the sliding door star
support attachment assembly. This AD
requires modifying the sliding door star
support stringer as specified in a
European Union Aviation Safety Agency
(EASA) AD, which is incorporated by
reference (IBR). This AD was prompted
by several incidents involving
Combined
helicopter left-hand side doors (both
Product class
energy factor
swinging and sliding) that revealed
(lbs/kWh)
weaknesses in the locking mechanism.
The FAA is issuing this AD to address
(A) Vented Electric, Standard
the unsafe condition on these products.
(4.4 ft3 or greater capacity) .....................................
3.73 DATES: This AD is effective January 21,
(B) Vented Electric, Compact
2021.
(120V) (less than 4.4 ft3
The Director of the Federal Register
capacity) ............................
3.61
approved the incorporation by reference
(C) Vented Electric, Compact
of a certain publication listed in this AD
(240V) (less than 4.4 ft3
capacity) ............................
3.27 as of January 21, 2021.
(D) Vented Gas ....................
3.30
ADDRESSES: For material incorporated
(E) Ventless Electric, Comby reference in this AD, contact the
pact (240V) (less than 4.4
ft3 capacity) .......................
2.55 EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221
(F) Ventless Electric, Combination Washer-Dryer ......
2.08 8999 000; email ADs@easa.europa.eu;
internet www.easa.europa.eu. You may
find this material on the EASA website
(ii) Vented, electric standard clothes
at https://ad.easa.europa.eu. You may
dryers and vented gas clothes dryers
view this material at the FAA, Office of
with a cycle time of less than 30
the Regional Counsel, Southwest
minutes are not currently subject to
Region, 10101 Hillwood Pkwy., Room
energy conservation standards.
6N–321, Fort Worth, TX 76177. For
*
*
*
*
*
information on the availability of this
[FR Doc. 2020–26976 Filed 12–15–20; 8:45 am]
material at the FAA, call 817–222–5110.
BILLING CODE 6450–01–P
It is also available in the AD docket on
the internet at https://
www.regulations.gov by searching for
DEPARTMENT OF TRANSPORTATION and locating Docket No. FAA–2016–
3343.
Federal Aviation Administration
Examining the AD Docket
14 CFR Part 39
You may examine the AD docket on
the internet at https://
[Docket No. FAA–2016–3343; Product
www.regulations.gov by searching for
Identifier 2015–SW–078–AD; Amendment
and locating Docket No. FAA–2016–
39–21353; AD 2020–25–11]
3343; or in person at Docket Operations
RIN 2120–AA64
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Airworthiness Directives; Airbus
The AD docket contains this final rule,
Helicopters
any comments received, and other
information. The address for Docket
AGENCY: Federal Aviation
Operations is U.S. Department of
Administration (FAA), DOT.
Transportation, Docket Operations, M–
ACTION: Final rule.
30, West Building Ground Floor, Room
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16:21 Dec 15, 2020
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SUMMARY:
PO 00000
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1.84
Integrated
water
factor
(gal/cycle/
cu.ft.)
4.7
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Kathleen Arrigotti, Aerospace Engineer,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South
216th St., Des Moines, WA; telephone
206–231–3218; email
kathleen.arrigotti@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2020–0095, dated April 29, 2020 (EASA
AD 2020–0095), to correct an unsafe
condition for certain Airbus Helicopters
Model EC120B and EC130B4
helicopters.
The FAA issued a supplemental
notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an
AD to supersede AD 2014–12–12,
Amendment 39–17873 (79 FR 36638,
June 30, 2014) (AD 2014–12–12). AD
2014–12–12 applied to certain Airbus
Helicopters Model EC120B and
EC130B4 helicopters. The SNPRM
published in the Federal Register on
September 22, 2020 (85 FR 59454). The
FAA preceded the SNPRM with a notice
of proposed rulemaking (NPRM) that
published in the Federal Register on
October 26, 2016 (81 FR 74362). The
NPRM was prompted by the
determination to expand the
applicability to all serial-numbered
EC120B helicopters with affected
sliding doors installed and require
compliance with revised service
information. The NPRM proposed to
require inspecting each upper and lower
locking pin control rod end fitting and
replacing it if necessary, cleaning and
dye-penetrant inspecting the star
support pin for cracking and replacing
it if necessary, and reinforcing the
sliding door star support stringer. The
SNPRM proposed to require modifying
the door locking/unlocking mechanism,
as specified in EASA AD 2020–0095.
The FAA is proposing this AD to
address failure of the sliding door star
support, which could inhibit the
operation of the sliding door from the
inside, delaying the evacuation of
passengers during an emergency. See
EASA AD 2020–0095 for additional
background information.
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Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The FAA received no
comments on the SNPRM or on the
determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data
and determined that air safety and the
public interest require adopting this
final rule as proposed, except for minor
editorial changes and an exception that
does not affect helicopters of U.S.
registry. The FAA has determined that
these minor changes:
• Are consistent with the intent that
was proposed in the SNPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in-the SNPRM.
Related Service Information Under 1
CFR Part 51
The FAA reviewed EASA AD 2020–
0095, which describes improved
procedures for modifying the door
locking/unlocking mechanism (e.g.
modifying the sliding door star support
by installing a reinforcing bracket and
replacing rod ends).
This material 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.
Differences Between This AD and the
EASA AD
EASA AD 2020–0095 specifies to do
the modification within 24 months. This
AD requires the modification be done
within 460 hours time-in-service (TIS),
based on an average of 230 hours TIS
per year. The FAA has determined this
compliance time represents the
maximum interval of time allowable for
the affected helicopters to continue to
safely operate before the modification is
done. While EASA AD 2020–0095
allows credit for Airbus Helicopters
Alert Service Bulletin No. EC120–
52A018, Revision 0, dated November
13, 2015 (ASB EC120–52A018 at
original issue), this AD does not because
the applicable helicopter is not U.S.registered.
khammond on DSKJM1Z7X2PROD with RULES
Costs of Compliance
The FAA estimates that this AD
would affect 261 helicopters of U.S.
Registry. Labor rates are estimated at
$85 per work-hour. Based on these
numbers, the FAA estimates that
operators may incur the following costs
in order to comply with this proposed
AD.
VerDate Sep<11>2014
16:21 Dec 15, 2020
Jkt 253001
Modifying the door locking/unlocking
mechanism takes about 20 work-hours
and parts cost about $642 for an
estimated cost of $2,342 per helicopter
and $611,262 for the U.S. fleet.
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
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) 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.
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:
■
PO 00000
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Fmt 4700
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81377
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
(AD) 2014–12–12, Amendment 39–
17873 (79 FR 36638, June 30, 2014); and
■ b. Adding the following new AD:
■
■
2020–25–11 Airbus Helicopters:
Amendment 39–21353; Docket No.
FAA–2016–3343; Product Identifier
2015–SW–078–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective January 21, 2021.
(b) Affected ADs
This AD replaces AD 2014–12–12,
Amendment 39–17873 (79 FR 36638, June
30, 2014).
(c) Applicability
This AD applies to Airbus Helicopters
Model EC120B and EC130B4 helicopters,
certificated in any category, as identified in
European Union Aviation Safety Agency
(EASA) AD 2020–0095, dated April 29, 2020
(EASA AD 2020–0095).
(d) Subject
Joint Aircraft System Component (JASC)
Code 5200, Doors.
(e) Reason
This AD was prompted by reports of
passengers not being able to open a
helicopter’s left-hand door after landing. The
FAA is issuing this AD to address failure of
the sliding door star support, which could
inhibit the operation of the sliding door from
the inside, delaying the evacuation of
passengers during an emergency.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, EASA AD 2020–0095.
(h) Exceptions to EASA AD 2020–0095
(1) Where EASA AD 2020–0095 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) Where paragraph (1) of EASA AD 2020–
0095 specifies to complete the actions within
24 months after its effective date, this AD
requires completion within 460 hours timein-service after the effective date of this AD.
(3) The ‘‘Remarks’’ section of EASA AD
2020–0095 does not apply to this AD.
(4) Although the service information
referenced in EASA AD 2020–0095 specifies
to discard certain parts, this AD does not
include that requirement.
(5) Where EASA AD 2020–0095 allows
credit for Airbus Helicopters Alert Service
Bulletin No. EC120–52A018, Revision 0,
dated November 13, 2015 (ASB EC120–
52A018 at original issue), this AD does not.
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81378
Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations
(i) Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(1) The Manager, Strategic Policy
Rotorcraft Section, FAA, may approve
AMOCs for this AD. Send your proposal to:
Manager, Strategic Policy Rotorcraft Section,
FAA, 10101 Hillwood Pkwy, Fort Worth, TX
76177; telephone 817–222–5110; email 9/
ASW/FTW/AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
Federal Aviation Administration
(j) Related Information
For more information about this AD,
contact Kathleen Arrigotti, Aerospace
Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA; telephone
206–231–3218; email kathleen.arrigotti@
faa.gov.
(k) Material Incorporated by Reference
khammond on DSKJM1Z7X2PROD with RULES
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2020–0095, dated April 29, 2020.
(ii) [Reserved]
(3) For EASA AD 2020–0095, contact the
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu.
(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. This
material may be found in the AD docket on
the internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2016–3343.
(5) You may view this material that is
incorporated by reference at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, email fedreg.legal@
nara.gov, or go to https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
Issued on December 3, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2020–27659 Filed 12–15–20; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
16:21 Dec 15, 2020
Jkt 253001
14 CFR Part 39
[Docket No. FAA–2020–0592; Project
Identifier AD–2020–00251–E; Amendment
39–21352; AD 2020–25–10]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
General Electric Company (GE) GEnx1B64/P2, GEnx-1B67/P2, GEnx-1B70/
75/P2, GEnx-1B70/P2, GEnx-1B70C/P2,
GEnx-1B74/75/P2, GEnx-1B76/P2,
GEnx-1B76A/P2, and GEnx-2B67/P
model turbofan engines with a certain
high-pressure turbine (HPT) rotor stage
2 disk installed. This AD was prompted
by a report of the potential for
undetected subsurface anomalies
formed during the manufacturing
process that could result in uncontained
failure of the HPT rotor stage 2 disk.
This AD requires an immersion
ultrasonic inspection (USI) of the HPT
rotor stage 2 disk and, depending on the
results of the inspection, replacement of
the HPT rotor stage 2 disk with a part
eligible for installation. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective January 21,
2021.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 21, 2021.
ADDRESSES: For service information
identified in this final rule, contact
General Electric Company, GE Aviation,
Room 285, 1 Neumann Way, Cincinnati,
OH 45215; phone: (513) 552–3272;
email: aviation.fleetsupport@ge.com.
You may view this service information
at the FAA, Airworthiness Products
Section, Operational Safety Branch,
1200 District Avenue, Burlington, MA
01803. For information on the
availability of this material at the FAA,
call (781) 238–7759. It is also available
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0592.
SUMMARY:
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0592; or in person at Docket
PO 00000
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Fmt 4700
Sfmt 4700
Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
final rule, any comments received, and
other information. The address for
Docket Operations 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:
Mehdi Lamnyi, Aviation Safety
Engineer, ECO Branch, FAA, 1200
District Avenue, Burlington, MA 01803;
phone: (781) 238–7743; fax: (781) 238–
7199; email: Mehdi.Lamnyi@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all GE GEnx-1B64/P2, GEnx1B67/P2, GEnx-1B70/75/P2, GEnx1B70/P2, GEnx-1B70C/P2, GEnx-1B74/
75/P2, GEnx-1B76/P2, GEnx-1B76A/P2,
and GEnx-2B67/P model turbofan
engines with a certain HPT rotor stage
2 disk installed. The NPRM published
in the Federal Register on June 12, 2020
(85 FR 35816). The NPRM was
prompted by a report of the potential for
undetected subsurface anomalies
formed during the manufacturing
process that could result in uncontained
failure of the HPT rotor stage 2 disk. In
the NPRM, the FAA proposed to require
an immersion USI of the HPT rotor stage
2 disk and, depending on the results of
the inspection, replacement of the HPT
rotor stage 2 disk with a part eligible for
installation. The FAA is issuing this AD
to address the unsafe condition on these
products.
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from six
commenters. The commenters were Air
Line Pilots Association, International
(ALPA); The Boeing Company (Boeing);
Cargolux Airlines International S.A.
(Cargolux); GE Aviation; United Airlines
(UAL) Engineering; and Qantas Airways
Limited (Qantas). One commenter
requested that the FAA update the
Affected ADs paragraph of this AD. One
commenter requested that the HPT rotor
stage 2 disks be replaced instead of
inspected. One commenter requested
that the FAA update the Definitions
paragraph of this AD. Two commenters
requested adding credit for previous
action. Three commenters supported the
AD. The following presents the
comments received on the NPRM and
the FAA’s response to each comment.
E:\FR\FM\16DER1.SGM
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]]>Agencies
[Federal Register Volume 85, Number 242 (Wednesday, December 16, 2020)]
[Rules and Regulations]
[Pages 81376-81378]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-27659]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-3343; Product Identifier 2015-SW-078-AD; Amendment
39-21353; AD 2020-25-11]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2014-12-
12, which applied to certain Airbus Helicopters Model EC120B and
EC130B4 helicopters. AD 2014-12-12 required inspecting and, if
necessary, replacing parts of the sliding door star support attachment
assembly. This AD requires modifying the sliding door star support
stringer as specified in a European Union Aviation Safety Agency (EASA)
AD, which is incorporated by reference (IBR). This AD was prompted by
several incidents involving helicopter left-hand side doors (both
swinging and sliding) that revealed weaknesses in the locking
mechanism. The FAA is issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective January 21, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 21,
2021.
ADDRESSES: For material incorporated by reference in this AD, contact
the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49
221 8999 000; email [email protected]; internet www.easa.europa.eu.
You may find this material on the EASA website at https://ad.easa.europa.eu. You may view this material 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. It is also available in the AD
docket on the internet at https://www.regulations.gov by searching for
and locating Docket No. FAA-2016-3343.
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-2016-
3343; 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 final rule, any comments received, and other information. The
address for Docket Operations 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: Kathleen Arrigotti, Aerospace
Engineer, Large Aircraft Section, International Validation Branch, FAA,
2200 South 216th St., Des Moines, WA; telephone 206-231-3218; email
[email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2020-0095, dated April 29, 2020
(EASA AD 2020-0095), to correct an unsafe condition for certain Airbus
Helicopters Model EC120B and EC130B4 helicopters.
The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an AD to supersede AD 2014-12-12,
Amendment 39-17873 (79 FR 36638, June 30, 2014) (AD 2014-12-12). AD
2014-12-12 applied to certain Airbus Helicopters Model EC120B and
EC130B4 helicopters. The SNPRM published in the Federal Register on
September 22, 2020 (85 FR 59454). The FAA preceded the SNPRM with a
notice of proposed rulemaking (NPRM) that published in the Federal
Register on October 26, 2016 (81 FR 74362). The NPRM was prompted by
the determination to expand the applicability to all serial-numbered
EC120B helicopters with affected sliding doors installed and require
compliance with revised service information. The NPRM proposed to
require inspecting each upper and lower locking pin control rod end
fitting and replacing it if necessary, cleaning and dye-penetrant
inspecting the star support pin for cracking and replacing it if
necessary, and reinforcing the sliding door star support stringer. The
SNPRM proposed to require modifying the door locking/unlocking
mechanism, as specified in EASA AD 2020-0095.
The FAA is proposing this AD to address failure of the sliding door
star support, which could inhibit the operation of the sliding door
from the inside, delaying the evacuation of passengers during an
emergency. See EASA AD 2020-0095 for additional background information.
[[Page 81377]]
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The FAA received no comments on the SNPRM
or on the determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data and determined that air safety
and the public interest require adopting this final rule as proposed,
except for minor editorial changes and an exception that does not
affect helicopters of U.S. registry. The FAA has determined that these
minor changes:
Are consistent with the intent that was proposed in the
SNPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in-the SNPRM.
Related Service Information Under 1 CFR Part 51
The FAA reviewed EASA AD 2020-0095, which describes improved
procedures for modifying the door locking/unlocking mechanism (e.g.
modifying the sliding door star support by installing a reinforcing
bracket and replacing rod ends).
This material 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.
Differences Between This AD and the EASA AD
EASA AD 2020-0095 specifies to do the modification within 24
months. This AD requires the modification be done within 460 hours
time-in-service (TIS), based on an average of 230 hours TIS per year.
The FAA has determined this compliance time represents the maximum
interval of time allowable for the affected helicopters to continue to
safely operate before the modification is done. While EASA AD 2020-0095
allows credit for Airbus Helicopters Alert Service Bulletin No. EC120-
52A018, Revision 0, dated November 13, 2015 (ASB EC120-52A018 at
original issue), this AD does not because the applicable helicopter is
not U.S.-registered.
Costs of Compliance
The FAA estimates that this AD would affect 261 helicopters of U.S.
Registry. Labor rates are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates that operators may incur the following
costs in order to comply with this proposed AD.
Modifying the door locking/unlocking mechanism takes about 20 work-
hours and parts cost about $642 for an estimated cost of $2,342 per
helicopter and $611,262 for the U.S. fleet.
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
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) 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.
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:
0
a. Removing Airworthiness Directive (AD) 2014-12-12, Amendment 39-17873
(79 FR 36638, June 30, 2014); and
0
b. Adding the following new AD:
2020-25-11 Airbus Helicopters: Amendment 39-21353; Docket No. FAA-
2016-3343; Product Identifier 2015-SW-078-AD.
(a) Effective Date
This airworthiness directive (AD) is effective January 21, 2021.
(b) Affected ADs
This AD replaces AD 2014-12-12, Amendment 39-17873 (79 FR 36638,
June 30, 2014).
(c) Applicability
This AD applies to Airbus Helicopters Model EC120B and EC130B4
helicopters, certificated in any category, as identified in European
Union Aviation Safety Agency (EASA) AD 2020-0095, dated April 29,
2020 (EASA AD 2020-0095).
(d) Subject
Joint Aircraft System Component (JASC) Code 5200, Doors.
(e) Reason
This AD was prompted by reports of passengers not being able to
open a helicopter's left-hand door after landing. The FAA is issuing
this AD to address failure of the sliding door star support, which
could inhibit the operation of the sliding door from the inside,
delaying the evacuation of passengers during an emergency.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2020-0095.
(h) Exceptions to EASA AD 2020-0095
(1) Where EASA AD 2020-0095 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where paragraph (1) of EASA AD 2020-0095 specifies to
complete the actions within 24 months after its effective date, this
AD requires completion within 460 hours time-in-service after the
effective date of this AD.
(3) The ``Remarks'' section of EASA AD 2020-0095 does not apply
to this AD.
(4) Although the service information referenced in EASA AD 2020-
0095 specifies to discard certain parts, this AD does not include
that requirement.
(5) Where EASA AD 2020-0095 allows credit for Airbus Helicopters
Alert Service Bulletin No. EC120-52A018, Revision 0, dated November
13, 2015 (ASB EC120-52A018 at original issue), this AD does not.
[[Page 81378]]
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Strategic Policy Rotorcraft Section, FAA, may
approve AMOCs for this AD. Send your proposal to: Manager, Strategic
Policy Rotorcraft Section, FAA, 10101 Hillwood Pkwy, Fort Worth, TX
76177; telephone 817-222-5110; email 9/ASW/FTW/[email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(j) Related Information
For more information about this AD, contact Kathleen Arrigotti,
Aerospace Engineer, Large Aircraft Section, International Validation
Branch, FAA, 2200 South 216th St., Des Moines, WA; telephone 206-
231-3218; email [email protected].
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2020-0095,
dated April 29, 2020.
(ii) [Reserved]
(3) For EASA AD 2020-0095, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; internet www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://ad.easa.europa.eu.
(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. This material may be
found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2016-3343.
(5) You may view this material that is incorporated by reference
at the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, email
[email protected], or go to https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on December 3, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020-27659 Filed 12-15-20; 8:45 am]
BILLING CODE 4910-13-P
