Airworthiness Directives; Bell Textron Canada Limited, 51038-51041 [2021-19605]
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Federal Register / Vol. 86, No. 175 / Tuesday, September 14, 2021 / Proposed Rules
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
■ a. Removing Airworthiness Directive
2021–06–06, Amendment 39–21473 (86
FR 14366, March 16, 2021); and
■ b. Adding the following new
airworthiness directive:
■
Bell Textron Canada Limited: Docket No.
FAA–2021–0729; Project Identifier
MCAI–2021–00364–R.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) action by
October 29, 2021.
(b) Affected ADs
This AD replaces AD 2021–06–06,
Amendment 39–21473 (86 FR 14366, March
16, 2021) (AD 2021–06–06).
(c) Applicability
This AD applies to Bell Textron Canada
Limited Model 505 helicopters, serial
number (S/N) 65011 through 65347
inclusive, certificated in any category.
(d) Subject
Joint Aircraft Service Component (JASC)
Code: 6710, Main Rotor Control.
(e) Unsafe Condition
This AD was prompted by a report of a
cracked pilot collective stick and grip
assembly. The FAA is issuing this AD to
detect a cracked pilot collective stick and
grip assembly. The unsafe condition, if not
addressed, could result in failure of the pilot
collective stick and grip assembly and
subsequent loss of control of the helicopter.
tkelley on DSK125TN23PROD with PROPOSALS
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Before further flight after the effective
date of this AD, revise the Limitations section
of the existing Rotorcraft Flight Manual
(RFM) for your helicopter by inserting Bell
505 RFM Temporary Revision (TR) for Pilot
Collective (ASB 505–21–20), BHT–505–FM–
1, Temporary Revision (TR–6) or Bell 505
RFM TR for Pilot Collective (ASB 505–21–
20), BHT–505–FM–2, Temporary Revision
(TR–1), each dated March 3, 2021, as
applicable to your helicopter. Using a
different document with information
identical to the information for the ‘‘Flight
Crew’’ and ‘‘Configuration,’’ as applicable to
your helicopter, in the RFM TR specified in
this paragraph for your helicopter is
acceptable for compliance with the
requirements of this paragraph. This action
may be performed by the owner/operator
(pilot) holding at least a private pilot
certificate and must be entered into the
aircraft records showing compliance with
this AD in accordance with § 43.9(a)(1)
through (4) and § 91.417(a)(2)(v). The record
must be maintained as required by § 91.417,
§ 121.380, or § 135.439.
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(2) Before further flight after the effective
date of this AD, and thereafter at intervals not
to exceed 25 hours time-in-service (TIS):
(i) Remove the pilot collective stick and
grip assembly from the jackshaft assembly
and clean the areas specified in Figure 2 of
Bell Alert Service Bulletin 505–21–20,
Revision C, dated March 11, 2021 (ASB 505–
21–20 Rev C) with a clean cloth C–516C or
equivalent moistened with dry cleaning
solvent C–304 or equivalent.
(ii) Perform a fluorescent penetrant
inspection (FPI) for a crack by following the
Accomplishment Instructions, Part I,
paragraph 5. (but not paragraphs 5.a. and b.)
of ASB 505–21–20 Rev C. Perform this FPI
in the areas specified in Figure 2 of ASB 505–
21–20 Rev C. If there is a crack, before further
flight, remove the pilot collective stick and
grip assembly from service.
(3) Within 12 months after the effective
date of this AD, remove the pilot collective
stick tube from service and install pilot
collective stick tube part number (P/N)
M207–20M301–043 by following the
Accomplishment Instructions, Part II,
paragraphs 3. through 4. of ASB 505–21–20
Rev C except where this service information
specifies discarding parts, you are required to
remove those parts from service instead.
Thereafter, remove from service pilot
collective stick tube P/N M207–20M301–043
before it accumulates 300 total hours TIS
(4) Completing the actions required in
paragraph (g)(3) of this AD constitutes a
terminating action for the requirements in
paragraphs (g)(1) and (2) of this AD.
(5) As of the effective date of this AD, do
not install any pilot collective stick and grip
assembly on any helicopter unless the
actions required by paragraphs (g)(2) and
(g)(3) of this AD have been accomplished.
(6) As of the effective date of this AD, relief
under any Master Minimum Equipment List
or Minimum Equipment List for the Audio
Panel is prohibited when the aircraft is
operated with a single pilot.
(h) Credit for Previous Actions
If you performed an FPI of the pilot
collective stick and grip assembly before the
effective date of this AD using Bell Alert
Service Bulletin 505–21–20, dated February
20, 2021, Bell Alert Service Bulletin 505–21–
20, Revision A, dated February 26, 2021, or
Bell Alert Service Bulletin 505–21–20,
Revision B, dated March 3, 2021, you met the
before further flight FPI requirement of
paragraph (g)(2) of this AD.
(i) Special Flight Permits
A special flight permit to a maintenance
facility may be granted provided that:
(1) There are no passengers on-board,
(2) The helicopter is flown from the copilot
seat only, and
(3) The GMA (intercom) is operative.
(j) 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
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appropriate. If sending information directly
to the manager of the International Validation
Branch, send it to the attention of the person
identified in paragraph (k)(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.
(k) Related Information
(1) For more information about this AD,
contact Hal Jensen, Aerospace Engineer,
Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 950 L’Enfant
Plaza N SW, Washington, DC 20024;
telephone (202) 267–9167; email hal.jensen@
faa.gov.
(2) For service information identified in
this AD, contact Bell Textron Canada
Limited, 12,800 Rue de l’Avenir, Mirabel,
Quebec J7J1R4; 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/contactsupport. You may view this 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.
(3) The subject of this AD is addressed in
Transport Canada AD CF–2021–05R3, dated
March 19, 2021. You may view the Transport
Canada AD on the internet at https://
www.regulations.gov in Docket No. FAA–
2021–0729.
Issued on September 2, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–19608 Filed 9–13–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0728; Project
Identifier MCAI–2020–00656–R]
RIN 2120–AA64
Airworthiness Directives; Bell Textron
Canada Limited
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt 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 proposed AD was
SUMMARY:
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Federal Register / Vol. 86, No. 175 / Tuesday, September 14, 2021 / Proposed Rules
tkelley on DSK125TN23PROD with PROPOSALS
prompted by reports of cracked or
missing nuts on the tail rotor drive shaft
(TRDS) disc pack (Thomas) couplings.
This proposed AD would require
removing certain nuts from service,
installing newly designed nuts, and
applying a specific torque and a torque
stripe to each newly installed nut. This
proposed AD would then require, 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 proposed AD would
prohibit installing any affected nut on
any TRDS Thomas coupling.
The FAA is proposing this AD to
address the unsafe condition on these
products.
DATES: The FAA must receive comments
on this proposed AD by October 29,
2021.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE, Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays.
For service information identified in
this NPRM, 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 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.
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
NPRM, the Transport Canada AD, any
comments received, and other
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21:00 Sep 13, 2021
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information. The street address for
Docket Operations is listed above.
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:
FOR FURTHER INFORMATION CONTACT:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2021–0728; Project Identifier
MCAI–2020–00656–R’’ at the beginning
of your comments. The most helpful
comments reference a specific portion of
the proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend this proposal
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to 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.
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Any commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
Background
Transport Canada, which is the
aviation authority for Canada, has
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
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 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.
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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.
FAA’s Determination
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 the Transport Canada AD.
The FAA is proposing this AD after
evaluating all known relevant
information and determining that an
unsafe condition is likely to exist or
develop on other helicopters of the same
type design.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Bell Alert Service
Bulletin 206–19–136, dated August 27,
2019, and Bell Alert Service Bulletin
206L–19–181, Revision A, dated August
29, 2019. 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.
tkelley on DSK125TN23PROD with PROPOSALS
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
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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.
Proposed AD Requirements in This
NPRM
This proposed AD would require
within 600 hours time-in-service (TIS)
after the effective date of this AD,
removing from service each affected nut,
and installing a newly designed nut.
This proposed AD would also require
applying a specific torque and a torque
stripe to each newly installed nut. This
proposed AD would also 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, this
proposed AD would require further
inspections and removing certain parts
from service. Finally, this proposed AD
would prohibit installing any affected
nut on any on any TRDS Thomas
coupling.
Differences Between This Proposed AD
and the Transport Canada AD
The Transport Canada AD requires
compliance within 600 hours air time or
within the next 24-months, whichever
occurs first, whereas this proposed AD
would require compliance within 600
hours TIS and an additional inspection
at 25 hours TIS after installation of
certain nuts.
Costs of Compliance
The FAA estimates that this proposed
AD would affect 1439 helicopters of
U.S. Registry. The FAA estimates that
operators may incur the following costs
in order to comply with this proposed
AD. Labor costs are estimated at $85 per
work-hour.
Replacing each affected nut with the
newly designed nut and applying torque
and a torque stripe would take about 4
work-hours, and parts would cost about
$75 for an estimated cost of $415 per
nut replacement and $597,185 per nut
replacement for the U.S. fleet.
Replacing each TRDS Thomas
coupling would take about 4 workhours, and parts would cost about
$4,000 for an estimated cost of $4,340
per TRDS Thomas coupling
replacement.
If required, inspecting the torque of
each newly installed nut, and inspecting
each TRDS Thomas coupling, each bolt,
nut and washer for elongated holes and
fretting on the fasteners would take
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about 0.5 work-hours for an estimated
cost of $43 per inspection.
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
The FAA determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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, I certify
this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Would not affect intrastate
aviation in Alaska, and
(3) Would 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 Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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.
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Federal Register / Vol. 86, No. 175 / Tuesday, September 14, 2021 / Proposed Rules
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
Bell Textron Canada Limited: Docket No.
FAA–2021–0728; Project Identifier
MCAI–2020–00656–R.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by October 29,
2021.
(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.
tkelley on DSK125TN23PROD with PROPOSALS
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(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 Nm (50 in lb)
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
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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 Nm (50 in lb) 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.
(C) For each nut installed as required by
paragraphs (g)(1)(iii)(A) and (B) of this AD,
apply a torque of 5.65 Nm (50 in lb) 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 Nm (50 in lb) 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
PO 00000
Frm 00020
Fmt 4702
Sfmt 9990
51041
(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.
(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 matthew.fuller@faa.gov.
(2) For 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.
You may view this 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.
(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 on the internet at https://
www.regulations.gov in the AD Docket.
Issued on September 2, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–19605 Filed 9–13–21; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\14SEP1.SGM
14SEP1
]]>Agencies
[Federal Register Volume 86, Number 175 (Tuesday, September 14, 2021)]
[Proposed Rules]
[Pages 51038-51041]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-19605]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0728; Project Identifier MCAI-2020-00656-R]
RIN 2120-AA64
Airworthiness Directives; Bell Textron Canada Limited
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt 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 proposed AD
was
[[Page 51039]]
prompted by reports of cracked or missing nuts on the tail rotor drive
shaft (TRDS) disc pack (Thomas) couplings. This proposed AD would
require removing certain nuts from service, installing newly designed
nuts, and applying a specific torque and a torque stripe to each newly
installed nut. This proposed AD would then require, 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 proposed AD would prohibit installing any affected nut on
any TRDS Thomas coupling.
The FAA is proposing this AD to address the unsafe condition on
these products.
DATES: The FAA must receive comments on this proposed AD by October 29,
2021.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, 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 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.
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 NPRM, the
Transport Canada AD, any comments received, and other information. The
street address for Docket Operations is listed above.
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:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2021-0728; Project Identifier
MCAI-2020-00656-R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to 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]. Any commentary that the FAA receives which is
not specifically designated as CBI will be placed in the public docket
for this rulemaking.
Background
Transport Canada, which is the aviation authority for Canada, has
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 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 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.
[[Page 51040]]
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.
FAA's Determination
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 the Transport Canada AD. The FAA is proposing this AD
after evaluating all known relevant information and determining that an
unsafe condition is likely to exist or develop on other helicopters of
the same type design.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Bell Alert Service Bulletin 206-19-136, dated
August 27, 2019, and Bell Alert Service Bulletin 206L-19-181, Revision
A, dated August 29, 2019. 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.
Proposed AD Requirements in This NPRM
This proposed AD would require within 600 hours time-in-service
(TIS) after the effective date of this AD, removing from service each
affected nut, and installing a newly designed nut. This proposed AD
would also require applying a specific torque and a torque stripe to
each newly installed nut. This proposed AD would also 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,
this proposed AD would require further inspections and removing certain
parts from service. Finally, this proposed AD would prohibit installing
any affected nut on any on any TRDS Thomas coupling.
Differences Between This Proposed AD and the Transport Canada AD
The Transport Canada AD requires compliance within 600 hours air
time or within the next 24-months, whichever occurs first, whereas this
proposed AD would require compliance within 600 hours TIS and an
additional inspection at 25 hours TIS after installation of certain
nuts.
Costs of Compliance
The FAA estimates that this proposed AD would affect 1439
helicopters of U.S. Registry. The FAA estimates that operators may
incur the following costs in order to comply with this proposed AD.
Labor costs are estimated at $85 per work-hour.
Replacing each affected nut with the newly designed nut and
applying torque and a torque stripe would take about 4 work-hours, and
parts would cost about $75 for an estimated cost of $415 per nut
replacement and $597,185 per nut replacement for the U.S. fleet.
Replacing each TRDS Thomas coupling would take about 4 work-hours,
and parts would cost about $4,000 for an estimated cost of $4,340 per
TRDS Thomas coupling replacement.
If required, inspecting the torque of each newly installed nut, and
inspecting each TRDS Thomas coupling, each bolt, nut and washer for
elongated holes and fretting on the fasteners would take about 0.5
work-hours for an estimated cost of $43 per inspection.
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
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would 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 Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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.
[[Page 51041]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
Bell Textron Canada Limited: Docket No. FAA-2021-0728; Project
Identifier MCAI-2020-00656-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by October 29, 2021.
(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.
(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 Nm (50 in lb) 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 Nm (50 in
lb) 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.
(C) For each nut installed as required by paragraphs
(g)(1)(iii)(A) and (B) of this AD, apply a torque of 5.65 Nm (50 in
lb) 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 Nm (50 in
lb) 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].
(2) For 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. You may view this
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.
(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
on the internet at https://www.regulations.gov in the AD Docket.
Issued on September 2, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021-19605 Filed 9-13-21; 8:45 am]
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