Airworthiness Directives; Bell Textron Canada Limited Helicopters, 72833-72836 [2021-27645]
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Federal Register / Vol. 86, No. 244 / Thursday, December 23, 2021 / Rules and Regulations
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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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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CF–2019–34 advised of reports of
cracked or missing nuts at the TRDS
Thomas couplings, which could have
been caused by improper torque or
hydrogen embrittlement. This
condition, if not addressed, could result
in loss of the tail rotor and subsequent
loss of control of the helicopter.
After Transport Canada issued
Transport Canada AD CF–2019–34, it
was determined that helicopters
modified in accordance with
Supplemental Type Certificate (STC)
SH2750NM or Transport Canada STC
SH99–202, were not able to comply
with Transport Canada AD CF–2019–34.
Accordingly, Transport Canada issued
AD CF–2020–15, dated May 13, 2020
(Transport Canada AD CF–2020–15)
which supersedes Transport Canada AD
CF–2019–34, and contains a new
requirement for helicopters with STC
SH2750NM or Transport Canada STC
SH99–202 installed or models that have
been modified per Bell Service
Instruction BHT–206–SI–2052, Revision
1, dated October 14, 2010 (BHT–206–
SI–2052). Transport Canada advises for
certain model helicopters, the newly
designed nuts cannot be installed
because STC SH2750NM and Transport
Canada STC SH99–202 install a pulley
at the Thomas coupling location causing
insufficient clearance. Transport Canada
further advises for certain model
helicopters with STC SH2750NM or
Transport Canada STC SH99–202
installed, different part-numbered nuts
may be installed which were not
identified in the applicable service
information and are now required to be
replaced with a new part-numbered nut
that is not vulnerable to the unsafe
condition. Accordingly, Air Comm
Corporation, the STC holder for STC
SH2750NM, issued new service
information to address these additional
issues and provide newly developed
instructions which apply to certain
model helicopters with STC SH2750NM
or Transport Canada STC SH99–202
installed.
Additionally, Transport Canada
advises that BHT–206–SI–2052, which
is optional, specifies procedures for
Model 206L–1 and 206L–3 helicopters
to upgrade the airframe and systems and
also includes installation of the Model
206L–4 TRDS Thomas coupling.
According to Transport Canada, models
that have incorporated BHT–206–SI–
2052, with STC SH2750NM or
Transport Canada STC SH99–202
installed, will have the Model 206L–4
helicopter pulley configuration and are
subject to the Air Comm Corporation
service information.
Accordingly, Transport Canada AD
CF–2020–15 requires the replacement of
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the affected nuts with the newly
designed nuts at each TRDS Thomas
coupling.
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from
one commenter; Bell. Bell
recommended certain changes
pertaining to the torque limits applied
to each newly installed nut and the time
for performing the torque recheck. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Bell commented that the NPRM calls
for an initial torque of 50 in/lb to each
nut, whereas the Bell maintenance
manual requires an initial torque of 50–
70 in/lb to each nut. Additionally, Bell
explained that, as per its Standards
Practice Manual (BHT–ALL–SPM)
Chapter 2, tare torque must also be
taken into consideration for self-locking
hardware and that the total assembly
torque is the measured tare torque plus
the standard torque or specified torque.
Bell requested that the installation
torque in the AD be revised to read 50–
70 in/lb.
The FAA agrees that in this instance
the maximum initial torque limit and
the tare torque should be consistent
with Bell’s maintenance manuals and
has revised this AD accordingly.
Bell also commented that the NPRM
calls for the torque recheck to be
performed within 25 hours, whereas its
maintenance manual requires the torque
recheck between 10–25 hours. Bell
recommended that the torque recheck
be done within 25 hours TIS. The FAA
agrees with the comment but no changes
to this AD were necessary.
Conclusion
These helicopters have been approved
by the aviation authority of Canada and
are approved for operation in the United
States. Pursuant to the FAA’s bilateral
agreement with Canada, Transport
Canada, its technical representative, has
notified the FAA of the unsafe condition
described in its AD. The FAA reviewed
the relevant data, considered the
comments received, 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.
However, after the NPRM was
published, the FAA discovered that
costs were inadvertently excluded in the
NPRM; those costs, which are nominal,
are included in this final rule. Except
for minor editorial changes, the change
to the costs of compliance, and any
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other changes described previously, this
AD is adopted as proposed in the
NPRM. None of the changes will
significantly increase the economic
burden on any operator.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Bell Alert Service
Bulletin 206–19–136, dated August 27,
2019 for FAA-certificated Model 206,
206A-series, and 206B-series helicopters
and non FAA-certificated Model TH–67
helicopters and Bell Alert Service
Bulletin 206L–19–181, Revision A,
dated August 29, 2019 for Model 206L,
206L–1, 206L–3, and 206L–4
helicopters. This service information
specifies procedures for replacing the
affected nuts with the newly designed
corrosion-resistant nuts.
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.
Other Related Service Information
The FAA reviewed Air Comm
Corporation Service Bulletin SB 206EC–
092619, Revision NC, dated September
26, 2019, which also specifies
procedures for replacing the affected
nuts with the newly designed corrosionresistant nuts, but explains that affected
helicopters equipped with Air Comm
Corporation air conditioning systems
installed under STC SH2750NM use the
affected nut to attach a pulley onto the
TRDS, which causes clearance issues for
the nuts to be installed at the coupling.
Therefore, this service bulletin specifies
replacing the nut with a lower profile
nut.
The FAA also reviewed BHT–206–SI–
2052. This service information specifies
procedures to upgrade Model 206L–1
and 206L–3 helicopters to allow
operations at an increased internal gross
weight.
Differences Between This AD and the
Transport Canada AD
Transport Canada AD CF–2020–15
requires compliance within 600 hours
air time or within the next 24-months,
whichever occurs first, whereas this AD
requires compliance within 600 hours
TIS and an additional inspection within
25 hours TIS after installation of certain
nuts.
Costs of Compliance
The FAA estimates that this AD
affects 1,439 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.
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Replacing each affected nut with the
newly designed nut and applying torque
and a torque stripe will take about 4
work-hours, and parts will cost about
$75 for an estimated cost of $415 per
nut replacement and $597,185 per nut
replacement for the U.S. fleet.
Checking the torque, and if
applicable, applying a torque stripe, will
take a minimal amount of time and have
a nominal parts cost. If required,
inspecting each TRDS Thomas coupling,
and each bolt, nut, and washer for
elongated holes and fretting on the
fasteners will take about 0.5 work-hour
for an estimated cost of $43 per
inspection. Replacing each TRDS
Thomas coupling will take about 4
work-hours, and parts will cost about
$4,000 for an estimated cost of $4,340
per TRDS Thomas coupling
replacement. Replacing each nut will
take about 4 work-hours, and parts will
cost about $75 for an estimated cost of
$415 per nut replacement. Replacing a
bolt or washer will take a minimal
amount of time and parts will cost a
nominal amount.
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.
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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,
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(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:
■
2021–26–08 Bell Textron Canada Limited:
Amendment 39–21867; Docket No.
FAA–2021–0728; Project Identifier
MCAI–2020–00656–R.
(a) Effective Date
This airworthiness directive (AD) is
effective January 27, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bell Textron Canada
Limited Model 206, 206A, 206A–1, 206B,
206B–1, 206L, 206L–1, 206L–3, and 206L–4
helicopters, certificated in any category, with
nut part number (P/N) MS21042L4 or P/N
MS21042L5 installed on the tail rotor drive
shaft (TRDS) disc pack (Thomas) couplings.
Note 1 to paragraph (c): Helicopters with
an OH–58A designation are Model 206A–1
helicopters.
(d) Subject
Joint Aircraft Service Component (JASC)
Code: 6510, Tail Rotor Drive Shaft.
(e) Unsafe Condition
This AD was prompted by reports of
cracked or missing nuts installed on the
TRDS Thomas couplings. The FAA is issuing
this AD to prevent failure or loss of a nut on
the TRDS Thomas couplings. The unsafe
condition, if not addressed, could result in
loss of the tail rotor and subsequent loss of
control of the helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Required Actions
(1) Within 600 hours time-in-service (TIS)
after the effective date of this AD:
(i) For helicopters that have not been
modified by installing Supplemental Type
Certificate (STC) SH2750NM:
(A) Remove each nut P/N MS21042L4
installed on each TRDS Thomas coupling
from service, and replace with nut P/N
NAS9926–4L. The location of nut P/N
NAS9926–4L is depicted in Detail A Figure
1 of Bell Alert Service Bulletin (ASB) 206–
19–136, dated August 27, 2019 (ASB 206–19–
136) or Bell ASB 206L–19–181, Revision A,
dated August 29, 2019 (ASB 206L–19–181),
as applicable to your model helicopter.
(B) Apply a torque of 5.65–7.90 Nm (50–
70 in lb) plus tare torque to each nut installed
as required by paragraph (g)(1)(i)(A) of this
AD, and apply a torque stripe using torque
seal lacquer (C–049) or equivalent lacquer, as
shown in Figure 2 of ASB 206–19–136 or
ASB 206L–19–181, as applicable to your
model helicopter.
Note 2 to paragraph (g)(1)(i)(B): Torque
stripes are referred to as witness marks in
ASB 206–19–136 and ASB 206L–19–181.
(ii) For Bell Textron Canada Limited Model
206, 206A, 206A–1, 206B, 206B–1, and 206L
helicopters that have been modified by
installing STC SH2750NM and Model 206L–
1 and 206L–3 helicopters that have been
modified by installing STC SH2750NM but
have not been modified by accomplishing
Bell Service Instruction BHT–206–SI–2052,
Revision 1, dated October 14, 2010 (BHT–
206–SI–2052):
(A) Remove each nut P/N MS21042L4
installed on each TRDS Thomas coupling
from service, except for nuts P/N MS21042L4
installed on the forward short TRDS Thomas
coupling, and replace with nut P/N
NAS9926–4L. The location of nut P/N
NAS9926–4L is depicted in Detail A Figure
1 of ASB 206–19–136 or ASB 206L–19–181
as applicable to your model helicopter.
(B) Remove each nut P/N MS21042L4
installed on the forward short TRDS Thomas
coupling from service and replace with nut
P/N 90–132L4.
(C) For each nut installed as required by
paragraphs (g)(1)(ii)(A) and (B) of this AD,
apply a torque of 5.65–7.90 Nm (50–70 in lb)
plus tare torque to each nut and apply a
torque stripe using torque seal lacquer (C–
049) or equivalent lacquer, as shown in
Figure 2 of ASB 206–19–136 or ASB 206L–
19–181, as applicable to your model
helicopter.
(iii) For Bell Textron Canada Limited
Model 206L–1 and 206L–3 helicopters that
have been modified by installing STC
SH2750NM and have been modified by
accomplishing BHT–206–SI–2052:
(A) Remove each nut P/N MS21042L4
installed on each TRDS Thomas coupling
from service, except for nuts P/N MS21042L4
installed on the forward short TRDS Thomas
coupling, and replace with nut P/N
NAS9926–4L. The location of nut P/N
NAS9926–4L is depicted in Detail A Figure
1 of ASB 206L–19–181.
(B) Remove each nut P/N MS21042L4
installed on the forward short TRDS Thomas
coupling from service and replace with nut
P/N 90–132L4.
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(C) For each nut installed as required by
paragraphs (g)(1)(iii)(A) and (B) of this AD,
apply a torque of 5.65–7.90 Nm (50–70 in lb)
plus tare torque to each nut, and apply a
torque stripe using torque seal lacquer (C–
049) or equivalent lacquer, as shown in
Figure 2 of ASB 206L–19–181.
(iv) For Bell Textron Canada Limited
Model 206L–4 helicopters that have been
modified by installing STC SH2750NM:
(A) Remove each nut P/N MS21042L4
installed on each TRDS Thomas coupling
from service, except for nuts P/N MS21042L4
installed on the forward short TRDS Thomas
coupling, and replace with nut P/N
NAS9926–4L. The location of nut P/N
NAS9926–4L is depicted in Detail A Figure
1 of ASB 206L–19–181.
(B) Remove from service each nut P/N
MS21042L5 installed on the forward short
TRDS Thomas coupling and replace with nut
P/N 90–132L5.
(C) For each nut installed as required by
paragraphs (g)(1)(iv)(A) and (B) of this AD,
apply a torque of 5.65–7.90 Nm (50–70 in lb)
plus tare torque to each nut, and apply a
torque stripe using torque seal lacquer (C–
049) or equivalent lacquer, as shown in
Figure 2 of ASB 206L–19–181.
(2) Within 25 hours TIS after installation
of any nut P/N NAS9926–4L, P/N 90–132L4,
or P/N 90–132L5, as required by paragraphs
(g)(1)(i)(A), (ii)(A) and (B), (iii)(A) and (B), or
(iv)(A) and (B) of this AD, apply a torque of
5.65 Nm (50 in lb) to each nut.
(i) If the nut does not move, apply a torque
stripe using torque seal lacquer (C–049) or
equivalent lacquer, as shown in Figure 2 of
ASB 206–19–136 or ASB 206L–19–181, as
applicable to your model helicopter.
(ii) If any nut moves, inspect each TRDS
Thomas coupling and each bolt, nut, and
washer for elongated holes and fretting on
the fasteners. If any TRDS Thomas coupling
has an elongated hole, remove the TRDS
Thomas coupling from service. If any bolt,
nut, or washer has any fretting, remove the
affected part from service.
(3) As of the effective date of this AD, do
not install nut P/N MS21042L4 or
MS21042L5 on any TRDS Thomas coupling.
(h) 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 (i)(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.
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) Bell Service Instruction BHT–206–SI–
2052, Revision 1, dated October 14, 2010,
which is not incorporated by reference,
contains additional information about the
subject of this AD. This service information
is available at the contact information
specified in paragraphs (j)(3) and (4) of this
AD.
(3) The subject of this AD is addressed in
Transport Canada AD CF–2020–15, dated
May 13, 2020. You may view the Transport
Canada AD at https://www.regulations.gov in
Docket No. FAA–2021–0728.
(j) 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) Bell Alert Service Bulletin 206–19–136,
dated August 27, 2019.
(ii) Bell Alert Service Bulletin 206L–19–
181, Revision A, dated August 29, 2019.
(3) For Bell service information identified
in this AD, 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.
(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 12, 2021.
Ross Landes,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–27645 Filed 12–22–21; 8:45 am]
BILLING CODE 4910–13–P
19:16 Dec 22, 2021
Jkt 256001
PO 00000
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0716; Project
Identifier 2019–CE–023–AD; Amendment
39–21799; AD 2021–23–01]
RIN 2120–AA64
Airworthiness Directives; Stemme AG
Gliders
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Stemme AG Model Stemme S 12 gliders.
This AD was prompted by mandatory
continuing airworthiness information
(MCAI) issued by the aviation authority
of another country to identify and
correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as an airspeed
indicator (ASI) with speed markings
inconsistent with the approved and
published values. This AD requires
inspecting the ASI markings and,
depending on findings, either replacing
the ASI or amending the existing aircraft
flight manual (AFM) until the ASI is
replaced. The FAA is issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
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
STEMME AG, Flugplatzstrasse F2, Nr.
6–7, D–15344 Strausberg, Germany;
phone: +49 (0) 3341 3612–0; fax: +49 (0)
3341 3612–30; email: airworthiness@
stemme.de; website: https://
www.stemme.com. You may view this
service information at the 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. It is also
available at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0716.
DATES:
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0716; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
(i) Related Information
(1) For more information about this AD,
contact Matt Fuller, AD Program Manager,
VerDate Sep<11>2014
DEPARTMENT OF TRANSPORTATION
Frm 00058
Fmt 4700
Sfmt 4700
E:\FR\FM\23DER1.SGM
23DER1
Agencies
[Federal Register Volume 86, Number 244 (Thursday, December 23, 2021)]
[Rules and Regulations]
[Pages 72833-72836]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-27645]
-----------------------------------------------------------------------
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
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: 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 [email protected]; 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.
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 [email protected].
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
[[Page 72834]]
CF-2019-34 advised of reports of cracked or missing nuts at the TRDS
Thomas couplings, which could have been caused by improper torque or
hydrogen embrittlement. This condition, if not addressed, could result
in loss of the tail rotor and subsequent loss of control of the
helicopter.
After Transport Canada issued Transport Canada AD CF-2019-34, it
was determined that helicopters modified in accordance with
Supplemental Type Certificate (STC) SH2750NM or Transport Canada STC
SH99-202, were not able to comply with Transport Canada AD CF-2019-34.
Accordingly, Transport Canada issued AD CF-2020-15, dated May 13, 2020
(Transport Canada AD CF-2020-15) which supersedes Transport Canada AD
CF-2019-34, and contains a new requirement for helicopters with STC
SH2750NM or Transport Canada STC SH99-202 installed or models that have
been modified per Bell Service Instruction BHT-206-SI-2052, Revision 1,
dated October 14, 2010 (BHT-206-SI-2052). Transport Canada advises for
certain model helicopters, the newly designed nuts cannot be installed
because STC SH2750NM and Transport Canada STC SH99-202 install a pulley
at the Thomas coupling location causing insufficient clearance.
Transport Canada further advises for certain model helicopters with STC
SH2750NM or Transport Canada STC SH99-202 installed, different part-
numbered nuts may be installed which were not identified in the
applicable service information and are now required to be replaced with
a new part-numbered nut that is not vulnerable to the unsafe condition.
Accordingly, Air Comm Corporation, the STC holder for STC SH2750NM,
issued new service information to address these additional issues and
provide newly developed instructions which apply to certain model
helicopters with STC SH2750NM or Transport Canada STC SH99-202
installed.[FEDREG][VOL]*[/VOL][NO]*[/NO][DATE]*[/
DATE][RULES][RULE][PREAMB][AGENCY]*[/AGENCY][SUBJECT]*[/SUBJECT][/
PREAMB][SUPLINF][HED]*[/HED]
Additionally, Transport Canada advises that BHT-206-SI-2052, which
is optional, specifies procedures for Model 206L-1 and 206L-3
helicopters to upgrade the airframe and systems and also includes
installation of the Model 206L-4 TRDS Thomas coupling. According to
Transport Canada, models that have incorporated BHT-206-SI-2052, with
STC SH2750NM or Transport Canada STC SH99-202 installed, will have the
Model 206L-4 helicopter pulley configuration and are subject to the Air
Comm Corporation service information.
Accordingly, Transport Canada AD CF-2020-15 requires the
replacement of the affected nuts with the newly designed nuts at each
TRDS Thomas coupling.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from one commenter; Bell. Bell
recommended certain changes pertaining to the torque limits applied to
each newly installed nut and the time for performing the torque
recheck. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Bell commented that the NPRM calls for an initial torque of 50 in/
lb to each nut, whereas the Bell maintenance manual requires an initial
torque of 50-70 in/lb to each nut. Additionally, Bell explained that,
as per its Standards Practice Manual (BHT-ALL-SPM) Chapter 2, tare
torque must also be taken into consideration for self-locking hardware
and that the total assembly torque is the measured tare torque plus the
standard torque or specified torque. Bell requested that the
installation torque in the AD be revised to read 50-70 in/lb.
The FAA agrees that in this instance the maximum initial torque
limit and the tare torque should be consistent with Bell's maintenance
manuals and has revised this AD accordingly.
Bell also commented that the NPRM calls for the torque recheck to
be performed within 25 hours, whereas its maintenance manual requires
the torque recheck between 10-25 hours. Bell recommended that the
torque recheck be done within 25 hours TIS. The FAA agrees with the
comment but no changes to this AD were necessary.
Conclusion
These helicopters have been approved by the aviation authority of
Canada and are approved for operation in the United States. Pursuant to
the FAA's bilateral agreement with Canada, Transport Canada, its
technical representative, has notified the FAA of the unsafe condition
described in its AD. The FAA reviewed the relevant data, considered the
comments received, 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. However, after the NPRM was
published, the FAA discovered that costs were inadvertently excluded in
the NPRM; those costs, which are nominal, are included in this final
rule. Except for minor editorial changes, the change to the costs of
compliance, and any other changes described previously, this AD is
adopted as proposed in the NPRM. None of the changes will significantly
increase the economic burden on any operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Bell Alert Service Bulletin 206-19-136, dated
August 27, 2019 for FAA-certificated Model 206, 206A-series, and 206B-
series helicopters and non FAA-certificated Model TH-67 helicopters and
Bell Alert Service Bulletin 206L-19-181, Revision A, dated August 29,
2019 for Model 206L, 206L-1, 206L-3, and 206L-4 helicopters. This
service information specifies procedures for replacing the affected
nuts with the newly designed corrosion-resistant nuts.
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.
Other Related Service Information
The FAA reviewed Air Comm Corporation Service Bulletin SB 206EC-
092619, Revision NC, dated September 26, 2019, which also specifies
procedures for replacing the affected nuts with the newly designed
corrosion-resistant nuts, but explains that affected helicopters
equipped with Air Comm Corporation air conditioning systems installed
under STC SH2750NM use the affected nut to attach a pulley onto the
TRDS, which causes clearance issues for the nuts to be installed at the
coupling. Therefore, this service bulletin specifies replacing the nut
with a lower profile nut.
The FAA also reviewed BHT-206-SI-2052. This service information
specifies procedures to upgrade Model 206L-1 and 206L-3 helicopters to
allow operations at an increased internal gross weight.
Differences Between This AD and the Transport Canada AD
Transport Canada AD CF-2020-15 requires compliance within 600 hours
air time or within the next 24-months, whichever occurs first, whereas
this AD requires compliance within 600 hours TIS and an additional
inspection within 25 hours TIS after installation of certain nuts.
Costs of Compliance
The FAA estimates that this AD affects 1,439 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.
[[Page 72835]]
Replacing each affected nut with the newly designed nut and
applying torque and a torque stripe will take about 4 work-hours, and
parts will cost about $75 for an estimated cost of $415 per nut
replacement and $597,185 per nut replacement for the U.S. fleet.
Checking the torque, and if applicable, applying a torque stripe,
will take a minimal amount of time and have a nominal parts cost. If
required, inspecting each TRDS Thomas coupling, and each bolt, nut, and
washer for elongated holes and fretting on the fasteners will take
about 0.5 work-hour for an estimated cost of $43 per inspection.
Replacing each TRDS Thomas coupling will take about 4 work-hours, and
parts will cost about $4,000 for an estimated cost of $4,340 per TRDS
Thomas coupling replacement. Replacing each nut will take about 4 work-
hours, and parts will cost about $75 for an estimated cost of $415 per
nut replacement. Replacing a bolt or washer will take a minimal amount
of time and parts will cost a nominal amount.[FEDREG][VOL]*[/
VOL][NO]*[/NO][DATE]*[/DATE][RULES][RULE][PREAMB][AGENCY]*[/
AGENCY][SUBJECT]*[/SUBJECT][/PREAMB][SUPLINF][HED]*[/HED]
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 adding the following new airworthiness
directive:
2021-26-08 Bell Textron Canada Limited: Amendment 39-21867; Docket
No. FAA-2021-0728; Project Identifier MCAI-2020-00656-R.
(a) Effective Date
This airworthiness directive (AD) is effective January 27, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bell Textron Canada Limited Model 206, 206A,
206A-1, 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4 helicopters,
certificated in any category, with nut part number (P/N) MS21042L4
or P/N MS21042L5 installed on the tail rotor drive shaft (TRDS) disc
pack (Thomas) couplings.
Note 1 to paragraph (c): Helicopters with an OH-58A designation
are Model 206A-1 helicopters.
(d) Subject
Joint Aircraft Service Component (JASC) Code: 6510, Tail Rotor
Drive Shaft.
(e) Unsafe Condition
This AD was prompted by reports of cracked or missing nuts
installed on the TRDS Thomas couplings. The FAA is issuing this AD
to prevent failure or loss of a nut on the TRDS Thomas couplings.
The unsafe condition, if not addressed, could result in loss of the
tail rotor and subsequent loss of control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.[FEDREG][VOL]*[/VOL][NO]*[/NO][DATE]*[/
DATE][RULES][RULE][PREAMB][AGENCY]*[/AGENCY][SUBJECT]*[/SUBJECT][/
PREAMB][SUPLINF][HED]*[/HED]
(g) Required Actions
(1) Within 600 hours time-in-service (TIS) after the effective
date of this AD:
(i) For helicopters that have not been modified by installing
Supplemental Type Certificate (STC) SH2750NM:
(A) Remove each nut P/N MS21042L4 installed on each TRDS Thomas
coupling from service, and replace with nut P/N NAS9926-4L. The
location of nut P/N NAS9926-4L is depicted in Detail A Figure 1 of
Bell Alert Service Bulletin (ASB) 206-19-136, dated August 27, 2019
(ASB 206-19-136) or Bell ASB 206L-19-181, Revision A, dated August
29, 2019 (ASB 206L-19-181), as applicable to your model helicopter.
(B) Apply a torque of 5.65-7.90 Nm (50-70 in lb) plus tare
torque to each nut installed as required by paragraph (g)(1)(i)(A)
of this AD, and apply a torque stripe using torque seal lacquer (C-
049) or equivalent lacquer, as shown in Figure 2 of ASB 206-19-136
or ASB 206L-19-181, as applicable to your model helicopter.
Note 2 to paragraph (g)(1)(i)(B): Torque stripes are referred to
as witness marks in ASB 206-19-136 and ASB 206L-19-181.
(ii) For Bell Textron Canada Limited Model 206, 206A, 206A-1,
206B, 206B-1, and 206L helicopters that have been modified by
installing STC SH2750NM and Model 206L-1 and 206L-3 helicopters that
have been modified by installing STC SH2750NM but have not been
modified by accomplishing Bell Service Instruction BHT-206-SI-2052,
Revision 1, dated October 14, 2010 (BHT-206-SI-2052):
(A) Remove each nut P/N MS21042L4 installed on each TRDS Thomas
coupling from service, except for nuts P/N MS21042L4 installed on
the forward short TRDS Thomas coupling, and replace with nut P/N
NAS9926-4L. The location of nut P/N NAS9926-4L is depicted in Detail
A Figure 1 of ASB 206-19-136 or ASB 206L-19-181 as applicable to
your model helicopter.
(B) Remove each nut P/N MS21042L4 installed on the forward short
TRDS Thomas coupling from service and replace with nut P/N 90-132L4.
(C) For each nut installed as required by paragraphs
(g)(1)(ii)(A) and (B) of this AD, apply a torque of 5.65-7.90 Nm
(50-70 in lb) plus tare torque to each nut and apply a torque stripe
using torque seal lacquer (C-049) or equivalent lacquer, as shown in
Figure 2 of ASB 206-19-136 or ASB 206L-19-181, as applicable to your
model helicopter.
(iii) For Bell Textron Canada Limited Model 206L-1 and 206L-3
helicopters that have been modified by installing STC SH2750NM and
have been modified by accomplishing BHT-206-SI-2052:
(A) Remove each nut P/N MS21042L4 installed on each TRDS Thomas
coupling from service, except for nuts P/N MS21042L4 installed on
the forward short TRDS Thomas coupling, and replace with nut P/N
NAS9926-4L. The location of nut P/N NAS9926-4L is depicted in Detail
A Figure 1 of ASB 206L-19-181.
(B) Remove each nut P/N MS21042L4 installed on the forward short
TRDS Thomas coupling from service and replace with nut P/N 90-132L4.
[[Page 72836]]
(C) For each nut installed as required by paragraphs
(g)(1)(iii)(A) and (B) of this AD, apply a torque of 5.65-7.90 Nm
(50-70 in lb) plus tare torque to each nut, and apply a torque
stripe using torque seal lacquer (C-049) or equivalent lacquer, as
shown in Figure 2 of ASB 206L-19-181.
(iv) For Bell Textron Canada Limited Model 206L-4 helicopters
that have been modified by installing STC SH2750NM:
(A) Remove each nut P/N MS21042L4 installed on each TRDS Thomas
coupling from service, except for nuts P/N MS21042L4 installed on
the forward short TRDS Thomas coupling, and replace with nut P/N
NAS9926-4L. The location of nut P/N NAS9926-4L is depicted in Detail
A Figure 1 of ASB 206L-19-181.
(B) Remove from service each nut P/N MS21042L5 installed on the
forward short TRDS Thomas coupling and replace with nut P/N 90-
132L5.
(C) For each nut installed as required by paragraphs
(g)(1)(iv)(A) and (B) of this AD, apply a torque of 5.65-7.90 Nm
(50-70 in lb) plus tare torque to each nut, and apply a torque
stripe using torque seal lacquer (C-049) or equivalent lacquer, as
shown in Figure 2 of ASB 206L-19-181.
(2) Within 25 hours TIS after installation of any nut P/N
NAS9926-4L, P/N 90-132L4, or P/N 90-132L5, as required by paragraphs
(g)(1)(i)(A), (ii)(A) and (B), (iii)(A) and (B), or (iv)(A) and (B)
of this AD, apply a torque of 5.65 Nm (50 in lb) to each nut.
(i) If the nut does not move, apply a torque stripe using torque
seal lacquer (C-049) or equivalent lacquer, as shown in Figure 2 of
ASB 206-19-136 or ASB 206L-19-181, as applicable to your model
helicopter.
(ii) If any nut moves, inspect each TRDS Thomas coupling and
each bolt, nut, and washer for elongated holes and fretting on the
fasteners. If any TRDS Thomas coupling has an elongated hole, remove
the TRDS Thomas coupling from service. If any bolt, nut, or washer
has any fretting, remove the affected part from service.
(3) As of the effective date of this AD, do not install nut P/N
MS21042L4 or MS21042L5 on any TRDS Thomas coupling.
(h) 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 (i)(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.
(i) 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].[FEDREG][VOL]*[/VOL][NO]*[/NO][DATE]*[/
DATE][RULES][RULE][PREAMB][AGENCY]*[/AGENCY][SUBJECT]*[/SUBJECT][/
PREAMB][SUPLINF][HED]*[/HED]
(2) Bell Service Instruction BHT-206-SI-2052, Revision 1, dated
October 14, 2010, which is not incorporated by reference, contains
additional information about the subject of this AD. This service
information is available at the contact information specified in
paragraphs (j)(3) and (4) of this AD.
(3) The subject of this AD is addressed in Transport Canada AD
CF-2020-15, dated May 13, 2020. You may view the Transport Canada AD
at https://www.regulations.gov in Docket No. FAA-2021-0728.
(j) 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) Bell Alert Service Bulletin 206-19-136, dated August 27,
2019.
(ii) Bell Alert Service Bulletin 206L-19-181, Revision A, dated
August 29, 2019.
(3) For Bell service information identified in this AD, 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 [email protected]; or at https://www.bellflight.com/support/contact-support.
(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 12, 2021.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021-27645 Filed 12-22-21; 8:45 am]
BILLING CODE 4910-13-P[FEDREG][VOL]*[/VOL][NO]*[/NO][DATE]*[/
DATE][RULES]