COMPANY FEDERAL REGISTER DOCUMENT SUBMISSION TEMPLATE  (7/1/2006)

EPA Registration Division contact: Dan Peacock<PHONE_NUMBER>

INSTRUCTIONS:  Please utilize this outline in preparing tolerance
petition documents.  In cases where the outline element does not apply
please insert “NA-Remove” and maintain the outline.  The comment
notes that appear on the left margin represent hidden typesetting codes
designed to expedite the processing of the Federal Register document.
Please do not remove or alter these comment notes or change the margins,
font, or format in your document. Simply replace the instructions that
appear in italics and brackets, i.e., “[insert company name],” with
the information specific to your action.]

TEMPLATE:

Gowan Company

[Insert petition number]

	EPA has received a pesticide petition ([insert petition number]) from
Gowan Company, 370 S. Main Street, Yuma, AZ   85364, proposing, pursuant
to section 408(d) of the Federal Food, Drug, and Cosmetic Act (FFDCA),
21 U.S.C. 346a(d), to amend 40 CFR part 180.

(Options (pick one)

	1. by establishing a tolerance for residues of

	fenazaquin [3-[2-[4-(1,1-dimethylethyl) phenyl] ethoxy] quinazoline] in
or on the raw agricultural commodity pome fruit group at 0.35, cucurbit
group at 0.25, almond hulls at 4.5, apple wet pomace at 0.6, berry fruit
group at 0.6, fruiting vegetable group at 0.25, grape at 0.9, hop at
2.0, mint at 6.0, stone fruit group at 1.5, strawberry at 1.5, tree nut
group at 0.02, alfalfa forage at 4.5, alfalfa hay at 8.0 ppm,  avocado
at 0.15, citrus fruit group at 0.3, citrus oil at 2.5, cottonseed
(undelinted) at 0.5, cotton gin byproducts at 12.0, shelled dry bean
subgroup at 0.2, edible podded bean subgroup at 0.3, succulent beans and
pea subgroup at 0.02, field corn grain at 0.15, field corn forage at
9.0, field corn stover at 30, field corn aspirated grain fractions at
9.0, field corn refined oil at 0.6, sweet corn at 0.04 and sweet corn
forage at 9.0  parts per million (ppm).  EPA has determined that the
petition contains data or information regarding the elements set forth
in section 408 (d)(2) of the FDDCA; however, EPA has not fully evaluated
the sufficiency of the submitted data at this time or whether the data
supports granting of the petition. Additional data may be needed before
EPA rules on the petition.

A. Residue Chemistry

	1. Plant metabolism. Apple metabolism work (MRID 45029914) demonstrates
that TRR are reduced to less than 25% of their original value at 70 DAT
after a late season treatment and are reduced to between 1 – 4% of
their original value at 105 DAT after an early season application.
Virtually all of the TRR at 0 DAT is solvent washable fenazaquin on the
surface of the apples.  At 70 DAT identified parent fenazaquin is less
than 35% TRR.  At 105 DAT, 12 – 21% TRR was identified as parent
fenazaquin.  At harvest, fenazaquin is the predominant residue in apples
with smaller amounts of other metabolites.

	2. Analytical method. [Residues of fenazaquin are extracted from the
sample matrices by blending with acetonitrile.  An aliquot is
transferred to a separatory funnel and partitioned between water and
methylene chloride.  A 10% portion of the methylene chloride layer is
evaporated and the residue is reconstituted in acetonitrile for
instrumental analysis by LC/MS/MS with positive-ion electrospray
ionization tandem mass spectrometry.  The method had a Limit of
Quantitation of 0.01 ppm and a Limit of Detection of 0.003 ppm.]

	3. Magnitude of residues. [Residues of fenazaquin ranged from 0.023 to
0.082 mg/kg (ppm) in avocados, 0.031 to 1.65 ppm in alfalfa forage, 3.5
to 7.1 in alfalfa hay, 0.10 to 0.42 ppm in berries, 0.02 to 0.23 ppm in
whole citrus fruit, 0.013 to 0.325 ppm in undelinted cottonseed, 0.485
to 9.983 ppm in cotton gin trash, 0.02 to 0.17 ppm in cucurbit crops,
not detected to 0.168 ppm in dry beans, <0.01 to 0.223 ppm in fruiting
vegetables, 0.40 to 1.27 ppm in hops, not detectable to 0.28 ppm in pome
fruit, 0.12 to 1.20 ppm in stone fruit, 0.06 to 1.17 ppm in
strawberries, non-detected to 0.016 ppm in succulent beans and peas,
0.04 to 0.18 ppm in edible podded beans, 0.05 to 0.33 ppm in grapes,
0.359 to 1.27 ppm in hops, 0.52 to 5.45 ppm in mint, not detected to
0.051 ppm in field corn grain, not detected in sweet corn kernels plus
cob with husks removed, 0.254 to 6.04 ppm in corn forage, 0.101 to 21.3
ppm in corn stover, not detected to 0.02 ppm in tree nuts (0.22 to 1.17
ppm in almond hulls).]

B. Toxicological Profile

	1. Acute toxicity.  [EPA has reviewed the acute toxicity database and
has determined that fenazaquin is belongs in Category II for oral
toxicity; Category III for both inhalation exposure and eye irritation;
and Category IV for dermal exposure and skin irritation.

	2. Genotoxicty. [The genotoxicological database is complete.  All test
results for genotoxicity with fenazaquin have been negative.]

	3. Reproductive and developmental toxicity. [In rat and rabbit
developmental toxicity studies, no evidence of increased quantitative or
qualitative susceptibility exists following in utero exposure to
fenazaquin.  There are no qualitative or quantitative pre-natal
susceptibility issues and no residual uncertainties in the rat
two-generation reproduction study.]

	4. Subchronic toxicity. [The major findings following repeated oral
administration in rats, hamsters and dogs were decreases in body weight,
body weight gain, food intake, and food efficiency.  The lowest NOAEL
observed during these studies was 5 mg/kg/day in a 90-day feeding study
in dogs.]

	5. Chronic toxicity. [At the doses used in chronic toxicity studies (up
to 35 mg/kg/day), there were no organ specific toxicity findings.
Effects on body weight and weight gain and food intake efficiency were
identified in parental animals of the rat developmental and reproduction
studies and in the offspring of the reproduction rat study.  There were
no developmental findings in the rat study (up to 40 mg/kg) and no
parental or developmental findings of any kind up to 60 mg/kg/day in the
rabbit developmental study.

The EPA Health Effects Division Cancer Assessment Review Committee
reviewed the carcinogenicity study in hamsters, as well as the
carcinogenicity study conducted in rats, the mutagenicity studies, and
discussed the possible carcinogenic mode of action of fenazaquin.  Based
on the weight of evidence of these studies, and in accordance with the
2005 Guidelines for Carcinogen Risk Assessment, the members concluded
that the negative hamster findings along with the negative tumor
findings in the 24-month rat study and negative mutagenicity findings
support a cancer classification of “Not likely to Be Carcinogenic to
Humans” for fenazaquin.]

	6. Animal metabolism. [In rat, goat and hen metabolism studies,
orally-administered fenazaquin was quickly excreted in the feces.
Excretion of the dose was rapid with no accumulation or apparent target
organ.  The metabolites found were the result of oxidation or
hydrolysis.  A new hen study demonstrates metabolism similar to rats and
goats.  No toxic metabolites were detected in any metabolism studies.]

	7. Metabolite toxicology. [No toxic metabolites of fenazaquin have been
identified in any metabolism study.]

	8. Endocrine disruption. [EPA has reserved endocrine testing
requirements for fenazaquin pending consideration of appropriate
screening and/or testing protocols being considered under the Agency’s
Endocrine Disruptor Screening Program.]

C. Aggregate Exposure

	1. Dietary exposure. [Sufficient residue data for fenazaquin are
available to assess the proposed tolerances and conduct a dietary risk
assessment.  The acute dietary risk assessment is based on the aPAD set
by the Agency at 0.1 mg/kg/day.  The chronic dietary risk assessment was
based on the cPAD of 0.05 mg/kg/day.  The risk assessments were modeled
with DEEM-FCID v. 2.16.  The maximum dietary risk for any dietary
subpopulation was a maximum of 20.19% of the aPAD and 17.2% cPAD.]

	i. Food. [A probabilistic risk analysis using field residue data with
an assumption of 100% crop treated was run.  Empirically-derived
concentration factors were used when such data were available.  Where no
such data were available, default values were used for processed
commodities.]

	ii. Drinking Food. [Tier I estimates for fenazaquin levels in untreated
drinking water generated by EPA in the non-food petition decision were
included in the dietary risk assessment.  The Agency estimates were
0.002632 and 0.000064 ppm for acute and chronic scenarios,
respectively.]

	2. Non-dietary exposure. [No homeowner uses are proposed for fenazaquin
at this time.]

D. Cumulative Effects

	[Fenazaquin does not share a mechanism of toxicity with another
registered pesticide nor does it share a common toxic metabolite with
any other registered pesticide.  There are no available data to indicate
that fenazaquin has a common mechanism of toxicity with other
substances.]

E. Safety Determination

	1. U.S. population. [Total acute dietary exposure to the US population
from all proposed food uses is 0.008681 mg/kg/day, representing 8.68% of
the acute reference dose.  The total chronic exposure to the US
population was 0.002964 mg/kg/day, representing 5.9% of the chronic
reference dose.]

	2. Infants and children. [The Agency has set the FQPA factor for
fenazaquin at 1X based on lack of neurotoxic and teratogenic effects.
The highest risks calculated for any pre-teen dietary subgroup were
20.19% of the acute reference dose for children 1-2 years old and 17.2%
of the chronic reference dose for the same subpopulation.]

F. International Tolerances

	[No Codex MRL levels have been established for fenazaquin.  A number of
MRLs have been established for fenazaquin in crops in many other
countries.  EPA has established import tolerances for fenazaquin in
apples, pears, citrus fruit (except grapefruit) and citrus oil.]


[Federal Register: November 24, 2008 (Volume 73, Number 227)]
[Rules and Regulations]
[Page 70866-70867]
[DOCID:fr24no08-2]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1232; Directorate Identifier 2008-CE-070-AD;
Amendment 39-15747; AD 2008-24-07]
RIN 2120-AA64

Airworthiness Directives; Eclipse Aviation Corporation Model
EA500 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Eclipse Aviation Corporation (Eclipse) Model EA500 airplanes
equipped with a Pratt and Whitney Canada, Corp. (PWC) PW610F-A engine.
This AD requires you to incorporate operating limitations into Section
2, Limitations, of the airplane flight manual (AFM). This AD results
from several incidents of engine surge. We are issuing this AD to
prevent hard carbon buildup on the static vane, which could result in
engine surges. Engine surges may result in a necessary reduction in
thrust and decreased power for the affected engine. In some cases, this
could result in flight and landing under single-engine conditions.

DATES: This AD becomes effective on December 4, 2008.
    We must receive any comments on this AD by January 23, 2009.

ADDRESSES: Use one of the following addresses to comment on this AD.
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
    To view the comments to this AD, go to http://www.regulations.gov.
The docket number is FAA-2008-1232; Directorate Identifier 2008-CE-070-
AD.

FOR FURTHER INFORMATION CONTACT: Mitchell Soth, Flight Test Engineer,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone:<PHONE_NUMBER>;
fax:<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Discussion

    While in cruising flight at 40,000 feet altitude, an Eclipse EA500
airplane experienced a shudder from the right engine. This was followed
by a ``RT ENGINE EXCEEDANCE'' Crew Alerting System (CAS) message. The
crew reduced the throttle to idle and the shudder disappeared. The
right engine remained at idle until approximately 10,000 feet altitude.
The crew increased the power on the right engine and again felt the
shudder. The crew reduced the power on the right engine to idle and
landed without incident using single-engine procedures. PWC did a
borescope inspection and found carbon buildup on the static vane, which
caused the engine surging.
    When the PW610F-A engine is operated above 37,000 feet altitude,
for over an hour, and with high bleed flow, hard carbon forms due to
high local fuel air ratio near the combustor wall. The hard carbon may
break loose and obstruct one of the high pressure turbine vane gas path
passages, thus decreasing the surge margin to the point where engine
surging occurs.
    There have been several reports of engine surges that have required
reduced power, and, in some cases, the engine power was unrecoverable
and remained at reduced power for the remainder of the flight.
    This condition, if not corrected, could result in hard carbon
buildup on the static vane, which could result in engine surges. Engine
surges may result in a necessary reduction in thrust and decreased
power for the affected engine. In some cases, this could result in
flight and landing under single-engine conditions.

FAA's Determination and Requirements of This AD

    We are issuing this AD because we evaluated all the information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This AD requires
you to incorporate operating limitations into Section 2, Limitations,
of the AFM.
    The PW610F-A engines are currently only installed in the Eclipse
Model EA500 airplanes. If these engines were installed in other
airplanes, we would consider immediate AD action on those airplanes
since the engine would be of the same type design and the unsafe
condition could exist or develop in products of the same type design.
    The FAA considers the altitude limitation to be interim action. The
PWC PW610F-A engine is certificated in Canada and is certificated as a
foreign type validated engine under FAA TCDS E00074EN. The FAA
understands that Transport Canada (the airworthiness authority for
Canada) and PWC are considering potential actions to address the engine
aspects of this condition. In the meantime, the FAA is issuing this AD
on the Eclipse Model EA500 to mandate an altitude limitation.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because hard
carbon buildup on the static vane could result in engine surges. Engine
surges may require decreased power for the affected engine and, in some
cases, flight and landing under single-engine conditions. Therefore, we
determined that notice and opportunity for public comment before
issuing this AD are impracticable and that good cause exists for making
this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and an opportunity for
public comment. We invite you to send any written relevant data, views,
or arguments regarding this AD. Send your comments to an address listed
under the ADDRESSES section. Include the docket number ``FAA-2008-1232;
Directorate Identifier 2008-CE-070-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the AD in light
of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive concerning this AD.

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.
    We are 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

    We determined that 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) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); 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.
    We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the AD, the regulatory
evaluation, any comments received, and other information on the
Internet at http://www.regulations.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Office (telephone<PHONE_NUMBER>)
is located at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness
directive (AD):

2008-24-07 Eclipse Aviation Corporation: Amendment 39-15747; Docket
No. FAA-2008-1232; Directorate Identifier 2008-CE-070-AD.

Effective Date

    (a) This AD becomes effective on December 4, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model EA500 airplanes, all serial
numbers, that are:
    (1) Equipped with a Pratt and Whitney Canada, Corp. PW610F-A
engine; and
    (2) Certificated in any category.

Unsafe Condition

    (d) This AD is the result of several incidents of engine surge.
We are issuing this AD to prevent hard carbon buildup on the static
vane, which could result in engine surges. Engine surges may result
in a necessary reduction in thrust and decreased power for the
affected engine. In some cases, this could result in flight and
landing under single-engine conditions.

Compliance

    (e) Prior to further flight, unless already done, incorporate
the following language into Section 2, Limitations, of your airplane
flight manual (AFM): ``Per AD 2008-24-07, LIMIT THE MAXIMUM
OPERATING ALTITUDE TO 37,000 FEET (11277M) PRESSURE ALTITUDE.''
    (1) A person holding at least a private pilot certificate as
authorized by section 43.7 of the Federal Aviation Regulations (14
CFR 43.7) may insert the operating limitations into Section 2,
Limitations, of the AFM. Make an entry into the aircraft logbook
showing compliance with this portion of the AD in accordance with
section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
    (2) You may incorporate paragraph (e) of this AD into Section 2,
Limitations, of your AFM to comply with this AD.

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Fort Worth Airplane Certification Office, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to Attn:
Mitchell Soth, Aerospace Engineer, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO.

    Issued in Kansas City, Missouri, on November 17, 2008.
Kim Smith,
Manager Small Airplane Directorate, Aircraft Certification Service.
 [FR Doc. E8-27699 Filed 11-21-08; 8:45 am]

BILLING CODE 4910-13-P


[Federal Register Volume 87, Number 222 (Friday, November 18, 2022)]
[Rules and Regulations]
[Pages 69155-69158]
[FR Doc No: 2022-25028]

========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents.

========================================================================

Federal Register / Vol. 87, No. 222 / Friday, November 18, 2022 /
Rules and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0807; Project Identifier AD-2022-00214-R;
Amendment 39-22188; AD 2022-20-04]
RIN 2120-AA64

Airworthiness Directives; Bell Textron Canada Limited Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding airworthiness directive (AD) 2021-26-
08, which applied to certain Bell Textron Canada Limited Model 206,
206A, 206A-1, 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4
helicopters. AD 2021-26-08 required removing certain nuts from service;
installing newly designed nuts; applying a specific torque, and a
torque stripe to each newly installed nut; 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. AD 2021-
26-08 also prohibited installing any affected nut on any tail rotor
drive shaft (TRDS) disc pack (Thomas) coupling. Since the FAA issued AD
2021-26-08, the FAA determined certain torque values and part numbers
(P/Ns) need to be revised. This AD was prompted by reports of cracked
or missing nuts installed on the TRDS Thomas couplings and the need to
revise certain torque values and P/Ns in AD 2021-26-08. This AD
requires removing certain nuts from service; installing newly designed
nuts; applying torque and a torque stripe; and additional corrective
actions if necessary. This AD also prohibits installing any affected
nut on any TRDS Thomas coupling, as specified in a Transport Canada AD,
which is incorporated by reference. The FAA is issuing this AD to
address the unsafe condition on these products.

DATES: This AD is effective December 23, 2022.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 23,
2022.

ADDRESSES: For Transport Canada material incorporated by reference
(IBR) in this final rule, contact Transport Canada, Transport Canada
National Aircraft Certification, 159 Cleopatra Drive, Nepean, Ontario,
K1A 0N5, CANADA; telephone<PHONE_NUMBER>; email
[email protected];
internet tc.canada.ca/en/aviation. You may find the Transport Canada
material on the Transport Canada website at tc.canada.ca/en/aviation.
For Air Comm Corporation service information identified in this final
rule, contact Air Comm Corporation, 1575 West 124th Ave. #210,
Westminster, CO 80234; telephone<PHONE_NUMBER>; email
aircommcorp.com">[email protected]aircommcorp.com; or at aircommcorp.com. For Bell 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 bellflight.com/support/contact-support. You may view this material at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort
Worth, TX 76177. For information on the availability of this material
at the FAA, call<PHONE_NUMBER>. Service information that is IBRed is
also available in the AD docket at regulations.gov by searching for and
locating Docket No. FAA-2022-0807.

Examining the AD Docket

    You may examine the AD docket at regulations.gov by searching for
and locating Docket No. FAA-2022-0807; 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 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<PHONE_NUMBER>; email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2021-26-08, Amendment 39-21867 (86 FR
72833, December 23, 2021) (AD 2021-26-08). AD 2021-26-08 applied to
Bell Textron Canada Limited Model 206, 206A, 206A-1, 206B, 206B-1,
206L, 206L-1, 206L-3, and 206L-4 helicopters, with nut P/N MS21042L4 or
P/N MS21042L5 installed on the TRDS Thomas couplings. AD 2021-26-08
required removing certain nuts from service, installing newly designed
nuts, and applying a specific torque and a torque stripe to each newly
installed nut. AD 2021-26-08 also required, 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,
AD 2021-26-08 prohibited installing any affected nut on any TRDS Thomas
coupling. The FAA issued AD 2021-26-08 to prevent failure or loss of a
nut on any TRDS Thomas coupling.
    AD 2021-26-08 was prompted by Transport Canada AD CF-2020-15, dated
May 13, 2020 (Transport Canada AD CF-2020-15). Transport Canada, which
is the aviation authority for Canada, issued Transport Canada AD CF-
2020-15 to correct an unsafe condition for 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-2020-15
specifies for certain model helicopters, newly designed nuts cannot be
installed because Supplemental Type Certificate (STC) SH2750NM and
Transport Canada STC SH99-202 install a pulley at the Thomas coupling
location causing insufficient clearance. Transport Canada advises, for
certain

model helicopters with STC SH2750NM or Transport Canada STC SH99-202
installed, different part-numbered nuts may be installed and are now
required to be replaced with a new part-numbered nut that is not
vulnerable to the unsafe condition.
    The NPRM published in the Federal Register on June 30, 2022 (87 FR
39015). The NPRM was prompted by reports of cracked or missing nuts
installed on the TRDS Thomas couplings. The NPRM was also prompted by
the determination that certain P/Ns and certain torque values in
paragraph (g) of AD 2021-26-08 need to be revised. Furthermore, the FAA
advises that the 50-70 in lb torque values are only applicable to
certain bolts and nuts, and a 150-180 in lb torque value is required
for other bolts and nuts that are required to be installed by this AD.
The FAA also advises that certain part-numbered nuts that are required
to be installed according to AD 2021-26-08 need to be removed from
service and replaced due to a certain pulley configuration. The NPRM
proposed to require removing certain nuts from service; installing
newly designed nuts; applying torque and a torque stripe; and
additional corrective actions if necessary. The NPRM also proposed to
prohibit installing any affected nut on any TRDS Thomas coupling, as
specified in Transport Canada AD CF-2020-15.
    The FAA is issuing this AD to prevent failure or loss of a nut on
the TRDS Thomas couplings, which if not addressed could result in loss
of the tail rotor and subsequent loss of control of the helicopter. See
Transport Canada AD CF-2020-15 for additional background information.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of
the costs.

Conclusion

    These helicopters have been approved by 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. This AD is adopted as
proposed in the NPRM, except the FAA has removed the note to the
applicability paragraph and updated the identification of Model 206A-1
helicopters in the applicability paragraph to Model 206A-1 (OH-58A)
helicopters to match the FAA type certificate data sheet. None of these
changes will increase the economic burden on any operator.

Related Service Information Under 1 CFR Part 51

    Transport Canada AD CF-2020-15 requires the replacement of certain
part-numbered nuts with newly designed nuts at each TRDS Thomas
coupling and prohibits installing any affected nut on any TRDS Thomas
coupling. The replacement includes applying torque, and a torque
stripe.
    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.
    This material is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.

Other Related Service Information

    The FAA also reviewed Bell Alert Service Bulletin (ASB) 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 ASB 206L-19-181, dated August 27, 2019, and
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. Revision A of Bell ASB 206L-19-181 corrects a typographical
error.
    Additionally, the FAA reviewed Bell Service Instruction BHT-206-SI-
2052, Revision 1, dated October 14, 2010. 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 Transport Canada AD CF-2020-15

    Transport Canada AD CF-2020-15 requires compliance with certain
actions within 600 hours air time or within the next 24 months,
whichever occurs first, whereas this AD requires compliance within 600
hours time-in-service only. Service information referenced in Transport
Canada AD CF-2020-15 specifies if any P/N MS21042L4 nuts are found
loose or damaged, reporting the location and providing the information
to Bell, whereas this AD requires if any P/N MS21042L4 nuts are found
loose or damaged, inspecting each TRDS Thomas coupling, including each
bolt, nut, and washer, for any elongated holes, fretting on the
fasteners, and damaged fasteners, and depending on the results of the
inspection, removing from service each affected part and replacing it
with an airworthy part.

Costs of Compliance

    The FAA estimates that this AD affects 1,359 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.
    Replacing each affected nut with the newly designed nut and
applying torque and a torque stripe takes about 4 work-hours, and parts
cost about $75 for an estimated cost of $415 per nut replacement and
$563,985 per nut replacement for the U.S. fleet.
    In addition, the costs of the actions that are part of the required
replacement are as follows:
    If required, due to loose or damaged nuts found, inspecting each
TRDS Thomas coupling, and each bolt, nut, and washer for elongated
holes and fretting on the fasteners takes about 0.5 work-hour for an
estimated cost of $43 per inspection.
    If required, replacing each TRDS Thomas coupling takes about 4
work-hours, and parts cost about $4,000 for an estimated cost of $4,340
per TRDS Thomas coupling replacement.
    If required, replacing a bolt or washer takes a minimal amount of
time and parts 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.

Regulatory Findings

    This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2021-26-08, Amendment 39-21867
(86 FR 72833, December 23, 2021); and
0
b. Adding the following new AD:

2022-20-04 Bell Textron Canada Limited: Amendment 39-22188; Docket
No. FAA-2022-0807; Project Identifier AD-2022-00214-R.

(a) Effective Date

    This airworthiness directive (AD) is effective December 23,
2022.

(b) Affected ADs

    This AD replaces AD 2021-26-08, Amendment 39-21867 (86 FR 72833,
December 23, 2021) (AD 2021-26-08).

(c) Applicability

    This AD applies to Bell Textron Canada Limited Model 206, 206A,
206A-1 (OH-58A), 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4
helicopters, all serial numbers, certificated in any category.

(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 tail rotor drive shaft (TRDS) disc pack (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) Requirements

    Except as specified in paragraphs (h) and (i) of this AD: Comply
with all required actions and compliance times specified in, and in
accordance with, Transport Canada AD CF-2020-15, dated May 13, 2020
(Transport Canada AD CF-2020-15).

(h) Exceptions to Transport Canada AD CF-2020-15

    (1) Where Transport Canada AD CF-2020-15 requires compliance in
terms of air time, this AD requires using hours time-in-service
(TIS).
    (2) Where Transport Canada AD CF-2020-15 refers to the effective
dates specified in paragraphs (h)(2)(i) and (ii) of this AD, this AD
requires using the effective date of this AD.
    (i) October 9, 2019 (the effective date of Transport Canada AD
CF-2019-34, dated September 25, 2019).
    (ii) The effective date of Transport Canada AD CF-2020-15.
    (3) Where Transport Canada AD CF-2020-15 defines Group 1
helicopters as those models ``that have not been modified by
installing STC SH2750NM or STC SH99-202,'' replace ``that have not
been modified by installing STC SH2750NM or STC SH99-202'' with
``that have not been modified by installing STC SH2750NM.''
    (4) Where Transport Canada AD CF-2020-15 defines Group 4
helicopters as those models ``that have been modified by installing
STC SH2750NM or STC SH99-202,'' replace ``that have been modified by
installing STC SH2750NM or STC SH99-202'' with ``that have been
modified by installing STC SH2750NM.''
    (5) Where Transport Canada AD CF-2020-15 requires compliance
within 600 hours air time or 24 months, whichever occurs first, this
AD requires compliance within 600 hours TIS only and does not allow
a compliance time of 24 months.
    (6) Where any paragraph of Transport Canada AD CF-2020-15
specifies to replace part number (P/N) MS21042 nuts with P/N NAS9926
nuts, this AD requires removing P/N MS21042 nuts from service and
replacing with P/N NAS9926 nuts.
    (7) Where any paragraph of any service information referenced in
Transport Canada AD CF-2020-15 specifies to replace P/N MS21042L4
nuts with P/N 90-132L4 nuts, this AD requires removing P/N MS21042L4
nuts from service and replacing with P/N 90-132L4 nuts, in
accordance with Air Comm Corporation Service Bulletin SB 206EC-
092619, Revision NC, dated September 26, 2019 (SB 206EC-092619 Rev
NC).
    (8) Where any paragraph of any service information referenced in
Transport Canada AD CF-2020-15 specifies to replace P/N MS21042L5
nuts with P/N 90-132L5 nuts, this AD requires removing P/N MS21042L5
nuts from service and replacing with P/N 90-132L5 nuts, in
accordance with SB 206EC-092619 Rev NC.
    (9) Where any paragraph of any service information referenced in
Transport Canada AD CF-2020-15 specifies if any P/N MS21042L4 nuts
are found loose or damaged, report at which location and provide the
information to Product Support Engineering at
[email protected], this AD requires if any P/N MS21042L4
nuts are found loose or damaged, before further flight, inspecting
each TRDS Thomas coupling, including each bolt, nut, and washer, for
any elongated holes, fretting on the fasteners, and damaged
fasteners. If there is any elongated hole, fretting on the
fasteners, or damaged fasteners, this AD requires before further
flight, removing from service each affected part and replacing it
with an airworthy part.

(i) No Reporting Requirement

    Although the service information referenced in Transport Canada
AD CF-2020-15 specifies to submit certain information to the
manufacturer, this AD does not include that requirement.

(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 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) 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.

(k) Related Information

    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<PHONE_NUMBER>; email [email protected].

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
    (i) Air Comm Corporation Service Bulletin SB 206EC-092619,
Revision NC, dated September 26, 2019.
    (ii) Transport Canada AD CF-2020-15, dated May 13, 2020.
    (3) For Air Comm Corporation service information identified in
this AD, contact Air Comm Corporation, 1575 West 124th Ave. #210,
Westminster, CO 80234; telephone<PHONE_NUMBER>; email
aircommcorp.com">[email protected]aircommcorp.com; or at aircommcorp.com. For Transport Canada
AD CF-2020-15, contact Transport Canada, Transport Canada National
Aircraft Certification, 159 Cleopatra Drive, Nepean, Ontario, K1A
0N5, CANADA; telephone<PHONE_NUMBER>; email
[email protected];
internet tc.canada.ca/en/aviation. You may find the Transport Canada
material on the Transport Canada website at tc.canada.ca/en/
aviation.
    (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<PHONE_NUMBER>. This material may be
found in the AD docket at regulations.gov by searching for and
locating Docket No. FAA-2022-0807.
    (5) You may view this material that is incorporated by reference
at the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, email
[email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on September 19, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-25028 Filed 11-17-22; 8:45 am]
BILLING CODE 4910-13-P