Airworthiness Directives; Airbus Helicopters, 72829-72833 [2021-27625]
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Federal Register / Vol. 86, No. 244 / Thursday, December 23, 2021 / Rules and Regulations
Engineer, General Aviation & Rotorcraft
Section, International Validation Branch,
FAA, 901 Locust, Room 301, Kansas City,
MO 64106; phone: (816) 329–4165; fax: (816)
329–4090; email: jim.rutherford@faa.gov.
(2) Refer to European Union Aviation
Safety Agency (EASA) AD 2020–0056, dated
March 13, 2020, for more information. You
may examine the EASA AD in the AD docket
at https://www.regulations.gov by searching
for and locating Docket No. FAA–2021–0792.
(j) 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) Solo Kleinmotoren GmbH Service
Bulletin No. 4600–11, Ausgabe 1 (English
translation: Issue 1), dated August 19, 2019.
Note 1 to paragraph (j)(2)(i): This service
information contains German to English
translation. EASA used the English
translation in referencing the document from
Stemme AG. For enforceability purposes, the
FAA will cite the service information in
English as it appears on the document.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Solo Kleinmotoren GmbH,
Postfach 600152, D71050 Sindelfingen,
Germany; phone: +49 703 1301–0; fax: +49
703 1301–136; email: aircraft@sologermany.com; website: https://
aircraft.solo.global/gb/.
(4) You may view this service information
at FAA, Airworthiness Products Section,
Operational Safety Branch, 901 Locust,
Kansas City, MO 64106. For information on
the availability of this material at the FAA,
call (816) 329–4148.
(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 November 18, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–27636 Filed 12–22–21; 8:45 am]
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BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0872; Project
Identifier MCAI–2021–00312–R; Amendment
39–21866; AD 2021–26–07]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2020–11–
05, which applied to all Airbus
Helicopters Model EC120B helicopters.
AD 2020–11–05 required repetitive
inspections of the tail rotor (TR) hub
body for cracks and applicable
corrective actions if necessary, and
repetitive replacement of the attachment
bolts, washers, and nuts of the TR hub
body. This AD was prompted by a
report of recurrent loss of tightening
torque on several attachment bolts on
the TR hub body. This AD retains
certain requirements of AD 2020–11–05,
adds repetitive inspections, requires
additional corrective actions, and
updates applicable service information.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective January 27,
2022.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 27, 2022.
ADDRESSES: For service information
identified in this final rule, contact
Airbus Helicopters, 2701 North 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
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. It is also available
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–00872.
SUMMARY:
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0872; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
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Monday through Friday, except Federal
holidays. The AD docket contains this
final rule, the European Union Aviation
Safety Agency (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:
Andrea Jimenez, Aerospace Engineer,
COS Program Management Section,
Operational Safety Branch, Compliance
& Airworthiness Division, FAA, 1600
Stewart Ave., Suite 410, Westbury, NY
11590; telephone (516) 228–7330; email
andrea.jimenez@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2020–11–05,
Amendment 39–21130 (85 FR 31042,
May 22, 2020), (AD 2020–11–05). AD
2020–11–05 applied to Airbus
Helicopters Model EC120B helicopters,
all serial numbers. The NPRM
published in the Federal Register on
October 8, 2021 (86 FR 56220). In the
NPRM, the FAA proposed to retain
some of the requirements of AD 2020–
11–05, and proposed to require, within
15 hours time-in-service (TIS) or 7 days,
whichever occurs first, performing
repetitive inspections of the TR hub
body for a crack and depending on the
inspection results, removing the affected
parts from service. The NPRM also
proposed to require inspecting the TR
spline flange for corrosion, impacts,
fretting, wear, and a crack and
depending on the inspection results,
removing the TR splined flange from
service. For helicopters with 9,000 or
more total hours TIS or with unknown
total hours TIS, the NPRM proposed to
require, within 15 hours TIS or 7 days,
whichever occurs first, and thereafter at
intervals not to exceed 1,000 hours TIS,
removing from service any bolt, washer,
and nut installed on the TR hub body,
replacing them with airworthy parts,
inspecting the TR splined flange, and
depending on the inspection results,
removing the TR splined flange from
service.
Additionally, the NPRM proposed to
require, for helicopters with less than
9,000 total hours TIS, within 1,000
hours TIS or before accumulating 9,000
total hours TIS, whichever occurs first,
and thereafter at intervals not to exceed
1,000 hours TIS, removing from service
any bolt, washer, and nut installed on
the TR hub body replacing them with
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Federal Register / Vol. 86, No. 244 / Thursday, December 23, 2021 / Rules and Regulations
airworthy parts, inspecting the TR
splined flange, and depending on the
inspection results, removing the TR
splined flange from service. Finally, the
NPRM proposed to prohibit the
installation of a certain part-numbered
TR hub body unless certain actions have
been accomplished.
The NPRM was prompted by EASA
AD 2021–0069, dated March 11, 2021
(EASA AD 2021–0069), 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, Model
EC120 B helicopters, all serial numbers.
EASA advises that an inspection of the
TR hub body revealed a recurring loss
of tightening torque on several
attachment bolts. This condition, if not
addressed, could result in cracking and
potential loss of the TR drive and
consequent loss of yaw control of the
helicopter.
Accordingly, EASA AD 2021–0069
retains the requirements of EASA AD
2019–0272R1, dated November 18, 2019
(EASA AD 2019–0272R1), which
prompted AD 2020–11–05, and requires
additional repetitive detailed
inspections of the interface between the
TR hub body part number
C642A0100103 and the splined flange.
Depending on the inspection results,
EASA AD 2021–0069 requires
accomplishment of applicable corrective
actions.
Discussion of Final Airworthiness
Directive
Comments
The FAA received no comments on
the NPRM or on the determination of
the costs.
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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. Except
for minor editorial changes, this AD is
adopted as proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Airbus Helicopters
Emergency Alert Service Bulletin
05A020, Revision 2, dated February 8,
2021. This service information specifies
procedures for repetitive inspections of
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the TR hub body for cracks and the TR
spline flange for cracks and fretting and
the appropriate corrective actions.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Differences Between This AD and EASA
AD 2021–0069
EASA AD 2021–0069 uses flight
hours (FH) for certain compliance times,
whereas this AD uses hours TIS. EASA
AD 2021–0069 retains the compliance
time of November 1, 2019 for certain
actions, which is the effective date of
EASA AD 2019–0272R1, whereas this
AD requires compliance in terms of the
effective date of this AD.
Where Note 1 of EASA AD 2021–0069
allows a non-cumulative tolerance of
100 FH to be applied to the compliance
times for the initial replacement of
bolts, washers, and nuts (Table 1 of
EASA AD 2021–0069) to allow for
synchronization of the required
inspections with other maintenance
tasks, this AD does not allow a noncumulative tolerance to be applied to
the compliance times.
Costs of Compliance
The FAA estimates that this AD
affects 89 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.
Visually inspecting each TR hub body
for a crack takes about 0.25 work-hour
for an estimated cost of $22 per
inspection and $1,958 for the U.S. fleet
per inspection.
Visually inspecting each TR spline
flange for corrosion, impacts, fretting,
wear, and a crack takes about 0.25 workhour for an estimated cost of $22 per
inspection and $1,958 for the U.S. fleet
per inspection.
Replacing a TR hub body takes about
2 work-hours and parts would cost
about $16,417 for an estimated cost of
$16,587 per TR hub body replacement.
Replacing a TR spline flange takes
about 0.5 work-hour and parts would
cost about $2,950 for an estimated cost
of $2,993 per TR spline flange
replacement.
Replacing a bolt, washer, and nut
takes about 0.5 work-hour and parts
would cost about $68 for an estimated
cost of $111 per replacement.
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
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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.
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:
a. Removing Airworthiness Directive
2020–11–05, Amendment 39–21130 (85
FR 31042, May 22, 2020); and
■ b. Adding the following new
airworthiness directive:
■
■
2021–26–07 Airbus Helicopters:
Amendment 39–21866; Docket No.
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(a) Effective Date
This airworthiness directive (AD) is
effective January 27, 2022.
(b) Affected ADs
This AD replaces AD 2020–11–05,
Amendment 39–21130 (85 FR 31042, May 22,
2020) (AD 2020–11–05).
(c) Applicability
This AD applies to Airbus Helicopters
Model EC120B helicopters, certificated in
any category, all serial numbers.
(d) Subject
Joint Aircraft Service Component (JASC)
Code: 6400, Tail rotor system.
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(e) Unsafe Condition
This AD was prompted by a report of
recurrent loss of tightening torque on several
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19:16 Dec 22, 2021
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Within 15 hours time-in-service (TIS) or
7 days, whichever occurs first after the
effective date of this AD, and thereafter at
intervals not to exceed 15 hours TIS, using
a light source and mirror, visually inspect TR
hub body part number (P/N) C642A0100103
for a crack in the entire inspection area
depicted in Figure 1 of Airbus Helicopters
Emergency Alert Service Bulletin 05A020
Revision 2, dated February 8, 2021. If there
is a crack, before further flight, perform the
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actions in paragraphs (g)(1)(i) and (ii) of this
AD.
(i) Remove the TR hub body and each bolt,
washer, and nut installed on the TR hub
body from service and replace with airworthy
parts.
(ii) Inspect the TR splined flange for
corrosion, impacts, fretting, wear, and a crack
in the areas identified in Figure 2 to
paragraph (g)(1)(ii) of this AD. If the
condition of the part (including corrosion,
impacts, fretting, wear, or cracks) exceeds the
criteria as specified in Figure 1 to paragraph
(g)(1)(ii) of this AD, before further flight,
remove the splined flange from service and
replace with an airworthy part.
Note 1 to paragraph (g)(1)(ii): You may
refer to ‘‘Detailed Check—Splined Flange,’’
Task 64–21–00, 6–5, Airbus Aircraft
Maintenance Manual (AMM), dated October
15, 2020, which pertains to the TR splined
flange inspection.
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attachment bolts on the tail rotor (TR) hub
body. The FAA is issuing this AD to detect
cracking and fretting, which if not addressed,
could result in potential loss of the TR drive
and consequent loss of yaw control of the
helicopter.
FAA–2021–0872; Project Identifier
MCAI–2021–00312–R.
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BILLING CODE 4910–13–C
(2) For helicopters with 9,000 or more total
hours TIS, or with unknown total hours TIS,
within 15 hours TIS or 7 days, whichever
occurs first after the effective date of this AD,
and thereafter at intervals not to exceed 1,000
hours TIS, remove each bolt, washer, and nut
installed on the TR hub body from service
and replace with airworthy parts and perform
the actions in paragraph (g)(1)(ii) of this AD.
(3) For helicopters with less than 9,000
total hours TIS, within 1,000 hours TIS or
before accumulating 9,000 total hours TIS,
whichever occurs first after the effective date
of this AD, and thereafter at intervals not to
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exceed 1,000 hours TIS, remove each bolt,
washer, and nut installed on the TR hub
body from service and replace with airworthy
parts and perform the actions in paragraph
(g)(1)(ii) of this AD.
(4) As of the effective date of this AD, do
not install TR hub body P/N C642A0100103
on any helicopter, unless the actions of
paragraph (g)(1) of this AD have been
accomplished.
(h) Special Flight Permits
A special flight permit may be permitted
provided that there are no passengers
onboard.
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(i) 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 (j)(1) of this AD.
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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.
(j) Related Information
(1) For more information about this AD,
contact Andrea Jimenez, Aerospace Engineer,
COS Program Management Section,
Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 1600 Stewart
Ave., Suite 410, Westbury, NY 11590;
telephone (516) 228–7330; email
andrea.jimenez@faa.gov.
(2) Service information identified in this
AD, is available at the contact information
specified in paragraphs (k)(3) and (4) of this
AD.
(3) The subject of this AD is addressed in
European Union Aviation Safety Agency
(EASA) AD 2021–0069, dated March 11,
2021. You may view the EASA AD on the
internet at https://www.regulations.gov in
Docket No. FAA–2021–0872.
(k) 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 05A020, Revision 2, dated
February 8, 2021.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Airbus Helicopters, 2701
North 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 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.
(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 9, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–27625 Filed 12–22–21; 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–2021–0728; Project
Identifier MCAI–2020–00656–R; Amendment
39–21867; AD 2021–26–08]
RIN 2120–AA64
Airworthiness Directives; Bell Textron
Canada Limited Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Bell Textron Canada Limited Model
206, 206A, 206A–1, 206B, 206B–1,
206L, 206L–1, 206L–3, and 206L–4
helicopters. This AD was prompted by
reports of cracked or missing nuts on
the tail rotor drive shaft (TRDS) disc
pack (Thomas) couplings. This AD
requires removing certain nuts from
service, installing newly designed nuts,
and applying a specific torque and a
torque stripe to each newly installed
nut. This AD then requires, after the
installation of each newly designed nut,
inspecting the torque and, depending on
the inspection results, either applying a
torque stripe or performing further
inspections and removing certain parts
from service. Finally, this AD prohibits
installing any affected nut on any TRDS
Thomas coupling. The FAA is issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective January 27,
2022.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of January 27, 2022.
ADDRESSES: For service information
identified in this final rule, contact Bell
Textron Canada Limited, 12,800 Rue de
l’Avenir, Mirabel, Quebec J7J 1R4,
Canada; telephone 1–450–437–2862 or
1–800–363–8023; fax 1–450–433–0272;
email productsupport@bellflight.com; or
at https://www.bellflight.com/support/
contact-support. 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. 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 at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0728.
SUMMARY:
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72833
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0728; 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 Transport Canada 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, 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.
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 Bell Textron Canada Limited
Model 206, 206A, 206A–1, 206B, 206B–
1, 206L, 206L–1, 206L–3, and 206L–4
helicopters with nut part number (P/N)
MS21042L4 or P/N MS21042L5
installed on the TRDS Thomas
couplings. The NPRM published in the
Federal Register on September 14, 2021
(86 FR 51038). In the NPRM, the FAA
proposed to require, within 600 hours
time-in-service (TIS) after the effective
date of this AD, removing each affected
nut from service, installing a newly
designed nut, and applying a specific
torque and a torque stripe to each newly
installed nut. The NPRM also proposed
to require, within 25 hours TIS after
installation of each newly designed nut,
inspecting the torque of each nut, and
depending on the results of the
inspection, further inspections and
removing certain parts from service.
Finally, the NPRM proposed to prohibit
installing any affected nut on any TRDS
Thomas coupling.
The NPRM was prompted by a series
of ADs issued by Transport Canada,
which is the aviation authority for
Canada. Initially, Transport Canada
issued Canadian AD CF–2019–34, dated
September 25, 2019 (Transport Canada
AD CF–2019–34), to correct an unsafe
condition for Bell Helicopter Textron
Canada Limited (now Bell Textron
Canada Limited) Model 206, 206A,
206A–1, 206B, 206B–1, 206L, 206L–1,
206L–3, and 206L–4 helicopters, all
serial numbers. Transport Canada AD
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]]>Agencies
[Federal Register Volume 86, Number 244 (Thursday, December 23, 2021)]
[Rules and Regulations]
[Pages 72829-72833]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-27625]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0872; Project Identifier MCAI-2021-00312-R;
Amendment 39-21866; AD 2021-26-07]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2020-11-
05, which applied to all Airbus Helicopters Model EC120B helicopters.
AD 2020-11-05 required repetitive inspections of the tail rotor (TR)
hub body for cracks and applicable corrective actions if necessary, and
repetitive replacement of the attachment bolts, washers, and nuts of
the TR hub body. This AD was prompted by a report of recurrent loss of
tightening torque on several attachment bolts on the TR hub body. This
AD retains certain requirements of AD 2020-11-05, adds repetitive
inspections, requires additional corrective actions, and updates
applicable service information. The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective January 27, 2022.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 27,
2022.
ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, 2701 North 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 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. It is also available at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2021-00872.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0872; 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
European Union Aviation Safety Agency (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: Andrea Jimenez, Aerospace Engineer,
COS Program Management Section, Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY
11590; telephone (516) 228-7330; email [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2020-11-05, Amendment 39-21130 (85 FR
31042, May 22, 2020), (AD 2020-11-05). AD 2020-11-05 applied to Airbus
Helicopters Model EC120B helicopters, all serial numbers. The NPRM
published in the Federal Register on October 8, 2021 (86 FR 56220). In
the NPRM, the FAA proposed to retain some of the requirements of AD
2020-11-05, and proposed to require, within 15 hours time-in-service
(TIS) or 7 days, whichever occurs first, performing repetitive
inspections of the TR hub body for a crack and depending on the
inspection results, removing the affected parts from service. The NPRM
also proposed to require inspecting the TR spline flange for corrosion,
impacts, fretting, wear, and a crack and depending on the inspection
results, removing the TR splined flange from service. For helicopters
with 9,000 or more total hours TIS or with unknown total hours TIS, the
NPRM proposed to require, within 15 hours TIS or 7 days, whichever
occurs first, and thereafter at intervals not to exceed 1,000 hours
TIS, removing from service any bolt, washer, and nut installed on the
TR hub body, replacing them with airworthy parts, inspecting the TR
splined flange, and depending on the inspection results, removing the
TR splined flange from service.
Additionally, the NPRM proposed to require, for helicopters with
less than 9,000 total hours TIS, within 1,000 hours TIS or before
accumulating 9,000 total hours TIS, whichever occurs first, and
thereafter at intervals not to exceed 1,000 hours TIS, removing from
service any bolt, washer, and nut installed on the TR hub body
replacing them with
[[Page 72830]]
airworthy parts, inspecting the TR splined flange, and depending on the
inspection results, removing the TR splined flange from service.
Finally, the NPRM proposed to prohibit the installation of a certain
part-numbered TR hub body unless certain actions have been
accomplished.
The NPRM was prompted by EASA AD 2021-0069, dated March 11, 2021
(EASA AD 2021-0069), 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, Model
EC120 B helicopters, all serial numbers. EASA advises that an
inspection of the TR hub body revealed a recurring loss of tightening
torque on several attachment bolts. This condition, if not addressed,
could result in cracking and potential loss of the TR drive and
consequent loss of yaw control of the helicopter.
Accordingly, EASA AD 2021-0069 retains the requirements of EASA AD
2019-0272R1, dated November 18, 2019 (EASA AD 2019-0272R1), which
prompted AD 2020-11-05, and requires additional repetitive detailed
inspections of the interface between the TR hub body part number
C642A0100103 and the splined flange. Depending on the inspection
results, EASA AD 2021-0069 requires accomplishment of applicable
corrective actions.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the NPRM 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. Except for minor editorial changes,
this AD is adopted as proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Airbus Helicopters Emergency Alert Service
Bulletin 05A020, Revision 2, dated February 8, 2021. This service
information specifies procedures for repetitive inspections of the TR
hub body for cracks and the TR spline flange for cracks and fretting
and the appropriate corrective actions.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES
section.[FEDREG][VOL]*[/VOL][NO]*[/NO][DATE]*[/
DATE][RULES][RULE][PREAMB][AGENCY]*[/AGENCY][SUBJECT]*[/SUBJECT][/
PREAMB][SUPLINF][HED]*[/HED]
Differences Between This AD and EASA AD 2021-0069
EASA AD 2021-0069 uses flight hours (FH) for certain compliance
times, whereas this AD uses hours TIS. EASA AD 2021-0069 retains the
compliance time of November 1, 2019 for certain actions, which is the
effective date of EASA AD 2019-0272R1, whereas this AD requires
compliance in terms of the effective date of this AD.
Where Note 1 of EASA AD 2021-0069 allows a non-cumulative tolerance
of 100 FH to be applied to the compliance times for the initial
replacement of bolts, washers, and nuts (Table 1 of EASA AD 2021-0069)
to allow for synchronization of the required inspections with other
maintenance tasks, this AD does not allow a non-cumulative tolerance to
be applied to the compliance times.
Costs of Compliance
The FAA estimates that this AD affects 89 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.
Visually inspecting each TR hub body for a crack takes about 0.25
work-hour for an estimated cost of $22 per inspection and $1,958 for
the U.S. fleet per inspection.
Visually inspecting each TR spline flange for corrosion, impacts,
fretting, wear, and a crack takes about 0.25 work-hour for an estimated
cost of $22 per inspection and $1,958 for the U.S. fleet per
inspection.
Replacing a TR hub body takes about 2 work-hours and parts would
cost about $16,417 for an estimated cost of $16,587 per TR hub body
replacement.
Replacing a TR spline flange takes about 0.5 work-hour and parts
would cost about $2,950 for an estimated cost of $2,993 per TR spline
flange replacement.
Replacing a bolt, washer, and nut takes about 0.5 work-hour and
parts would cost about $68 for an estimated cost of $111 per
replacement.
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.
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 2020-11-05, Amendment 39-21130 (85
FR 31042, May 22, 2020); and
0
b. Adding the following new airworthiness directive:
2021-26-07 Airbus Helicopters: Amendment 39-21866; Docket No.
[[Page 72831]]
FAA-2021-0872; Project Identifier MCAI-2021-00312-R.
(a) Effective Date
This airworthiness directive (AD) is effective January 27, 2022.
(b) Affected ADs
This AD replaces AD 2020-11-05, Amendment 39-21130 (85 FR 31042,
May 22, 2020) (AD 2020-11-05).
(c) Applicability
This AD applies to Airbus Helicopters Model EC120B helicopters,
certificated in any category, all serial numbers.
(d) Subject
Joint Aircraft Service Component (JASC) Code: 6400, Tail rotor
system.
(e) Unsafe Condition
This AD was prompted by a report of recurrent loss of tightening
torque on several attachment bolts on the tail rotor (TR) hub body.
The FAA is issuing this AD to detect cracking and fretting, which if
not addressed, could result in potential loss of the TR drive and
consequent loss of yaw control of the helicopter.
(f) Compliance[FEDREG][VOL]*[/VOL][NO]*[/NO][DATE]*[/
DATE][RULES][RULE][PREAMB][AGENCY]*[/AGENCY][SUBJECT]*[/SUBJECT][/
PREAMB][SUPLINF][HED]*[/HED]
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Within 15 hours time-in-service (TIS) or 7 days, whichever
occurs first after the effective date of this AD, and thereafter at
intervals not to exceed 15 hours TIS, using a light source and
mirror, visually inspect TR hub body part number (P/N) C642A0100103
for a crack in the entire inspection area depicted in Figure 1 of
Airbus Helicopters Emergency Alert Service Bulletin 05A020 Revision
2, dated February 8, 2021. If there is a crack, before further
flight, perform the actions in paragraphs (g)(1)(i) and (ii) of this
AD.
(i) Remove the TR hub body and each bolt, washer, and nut
installed on the TR hub body from service and replace with airworthy
parts.
(ii) Inspect the TR splined flange for corrosion, impacts,
fretting, wear, and a crack in the areas identified in Figure 2 to
paragraph (g)(1)(ii) of this AD. If the condition of the part
(including corrosion, impacts, fretting, wear, or cracks) exceeds
the criteria as specified in Figure 1 to paragraph (g)(1)(ii) of
this AD, before further flight, remove the splined flange from
service and replace with an airworthy part.
Note 1 to paragraph (g)(1)(ii): You may refer to ``Detailed
Check--Splined Flange,'' Task 64-21-00, 6-5, Airbus Aircraft
Maintenance Manual (AMM), dated October 15, 2020, which pertains to
the TR splined flange inspection.
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(2) For helicopters with 9,000 or more total hours TIS, or with
unknown total hours TIS, within 15 hours TIS or 7 days, whichever
occurs first after the effective date of this AD, and thereafter at
intervals not to exceed 1,000 hours TIS, remove each bolt, washer,
and nut installed on the TR hub body from service and replace with
airworthy parts and perform the actions in paragraph (g)(1)(ii) of
this AD.
(3) For helicopters with less than 9,000 total hours TIS, within
1,000 hours TIS or before accumulating 9,000 total hours TIS,
whichever occurs first after the effective date of this AD, and
thereafter at intervals not to exceed 1,000 hours TIS, remove each
bolt, washer, and nut installed on the TR hub body from service and
replace with airworthy parts and perform the actions in paragraph
(g)(1)(ii) of this AD.
(4) As of the effective date of this AD, do not install TR hub
body P/N C642A0100103 on any helicopter, unless the actions of
paragraph (g)(1) of this AD have been accomplished.
(h) Special Flight Permits
A special flight permit may be permitted provided that there are
no passengers onboard.
(i) 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 (j)(1) of
this AD.
[[Page 72833]]
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.
(j) Related Information
(1) For more information about this AD, contact Andrea Jimenez,
Aerospace Engineer, COS Program Management Section, Operational
Safety Branch, Compliance & Airworthiness Division, FAA, 1600
Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228-
7330; email [email protected].
(2) Service information identified in this AD, is available at
the contact information specified in paragraphs (k)(3) and (4) of
this AD.
(3) The subject of this AD is addressed in European Union
Aviation Safety Agency (EASA) AD 2021-0069, dated March 11, 2021.
You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA-2021-0872.
(k) 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 the AD specifies otherwise.
(i) Airbus Helicopters Emergency Alert Service Bulletin 05A020,
Revision 2, dated February 8, 2021.
(ii) [Reserved]
(3) For service information identified in this AD, contact
Airbus Helicopters, 2701 North 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 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.
(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: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on December 9, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-27625 Filed 12-22-21; 8:45 am]
BILLING CODE 4910-13-P[FEDREG][VOL]*[/VOL][NO]*[/NO][DATE]*[/
DATE][RULES]
