Airworthiness Directives; Airbus Helicopters, 19080-19082 [2020-07138]
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19080
Federal Register / Vol. 85, No. 66 / Monday, April 6, 2020 / Rules and Regulations
Hillwood Pkwy., Fort Worth, TX 76177;
telephone 817–222–5110; email 9-ASW-FTWAMOC-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.
(g) Additional Information
The subject of this AD is addressed in
European Union Aviation Safety Agency
(previously European Aviation Safety
Agency) (EASA) AD No. 2017–0189, dated
September 22, 2017. You may view the EASA
AD on the internet at https://
www.regulations.gov in Docket No. FAA–
2018–0019.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6320, Main Rotor Gearbox.
(i) Material Incorporated by Reference
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(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Helicopters Emergency Alert
Service Bulletin (EASB) No. 01.00.86,
Revision 1, dated August 25, 2017.
(ii) Airbus Helicopters EASB No. 04A013,
Revision 1, dated August 25, 2017.
(3) For service information identified in
this AD, 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.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call 817–222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on March 25, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–07140 Filed 4–3–20; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–1015; Product
Identifier 2018–SW–104–AD; Amendment
39–19882; AD 2020–06–13]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for Airbus
Helicopters Model AS332C, AS332C1,
AS332L, and AS332L1 helicopters. This
AD requires determining the
accumulated hours time-in-service (TIS)
of certain part-numbered main gearbox
(MGB) suspension bar attachment
fittings (fittings) and bolts, and
establishes new life limits. This AD was
prompted by the outcome of tests and
analyses performed by Airbus
Helicopters. The actions of this AD are
intended to address an unsafe condition
on these products.
DATES: This AD is effective May 11,
2020.
ADDRESSES: For service information
identified in this final 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 view
the referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov in Docket No.
FAA–2019–1015; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
AD, the European Union Aviation
Safety Agency (previously European
Aviation Safety Agency) (EASA) AD,
any comments received, and other
information. The street 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: Matt
Fuller, Senior Aviation Safety Engineer,
PO 00000
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Safety Management Section, Rotorcraft
Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone 817–222–5110; email
matthew.fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On December 9, 2019, at 84 FR 67246,
the Federal Register published the
FAA’s notice of proposed rulemaking
(NPRM), which proposed to amend 14
CFR part 39 by adding an AD that
would apply to Airbus Helicopters
Model AS332C, AS332C1, AS332L, and
AS332L1 helicopters, with an MGB
suspension bar right-hand side (RH) rear
fitting part number (P/N) 330A22–2702–
07 and bolt P/N 330A22–0135–20, MGB
suspension bar left-hand side (LH) rear
fitting P/N 330A22–2702–06 and bolt P/
N 330A22–0135–20, or MGB suspension
bar front bolt P/N 330A22–0134–20
installed. The NPRM proposed to
require within 50 hours TIS, reviewing
the helicopter records to determine the
total hours TIS of the MGB suspension
bar RH and LH rear fittings. The NPRM
also proposed to require removing from
service the RH rear fitting and its bolts
and the LH rear fitting and its bolts
based on the accumulated total hours
TIS of the fittings and other conditions.
Thereafter, the NPRM proposed to
require removing from service the RH
rear fitting and its bolts at intervals not
to exceed 1,470 hours TIS, removing
from service the LH rear fitting at
intervals not to exceed 13,600 hours
TIS, and removing from service the LH
rear bolts during each Major Inspection
‘‘G.’’ Finally, the NPRM proposed to
require removing from service the front
bolts during each Major Inspection ‘‘G.’’
The proposed requirements were
intended to prevent structural failure of
the MGB suspension bar fittings and
bolts, possibly resulting in detachment
of the MGB suspension bars.
The NPRM was prompted by EASA
AD No. 2018–0260, dated December 3,
2018, issued by EASA, which is the
Technical Agent for the Member States
of the European Union, to correct an
unsafe condition for Airbus Helicopters
(formerly Eurocopter, Eurocopter
France, Aerospatiale) Model AS 332 C,
AS 332 C1, AS 332 L, and AS 332 L1
helicopters. From review of reported
Model EC 225 LP data, EASA advises
that the installation of the MGB upper
deck fittings of the three MGB
suspension bars could lead to tightening
torque loss on the fittings’ attachment
screws (bolts). Due to design
similarities, Model AS 332 C, AS 332
C1, AS 332 L, and AS 332 L1
helicopters could also be affected by the
same installation condition.
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Federal Register / Vol. 85, No. 66 / Monday, April 6, 2020 / Rules and Regulations
Investigations determined that a life
limit reduction of the MGB suspension
bar fittings and screws was necessary for
these model helicopters.
EASA states that this condition, if not
corrected, could lead to structural
failure of the MGB suspension bar
fittings and screws, possibly resulting in
detachment of the MGB suspension
bars. Accordingly, the EASA AD
requires determining the accumulated
service life of the affected parts and
introduced new life limits.
Comments
The FAA gave the public the
opportunity to participate in developing
this AD, but the FAA did not receive
any comments on the NPRM.
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 of the unsafe condition described
in its AD. The FAA is issuing this AD
after evaluating all information
provided by EASA and determining the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
Interim Action
The FAA considers this AD to be an
interim action. The design approval
holder is currently developing a
modification that will address the
unsafe condition identified in this AD.
Once this modification is developed,
approved, and available, the FAA might
consider additional rulemaking.
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Differences Between This AD and the
EASA AD
The EASA AD allows an option for
the first MGB RH rear fitting
replacement to inspect torque and
specifies different replacement
compliance times based on the torque
inspection results, whereas this AD does
not.
Related Service Information
The FAA reviewed Airbus Helicopters
Alert Service Bulletin No. AS332–
01.00.90, Revision 0, dated November
21, 2018. This service information
specifies determining the accumulated
hours TIS of certain part-numbered rear
MGB suspension bar fittings and screws.
This service information further
specifies criteria to determine the initial
replacement compliance time of those
parts and a new life limit for those parts
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thereafter. This service information also
establishes a life limit for the front MGB
attachment screws.
Costs of Compliance
The FAA estimates that this AD
affects 14 helicopters of U.S. Registry.
The FAA estimates that operators may
incur the following costs in order to
comply with this AD. Labor costs are
estimated at $85 per work-hour.
Determining the total hours TIS of the
rear MGB fittings takes about 0.5 workhour for an estimated cost of $43 per
helicopter and $602 for the U.S. fleet.
Replacing a rear MGB fitting and its
set of four bolts takes about 8 workhours and parts cost about $12,937, for
an estimated cost of $13,617 per
replacement cycle.
Replacing a set of four MGB
attachment bolts takes about 4 workhours and parts cost about $224, for an
estimated cost of $564 per replacement
cycle.
Replacing a LH rear MGB fitting takes
about 8 work-hours and parts cost about
$12,713, for an estimated cost of
$13,393 per replacement 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 helicopters identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
PO 00000
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19081
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:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2020–06–13 Airbus Helicopters:
Amendment 39–19882; Docket No.
FAA–2019–1015; Product Identifier
2018–SW–104–AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model AS332C, AS332C1, AS332L, and
AS332L1 helicopters, certificated in any
category, with a main gearbox (MGB)
suspension bar right-hand side (RH) rear
attachment fitting (fitting) part number (P/N)
330A22–2702–07 and bolt P/N 330A22–
0135–20, MGB suspension bar left-hand side
(LH) rear fitting P/N 330A22–2702–06 and
bolt P/N 330A22–0135–20, or MGB
suspension bar front bolt P/N 330A22–0134–
20 installed.
(b) Unsafe Condition
This AD defines the unsafe condition as
MGB suspension bar fittings and bolts
remaining in service beyond their fatigue life.
This condition could result in failure of an
MGB attachment assembly, detachment of an
MGB suspension bar, and subsequent loss of
helicopter control.
(c) Effective Date
This AD becomes effective May 11, 2020.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) Within 50 hours time-in-service (TIS),
review records to determine the total hours
TIS of each MGB suspension bar RH and LH
rear fitting.
(i) For any RH rear fitting that has
accumulated 1,470 or more total hours TIS,
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19082
Federal Register / Vol. 85, No. 66 / Monday, April 6, 2020 / Rules and Regulations
before further flight, remove from service the
RH rear fitting and its bolts.
(ii) For any RH rear fitting that has
accumulated less than 1,470 total hours TIS,
remove from service the RH rear fitting and
its bolts before the fitting accumulates 1,470
total hours TIS.
(iii) For any LH rear fitting that has
accumulated 13,600 or more total hours TIS,
before further flight, remove from service the
LH rear fitting and its bolts.
(iv) For any LH rear fitting that has
accumulated less than 13,600 total hours TIS:
(A) If a Major Inspection ‘‘G’’ has not been
completed since the LH rear fitting has been
installed, remove from service the LH rear
bolts during the next Major Inspection ‘‘G’’
inspection; or
Note 1 to paragraph (e)(1)(iv)(A) of this AD:
Major Inspection ‘‘G’’ (7,500 hours TIS
between overhauls) is defined in
Maintenance Manual MET 05–29–00–601.
(B) If a Major Inspection ‘‘G’’ has been
completed since the LH rear fitting has been
installed, before further flight, remove from
service the LH rear bolts; and
(C) Remove from service the LH rear fitting
before the fitting accumulates 13,600 total
hours TIS.
(2) Thereafter following paragraph (e)(1) of
this AD, remove from service any RH rear
fitting and its bolts at intervals not to exceed
1,470 hours TIS, remove from service any LH
rear fitting at intervals not to exceed 13,600
hours TIS, and remove from service any LH
rear bolts during each Major Inspection ‘‘G.’’
(3) During the next Major Inspection ‘‘G,’’
remove from service the MGB suspension bar
front bolts. Thereafter, remove from service
the front bolts during each Major Inspection
‘‘G.’’
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(f) 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: Matt Fuller, Senior Aviation
Safety Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone 817–222–5110; email 9-ASW-FTWAMOC-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.
(g) Additional Information
(1) Airbus Helicopters Alert Service
Bulletin No. AS332–01.00.90, Revision 0,
dated November 21, 2018, which is not
incorporated by reference, contains
additional information about the subject of
this AD. For service information identified in
this AD, 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 view the
VerDate Sep<11>2014
16:25 Apr 03, 2020
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referenced service information at the FAA,
Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N–
321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in
European Union Aviation Safety Agency
(previously European Aviation Safety
Agency) (EASA) AD No. 2018–0260, dated
December 3, 2018. You may view the EASA
AD on the internet at https://
www.regulations.gov in Docket No. FAA–
2019–1015.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6320 Main Rotor Gearbox.
Issued on March 27, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–07138 Filed 4–3–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF THE TREASURY
Internal Revenue Service
26 CFR Part 1
RIN 1545–BO4
Investing in Qualified Opportunity
Funds; Correcting Amendments
Internal Revenue Service (IRS),
Treasury.
ACTION: Correcting amendments.
AGENCY:
This document contains
corrections to Treasury Decision 9889,
which was published in the Federal
Register on Monday, January 13, 2020.
Treasury Decision 9889 contained final
regulations under the Internal Revenue
Code (the ‘‘Code) that govern the extent
to which taxpayers may elect the
Federal income tax benefits with respect
to certain equity interests in a qualified
opportunity fund (QOF).
DATES: These corrections are effective
on April 1, 2020, and applicable as of
January 13, 2020.
FOR FURTHER INFORMATION CONTACT:
Concerning section 1400Z–2 and these
regulations generally, Alfred H. Bae,
(202) 317–7006, or Kyle C. Griffin, (202)
317–4718, of the Office of Associate
Chief Counsel (Income Tax and
Accounting); concerning issues related
to C corporations and consolidated
groups, Jeremy Aron-Dine, (202) 317–
6848, or Sarah Hoyt, (202) 317–5024, of
the Office of Associate Chief Counsel
(Corporate); concerning issues related to
gains from financial contracts, REITs, or
RICs, Andrea Hoffenson or Pamela Lew,
(202) 317–7053, of the Office of
Associate Chief Counsel (Financial
SUMMARY:
Frm 00006
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Background
The final regulations (TD 9889) that
are the subject of this correction are
under section 1400Z–2 of the Code.
Need for Correction
As published on January 13, 2020 (85
FR 1866) contained errors that may
prove to be misleading and need to be
corrected.
List of Subjects in 26 CFR Part 1
Income taxes, Reporting and
recordkeeping requirements.
[TD 9889]
PO 00000
Institutions and Products); concerning
issues related to investments by foreign
persons, Eric Florenz, (202) 317–6941,
or Milton Cahn (202) 317–6937, of the
Office of Associate Chief Counsel
(International); concerning issues
related to partnerships, S corporations
or trusts, Marla Borkson, Sonia Kothari,
or Vishal Amin, at (202) 317–6850, and
concerning issues related to estates and
gifts, Leslie Finlow or Lorraine Gardner,
at (202) 317–6859, of the Office of
Associate Chief Counsel (Passthroughs
and Special Industries). These numbers
are not toll-free numbers.
SUPPLEMENTARY INFORMATION:
Sfmt 4700
Correction of Publication
Accordingly, 26 CFR part 1 is
corrected by making the following
correcting amendments:
PART 1—INCOME TAXES
Paragraph 1. The authority citation
continues to read in part as follows:
■
Authority: 26 U.S.C. 7805 * * *
Par. 2. Section1.1400Z2–0 is
amended:
■ a. By revising the entry for
§ 1.1400Z2(a)–1(d)(2);
■ b. In the entry for § 1.1400Z2(b)–1(h)
introductory text, by removing the
language ‘‘S corporations’’; and
■ c. By revising the entry for
§ 1.1400Z2(d)–1(a)(4).
The revisions read as follows:
■
§ 1.1400Z2–0
*
Table of Contents.
*
*
*
*
§ 1.1400Z2(a)–1 Deferring tax on
capital gains by investing in opportunity
zones.
*
*
*
*
*
(d) * * *
(2) Annual reporting of qualifying
investments.
*
*
*
*
*
§ 1.1400Z2(d)–1 Qualified
opportunity funds and qualified
opportunity zone businesses.
(a) * * *
(4) [Reserved]
*
*
*
*
*
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]]>Agencies
[Federal Register Volume 85, Number 66 (Monday, April 6, 2020)]
[Rules and Regulations]
[Pages 19080-19082]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-07138]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-1015; Product Identifier 2018-SW-104-AD; Amendment
39-19882; AD 2020-06-13]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1
helicopters. This AD requires determining the accumulated hours time-
in-service (TIS) of certain part-numbered main gearbox (MGB) suspension
bar attachment fittings (fittings) and bolts, and establishes new life
limits. This AD was prompted by the outcome of tests and analyses
performed by Airbus Helicopters. The actions of this AD are intended to
address an unsafe condition on these products.
DATES: This AD is effective May 11, 2020.
ADDRESSES: For service information identified in this final 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 view the referenced service information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321,
Fort Worth, TX 76177.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2019-1015; or in person at Docket
Operations between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays. The AD docket contains this AD, the European Union
Aviation Safety Agency (previously European Aviation Safety Agency)
(EASA) AD, any comments received, and other information. The street
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: Matt Fuller, Senior 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:
Discussion
On December 9, 2019, at 84 FR 67246, the Federal Register published
the FAA's notice of proposed rulemaking (NPRM), which proposed to amend
14 CFR part 39 by adding an AD that would apply to Airbus Helicopters
Model AS332C, AS332C1, AS332L, and AS332L1 helicopters, with an MGB
suspension bar right-hand side (RH) rear fitting part number (P/N)
330A22-2702-07 and bolt P/N 330A22-0135-20, MGB suspension bar left-
hand side (LH) rear fitting P/N 330A22-2702-06 and bolt P/N 330A22-
0135-20, or MGB suspension bar front bolt P/N 330A22-0134-20 installed.
The NPRM proposed to require within 50 hours TIS, reviewing the
helicopter records to determine the total hours TIS of the MGB
suspension bar RH and LH rear fittings. The NPRM also proposed to
require removing from service the RH rear fitting and its bolts and the
LH rear fitting and its bolts based on the accumulated total hours TIS
of the fittings and other conditions. Thereafter, the NPRM proposed to
require removing from service the RH rear fitting and its bolts at
intervals not to exceed 1,470 hours TIS, removing from service the LH
rear fitting at intervals not to exceed 13,600 hours TIS, and removing
from service the LH rear bolts during each Major Inspection ``G.''
Finally, the NPRM proposed to require removing from service the front
bolts during each Major Inspection ``G.''
The proposed requirements were intended to prevent structural
failure of the MGB suspension bar fittings and bolts, possibly
resulting in detachment of the MGB suspension bars.
The NPRM was prompted by EASA AD No. 2018-0260, dated December 3,
2018, issued by EASA, which is the Technical Agent for the Member
States of the European Union, to correct an unsafe condition for Airbus
Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale)
Model AS 332 C, AS 332 C1, AS 332 L, and AS 332 L1 helicopters. From
review of reported Model EC 225 LP data, EASA advises that the
installation of the MGB upper deck fittings of the three MGB suspension
bars could lead to tightening torque loss on the fittings' attachment
screws (bolts). Due to design similarities, Model AS 332 C, AS 332 C1,
AS 332 L, and AS 332 L1 helicopters could also be affected by the same
installation condition.
[[Page 19081]]
Investigations determined that a life limit reduction of the MGB
suspension bar fittings and screws was necessary for these model
helicopters.
EASA states that this condition, if not corrected, could lead to
structural failure of the MGB suspension bar fittings and screws,
possibly resulting in detachment of the MGB suspension bars.
Accordingly, the EASA AD requires determining the accumulated service
life of the affected parts and introduced new life limits.
Comments
The FAA gave the public the opportunity to participate in
developing this AD, but the FAA did not receive any comments on the
NPRM.
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 of the
unsafe condition described in its AD. The FAA is issuing this AD after
evaluating all information provided by EASA and determining the unsafe
condition exists and is likely to exist or develop on other helicopters
of these same type designs and that air safety and the public interest
require adopting the AD requirements as proposed.
Interim Action
The FAA considers this AD to be an interim action. The design
approval holder is currently developing a modification that will
address the unsafe condition identified in this AD. Once this
modification is developed, approved, and available, the FAA might
consider additional rulemaking.
Differences Between This AD and the EASA AD
The EASA AD allows an option for the first MGB RH rear fitting
replacement to inspect torque and specifies different replacement
compliance times based on the torque inspection results, whereas this
AD does not.
Related Service Information
The FAA reviewed Airbus Helicopters Alert Service Bulletin No.
AS332-01.00.90, Revision 0, dated November 21, 2018. This service
information specifies determining the accumulated hours TIS of certain
part-numbered rear MGB suspension bar fittings and screws. This service
information further specifies criteria to determine the initial
replacement compliance time of those parts and a new life limit for
those parts thereafter. This service information also establishes a
life limit for the front MGB attachment screws.
Costs of Compliance
The FAA estimates that this AD affects 14 helicopters of U.S.
Registry. The FAA estimates that operators may incur the following
costs in order to comply with this AD. Labor costs are estimated at $85
per work-hour.
Determining the total hours TIS of the rear MGB fittings takes
about 0.5 work-hour for an estimated cost of $43 per helicopter and
$602 for the U.S. fleet.
Replacing a rear MGB fitting and its set of four bolts takes about
8 work-hours and parts cost about $12,937, for an estimated cost of
$13,617 per replacement cycle.
Replacing a set of four MGB attachment bolts takes about 4 work-
hours and parts cost about $224, for an estimated cost of $564 per
replacement cycle.
Replacing a LH rear MGB fitting takes about 8 work-hours and parts
cost about $12,713, for an estimated cost of $13,393 per replacement
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 helicopters identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. 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 adding the following new airworthiness
directive (AD):
2020-06-13 Airbus Helicopters: Amendment 39-19882; Docket No. FAA-
2019-1015; Product Identifier 2018-SW-104-AD.
(a) Applicability
This AD applies to Airbus Helicopters Model AS332C, AS332C1,
AS332L, and AS332L1 helicopters, certificated in any category, with
a main gearbox (MGB) suspension bar right-hand side (RH) rear
attachment fitting (fitting) part number (P/N) 330A22-2702-07 and
bolt P/N 330A22-0135-20, MGB suspension bar left-hand side (LH) rear
fitting P/N 330A22-2702-06 and bolt P/N 330A22-0135-20, or MGB
suspension bar front bolt P/N 330A22-0134-20 installed.
(b) Unsafe Condition
This AD defines the unsafe condition as MGB suspension bar
fittings and bolts remaining in service beyond their fatigue life.
This condition could result in failure of an MGB attachment
assembly, detachment of an MGB suspension bar, and subsequent loss
of helicopter control.
(c) Effective Date
This AD becomes effective May 11, 2020.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
(1) Within 50 hours time-in-service (TIS), review records to
determine the total hours TIS of each MGB suspension bar RH and LH
rear fitting.
(i) For any RH rear fitting that has accumulated 1,470 or more
total hours TIS,
[[Page 19082]]
before further flight, remove from service the RH rear fitting and
its bolts.
(ii) For any RH rear fitting that has accumulated less than
1,470 total hours TIS, remove from service the RH rear fitting and
its bolts before the fitting accumulates 1,470 total hours TIS.
(iii) For any LH rear fitting that has accumulated 13,600 or
more total hours TIS, before further flight, remove from service the
LH rear fitting and its bolts.
(iv) For any LH rear fitting that has accumulated less than
13,600 total hours TIS:
(A) If a Major Inspection ``G'' has not been completed since the
LH rear fitting has been installed, remove from service the LH rear
bolts during the next Major Inspection ``G'' inspection; or
Note 1 to paragraph (e)(1)(iv)(A) of this AD: Major Inspection
``G'' (7,500 hours TIS between overhauls) is defined in Maintenance
Manual MET 05-29-00-601.
(B) If a Major Inspection ``G'' has been completed since the LH
rear fitting has been installed, before further flight, remove from
service the LH rear bolts; and
(C) Remove from service the LH rear fitting before the fitting
accumulates 13,600 total hours TIS.
(2) Thereafter following paragraph (e)(1) of this AD, remove
from service any RH rear fitting and its bolts at intervals not to
exceed 1,470 hours TIS, remove from service any LH rear fitting at
intervals not to exceed 13,600 hours TIS, and remove from service
any LH rear bolts during each Major Inspection ``G.''
(3) During the next Major Inspection ``G,'' remove from service
the MGB suspension bar front bolts. Thereafter, remove from service
the front bolts during each Major Inspection ``G.''
(f) 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:
Matt Fuller, Senior Aviation Safety Engineer, Safety Management
Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone 817-222-5110; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, 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.
(g) Additional Information
(1) Airbus Helicopters Alert Service Bulletin No. AS332-
01.00.90, Revision 0, dated November 21, 2018, which is not
incorporated by reference, contains additional information about the
subject of this AD. For service information identified in this AD,
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 view the referenced service information at the
FAA, Office of the Regional Counsel, Southwest Region, 10101
Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in European Union
Aviation Safety Agency (previously European Aviation Safety Agency)
(EASA) AD No. 2018-0260, dated December 3, 2018. You may view the
EASA AD on the internet at https://www.regulations.gov in Docket No.
FAA-2019-1015.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6320 Main Rotor
Gearbox.
Issued on March 27, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-07138 Filed 4-3-20; 8:45 am]
BILLING CODE 4910-13-P
