Airworthiness Directives; Leonardo S.p.a. Helicopters, 70972-70975 [2021-26973]
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Federal Register / Vol. 86, No. 237 / Tuesday, December 14, 2021 / Rules and Regulations
send it to the attention of the person
identified paragraph (k) of this AD.
Information may be emailed to: ANE-ADAMOC@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.
(k) Related Information
For more information about this AD,
contact Scott M. Stevenson, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: (781)
238–7132; fax: (781) 238–7199; email:
scott.m.stevenson@faa.gov.
(l) 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 the AD specifies otherwise.
(i) GE CF34–8C Service Bulletin (SB) 75–
0028 R00, dated November 2, 2021.
(ii) GE CF34–8E SB 75–0023 R00, dated
November 2, 2021.
(3) For GE service information identified in
this AD, contact General Electric Company,
1 Neumann Way, Cincinnati, OH 45215;
phone: (513) 552–3272; email:
aviation.fleetsupport@ge.com; website:
https://www.ge.com.
(4) You may view this service information
at 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 (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: fr.inspection@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on December 1, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–27045 Filed 12–9–21; 4:15 pm]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
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14 CFR Part 39
[Docket No. FAA–2020–0283; Project
Identifier 2018–SW–045–AD; Amendment
39–21821; AD 2021–23–22]
RIN 2120–AA64
Airworthiness Directives; Leonardo
S.p.a. Helicopters
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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ACTION:
Final rule.
The FAA is adopting a new
airworthiness directive (AD) for certain
Leonardo S.p.a. Model AB139 and
AW139 helicopters. This AD was
prompted by reports of failed main rotor
(MR) dampers. This AD requires various
inspections of certain MR dampers, as
specified in a European Aviation Safety
Agency (now European Union Aviation
Safety Agency) (EASA) AD, which is
incorporated by reference. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective January 18,
2022.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 18, 2022.
ADDRESSES: For EASA material
incorporated by reference (IBR) in this
AD, contact EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany;
telephone +49 221 8999 000; email
ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find the
EASA material on the EASA website at
https://ad.easa.europa.eu. For Leonardo
Helicopters service information
identified in this final rule, 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://customerportal.leonardo
company.com/en-US/. 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. Service
information that is incorporated by
reference is also available in the AD
docket at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2020–0283.
SUMMARY:
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0283; 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, the EASA AD, 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: Matt
Fuller, AD Program Manager, General
PO 00000
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Aviation & Rotorcraft Unit,
Airworthiness Products Section,
Operational Safety Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email
matthew.fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–
0112R1, dated June 4, 2018 (EASA AD
2018–0112R1), which is the most recent
of a series of ADs issued by EASA, to
correct an unsafe condition for certain
Leonardo S.p.A. Helicopters (formerly
Finmeccanica S.p.A., Helicopter
Division (FHD), AgustaWestland S.p.A.,
Agusta S.p.A.), AgustaWestland
Philadelphia Corporation (formerly
Agusta Aerospace Corporation) Model
AB139 and AW139 helicopters.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain serial-numbered
Leonardo S.p.A. Model AB139 and
AW139 helicopters with an MR damper
part number (P/N) 3G6220V01351,
3G6220V01352, or 3G6220V01353
installed. The NPRM published in the
Federal Register on March 31, 2020 (85
FR 17788). The NPRM was prompted by
reports of failed MR dampers. The
NPRM proposed to require, for an
affected helicopter with MR damper
P/N 3G6220V01351, 3G6220V01352, or
3G6220V01353 installed, reducing the
installation torque of each hub
attachment bolt for each MR damper.
For an affected helicopter with MR
damper P/N 3G6220V01351 or
3G6220V01352 installed, the NPRM
proposed to require: Repetitively
inspecting the MR damper rod end (rod
end) and MR damper body end (body
end) for a crack; dye penetrant
inspecting or eddy current inspecting
certain rod and body ends for a crack;
repetitively inspecting the rod and body
end bearings for rotation in the damper
seat and for misaligned slippage marks;
repetitively inspecting the rod end
broached ring nut; and repetitively
inspecting the bearing friction torque
value of the body and rod ends, and the
MR damper anti-rotation block.
Depending on the results of the various
inspections, the NPRM proposed to
require removing a part from service or
replacing a part. For an affected
helicopter with MR damper P/N
3G6220V01351 or 3G6220V01352
installed, the NPRM also proposed to
require inspecting each rod end to
determine if special washer P/N
3G6220A05052 is installed, and
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depending on the results, aligning the
rod ends and broached rings, replacing
any broached ring that cannot be
aligned, inspecting the broached rings
for wear and damage, and replacing the
broached ring and installing a special
washer. Lastly, the NPRM proposed to
require installing MR damper P/N
3G220V01353, prohibit installing MR
damper P/N 3G6220V01351 and P/N
3G6220V01352 on any helicopter, and
allow the installation of MR damper P/
N 3G220V01353 to constitute
terminating action for all of the
proposed repetitive required actions.
The FAA issued a supplemental
notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an
AD that would apply to Leonardo S.p.a.
Model AB139 and AW139 helicopters as
identified in EASA AD 2018–0112R1.
The SNPRM published in the Federal
Register on September 14, 2021 (86 FR
51022). The FAA issued the SNPRM to
add an action required by EASA AD
2018–0112R1 that was inadvertently
omitted in the NPRM, correct thresholds
for different actions proposed in the
NPRM, and add the option to
accomplish an eddy current inspection
for some inspections. The SNPRM also
utilized the FAA’s new practice of
proposing to incorporate EASA AD
2018–0112R1 by reference.
The FAA is issuing this AD to address
a crack in an MR damper, which could
result in seizure of the MR damper,
detachment of the MR damper in-flight,
and subsequent loss of control of the
helicopter. See EASA AD 2018–0112R1
for additional background information.
Discussion of Final Airworthiness
Directive
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Comments
The FAA received no comments on
the SNPRM or on the determination of
the costs.
Conclusion
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 reviewed
the relevant data and determined that
air safety requires adopting this AD as
proposed. Accordingly, the FAA is
issuing this AD to address the unsafe
condition on these helicopters.
Related Service Information Under 1
CFR Part 51
EASA AD 2018–0112R1 requires
reducing the installation torque of the
bolts affixing each affected MR damper
to the MR hub. For certain affected MR
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dampers, EASA AD 2018–0112R1
requires a one-time dye penetrant
inspection of the rod and body ends,
and a repetitive detailed visual
inspection of the rod and body ends.
EASA AD 2018–0112R1 allows an eddy
current inspection as an alternative to
those inspections. For certain affected
MR dampers, EASA AD 2018–0112R1
also requires repetitively inspecting the
rod and body end bearings for rotation,
visually inspecting the rod end
broached ring nut, accomplishing a
bearing friction inspection of the body
and rod end bearings, and a detailed
inspection of the anti-rotation block.
EASA AD 2018–0112R1 also requires a
one-time visual inspection of certain
affected MR damper rod end
installations and a torque check of the
MR damper broached ring nut. For
certain affected MR dampers, EASA AD
2018–0112R1 requires replacing any
special washer P/N 3G6220A05051 with
a new washer P/N 3G6220A05052. If
there is a crack or damage detected in
any inspection, EASA AD 2018–0112R1
requires contacting Leonardo and, if the
discrepancy is confirmed, replacing the
MR damper. EASA AD 2018–0112R1
also requires corrective actions if any
discrepancy is detected in the
inspections for rotation, friction, and
torque. EASA AD 2018–0112R1 allows
installing MR damper P/N
3G6220V01353 on a helicopter,
provided that it is installed using the
correct torque values. Lastly, EASA AD
2018–0112R1 prohibits installing MR
damper P/N 3G6220V01351 and P/N
3G6220V01352 on any helicopter.
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
Where EASA AD 2018–0112R1
requires the compliance time of after the
last flight (ALF) of the day inspection,
this AD requires the compliance time of
before the first flight of the day. Some
compliance times in EASA AD 2018–
0112R1 are on condition of part removal
or replacement, whereas this AD does
not include those compliance times.
EASA AD 2018–0112R1 requires a
torque check of the MR damper
broached ring nut, whereas this AD
requires a torque inspection instead to
clarify that the action must be
accomplished by a mechanic that meets
the requirements of 14 CFR part 65
subpart D. EASA AD 2018–0112R1
requires making sure that there are no
scratches or dents on the rod end,
however it does not state corrective
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action for this requirement; this AD
requires removing the rod end from
service if there is a scratch or dent on
the rod end. Where EASA AD 2018–
0112R1 requires contacting Leonardo
and replacing the MR damper with a
serviceable part, this AD requires
replacing or removing parts from service
instead. Where EASA AD 2018–0112R1
requires accomplishing applicable
corrective action(s) as specified in, and
in accordance with, the instructions in
service information, this AD requires
removing parts from service for some of
the corrective actions instead. Where
EASA AD 2018–0112R1 requires a onetime dye penetrant inspection of certain
rod ends when installed, this AD does
not. Instead, this AD prohibits installing
certain rod ends that are not marked
with a black dot and therefore have not
been inspected.
Costs of Compliance
The FAA estimates that this AD
affects 126 helicopters of U.S. Registry.
Labor rates are estimated at $85 per
work-hour. Based on these numbers, the
FAA estimates the following costs to
comply with this AD.
Performing the MR damper
inspections takes about 24 work-hours,
for an estimated cost of $2,040 per
helicopter and $257,040 for the U.S.
fleet, per inspection cycle.
Replacing a rod end takes about 3
work-hours and parts cost about $500,
for an estimated cost of $755 per rod
end. Replacing a broached ring and
broached ring nut takes about 3 workhours and parts cost about $125, for an
estimated cost of $380 per broached ring
and broached ring nut. Replacing an
anti-rotation block takes about 3 workhours and parts cost about $50, for an
estimated cost of $305 per anti-rotation
block. Replacing an MR damper takes
about 2 work-hours and parts cost about
$18,000, for an estimated cost of
$18,170 per MR damper.
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
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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.
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:
■
2021–23–22 Leonardo S.p.a.: Amendment
39–21821; Docket No. FAA–2020–0283;
Project Identifier 2018–SW–045–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective January 18, 2022.
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(b) Affected ADs
None.
(c) Applicability
This AD applies to Leonardo S.p.a. Model
AB139 and AW139 helicopters, certificated
in any category, as identified in European
Aviation Safety Agency (now European
Union Aviation Safety Agency) (EASA) AD
2018–0112R1, dated June 4, 2018 (EASA AD
2018–0112R1).
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(d) Subject
Joint Aircraft Service Component (JASC)
Code: 6200, Main Rotor System.
(e) Unsafe Condition
This AD was prompted by reports of failed
main rotor (MR) dampers. The FAA is issuing
this AD to address a crack in an MR damper.
The unsafe condition, if not addressed, could
result in seizure of the MR damper,
detachment of the MR damper in-flight, and
subsequent loss of control of the helicopter.
(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 2018–0112R1.
(h) Exceptions to EASA AD 2018–0112R1
(1) Where EASA AD 2018–0112R1 requires
compliance in terms of flight hours (FH), this
AD requires using hours time-in-service
(TIS).
(2) Where EASA AD 2018–0112R1 refers to
FH accumulated by a part since new (first
installation on a helicopter) or since
overhaul, this AD requires using total hours
TIS.
(3) Where EASA AD 2018–0112R1 refers to
its effective date; May 10, 2016 (the effective
date of EASA AD 2016–0087, dated May 3,
2016); July 28, 2016 (the effective date of
EASA AD 2016–0140, dated July 14, 2016);
or September 11, 2017 (the effective date of
EASA AD 2017–0160, dated August 28,
2017), this AD requires using the effective
date of this AD.
(4) Where EASA AD 2018–0112R1 requires
the compliance time of during an ‘‘after the
last flight (ALF) of the day inspection,’’ this
AD requires the compliance time of before
the first flight of the day.
(5) Where the service information
referenced in EASA AD 2018–0112R1
specifies using a magnifying glass, this AD
requires using a 5X or higher power
magnifying glass.
(6) Where the service information
referenced in EASA AD 2018–0112R1
specifies discarding parts, this AD requires
removing those parts from service.
(7) Where paragraph (2) of EASA AD 2018–
0112R1 requires compliance within 30 FH
after 10 May 2016 (the effective date of EASA
AD 2016–0087, dated May 3, 2016), or at the
first MR damper removal, whichever occurs
first, for a MR damper that has accumulated
300 or more FH, this AD requires compliance
within 30 hours TIS after the effective date
of this AD for a MR damper that has
accumulated 300 or more total hours TIS.
(8) This AD does not require the actions
required by paragraph (3) of EASA AD 2018–
0112R1.
(9) Where paragraph (8) of EASA AD 2018–
0112R1 refers to having a serial number (S/
N) specified in Part V of FHD BT 139–450,
this AD requires the actions of that paragraph
for helicopters with an MR damper part
number (P/N) 3G6220V01351 or
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3G6220V01352 with an S/N up to MCR8086
inclusive, installed, that has accumulated
less than 600 total hours TIS.
(10) Where paragraph (10) of EASA AD
2018–0112R1 refers to having an S/N
specified in in Part VII of FHD BT 139–450,
this AD requires the actions of that paragraph
for helicopters with:
(i) MR damper P/N 3G6220V01351 or
3G6220V01352 with an S/N up to MCR8764
inclusive, and with rod end P/N M006–
01H004–041, –045, or –053, installed, except
MR dampers confirmed of having 60–80 Nm
applied and MR dampers marked with ‘‘BT
139–446 Part II’’ or ‘‘BT 139–446 Part III’’ on
the logcard; or
(ii) MR damper P/N 3G6220V01351 or
3G6220V01352 that has had the damper rod
end assembly removed before the issuance of
‘‘BT 139–446’’ installed, even if it has an S/
N higher than MCR8764 or it has been
confirmed of having 60–80 Nm applied.
Note 1 to paragraph (h)(10): MR dampers
confirmed of having 60–80 Nm applied are
listed in Table 1 (two pages) of Annex A, of
Leonardo Helicopters Alert Service Bulletin
No. 139–450, Revision D, dated May 28,
2019.
(11) Where paragraph (10) of EASA AD
2018–0112R1 requires a torque check, this
AD requires a torque inspection.
(12) Where the service information
referenced in paragraph (10) of EASA AD
2018–0112R1 specifies making sure that
there are not scratches or dents on the rod
end, this AD requires, before further flight,
removing the rod end from service if there is
a scratch or dent on the rod end.
(13) Where paragraph (12) of EASA AD
2018–0112R1 requires contacting Leonardo
and replacing the MR damper with a
serviceable part, this AD does not. This AD
requires the following:
(i) If there is a crack in an MR damper body
end, before further flight, replace the MR
damper.
(ii) If there is a crack in an MR damper rod
end, before further flight, remove the MR
damper rod end from service.
(iii) If there is damage in any teeth of a rod
end broached ring nut or damper piston slot,
or if the engagement or alignment is not
correct, before further flight, remove the rod
end broached ring nut from service.
(14) Paragraph (13) of EASA AD 2018–
0112R1 requires accomplishing the
applicable corrective action(s) ‘‘as specified
in, and in accordance with, the instructions
of FHD BT 139–450 or FHD BT 139–452, as
applicable,’’ except where:
(i) If there is any bearing seat rotation or
misaligned slippage mark in the MR damper
rod end, this AD requires, before further
flight, removing the MR damper rod end from
service.
(ii) If the MR damper rod end torque value
is more than 30.0 Nm (265.5 in lb), this AD
requires, before further flight, removing the
MR damper rod end from service.
(iii) If any MR damper anti-rotation block
dimension measurement exceeds allowable
limits, this AD requires, before further flight,
removing the anti-rotation block from
service.
(15) This AD does not mandate compliance
with the ‘‘Remarks’’ section of EASA AD
2018–0112R1.
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(i) Parts Prohibition
As of the effective date of this AD, do not
install an MR damper rod end P/N M006–
01H004–041, M006–01H004–045, or M006–
01H004–053 on any helicopter, unless it is
marked with a black dot indicating that it has
passed inspections specified by Leonardo
Helicopters BT 139–450.
(j) No Reporting Requirement
Although the service information
referenced in EASA AD 2018–0112R1
specifies to submit certain information to the
manufacturer, this AD does not include that
requirement.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the International Validation
Branch, send it to the attention of the person
identified in paragraph (l)(1) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@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.
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(l) Related Information
(1) For more information about this AD,
contact Matt Fuller, AD Program Manager,
General Aviation & Rotorcraft Unit,
Airworthiness Products Section, Operational
Safety Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817) 222–
5110; email matthew.fuller@faa.gov.
(2) Leonardo Helicopters Alert Service
Bulletin No. 139–450, Revision D, dated May
28, 2019, which is not incorporated by
reference, contains additional information
about the subject of this AD. 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://
customerportal.leonardocompany.com/enUS/. You may view this referenced service
information at the contact information
specified in paragraph (m)(4) of this AD.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) European Aviation Safety Agency (now
European Union Aviation Safety Agency)
(EASA) AD 2018–0112R1, dated June 4,
2018.
(ii) [Reserved]
(3) For EASA AD 2018–0112R1, contact
EASA, Konrad-Adenauer-Ufer 3, 50668
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Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find the
EASA material 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
at https://www.regulations.gov by searching
for and locating Docket No. FAA–2020–0283.
(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
fr.inspection@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on November 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–26973 Filed 12–13–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HOMELAND
SECURITY
Coast Guard
33 CFR Part 165
[Docket Number USCG–2021–0911]
RIN 1625–AA11
Safety Zone; Oil Pipeline Repairs; San
Pedro Bay, CA
Coast Guard, Department of
Homeland Security (DHS).
ACTION: Temporary final rule.
AGENCY:
The Coast Guard is
establishing a temporary safety zone for
the oil pipeline repair operations in the
vicinity of a damaged pipeline, off the
coast of Orange County and near San
Pedro Bay, CA. The safety zone is
necessary to reduce significant hazards
to vessels, the harbor, and the public
during ongoing pipeline repair and oil
recovery operations. Entry of persons or
vessels into this temporary safety zone
is prohibited unless specifically
authorized by the Captain of the Port,
Los Angeles-Long Beach, or her
designated representative.
DATES: This rule is effective without
actual notice from December 14, 2021,
until January 17, 2022. For purposes of
enforcement, actual notice will be used
from December 9, 2021, through
December 14, 2021.
ADDRESSES: To view documents
mentioned in this preamble as being
SUMMARY:
PO 00000
Frm 00031
Fmt 4700
Sfmt 4700
70975
available in the docket, go to https://
www.regulations.gov, type USCG–2021–
0911 in the ‘‘SEARCH’’ box and click
‘‘SEARCH.’’ Click on Open Docket
Folder on the line associated with this
rule.
FOR FURTHER INFORMATION CONTACT: If
you have questions on this rule, call or
email LCDR Maria Wiener, Waterways
Management, U.S. Coast Guard Sector
Los Angeles-Long Beach; telephone
(310) 357–1603, email Maria.C.Wiener@
uscg.mil.
SUPPLEMENTARY INFORMATION:
I. Table of Abbreviations
CFR Code of Federal Regulations
DHS Department of Homeland Security
FR Federal Register
NPRM Notice of proposed rulemaking
§ Section
U.S.C. United States Code
II. Background Information and
Regulatory History
The Coast Guard is issuing this
temporary rule without prior notice and
opportunity to comment pursuant to
authority under section 4(a) of the
Administrative Procedure Act (APA) (5
U.S.C. 553(b)). This provision
authorizes an agency to issue a rule
without prior notice and opportunity to
comment when the agency for good
cause finds that those procedures are
‘‘impracticable, unnecessary, or contrary
to the public interest.’’ Under 5 U.S.C.
553(b)(B), the Coast Guard finds that
good cause exists for not publishing a
notice of proposed rulemaking (NPRM)
with respect to this rule to ensure the
safety of response personnel and
mariners during repairs of the damaged
pipeline, as well as the potential oil
recovery of said pipeline. It is
impracticable to publish an NPRM,
because we must establish this safety
zone by December 9, 2021, due to
immediate action needed to minimize
potential danger to the public during oil
recovery operations for the discharge of
oil from pipeline.
Under 5 U.S.C. 553(d)(3), the Coast
Guard finds that good cause exists for
making this rule effective less than 30
days after publication in the Federal
Register. Delaying the effective date of
this rule would be contrary to public
interest because immediate action is
needed to respond to the potential
safety hazards associated with the
pipeline repair operations for the
damaged pipeline.
III. Legal Authority and Need for Rule
The Coast Guard is issuing this rule
under authority in 46 U.S.C. 70034
(previously 33 U.S.C. 1231). The
Captain of the Port (COTP), Los
E:\FR\FM\14DER1.SGM
14DER1
]]>Agencies
[Federal Register Volume 86, Number 237 (Tuesday, December 14, 2021)]
[Rules and Regulations]
[Pages 70972-70975]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-26973]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0283; Project Identifier 2018-SW-045-AD; Amendment
39-21821; AD 2021-23-22]
RIN 2120-AA64
Airworthiness Directives; Leonardo S.p.a. Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD was
prompted by reports of failed main rotor (MR) dampers. This AD requires
various inspections of certain MR dampers, as specified in a European
Aviation Safety Agency (now European Union Aviation Safety Agency)
(EASA) AD, which is incorporated by reference. The FAA is issuing this
AD to address the unsafe condition on these products.
DATES: This AD is effective January 18, 2022.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 18,
2022.
ADDRESSES: For EASA material incorporated by reference (IBR) in this
AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany;
telephone +49 221 8999 000; email [email protected]; internet
www.easa.europa.eu. You may find the EASA material on the EASA website
at https://ad.easa.europa.eu. For Leonardo Helicopters service
information identified in this final rule, 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://customerportal.leonardo company.com/en-US/. 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. Service information that is
incorporated by reference is also available in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0283.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0283; 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, the
EASA AD, 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: Matt Fuller, AD Program Manager,
General Aviation & Rotorcraft Unit, Airworthiness Products Section,
Operational Safety Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222-5110; email [email protected].
SUPPLEMENTARY INFORMATION:
Background
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2018-0112R1, dated June 4, 2018
(EASA AD 2018-0112R1), which is the most recent of a series of ADs
issued by EASA, to correct an unsafe condition for certain Leonardo
S.p.A. Helicopters (formerly Finmeccanica S.p.A., Helicopter Division
(FHD), AgustaWestland S.p.A., Agusta S.p.A.), AgustaWestland
Philadelphia Corporation (formerly Agusta Aerospace Corporation) Model
AB139 and AW139 helicopters.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain serial-numbered
Leonardo S.p.A. Model AB139 and AW139 helicopters with an MR damper
part number (P/N) 3G6220V01351, 3G6220V01352, or 3G6220V01353
installed. The NPRM published in the Federal Register on March 31, 2020
(85 FR 17788). The NPRM was prompted by reports of failed MR dampers.
The NPRM proposed to require, for an affected helicopter with MR damper
P/N 3G6220V01351, 3G6220V01352, or 3G6220V01353 installed, reducing the
installation torque of each hub attachment bolt for each MR damper. For
an affected helicopter with MR damper P/N 3G6220V01351 or 3G6220V01352
installed, the NPRM proposed to require: Repetitively inspecting the MR
damper rod end (rod end) and MR damper body end (body end) for a crack;
dye penetrant inspecting or eddy current inspecting certain rod and
body ends for a crack; repetitively inspecting the rod and body end
bearings for rotation in the damper seat and for misaligned slippage
marks; repetitively inspecting the rod end broached ring nut; and
repetitively inspecting the bearing friction torque value of the body
and rod ends, and the MR damper anti-rotation block. Depending on the
results of the various inspections, the NPRM proposed to require
removing a part from service or replacing a part. For an affected
helicopter with MR damper P/N 3G6220V01351 or 3G6220V01352 installed,
the NPRM also proposed to require inspecting each rod end to determine
if special washer P/N 3G6220A05052 is installed, and
[[Page 70973]]
depending on the results, aligning the rod ends and broached rings,
replacing any broached ring that cannot be aligned, inspecting the
broached rings for wear and damage, and replacing the broached ring and
installing a special washer. Lastly, the NPRM proposed to require
installing MR damper P/N 3G220V01353, prohibit installing MR damper P/N
3G6220V01351 and P/N 3G6220V01352 on any helicopter, and allow the
installation of MR damper P/N 3G220V01353 to constitute terminating
action for all of the proposed repetitive required actions.
The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an AD that would apply to Leonardo
S.p.a. Model AB139 and AW139 helicopters as identified in EASA AD 2018-
0112R1. The SNPRM published in the Federal Register on September 14,
2021 (86 FR 51022). The FAA issued the SNPRM to add an action required
by EASA AD 2018-0112R1 that was inadvertently omitted in the NPRM,
correct thresholds for different actions proposed in the NPRM, and add
the option to accomplish an eddy current inspection for some
inspections. The SNPRM also utilized the FAA's new practice of
proposing to incorporate EASA AD 2018-0112R1 by reference.
The FAA is issuing this AD to address a crack in an MR damper,
which could result in seizure of the MR damper, detachment of the MR
damper in-flight, and subsequent loss of control of the helicopter. See
EASA AD 2018-0112R1 for additional background information.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the SNPRM or on the determination
of the costs.
Conclusion
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 reviewed the relevant
data and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these helicopters.
Related Service Information Under 1 CFR Part 51
EASA AD 2018-0112R1 requires reducing the installation torque of
the bolts affixing each affected MR damper to the MR hub. For certain
affected MR dampers, EASA AD 2018-0112R1 requires a one-time dye
penetrant inspection of the rod and body ends, and a repetitive
detailed visual inspection of the rod and body ends. EASA AD 2018-
0112R1 allows an eddy current inspection as an alternative to those
inspections. For certain affected MR dampers, EASA AD 2018-0112R1 also
requires repetitively inspecting the rod and body end bearings for
rotation, visually inspecting the rod end broached ring nut,
accomplishing a bearing friction inspection of the body and rod end
bearings, and a detailed inspection of the anti-rotation block. EASA AD
2018-0112R1 also requires a one-time visual inspection of certain
affected MR damper rod end installations and a torque check of the MR
damper broached ring nut. For certain affected MR dampers, EASA AD
2018-0112R1 requires replacing any special washer P/N 3G6220A05051 with
a new washer P/N 3G6220A05052. If there is a crack or damage detected
in any inspection, EASA AD 2018-0112R1 requires contacting Leonardo
and, if the discrepancy is confirmed, replacing the MR damper. EASA AD
2018-0112R1 also requires corrective actions if any discrepancy is
detected in the inspections for rotation, friction, and torque. EASA AD
2018-0112R1 allows installing MR damper P/N 3G6220V01353 on a
helicopter, provided that it is installed using the correct torque
values. Lastly, EASA AD 2018-0112R1 prohibits installing MR damper P/N
3G6220V01351 and P/N 3G6220V01352 on any helicopter.
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
Where EASA AD 2018-0112R1 requires the compliance time of after the
last flight (ALF) of the day inspection, this AD requires the
compliance time of before the first flight of the day. Some compliance
times in EASA AD 2018-0112R1 are on condition of part removal or
replacement, whereas this AD does not include those compliance times.
EASA AD 2018-0112R1 requires a torque check of the MR damper broached
ring nut, whereas this AD requires a torque inspection instead to
clarify that the action must be accomplished by a mechanic that meets
the requirements of 14 CFR part 65 subpart D. EASA AD 2018-0112R1
requires making sure that there are no scratches or dents on the rod
end, however it does not state corrective action for this requirement;
this AD requires removing the rod end from service if there is a
scratch or dent on the rod end. Where EASA AD 2018-0112R1 requires
contacting Leonardo and replacing the MR damper with a serviceable
part, this AD requires replacing or removing parts from service
instead. Where EASA AD 2018-0112R1 requires accomplishing applicable
corrective action(s) as specified in, and in accordance with, the
instructions in service information, this AD requires removing parts
from service for some of the corrective actions instead. Where EASA AD
2018-0112R1 requires a one-time dye penetrant inspection of certain rod
ends when installed, this AD does not. Instead, this AD prohibits
installing certain rod ends that are not marked with a black dot and
therefore have not been inspected.
Costs of Compliance
The FAA estimates that this AD affects 126 helicopters of U.S.
Registry. Labor rates are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates the following costs to comply with
this AD.
Performing the MR damper inspections takes about 24 work-hours, for
an estimated cost of $2,040 per helicopter and $257,040 for the U.S.
fleet, per inspection cycle.
Replacing a rod end takes about 3 work-hours and parts cost about
$500, for an estimated cost of $755 per rod end. Replacing a broached
ring and broached ring nut takes about 3 work-hours and parts cost
about $125, for an estimated cost of $380 per broached ring and
broached ring nut. Replacing an anti-rotation block takes about 3 work-
hours and parts cost about $50, for an estimated cost of $305 per anti-
rotation block. Replacing an MR damper takes about 2 work-hours and
parts cost about $18,000, for an estimated cost of $18,170 per MR
damper.
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
[[Page 70974]]
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.
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:
2021-23-22 Leonardo S.p.a.: Amendment 39-21821; Docket No. FAA-2020-
0283; Project Identifier 2018-SW-045-AD.
(a) Effective Date
This airworthiness directive (AD) is effective January 18, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Leonardo S.p.a. Model AB139 and AW139
helicopters, certificated in any category, as identified in European
Aviation Safety Agency (now European Union Aviation Safety Agency)
(EASA) AD 2018-0112R1, dated June 4, 2018 (EASA AD 2018-0112R1).
(d) Subject
Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor
System.
(e) Unsafe Condition
This AD was prompted by reports of failed main rotor (MR)
dampers. The FAA is issuing this AD to address a crack in an MR
damper. The unsafe condition, if not addressed, could result in
seizure of the MR damper, detachment of the MR damper in-flight, and
subsequent loss of control of the helicopter.
(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 2018-0112R1.
(h) Exceptions to EASA AD 2018-0112R1
(1) Where EASA AD 2018-0112R1 requires compliance in terms of
flight hours (FH), this AD requires using hours time-in-service
(TIS).
(2) Where EASA AD 2018-0112R1 refers to FH accumulated by a part
since new (first installation on a helicopter) or since overhaul,
this AD requires using total hours TIS.
(3) Where EASA AD 2018-0112R1 refers to its effective date; May
10, 2016 (the effective date of EASA AD 2016-0087, dated May 3,
2016); July 28, 2016 (the effective date of EASA AD 2016-0140, dated
July 14, 2016); or September 11, 2017 (the effective date of EASA AD
2017-0160, dated August 28, 2017), this AD requires using the
effective date of this AD.
(4) Where EASA AD 2018-0112R1 requires the compliance time of
during an ``after the last flight (ALF) of the day inspection,''
this AD requires the compliance time of before the first flight of
the day.
(5) Where the service information referenced in EASA AD 2018-
0112R1 specifies using a magnifying glass, this AD requires using a
5X or higher power magnifying glass.
(6) Where the service information referenced in EASA AD 2018-
0112R1 specifies discarding parts, this AD requires removing those
parts from service.
(7) Where paragraph (2) of EASA AD 2018-0112R1 requires
compliance within 30 FH after 10 May 2016 (the effective date of
EASA AD 2016-0087, dated May 3, 2016), or at the first MR damper
removal, whichever occurs first, for a MR damper that has
accumulated 300 or more FH, this AD requires compliance within 30
hours TIS after the effective date of this AD for a MR damper that
has accumulated 300 or more total hours TIS.
(8) This AD does not require the actions required by paragraph
(3) of EASA AD 2018-0112R1.
(9) Where paragraph (8) of EASA AD 2018-0112R1 refers to having
a serial number (S/N) specified in Part V of FHD BT 139-450, this AD
requires the actions of that paragraph for helicopters with an MR
damper part number (P/N) 3G6220V01351 or 3G6220V01352 with an S/N up
to MCR8086 inclusive, installed, that has accumulated less than 600
total hours TIS.
(10) Where paragraph (10) of EASA AD 2018-0112R1 refers to
having an S/N specified in in Part VII of FHD BT 139-450, this AD
requires the actions of that paragraph for helicopters with:
(i) MR damper P/N 3G6220V01351 or 3G6220V01352 with an S/N up to
MCR8764 inclusive, and with rod end P/N M006-01H004-041, -045, or -
053, installed, except MR dampers confirmed of having 60-80 Nm
applied and MR dampers marked with ``BT 139-446 Part II'' or ``BT
139-446 Part III'' on the logcard; or
(ii) MR damper P/N 3G6220V01351 or 3G6220V01352 that has had the
damper rod end assembly removed before the issuance of ``BT 139-
446'' installed, even if it has an S/N higher than MCR8764 or it has
been confirmed of having 60-80 Nm applied.
Note 1 to paragraph (h)(10): MR dampers confirmed of having 60-
80 Nm applied are listed in Table 1 (two pages) of Annex A, of
Leonardo Helicopters Alert Service Bulletin No. 139-450, Revision D,
dated May 28, 2019.
(11) Where paragraph (10) of EASA AD 2018-0112R1 requires a
torque check, this AD requires a torque inspection.
(12) Where the service information referenced in paragraph (10)
of EASA AD 2018-0112R1 specifies making sure that there are not
scratches or dents on the rod end, this AD requires, before further
flight, removing the rod end from service if there is a scratch or
dent on the rod end.
(13) Where paragraph (12) of EASA AD 2018-0112R1 requires
contacting Leonardo and replacing the MR damper with a serviceable
part, this AD does not. This AD requires the following:
(i) If there is a crack in an MR damper body end, before further
flight, replace the MR damper.
(ii) If there is a crack in an MR damper rod end, before further
flight, remove the MR damper rod end from service.
(iii) If there is damage in any teeth of a rod end broached ring
nut or damper piston slot, or if the engagement or alignment is not
correct, before further flight, remove the rod end broached ring nut
from service.
(14) Paragraph (13) of EASA AD 2018-0112R1 requires
accomplishing the applicable corrective action(s) ``as specified in,
and in accordance with, the instructions of FHD BT 139-450 or FHD BT
139-452, as applicable,'' except where:
(i) If there is any bearing seat rotation or misaligned slippage
mark in the MR damper rod end, this AD requires, before further
flight, removing the MR damper rod end from service.
(ii) If the MR damper rod end torque value is more than 30.0 Nm
(265.5 in lb), this AD requires, before further flight, removing the
MR damper rod end from service.
(iii) If any MR damper anti-rotation block dimension measurement
exceeds allowable limits, this AD requires, before further flight,
removing the anti-rotation block from service.
(15) This AD does not mandate compliance with the ``Remarks''
section of EASA AD 2018-0112R1.
[[Page 70975]]
(i) Parts Prohibition
As of the effective date of this AD, do not install an MR damper
rod end P/N M006-01H004-041, M006-01H004-045, or M006-01H004-053 on
any helicopter, unless it is marked with a black dot indicating that
it has passed inspections specified by Leonardo Helicopters BT 139-
450.
(j) No Reporting Requirement
Although the service information referenced in EASA AD 2018-
0112R1 specifies to submit certain information to the manufacturer,
this AD does not include that requirement.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, International Validation Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the International Validation Branch, send
it to the attention of the person identified in paragraph (l)(1) of
this AD. Information may be emailed to: [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.
(l) Related Information
(1) For more information about this AD, contact Matt Fuller, AD
Program Manager, General Aviation & Rotorcraft Unit, Airworthiness
Products Section, Operational Safety Branch, FAA, 10101 Hillwood
Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email
[email protected].
(2) Leonardo Helicopters Alert Service Bulletin No. 139-450,
Revision D, dated May 28, 2019, which is not incorporated by
reference, contains additional information about the subject of this
AD. 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://customerportal.leonardocompany.com/en-US/. You may view this
referenced service information at the contact information specified
in paragraph (m)(4) of this AD.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) European Aviation Safety Agency (now European Union Aviation
Safety Agency) (EASA) AD 2018-0112R1, dated June 4, 2018.
(ii) [Reserved]
(3) For EASA AD 2018-0112R1, contact EASA, Konrad-Adenauer-Ufer
3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; internet www.easa.europa.eu. You may find the
EASA material 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 at https://www.regulations.gov by searching
for and locating Docket No. FAA-2020-0283.
(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 November 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-26973 Filed 12-13-21; 8:45 am]
BILLING CODE 4910-13-P
