Airworthiness Directives; Bell Textron Inc. Helicopters, 80734-80739 [2024-22908]
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Federal Register / Vol. 89, No. 193 / Friday, October 4, 2024 / Rules and Regulations
[Docket No. FAA–2022–0600; Project
Identifier AD–2021–01160–R; Amendment
39–22827; AD 2024–17–02]
Other Related Material: For other
material identified in this final rule,
contact Bell Textron Inc., P.O. Box 482,
Fort Worth, TX 76101; phone: (450)
437–2862 or (800) 363–8023; fax: (450)
433–0272; email: productsupport@
bellflight.com; website: bellflight.com/
support/contact-support.
RIN 2120–AA64
FOR FURTHER INFORMATION CONTACT:
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; Bell Textron
Inc. Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
Background
The FAA is adopting a new
airworthiness directive (AD) for all Bell
Textron Inc. (Bell) Model 204B, 205A,
205A–1, 205B, and 210 helicopters. This
AD was prompted by an accident and
incidents involving failure of the tail
boom attachment structure. This AD
requires inspecting the tail boom
assembly hardware, replacing tail boom
attachment hardware, greasing the bolt
shanks, and inspecting torque. This AD
also prohibits installing steel alloy nuts
on any helicopter. The FAA is issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective November 8,
2024.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 8, 2024.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2022–0600; 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, 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.
Material Incorporated by Reference:
• For Bell material identified in this
AD, contact Bell Textron Inc., P.O. Box
482, Fort Worth, TX 76101; phone: (450)
437–2862 or (800) 363–8023; fax: (450)
433–0272; email: productsupport@
bellflight.com; website: 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 (817) 222–5110.
The FAA issued AD 2021–15–14,
Amendment 39–21661 (86 FR 39942,
July 26, 2021) (AD 2021–15–14) for
various restricted category helicopters.
AD 2021–15–14 was prompted by an
accident involving a Model UH–1B
helicopter and two forced landings
involving Model UH–1H and UH–1F
helicopters, due to tail boom attachment
structure failures. Each of the three
events involved a failure of the upper
left-hand (LH) tail boom attachment
fitting, which is the most heavily loaded
of the four tail boom attach points. The
FAA issued AD 2021–15–14 to address
fatigue cracking of tail boom attachment
fittings, cap angles, longerons, and bolts.
Due to their similarity to Model UH–
1B, UH–1H, and UH–1F helicopters, the
FAA determined that Bell Model 204B,
205A, 205A–1, 205B, and 210
helicopters are also affected by the same
unsafe condition and issued a notice of
proposed rulemaking (NPRM) to
propose the same actions as those
required in AD 2021–15–14. The NPRM
published in the Federal Register on
June 7, 2022 (87 FR 34587) to amend 14
CFR part 39 and would have applied to
Bell Model 204B, 205A, 205A–1, 205B,
and 210 helicopters. In the NPRM, the
FAA proposed to require revising the
helicopter’s existing rotorcraft flight
manual to incorporate pre-flight checks;
removing excess paint and sealant and
cleaning certain parts; and repetitively
inspecting structural components that
attach the tail boom to the fuselage.
Depending on the inspection results, the
FAA proposed to require repairing or
replacing components or re-bonding the
structure.
Based on comments received on the
NPRM, the FAA determined changes to
the proposed required actions were
necessary. Accordingly, the FAA issued
a supplemental notice of proposed
rulemaking (SNPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Bell Model 204B, 205A,
205A–1, 205B, and 210 helicopters. The
AGENCY:
SUMMARY:
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Michael Perrin, Aviation Safety
Engineer, FAA, 1801 S Airport Road,
Wichita, KS 67209; phone: (562) 627–
5362; email: Michael.j.perrin@faa.gov.
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SUPPLEMENTARY INFORMATION:
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SNPRM published in the Federal
Register on May 8, 2024 (89 FR 38846).
In the SNPRM, for Bell Model 204B
helicopters, the FAA proposed to
require, with the tail boom assembly
removed, removing the upper LH bolt
from service and inspecting the bolt’s
associated attachment hardware and,
depending on the inspection results,
removing the associated nut from
service. The FAA also proposed to
require visually inspecting each
bulkhead, bolt hole, attachment fitting,
the three other nuts, the upper righthand (RH) bolt, and two lower bolts,
including the bolt shank and head radii.
Depending on inspection results, the
FAA proposed to require repairing or
replacing an affected bulkhead or
affected fitting, removing certain partnumbered nuts, removing any affected
nut and its associated bolt from service,
and removing any affected bolt from
service.
For Bell Model 205A, 205A–1, and
205B helicopters, the FAA proposed to
require, with the tail boom assembly
removed, removing the upper LH bolt
from service and inspecting its
associated barrel nut and retainer and,
depending on the inspection results,
removing barrel nut and retainer from
service. The FAA also proposed to
require visually inspecting each
bulkhead, bolt hole, attachment fitting,
the three other barrel nuts, associated
retainers, the upper RH bolt, and two
lower bolts, including the bolt shank
and head radii. Depending on
inspection results, the FAA proposed to
require repairing or replacing an
affected bulkhead or affected fitting,
removing certain part-numbered barrel
nuts and retainers, removing any
affected barrel nuts and its associated
bolt from service, and removing any
affected bolt from service.
For Bell Model 210 helicopters, the
FAA proposed to require, with the tail
boom supported, removing the upper
LH steel alloy barrel nut, retainer, and
bolt from service and removing the
countersunk washer and plain washers
and replacing them with a new certain
part-numbered nickel alloy barrel nut,
new retainer, new bolt, an airworthy
countersunk washer, and airworthy
plain washers. The FAA also proposed
to require visually inspecting the upper
RH bolt and its associated hardware
and, depending on the inspection
results, removing the upper RH bolt and
barrel nut from service. Additionally,
the FAA proposed to require visually
inspecting the two lower bolts and the
associated barrel nuts and, depending
on the inspection results, removing any
affected barrel nut and its associated
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bolt from service and removing any
affected bolt from service.
For all applicable helicopters, the
FAA proposed to require, after the
initial inspections have been completed,
applying a coating of grease to each bolt
shank only, installing the applicable
hardware, and torquing each bolt.
Thereafter, the FAA proposed to require
inspecting the torque applied on each
bolt to determine if the torque has
stabilized and, depending on the results,
replacing and inspecting certain tail
boom attachment point hardware and
repeating the torque inspections or
applying torque stripes.
Lastly, the FAA proposed to prohibit
installing certain part-numbered steel
alloy nuts on Model 204B helicopters
and certain part-numbered steel alloy
barrel nuts on Model 205A, 205A–1,
205B, and 210 helicopters.
Discussion of Final Airworthiness
Directive
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Comments
The FAA received comments on the
SNPRM from Helicopter Maintenance
Corporation. The commenter requested
that the FAA revise the proposed AD to
allow credit for previous compliance
with the visual inspection of the tail
boom attach points and bulkhead,
replacement of affected hardware, and
the recurring inspections involving
removal of the tail boom. Helicopter
Maintenance Corporation stated that
aircraft that are in compliance with ASB
205–21–118 should only be obligated to
comply with any differences between
the AD and the alert service bulletin.
Paragraph (f) of this AD requires
compliance unless the actions have
already been done. Therefore, where
this AD requires actions without
incorporating Bell Alert Service Bulletin
(ASB) 210–21–15, Revision A, dated
February 23, 2022 (ASB 210–21–15, Rev
A), by reference, operators may take
credit for those actions they if were
done before the effective date of this
AD. Also, where this AD requires
actions in accordance with ASB 210–
21–15, Rev A, operators may take credit
for those actions only if they were done
before the effective date of this AD using
ASB 210–21–15, Rev A; this AD does
not allow credit for those actions if
previously done using the original
release of ASB 210–21–15, (dated
January 27, 2022). The FAA did not
change this AD as a result of this
comment.
Conclusion
The FAA reviewed the relevant data,
considered any comments received, and
determined that air safety requires
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adopting this AD as proposed.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products. Except for minor editorial
changes, this AD is adopted as proposed
in the SNPRM.
Material Incorporated by Reference
Under 1 CFR Part 51
The FAA reviewed Bell ASB 210–21–
15, Rev A. This material specifies
procedures for replacing the steel alloy
barrel nuts with nickel alloy barrel nuts,
inspecting and replacing the tail boom
attachment hardware, stabilizing the tail
boom attachment hardware torque,
applying torque seals, and subsequently
checking the torque.
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 Material
The FAA also reviewed Bell ASB
205–21–118, Bell ASB 204B–21–75, and
Bell ASB 205B–21–72, each Revision A
and dated February 23, 2022. This
material specifies the same procedures
as ASB 210–21–15, Rev A.
Differences Between This AD and the
Related Material
The related material specifies
checking torque, whereas this AD
requires inspecting torque because that
action is a maintenance action that must
be performed by persons authorized
under 14 CFR 43.3.
When stabilizing the tail boom
attachment hardware torque, the related
material does not clearly specify actions
for each time the torque is below the
minimum limit during any torque
stabilization inspection, whereas this
AD requires replacing and inspecting
certain tail boom attachment point
hardware, stabilizing the torque of the
replaced hardware set, and applying
torque stripes.
Costs of Compliance
The FAA estimates that this AD
affects 62 (five Model 204B helicopters,
fifty-three Model 205A, 205A–1, and
205B helicopters, and four Model 210
helicopters) of U.S. registry. Labor costs
are estimated at $85 per work-hour.
Based on these numbers, the FAA
estimates the following costs to comply
with this AD.
For the initial requirements for Model
204B helicopters, inspecting or
replacing up to four bolts (which
includes applying a coating of grease),
inspecting each bulkhead, inspecting
each fitting and bolt hole, inspecting
and stabilizing the torque, and applying
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torque stripes will take up to
approximately 8.5 work-hours for an
estimated labor cost of up to $723. The
parts cost for an upper LH bolt will be
approximately $196 and the parts cost
for the other bolts will be approximately
$89 per bolt. The parts cost for four new
nuts will be approximately $680. The
parts cost to apply torque stripes will be
a nominal amount. The estimated cost
for these actions will be up to
approximately $1,866 per helicopter
and $9,330 for the U.S. fleet.
For the initial requirements for Model
205A, 205A–1, and 205B helicopters,
replacing the four steel alloy barrel nuts
with new nickel alloy barrel nuts,
inspecting or replacing up to four bolts
(which includes applying a coating of
grease), inspecting each bulkhead,
inspecting and stabilizing the torque,
and applying torque stripes will take up
to approximately 8.5 work-hours for an
estimated labor cost of up to $723. The
parts cost for the four new nickel alloy
barrel nuts (including retainers) will be
approximately $680. The parts cost for
an upper LH bolt will be approximately
$196 and the parts cost for the other
bolts will be approximately $89 per bolt.
The parts cost to apply torque stripes
will be a nominal amount. The
estimated cost for these actions will be
up to approximately $1,866 per
helicopter and $98,898 for the U.S. fleet.
For the initial requirements for Model
210 helicopters, replacing the four steel
alloy barrel nuts with new nickel alloy
barrel nuts, inspecting or replacing up
to four bolts (which includes applying
a coating of grease), inspecting and
stabilizing the torque, and applying
torque stripes will take up to
approximately 8.5 work-hours for an
estimated labor cost of up to $723. The
parts cost for the four new nickel alloy
barrel nuts (including retainers) will be
approximately $680. The parts cost for
an upper LH bolt will be approximately
$196 and the parts cost for the other
bolts will be approximately $89 per bolt.
The parts cost to apply torque stripes
will be a nominal amount. The
estimated cost for these actions will be
up to approximately $1,866 per
helicopter and $7,464 for the U.S. fleet.
For all applicable helicopters,
inspecting the torque applied on each
bolt will take approximately 1 workhour for an estimated cost of $85 per
helicopter and $5,270 for the U.S. fleet,
per inspection cycle.
For all applicable helicopters,
replacing an upper LH bolt, stabilizing
the torque, and applying a torque stripe
will take up to approximately 5 workhours. The parts cost for an upper LH
bolt will be approximately $196 and the
parts cost to apply a torque stripe will
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be a nominal amount. The estimated
cost for these actions will be up to
approximately $621 per helicopter and
$38,502 for the U.S. fleet, per
replacement cycle. Inspecting one of the
other bolts, stabilizing the torque, and
applying a torque stripe will take up to
approximately 3.5 work-hours for an
estimated cost of $298 per other bolt
and $18,476 for the U.S. fleet per other
bolt per inspection cycle. If required,
replacing a bolt following that
inspection will take a minimal amount
of additional time and the parts cost
will be approximately $89.
If required as a result of failing any
torque inspection required by this AD,
visually inspecting a nut or a barrel nut,
replacing a bolt, stabilizing the torque,
and applying a torque stripe will take
up to approximately 5.5 work-hours per
failed hardware set. The parts cost for
an upper LH bolt will be approximately
$196 and the parts cost for the other
bolts will be approximately $89 per bolt.
The parts cost to apply a torque stripe
will be a nominal amount. The
estimated cost for these actions will be
$664 (upper LH bolt) or $557 (other
bolts), per failed hardware set. If
required, replacing a nut following that
inspection will take a minimal amount
of additional time and the parts cost for
a nut will be approximately $89 per nut.
If required, replacing a barrel nut
following that inspection will take a
minimal amount of additional time and
a parts cost of approximately $173 per
barrel nut.
The corrective action that may be
needed as a result of the bulkhead
inspection could vary significantly from
helicopter to helicopter. The FAA has
no data to determine the costs to
accomplish the corrective action or the
number of helicopters that may require
corrective action.
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.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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
Tail boom attachment point
Upper
Upper
Lower
Lower
Model 204B
left-hand bolt ...........................................................
right-hand bolt .........................................................
left-hand bolt ...........................................................
right-hand bolt .........................................................
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(h) Required Actions
(1) Within 300 hours time-in-service (TIS)
or 90 days after the effective date of this AD,
whichever occurs first, accomplish the
actions required by paragraphs (h)(1)(i), (ii),
or (iii) of this AD as applicable to your model
helicopter. For purposes of this AD, the word
‘‘new’’ is defined as having zero total hours
TIS.
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570–610
360–380
360–380
360–380
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Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Sfmt 4700
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2024–17–02 Bell Textron Inc.: Amendment
39–22827; Docket No. FAA–2022–0600;
Project Identifier AD–2021–01160–R.
(a) Effective Date
This airworthiness directive (AD) is
effective November 8, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bell Textron Inc. Model
204B, 205A, 205A–1, 205B, and 210
helicopters, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)
5302, Rotorcraft Tail Boom.
(e) Unsafe Condition
This AD was prompted by an accident and
incidents involving failure of the tail boom
attachment structure. The FAA is issuing this
AD to address fatigue cracking of tail boom
attachment fittings, cap angles, longerons,
and bolts. The unsafe condition, if not
addressed, could result in separation of the
tail boom from the helicopter and subsequent
loss of control of the helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Allowable Torque Values (in-lbs)
Model 205A/205A–1
Model 205B
1000–1200
1000–1200
400–430
400–430
(i) For Model 204B helicopters, accomplish
the actions required by paragraphs
(h)(1)(i)(A) through (C) of this AD.
(A) With the tail boom assembly removed,
remove the upper left-hand (LH) tail boom
attachment bolt (bolt) from service and
inspect its associated tail boom attachment
nut (nut) for mechanical damage, corrosion,
a crack, damaged threads, and wear, and to
determine whether it is a steel alloy part
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1000–1200
1000–1200
400–430
400–430
Model 210
1300–1600
1000–1200
400–430
400–430
number (P/N) NAS679A, NAS1291, or
MS21042. If there is any mechanical damage,
corrosion, a crack, a damaged thread, or
wear, or if nut P/N NAS679A, NAS1291, or
MS21042 is installed, before further flight,
remove the nut from service.
(B) Visually inspect each bulkhead (FS
195.00 and FS 195.03) and the bolt holes for
mechanical damage, corrosion, and cracks;
visually inspect each attachment fitting for
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mechanical damage, corrosion, cracks, and
loose fasteners; determine if any of the three
other nuts are a steel alloy P/N NAS679A,
NAS1291, or MS21042; and visually inspect
the other three nuts, the upper right-hand
(RH) bolt, and two lower bolts for mechanical
damage, corrosion, cracks, damaged threads,
and wear, including the bolt shank and head
radii of the bolts for a damaged thread, wear,
and mechanical damage.
(1) If there is any mechanical damage,
corrosion, or cracks on any bulkhead (FS
195.00 or FS 195.03), or any mechanical
damage, corrosion, or cracks on any bolt
holes, or if there is any mechanical damage,
corrosion, cracks, or loose fasteners on any
attachment fitting, before further flight, repair
or replace the affected bulkhead or the
affected attachment fitting, as appropriate, in
accordance with FAA-approved procedures.
(2) If there is any mechanical damage,
corrosion, a crack, a damaged thread, or wear
on any nut, or if nut P/N NAS679A,
NAS1291, or MS21042 is installed, before
further flight, remove the affected nut from
service. If there is a crack on any nut, before
further flight, also remove its associated bolt
from service.
(3) If there is any mechanical damage,
corrosion, a crack, a damaged thread, or wear
on the on the upper RH bolt or two lower
bolts, which includes the bolt shank or head
radii, before further flight, remove the
affected bolt from service.
(C) Apply a coating of Aeriol ThixO #2
(3810–0) or Aeriol ThixO SYN (3820–0)
aviation grease to each bolt shank only.
Install the hardware set of each tail boom
attachment point (nickel alloy nut P/N 90–
132L7 or 90–132L6, as applicable to the
affected tail boom attachment point, new
upper LH bolt P/N NAS627–21, upper RH
and two lower bolts P/N NAS626–20,
countersunk washer, and plain washers).
Torque each bolt by using the torque value
information identified in paragraph (g) of this
AD.
(ii) For Model 205A, 205A–1, and 205B
helicopters, accomplish the actions required
by paragraphs (h)(1)(ii)(A) through (C) of this
AD.
(A) With the tail boom assembly removed,
remove the upper LH bolt from service and
inspect its associated tail boom attachment
barrel nut (barrel nut) and retainer for
mechanical damage, corrosion, a crack,
damaged threads, and wear, and to determine
whether it is a steel alloy barrel nut P/N
NAS577B8A. If there is any mechanical
damage, corrosion, a crack, a damaged
thread, or wear, or if barrel nut P/N
NAS577B8A is installed, before further flight,
remove the barrel nut and its associated
retainer from service.
(B) Visually inspect each bulkhead (BS
17.31 and FS 243.89) and the bolt holes for
mechanical damage, corrosion, and cracks;
visually inspect each attachment fitting for
mechanical damage, corrosion, cracks, and
loose fasteners; determine if any of the three
other barrel nuts are steel alloy P/N
NAS577B8A or P/N NAS577B6A; and
visually inspect the other three barrel nuts
and the associated retainers, the upper RH
bolt, and two lower bolts for mechanical
damage, corrosion, cracks, damaged threads,
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and wear, including the bolt shank and head
radii of the bolts for a damaged thread, wear,
and mechanical damage.
(1) If there is any mechanical damage,
corrosion, or cracks on any bulkhead (BS
17.31 or FS 243.89), or any mechanical
damage, corrosion, or cracks on any bolt
holes, or if there is any mechanical damage,
corrosion, cracks, or loose fasteners on any
attachment fitting, before further flight, repair
or replace the affected bulkhead or the
affected attachment fitting, as appropriate, in
accordance with FAA-approved procedures.
(2) If there is any mechanical damage,
corrosion, a crack, a damaged thread, or wear
on any barrel nut or retainer, or if barrel nut
P/N NAS577B8A or NAS577B6A is installed,
before further flight, remove the affected
barrel nut and retainer (as a pair) from
service. If there is a crack on any nut, before
further flight, also remove its associated bolt
from service.
(3) If there is any mechanical damage,
corrosion, a crack, a damaged thread, or wear
on the upper RH bolt or two lower bolts,
which includes the bolt shank or head radii,
before further flight, remove the affected bolt
from service.
(C) Apply a coating of Aeriol ThixO #2
(3810–0) or Aeriol ThixO SYN (3820–0)
aviation grease to each bolt shank only.
Install the hardware set of each tail boom
attachment point (nickel alloy barrel nut P/
N NAS577C6A or P/N NAS577C8A and
retainer P/N NAS578C6A or P/N
NAS578C8A, as applicable to the affected tail
boom attachment point, new upper LH bolt
P/N NAS628–22, upper RH and two lower
bolts P/N NAS628–22 or NAS626–18, as
applicable to the affected tail boom
attachment point, countersunk washer, and
plain washers). Torque each bolt by using the
torque value information identified in
paragraph (g) of this AD.
(iii) For Model 210 helicopters, accomplish
the actions required by paragraphs
(h)(1)(iii)(A) through (C) of this AD.
(A) With the tail boom supported, remove
the upper LH bolt, and the steel alloy barrel
nut P/N NAS577B9A, including the retainer,
from service. Remove the countersunk
washer, and plain washers, and install new
nickel alloy barrel nut P/N NAS577C9A, new
retainer P/N NAS578C9A, airworthy
countersunk washer, airworthy plain
washers, and a new bolt in accordance with
the Accomplishment Instructions, Part I,
paragraphs 5 through 7 of Bell Alert Service
Bulletin (ASB) 210–21–15, Revision A, dated
February 23, 2022 (ASB 210–21–15, Rev A).
(B) Remove the upper RH bolt, steel alloy
barrel nut P/N NAS577B8A, countersunk
washer, and plain washers. Visually inspect
the upper RH bolt for any corrosion, damaged
threads, wear, and fatigue cracking. If the
upper RH bolt has any corrosion, damaged
threads, wear, or fatigue cracking, before
further flight, remove the upper RH bolt from
service. Visually inspect the removed barrel
nut for cracking. If there is any cracking in
the barrel nut, before further flight, remove
the upper RH bolt from service. Regardless of
the result of the upper RH steel alloy barrel
nut inspection, replace the barrel nut with a
new nickel alloy barrel nut P/N NAS577C8A
and new retainer P/N NAS578C8A. Install a
PO 00000
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80737
new upper RH bolt or reinstall the existing
upper RH bolt (if no cracks in the barrel nut,
and no corrosion, damaged threads, wear, or
fatigue cracking in the bolt were identified),
by following the Accomplishment
Instructions, part I, paragraphs 11 and 12,
including the caution above paragraph 11, of
ASB 210–21–15, Rev A.
(C) Remove one of the lower bolts, its
lower steel alloy barrel nut P/N NAS577B6A,
countersunk washer, and plain washers.
Visually inspect that lower bolt for any
corrosion, damaged threads, wear, and
fatigue cracking. If the lower bolt has any
corrosion, damaged threads, wear, or fatigue
cracking, before further flight, remove the
lower bolt from service. Visually inspect the
removed lower barrel nut for cracking. If
there is any cracking in the lower barrel nut,
before further flight, remove the lower bolt
from service. Regardless of the result of that
lower steel alloy barrel nut inspection,
replace the barrel nut with a new nickel alloy
barrel nut P/N NAS577C6A and new retainer
P/N NAS578C6A. Install a new lower bolt or
reinstall the existing lower bolt (if no cracks
in the barrel nut, and no corrosion, damaged
threads, wear, or fatigue cracking in the bolt
were identified), by following the
Accomplishment Instructions, part I,
paragraphs 16 through 17, including the
caution above paragraph 16, of ASB 210–21–
15, Rev A. Repeat the actions required by this
paragraph for the other lower attachment
point.
(2) After accumulating 1 hour TIS, but not
to exceed 5 hours TIS, after accomplishing
the actions required by paragraph (h)(1) of
this AD, using the torque value information
identified in paragraph (g) of this AD
applicable to your model helicopter, inspect
the torque applied on each bolt. Thereafter,
repeat the torque inspection of each bolt after
accumulating 1 hour TIS, but not to exceed
5 hours TIS, to determine if the torque has
stabilized. Do not exceed three torque
inspections total for each bolt and
accomplish the actions required by
paragraphs (h)(2)(i) and (ii) of this AD.
(i) If the torque on a bolt is below the
minimum allowable torque limit as a result
of any instance of the torque inspection or if
after three torque inspection attempts, the
torque on any bolt has not stabilized, before
further flight, accomplish the actions
required by paragraphs (h)(2)(i)(A) and (B) of
this AD.
(A) Remove the hardware set of one failed
tail boom attachment point (nut, bolt,
countersunk washer, and plain washers for
Model 204B helicopters, and barrel nut, bolt,
retainer, countersunk washer, and plain
washers for Model 205A, 205A–1, 205B, and
210 helicopters). For Model 204B helicopters,
remove the nut from service and for Model
205A, 205A–1, 205B, and 210 helicopters,
remove the barrel nut and retainer from
service as applicable to the affected tail boom
attachment point. Visually inspect the
removed bolt for any corrosion, damaged
threads, wear, and fatigue cracking. If the bolt
has any corrosion, a damaged thread, wear,
or fatigue cracking, before further flight,
remove the bolt from service.
(B) Apply a coating of Aeriol ThixO #2
(3810–0) or Aeriol ThixO SYN (3820–0)
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Federal Register / Vol. 89, No. 193 / Friday, October 4, 2024 / Rules and Regulations
aviation grease to the bolt shank only. Install
a new bolt or reinstall the existing bolt (if no
corrosion, damaged threads, wear, or fatigue
cracking in the bolt were identified) and the
hardware set of the affected tail boom
attachment point (new nut P/N 90–132L6 or
90–132L7, countersunk washer, and plain
washers for Model 204B helicopters, and new
nickel alloy barrel nut P/N NAS577C6A,
NAS577C8A or P/N NAS577C9A and new
retainer P/N NAS578C6A, NAS578C8A, or P/
N NAS577C9A, countersunk washer, and
plain washers for Model 205A, 205A–1,
205B, and 210 helicopters), as applicable to
the affected tail boom attachment point.
Torque the bolt by using the torque value
information identified in paragraph (g) of this
AD. Repeat the actions required by
paragraphs (h)(2)(i)(A) and (B) of this AD for
each failed tail boom attachment point, one
hardware set at a time. Then repeat the
actions required by paragraph (h)(2) of this
AD just for each newly installed or
reinstalled bolt until the torque for all four
tail boom attachment points stabilize.
(ii) If the torque for all four tail boom
attachment points has stabilized, before
further flight, apply a torque stripe to all four
bolts.
(3) Within 600 hours TIS or 12 months,
whichever occurs first after applying torque
stripes to all four bolts as required by
paragraph (h)(2)(ii) of this AD, and thereafter
within intervals not to exceed 600 hours TIS
or 12 months, whichever occurs first, inspect
the torque applied on each bolt using the
torque value information identified in
paragraph (g) of this AD, as applicable to
your model helicopter. If the torque on any
bolt is below the minimum allowable torque
limit, accomplish the actions required by
paragraphs (h)(3)(i) and (ii) of this AD.
(i) Before further flight, remove the
hardware set of one failed tail boom
attachment point (nut, bolt, countersunk
washer, and plain washers for Model 204B
helicopters, and barrel nut, retainer, bolt,
countersunk washer, and plain washers for
Model 205A, 205A–1, 205B, and 210
helicopters) and then accomplish the actions
required by paragraphs (h)(3)(i)(A), (B), or (C)
of this AD as applicable to your model
helicopter.
(A) For Model 204B helicopters, visually
inspect the removed nut for cracking,
corrosion, and loss of tare torque. If the nut
has any cracking, corrosion, or loss of tare
toque, before further flight, remove the nut
from service and replace with a new nut P/
N 90–132L7 or 90–132L6 as applicable to the
tail boom attachment point. Regardless of the
result of the nut inspection, remove the bolt
from service and replace it with a new bolt
by applying a coating of Aeriol ThixO #2
(3810–0) or Aeriol ThixO SYN (3820–0)
aviation grease to the bolt shank only, and
install the hardware set of the tail boom
attachment point (nut, bolt, and countersunk
washer, and plain washers). Torque each bolt
by using the torque value information
identified in paragraph (g) of this AD. Repeat
the actions required by this paragraph for
each failed tail boom attachment point, one
hardware set at a time.
(B) For Model 205A, 205A–1, and 205B
helicopters, visually inspect the removed
VerDate Sep<11>2014
17:03 Oct 03, 2024
Jkt 265001
barrel nut for cracking, corrosion, and loss of
tare torque. If the barrel nut has any cracking,
corrosion, or loss of tare toque, before further
flight, remove the barrel nut and retainer
from service and replace them with a new
nickel alloy barrel nut P/N NAS577C6A, or
NAS577C8A, and new retainer P/N
NAS578C6A, or NAS578C8A, with the P/N
of the new nickel alloy barrel nut and the P/
N of the new retainer being as applicable to
the affected tail boom attachment point.
Regardless of the result of the barrel nut
inspection, remove the bolt from service and
replace it with a new bolt. Apply a coating
of Aeriol ThixO #2 (3810–0) or Aeriol ThixO
SYN (3820–0) aviation grease to each bolt
shank only. Install the hardware set of each
tail boom attachment point (nickel alloy
barrel nut, retainer, bolt, countersunk
washer, and plain washers). Torque each bolt
by using the torque value information
identified in paragraph (g) of this AD. Repeat
the actions required by this paragraph for
each failed tail boom attachment point, one
hardware set at a time.
(C) For Model 210 helicopters, visually
inspect the removed barrel nut for cracking,
corrosion, and loss of tare torque. If the barrel
nut has any cracking, corrosion, or loss of
tare toque, before further flight, remove the
barrel nut and retainer from service and
replace them with a new nickel alloy barrel
nut P/N NAS577C6A, NAS577C8A, or
NAS577C9A, and new retainer P/N
NAS578C6A, NAS578C8A, or NAS578C9A,
with the P/N of the new nickel alloy barrel
nut and the P/N of the new retainer being as
applicable to the affected tail boom
attachment point. Regardless of the result of
the barrel nut inspection, remove the bolt
from service and replace it with a new bolt,
apply a coating of Aeriol ThixO #2 (3810–0)
or Aeriol ThixO SYN (3820–0) aviation
grease to each bolt shank only, and torque
each bolt by using the torque value
information identified in paragraph (g) of this
AD. Repeat the actions required by this
paragraph for each failed tail boom
attachment point, one hardware set at a time.
(ii) After accumulating 1 hour TIS, but not
to exceed 5 hours TIS after accomplishing the
actions required by paragraph (h)(3)(i) of this
AD, using the torque value information
identified in paragraph (g) of this AD as
applicable to your model helicopter, inspect
the torque applied on each newly installed
bolt. Thereafter, repeat the torque inspection
of those bolts after accumulating 1 hour TIS,
but not to exceed 5 hours TIS, to determine
if the torque has stabilized. Do not exceed
three torque inspections total for those bolts
and accomplish the actions required by
paragraphs (h)(2)(i) and (ii) of this AD.
(4) Within 5,000 hours TIS or 5 years after
accomplishing the actions required by
paragraph (h)(1) of this AD, whichever occurs
first, and thereafter within intervals not to
exceed 5,000 hours TIS or 5 years, whichever
occurs first, accomplish the actions required
by paragraphs (h)(4)(i) and (ii) of this AD.
(i) Accomplish the actions required by
paragraphs (h)(1)(i), (ii), or (iii) of this AD, as
applicable to your model helicopter.
(ii) After accumulating 1 hour TIS, but not
to exceed 5 hours TIS after accomplishing the
actions required by paragraph (h)(4)(i) of this
PO 00000
Frm 00024
Fmt 4700
Sfmt 4700
AD, using the torque value information
identified in paragraph (g) of this AD as
applicable to your model helicopter, inspect
the torque applied on each bolt. Thereafter,
repeat the torque inspection of those bolts
after accumulating 1 hour TIS, but not to
exceed 5 hours TIS, to determine if the
torque has stabilized. Do not exceed three
torque inspections total for those bolts and
accomplish the actions required by
paragraphs (h)(2)(i) and (ii) of this AD.
(5) As of the effective date of this AD, do
not install the following parts identified in
paragraphs (h)(5)(i) and (ii) of this AD on any
helicopter.
(i) For Model 204B helicopters: steel alloy
nut P/N NAS679A, NAS1291, or MS21042.
(ii) For Model 205A, 205A–1, 205B, and
210 helicopters: steel alloy barrel nut P/N
NAS577B9A, P/N NAS577B8A, or P/N
NAS577B6A.
(i) Special Flight Permit
A one-time special flight permit may be
issued in accordance with 14 CFR 21.197 and
21.199 in order to fly to a maintenance area
to perform the required actions in this AD.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Central Certification
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 certification office,
send it to the attention of the person
identified in paragraph (k) of this AD.
Information may be emailed to 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
For more information about this AD,
contact Michael Perrin, Aviation Safety
Engineer, FAA, 1801 S Airport Road,
Wichita, KS 67209; phone: (562) 627–5362;
email: Michael.j.perrin@faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the material listed in this paragraph under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as
applicable to do the actions required by this
AD, unless the AD specifies otherwise.
(i) Bell Alert Service Bulletin 210–21–15,
Revision A, dated February 23, 2022.
(ii) [Reserved]
(3) For Bell material identified in this AD,
contact Bell Textron Inc., P.O. Box 482, Fort
Worth, TX 76101; phone: (450) 437–2862 or
(800) 363–8023; fax: (450) 433–0272; email:
productsupport@bellflight.com; website:
bellflight.com/support/contact-support.
(4) You may view this material at the FAA,
Office of Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Fort Worth,
TX 76177. For information on the availability
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of this material at the FAA, call: (817) 222–
5110.
(5) You may view this material at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
visit www.archives.gov/federal-register/cfr/
ibr-locations or email fr.inspection@nara.gov.
Issued on September 27, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–22908 Filed 10–3–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2024–1655; Airspace
Docket No. 24–ANE–4]
RIN 2120–AA66
Establishment of Class E Airspace;
Matinicus Island, ME
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action establishes Class
E airspace extending upward from 700
feet above the surface for Matinicus
Island Airport, Matinicus Island, ME, to
accommodate new area navigation
(RNAV) global positioning system (GPS)
standard instrument approach
procedures serving this airport.
Controlled airspace is necessary for the
safety and management of instrument
flight rules (IFR) operations at this
airport.
SUMMARY:
Effective 0901 UTC, December
26, 2024. The Director of the Federal
Register approves this incorporation by
reference action under 1 CFR part 51,
subject to the annual revision of FAA
Order JO 7400.11 and publication of
conforming amendments.
ADDRESSES: A copy of the Notice of
Proposed Rulemaking (NPRM), all
comments received, this final rule, and
all background material may be viewed
online at www.regulations.gov using the
FAA Docket number. Electronic
retrieval help and guidelines are
available on the website. It is available
24 hours a day, 365 days a year.
FAA Order JO 7400.11J, Airspace
Designations, and Reporting Points, and
subsequent amendments can be viewed
online at www.faa.gov/air_traffic/
publications/. For further information,
you can contact the Airspace Policy
Group, Federal Aviation
Administration, 800 Independence
khammond on DSKJM1Z7X2PROD with RULES
DATES:
VerDate Sep<11>2014
17:03 Oct 03, 2024
Jkt 265001
Avenue SW, Washington, DC 20591;
telephone: (202) 267–8783.
FOR FURTHER INFORMATION CONTACT:
Robert Scott Stuart, Operations Support
Group, Eastern Service Center, Federal
Aviation Administration, 1701
Columbia Avenue, College Park, GA
30337; telephone: (404) 305–5926.
SUPPLEMENTARY INFORMATION:
Authority for This Rulemaking
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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. This rulemaking is
promulgated under the authority
described in Subtitle VII, Part A,
Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority, as it establishes
Class E airspace extending upward from
700 feet above the surface for Matinicus
Island Airport, Matinicus Island, ME.
History
The FAA published a notice of
proposed rulemaking for Docket No.
FAA 2024–1655 in the Federal Register
(89 FR 50536; June 14, 2024), proposing
to establish Class E airspace extending
upward from 700 feet above the surface
for Matinicus Island Airport, Matinicus
Island, ME. Interested parties were
invited to participate in this rulemaking
effort by submitting written comments
on the proposal to the FAA. No
comments were received.
Incorporation by Reference
Class E airspace is published in
paragraph 6005 of FAA Order JO
7400.11, Airspace Designations and
Reporting Points, which is incorporated
by reference in 14 CFR 71.1 on an
annual basis. This document amends
the current version of that order, FAA
Order JO 7400.11J, dated July 31, 2024,
and effective September 15, 2024. FAA
Order JO 7400.11J is publicly available
as listed in the ADDRESSES section of this
document. These amendments will be
published in the next update to FAA
Order JO 7400.11. FAA Order JO
7400.11J lists Class A, B, C, D, and E
airspace areas, air traffic service routes,
and reporting points.
The Rule
This amendment to 14 CFR part 71
establishes Class E airspace extending
upward from 700 feet above the surface
PO 00000
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Fmt 4700
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80739
within a 6-mile radius of Matinicus
Island Airport, Matinicus Island, ME,
providing the controlled airspace
required to support the new RNAV
(GPS) standard instrument approach
procedures for IFR operations at the
airport. Controlled airspace is necessary
for the safety and management of
instrument flight rules (IFR) operations
in the area.
Regulatory Notices and Analyses
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current. It, therefore: (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)
does not warrant preparation of a
Regulatory Evaluation as the anticipated
impact is so minimal. Since this is a
routine matter that will only affect air
traffic procedures and air navigation, it
is certified that this proposed rule,
when promulgated, will not have a
significant economic impact on a
substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
Environmental Review
The FAA has determined that this
action qualifies for categorical exclusion
under the National Environmental
Policy Act in accordance with FAA
Order 1050.1F, ‘‘Environmental
Impacts: Policies and Procedures,’’
paragraph 5–6.5a. This airspace action
is not expected to cause any potentially
significant environmental impacts, and
no extraordinary circumstances exist
that warrant the preparation of an
environmental assessment.
Lists of Subjects in 14 CFR Part 71
Airspace, Incorporation by reference,
Navigation (air).
The Amendment
In consideration of the foregoing, the
Federal Aviation Administration
amends 14 CFR part 71 as follows:
PART 71—DESIGNATION OF CLASS A,
B, C, D, AND E AIRSPACE AREAS; AIR
TRAFFIC SERVICE ROUTES; AND
REPORTING POINTS
1. The authority citation for 14 CFR
part 71 continues to read as follows:
■
Authority: 49 U.S.C. 106(f), 106(g); 40103,
40113, 40120; E.O. 10854, 24 FR 9565, 3 CFR,
1959–1963 Comp., p. 389.
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]]>Agencies
[Federal Register Volume 89, Number 193 (Friday, October 4, 2024)]
[Rules and Regulations]
[Pages 80734-80739]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-22908]
[[Page 80734]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0600; Project Identifier AD-2021-01160-R;
Amendment 39-22827; AD 2024-17-02]
RIN 2120-AA64
Airworthiness Directives; Bell Textron Inc. Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Bell Textron Inc. (Bell) Model 204B, 205A, 205A-1, 205B, and 210
helicopters. This AD was prompted by an accident and incidents
involving failure of the tail boom attachment structure. This AD
requires inspecting the tail boom assembly hardware, replacing tail
boom attachment hardware, greasing the bolt shanks, and inspecting
torque. This AD also prohibits installing steel alloy nuts on any
helicopter. The FAA is issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective November 8, 2024.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 8,
2024.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2022-0600; 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, 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.
Material Incorporated by Reference:
For Bell material identified in this AD, contact Bell
Textron Inc., P.O. Box 482, Fort Worth, TX 76101; phone: (450) 437-2862
or (800) 363-8023; fax: (450) 433-0272; email:
[email protected]; website: 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 (817) 222-5110.
Other Related Material: For other material identified in this final
rule, contact Bell Textron Inc., P.O. Box 482, Fort Worth, TX 76101;
phone: (450) 437-2862 or (800) 363-8023; fax: (450) 433-0272; email:
[email protected]; website: bellflight.com/support/contact-support.
FOR FURTHER INFORMATION CONTACT: Michael Perrin, Aviation Safety
Engineer, FAA, 1801 S Airport Road, Wichita, KS 67209; phone: (562)
627-5362; email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued AD 2021-15-14, Amendment 39-21661 (86 FR 39942, July
26, 2021) (AD 2021-15-14) for various restricted category helicopters.
AD 2021-15-14 was prompted by an accident involving a Model UH-1B
helicopter and two forced landings involving Model UH-1H and UH-1F
helicopters, due to tail boom attachment structure failures. Each of
the three events involved a failure of the upper left-hand (LH) tail
boom attachment fitting, which is the most heavily loaded of the four
tail boom attach points. The FAA issued AD 2021-15-14 to address
fatigue cracking of tail boom attachment fittings, cap angles,
longerons, and bolts.
Due to their similarity to Model UH-1B, UH-1H, and UH-1F
helicopters, the FAA determined that Bell Model 204B, 205A, 205A-1,
205B, and 210 helicopters are also affected by the same unsafe
condition and issued a notice of proposed rulemaking (NPRM) to propose
the same actions as those required in AD 2021-15-14. The NPRM published
in the Federal Register on June 7, 2022 (87 FR 34587) to amend 14 CFR
part 39 and would have applied to Bell Model 204B, 205A, 205A-1, 205B,
and 210 helicopters. In the NPRM, the FAA proposed to require revising
the helicopter's existing rotorcraft flight manual to incorporate pre-
flight checks; removing excess paint and sealant and cleaning certain
parts; and repetitively inspecting structural components that attach
the tail boom to the fuselage. Depending on the inspection results, the
FAA proposed to require repairing or replacing components or re-bonding
the structure.
Based on comments received on the NPRM, the FAA determined changes
to the proposed required actions were necessary. Accordingly, the FAA
issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14
CFR part 39 by adding an AD that would apply to all Bell Model 204B,
205A, 205A-1, 205B, and 210 helicopters. The SNPRM published in the
Federal Register on May 8, 2024 (89 FR 38846).
In the SNPRM, for Bell Model 204B helicopters, the FAA proposed to
require, with the tail boom assembly removed, removing the upper LH
bolt from service and inspecting the bolt's associated attachment
hardware and, depending on the inspection results, removing the
associated nut from service. The FAA also proposed to require visually
inspecting each bulkhead, bolt hole, attachment fitting, the three
other nuts, the upper right-hand (RH) bolt, and two lower bolts,
including the bolt shank and head radii. Depending on inspection
results, the FAA proposed to require repairing or replacing an affected
bulkhead or affected fitting, removing certain part-numbered nuts,
removing any affected nut and its associated bolt from service, and
removing any affected bolt from service.
For Bell Model 205A, 205A-1, and 205B helicopters, the FAA proposed
to require, with the tail boom assembly removed, removing the upper LH
bolt from service and inspecting its associated barrel nut and retainer
and, depending on the inspection results, removing barrel nut and
retainer from service. The FAA also proposed to require visually
inspecting each bulkhead, bolt hole, attachment fitting, the three
other barrel nuts, associated retainers, the upper RH bolt, and two
lower bolts, including the bolt shank and head radii. Depending on
inspection results, the FAA proposed to require repairing or replacing
an affected bulkhead or affected fitting, removing certain part-
numbered barrel nuts and retainers, removing any affected barrel nuts
and its associated bolt from service, and removing any affected bolt
from service.
For Bell Model 210 helicopters, the FAA proposed to require, with
the tail boom supported, removing the upper LH steel alloy barrel nut,
retainer, and bolt from service and removing the countersunk washer and
plain washers and replacing them with a new certain part-numbered
nickel alloy barrel nut, new retainer, new bolt, an airworthy
countersunk washer, and airworthy plain washers. The FAA also proposed
to require visually inspecting the upper RH bolt and its associated
hardware and, depending on the inspection results, removing the upper
RH bolt and barrel nut from service. Additionally, the FAA proposed to
require visually inspecting the two lower bolts and the associated
barrel nuts and, depending on the inspection results, removing any
affected barrel nut and its associated
[[Page 80735]]
bolt from service and removing any affected bolt from service.
For all applicable helicopters, the FAA proposed to require, after
the initial inspections have been completed, applying a coating of
grease to each bolt shank only, installing the applicable hardware, and
torquing each bolt. Thereafter, the FAA proposed to require inspecting
the torque applied on each bolt to determine if the torque has
stabilized and, depending on the results, replacing and inspecting
certain tail boom attachment point hardware and repeating the torque
inspections or applying torque stripes.
Lastly, the FAA proposed to prohibit installing certain part-
numbered steel alloy nuts on Model 204B helicopters and certain part-
numbered steel alloy barrel nuts on Model 205A, 205A-1, 205B, and 210
helicopters.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments on the SNPRM from Helicopter Maintenance
Corporation. The commenter requested that the FAA revise the proposed
AD to allow credit for previous compliance with the visual inspection
of the tail boom attach points and bulkhead, replacement of affected
hardware, and the recurring inspections involving removal of the tail
boom. Helicopter Maintenance Corporation stated that aircraft that are
in compliance with ASB 205-21-118 should only be obligated to comply
with any differences between the AD and the alert service bulletin.
Paragraph (f) of this AD requires compliance unless the actions
have already been done. Therefore, where this AD requires actions
without incorporating Bell Alert Service Bulletin (ASB) 210-21-15,
Revision A, dated February 23, 2022 (ASB 210-21-15, Rev A), by
reference, operators may take credit for those actions they if were
done before the effective date of this AD. Also, where this AD requires
actions in accordance with ASB 210-21-15, Rev A, operators may take
credit for those actions only if they were done before the effective
date of this AD using ASB 210-21-15, Rev A; this AD does not allow
credit for those actions if previously done using the original release
of ASB 210-21-15, (dated January 27, 2022). The FAA did not change this
AD as a result of this comment.
Conclusion
The FAA reviewed the relevant data, considered any 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 products. Except for minor editorial changes, this
AD is adopted as proposed in the SNPRM.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed Bell ASB 210-21-15, Rev A. This material specifies
procedures for replacing the steel alloy barrel nuts with nickel alloy
barrel nuts, inspecting and replacing the tail boom attachment
hardware, stabilizing the tail boom attachment hardware torque,
applying torque seals, and subsequently checking the torque.
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 Material
The FAA also reviewed Bell ASB 205-21-118, Bell ASB 204B-21-75, and
Bell ASB 205B-21-72, each Revision A and dated February 23, 2022. This
material specifies the same procedures as ASB 210-21-15, Rev A.
Differences Between This AD and the Related Material
The related material specifies checking torque, whereas this AD
requires inspecting torque because that action is a maintenance action
that must be performed by persons authorized under 14 CFR 43.3.
When stabilizing the tail boom attachment hardware torque, the
related material does not clearly specify actions for each time the
torque is below the minimum limit during any torque stabilization
inspection, whereas this AD requires replacing and inspecting certain
tail boom attachment point hardware, stabilizing the torque of the
replaced hardware set, and applying torque stripes.
Costs of Compliance
The FAA estimates that this AD affects 62 (five Model 204B
helicopters, fifty-three Model 205A, 205A-1, and 205B helicopters, and
four Model 210 helicopters) of U.S. registry. Labor costs are estimated
at $85 per work-hour. Based on these numbers, the FAA estimates the
following costs to comply with this AD.
For the initial requirements for Model 204B helicopters, inspecting
or replacing up to four bolts (which includes applying a coating of
grease), inspecting each bulkhead, inspecting each fitting and bolt
hole, inspecting and stabilizing the torque, and applying torque
stripes will take up to approximately 8.5 work-hours for an estimated
labor cost of up to $723. The parts cost for an upper LH bolt will be
approximately $196 and the parts cost for the other bolts will be
approximately $89 per bolt. The parts cost for four new nuts will be
approximately $680. The parts cost to apply torque stripes will be a
nominal amount. The estimated cost for these actions will be up to
approximately $1,866 per helicopter and $9,330 for the U.S. fleet.
For the initial requirements for Model 205A, 205A-1, and 205B
helicopters, replacing the four steel alloy barrel nuts with new nickel
alloy barrel nuts, inspecting or replacing up to four bolts (which
includes applying a coating of grease), inspecting each bulkhead,
inspecting and stabilizing the torque, and applying torque stripes will
take up to approximately 8.5 work-hours for an estimated labor cost of
up to $723. The parts cost for the four new nickel alloy barrel nuts
(including retainers) will be approximately $680. The parts cost for an
upper LH bolt will be approximately $196 and the parts cost for the
other bolts will be approximately $89 per bolt. The parts cost to apply
torque stripes will be a nominal amount. The estimated cost for these
actions will be up to approximately $1,866 per helicopter and $98,898
for the U.S. fleet.
For the initial requirements for Model 210 helicopters, replacing
the four steel alloy barrel nuts with new nickel alloy barrel nuts,
inspecting or replacing up to four bolts (which includes applying a
coating of grease), inspecting and stabilizing the torque, and applying
torque stripes will take up to approximately 8.5 work-hours for an
estimated labor cost of up to $723. The parts cost for the four new
nickel alloy barrel nuts (including retainers) will be approximately
$680. The parts cost for an upper LH bolt will be approximately $196
and the parts cost for the other bolts will be approximately $89 per
bolt. The parts cost to apply torque stripes will be a nominal amount.
The estimated cost for these actions will be up to approximately $1,866
per helicopter and $7,464 for the U.S. fleet.
For all applicable helicopters, inspecting the torque applied on
each bolt will take approximately 1 work-hour for an estimated cost of
$85 per helicopter and $5,270 for the U.S. fleet, per inspection cycle.
For all applicable helicopters, replacing an upper LH bolt,
stabilizing the torque, and applying a torque stripe will take up to
approximately 5 work-hours. The parts cost for an upper LH bolt will be
approximately $196 and the parts cost to apply a torque stripe will
[[Page 80736]]
be a nominal amount. The estimated cost for these actions will be up to
approximately $621 per helicopter and $38,502 for the U.S. fleet, per
replacement cycle. Inspecting one of the other bolts, stabilizing the
torque, and applying a torque stripe will take up to approximately 3.5
work-hours for an estimated cost of $298 per other bolt and $18,476 for
the U.S. fleet per other bolt per inspection cycle. If required,
replacing a bolt following that inspection will take a minimal amount
of additional time and the parts cost will be approximately $89.
If required as a result of failing any torque inspection required
by this AD, visually inspecting a nut or a barrel nut, replacing a
bolt, stabilizing the torque, and applying a torque stripe will take up
to approximately 5.5 work-hours per failed hardware set. The parts cost
for an upper LH bolt will be approximately $196 and the parts cost for
the other bolts will be approximately $89 per bolt. The parts cost to
apply a torque stripe will be a nominal amount. The estimated cost for
these actions will be $664 (upper LH bolt) or $557 (other bolts), per
failed hardware set. If required, replacing a nut following that
inspection will take a minimal amount of additional time and the parts
cost for a nut will be approximately $89 per nut. If required,
replacing a barrel nut following that inspection will take a minimal
amount of additional time and a parts cost of approximately $173 per
barrel nut.
The corrective action that may be needed as a result of the
bulkhead inspection could vary significantly from helicopter to
helicopter. The FAA has no data to determine the costs to accomplish
the corrective action or the number of helicopters that may require
corrective action.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2024-17-02 Bell Textron Inc.: Amendment 39-22827; Docket No. FAA-
2022-0600; Project Identifier AD-2021-01160-R.
(a) Effective Date
This airworthiness directive (AD) is effective November 8, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bell Textron Inc. Model 204B, 205A, 205A-1,
205B, and 210 helicopters, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) 5302, Rotorcraft Tail
Boom.
(e) Unsafe Condition
This AD was prompted by an accident and incidents involving
failure of the tail boom attachment structure. The FAA is issuing
this AD to address fatigue cracking of tail boom attachment
fittings, cap angles, longerons, and bolts. The unsafe condition, if
not addressed, could result in separation of the tail boom from the
helicopter and subsequent loss of control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Allowable Torque Values (in-lbs)
----------------------------------------------------------------------------------------------------------------
Tail boom attachment point Model 204B Model 205A/205A-1 Model 205B Model 210
----------------------------------------------------------------------------------------------------------------
Upper left-hand bolt............. 570-610 1000-1200 1000-1200 1300-1600
Upper right-hand bolt............ 360-380 1000-1200 1000-1200 1000-1200
Lower left-hand bolt............. 360-380 400-430 400-430 400-430
Lower right-hand bolt............ 360-380 400-430 400-430 400-430
----------------------------------------------------------------------------------------------------------------
(h) Required Actions
(1) Within 300 hours time-in-service (TIS) or 90 days after the
effective date of this AD, whichever occurs first, accomplish the
actions required by paragraphs (h)(1)(i), (ii), or (iii) of this AD
as applicable to your model helicopter. For purposes of this AD, the
word ``new'' is defined as having zero total hours TIS.
(i) For Model 204B helicopters, accomplish the actions required
by paragraphs (h)(1)(i)(A) through (C) of this AD.
(A) With the tail boom assembly removed, remove the upper left-
hand (LH) tail boom attachment bolt (bolt) from service and inspect
its associated tail boom attachment nut (nut) for mechanical damage,
corrosion, a crack, damaged threads, and wear, and to determine
whether it is a steel alloy part number (P/N) NAS679A, NAS1291, or
MS21042. If there is any mechanical damage, corrosion, a crack, a
damaged thread, or wear, or if nut P/N NAS679A, NAS1291, or MS21042
is installed, before further flight, remove the nut from service.
(B) Visually inspect each bulkhead (FS 195.00 and FS 195.03) and
the bolt holes for mechanical damage, corrosion, and cracks;
visually inspect each attachment fitting for
[[Page 80737]]
mechanical damage, corrosion, cracks, and loose fasteners; determine
if any of the three other nuts are a steel alloy P/N NAS679A,
NAS1291, or MS21042; and visually inspect the other three nuts, the
upper right-hand (RH) bolt, and two lower bolts for mechanical
damage, corrosion, cracks, damaged threads, and wear, including the
bolt shank and head radii of the bolts for a damaged thread, wear,
and mechanical damage.
(1) If there is any mechanical damage, corrosion, or cracks on
any bulkhead (FS 195.00 or FS 195.03), or any mechanical damage,
corrosion, or cracks on any bolt holes, or if there is any
mechanical damage, corrosion, cracks, or loose fasteners on any
attachment fitting, before further flight, repair or replace the
affected bulkhead or the affected attachment fitting, as
appropriate, in accordance with FAA-approved procedures.
(2) If there is any mechanical damage, corrosion, a crack, a
damaged thread, or wear on any nut, or if nut P/N NAS679A, NAS1291,
or MS21042 is installed, before further flight, remove the affected
nut from service. If there is a crack on any nut, before further
flight, also remove its associated bolt from service.
(3) If there is any mechanical damage, corrosion, a crack, a
damaged thread, or wear on the on the upper RH bolt or two lower
bolts, which includes the bolt shank or head radii, before further
flight, remove the affected bolt from service.
(C) Apply a coating of Aeriol ThixO #2 (3810-0) or Aeriol ThixO
SYN (3820-0) aviation grease to each bolt shank only. Install the
hardware set of each tail boom attachment point (nickel alloy nut P/
N 90-132L7 or 90-132L6, as applicable to the affected tail boom
attachment point, new upper LH bolt P/N NAS627-21, upper RH and two
lower bolts P/N NAS626-20, countersunk washer, and plain washers).
Torque each bolt by using the torque value information identified in
paragraph (g) of this AD.
(ii) For Model 205A, 205A-1, and 205B helicopters, accomplish
the actions required by paragraphs (h)(1)(ii)(A) through (C) of this
AD.
(A) With the tail boom assembly removed, remove the upper LH
bolt from service and inspect its associated tail boom attachment
barrel nut (barrel nut) and retainer for mechanical damage,
corrosion, a crack, damaged threads, and wear, and to determine
whether it is a steel alloy barrel nut P/N NAS577B8A. If there is
any mechanical damage, corrosion, a crack, a damaged thread, or
wear, or if barrel nut P/N NAS577B8A is installed, before further
flight, remove the barrel nut and its associated retainer from
service.
(B) Visually inspect each bulkhead (BS 17.31 and FS 243.89) and
the bolt holes for mechanical damage, corrosion, and cracks;
visually inspect each attachment fitting for mechanical damage,
corrosion, cracks, and loose fasteners; determine if any of the
three other barrel nuts are steel alloy P/N NAS577B8A or P/N
NAS577B6A; and visually inspect the other three barrel nuts and the
associated retainers, the upper RH bolt, and two lower bolts for
mechanical damage, corrosion, cracks, damaged threads, and wear,
including the bolt shank and head radii of the bolts for a damaged
thread, wear, and mechanical damage.
(1) If there is any mechanical damage, corrosion, or cracks on
any bulkhead (BS 17.31 or FS 243.89), or any mechanical damage,
corrosion, or cracks on any bolt holes, or if there is any
mechanical damage, corrosion, cracks, or loose fasteners on any
attachment fitting, before further flight, repair or replace the
affected bulkhead or the affected attachment fitting, as
appropriate, in accordance with FAA-approved procedures.
(2) If there is any mechanical damage, corrosion, a crack, a
damaged thread, or wear on any barrel nut or retainer, or if barrel
nut P/N NAS577B8A or NAS577B6A is installed, before further flight,
remove the affected barrel nut and retainer (as a pair) from
service. If there is a crack on any nut, before further flight, also
remove its associated bolt from service.
(3) If there is any mechanical damage, corrosion, a crack, a
damaged thread, or wear on the upper RH bolt or two lower bolts,
which includes the bolt shank or head radii, before further flight,
remove the affected bolt from service.
(C) Apply a coating of Aeriol ThixO #2 (3810-0) or Aeriol ThixO
SYN (3820-0) aviation grease to each bolt shank only. Install the
hardware set of each tail boom attachment point (nickel alloy barrel
nut P/N NAS577C6A or P/N NAS577C8A and retainer P/N NAS578C6A or P/N
NAS578C8A, as applicable to the affected tail boom attachment point,
new upper LH bolt P/N NAS628-22, upper RH and two lower bolts P/N
NAS628-22 or NAS626-18, as applicable to the affected tail boom
attachment point, countersunk washer, and plain washers). Torque
each bolt by using the torque value information identified in
paragraph (g) of this AD.
(iii) For Model 210 helicopters, accomplish the actions required
by paragraphs (h)(1)(iii)(A) through (C) of this AD.
(A) With the tail boom supported, remove the upper LH bolt, and
the steel alloy barrel nut P/N NAS577B9A, including the retainer,
from service. Remove the countersunk washer, and plain washers, and
install new nickel alloy barrel nut P/N NAS577C9A, new retainer P/N
NAS578C9A, airworthy countersunk washer, airworthy plain washers,
and a new bolt in accordance with the Accomplishment Instructions,
Part I, paragraphs 5 through 7 of Bell Alert Service Bulletin (ASB)
210-21-15, Revision A, dated February 23, 2022 (ASB 210-21-15, Rev
A).
(B) Remove the upper RH bolt, steel alloy barrel nut P/N
NAS577B8A, countersunk washer, and plain washers. Visually inspect
the upper RH bolt for any corrosion, damaged threads, wear, and
fatigue cracking. If the upper RH bolt has any corrosion, damaged
threads, wear, or fatigue cracking, before further flight, remove
the upper RH bolt from service. Visually inspect the removed barrel
nut for cracking. If there is any cracking in the barrel nut, before
further flight, remove the upper RH bolt from service. Regardless of
the result of the upper RH steel alloy barrel nut inspection,
replace the barrel nut with a new nickel alloy barrel nut P/N
NAS577C8A and new retainer P/N NAS578C8A. Install a new upper RH
bolt or reinstall the existing upper RH bolt (if no cracks in the
barrel nut, and no corrosion, damaged threads, wear, or fatigue
cracking in the bolt were identified), by following the
Accomplishment Instructions, part I, paragraphs 11 and 12, including
the caution above paragraph 11, of ASB 210-21-15, Rev A.
(C) Remove one of the lower bolts, its lower steel alloy barrel
nut P/N NAS577B6A, countersunk washer, and plain washers. Visually
inspect that lower bolt for any corrosion, damaged threads, wear,
and fatigue cracking. If the lower bolt has any corrosion, damaged
threads, wear, or fatigue cracking, before further flight, remove
the lower bolt from service. Visually inspect the removed lower
barrel nut for cracking. If there is any cracking in the lower
barrel nut, before further flight, remove the lower bolt from
service. Regardless of the result of that lower steel alloy barrel
nut inspection, replace the barrel nut with a new nickel alloy
barrel nut P/N NAS577C6A and new retainer P/N NAS578C6A. Install a
new lower bolt or reinstall the existing lower bolt (if no cracks in
the barrel nut, and no corrosion, damaged threads, wear, or fatigue
cracking in the bolt were identified), by following the
Accomplishment Instructions, part I, paragraphs 16 through 17,
including the caution above paragraph 16, of ASB 210-21-15, Rev A.
Repeat the actions required by this paragraph for the other lower
attachment point.
(2) After accumulating 1 hour TIS, but not to exceed 5 hours
TIS, after accomplishing the actions required by paragraph (h)(1) of
this AD, using the torque value information identified in paragraph
(g) of this AD applicable to your model helicopter, inspect the
torque applied on each bolt. Thereafter, repeat the torque
inspection of each bolt after accumulating 1 hour TIS, but not to
exceed 5 hours TIS, to determine if the torque has stabilized. Do
not exceed three torque inspections total for each bolt and
accomplish the actions required by paragraphs (h)(2)(i) and (ii) of
this AD.
(i) If the torque on a bolt is below the minimum allowable
torque limit as a result of any instance of the torque inspection or
if after three torque inspection attempts, the torque on any bolt
has not stabilized, before further flight, accomplish the actions
required by paragraphs (h)(2)(i)(A) and (B) of this AD.
(A) Remove the hardware set of one failed tail boom attachment
point (nut, bolt, countersunk washer, and plain washers for Model
204B helicopters, and barrel nut, bolt, retainer, countersunk
washer, and plain washers for Model 205A, 205A-1, 205B, and 210
helicopters). For Model 204B helicopters, remove the nut from
service and for Model 205A, 205A-1, 205B, and 210 helicopters,
remove the barrel nut and retainer from service as applicable to the
affected tail boom attachment point. Visually inspect the removed
bolt for any corrosion, damaged threads, wear, and fatigue cracking.
If the bolt has any corrosion, a damaged thread, wear, or fatigue
cracking, before further flight, remove the bolt from service.
(B) Apply a coating of Aeriol ThixO #2 (3810-0) or Aeriol ThixO
SYN (3820-0)
[[Page 80738]]
aviation grease to the bolt shank only. Install a new bolt or
reinstall the existing bolt (if no corrosion, damaged threads, wear,
or fatigue cracking in the bolt were identified) and the hardware
set of the affected tail boom attachment point (new nut P/N 90-132L6
or 90-132L7, countersunk washer, and plain washers for Model 204B
helicopters, and new nickel alloy barrel nut P/N NAS577C6A,
NAS577C8A or P/N NAS577C9A and new retainer P/N NAS578C6A,
NAS578C8A, or P/N NAS577C9A, countersunk washer, and plain washers
for Model 205A, 205A-1, 205B, and 210 helicopters), as applicable to
the affected tail boom attachment point. Torque the bolt by using
the torque value information identified in paragraph (g) of this AD.
Repeat the actions required by paragraphs (h)(2)(i)(A) and (B) of
this AD for each failed tail boom attachment point, one hardware set
at a time. Then repeat the actions required by paragraph (h)(2) of
this AD just for each newly installed or reinstalled bolt until the
torque for all four tail boom attachment points stabilize.
(ii) If the torque for all four tail boom attachment points has
stabilized, before further flight, apply a torque stripe to all four
bolts.
(3) Within 600 hours TIS or 12 months, whichever occurs first
after applying torque stripes to all four bolts as required by
paragraph (h)(2)(ii) of this AD, and thereafter within intervals not
to exceed 600 hours TIS or 12 months, whichever occurs first,
inspect the torque applied on each bolt using the torque value
information identified in paragraph (g) of this AD, as applicable to
your model helicopter. If the torque on any bolt is below the
minimum allowable torque limit, accomplish the actions required by
paragraphs (h)(3)(i) and (ii) of this AD.
(i) Before further flight, remove the hardware set of one failed
tail boom attachment point (nut, bolt, countersunk washer, and plain
washers for Model 204B helicopters, and barrel nut, retainer, bolt,
countersunk washer, and plain washers for Model 205A, 205A-1, 205B,
and 210 helicopters) and then accomplish the actions required by
paragraphs (h)(3)(i)(A), (B), or (C) of this AD as applicable to
your model helicopter.
(A) For Model 204B helicopters, visually inspect the removed nut
for cracking, corrosion, and loss of tare torque. If the nut has any
cracking, corrosion, or loss of tare toque, before further flight,
remove the nut from service and replace with a new nut P/N 90-132L7
or 90-132L6 as applicable to the tail boom attachment point.
Regardless of the result of the nut inspection, remove the bolt from
service and replace it with a new bolt by applying a coating of
Aeriol ThixO #2 (3810-0) or Aeriol ThixO SYN (3820-0) aviation
grease to the bolt shank only, and install the hardware set of the
tail boom attachment point (nut, bolt, and countersunk washer, and
plain washers). Torque each bolt by using the torque value
information identified in paragraph (g) of this AD. Repeat the
actions required by this paragraph for each failed tail boom
attachment point, one hardware set at a time.
(B) For Model 205A, 205A-1, and 205B helicopters, visually
inspect the removed barrel nut for cracking, corrosion, and loss of
tare torque. If the barrel nut has any cracking, corrosion, or loss
of tare toque, before further flight, remove the barrel nut and
retainer from service and replace them with a new nickel alloy
barrel nut P/N NAS577C6A, or NAS577C8A, and new retainer P/N
NAS578C6A, or NAS578C8A, with the P/N of the new nickel alloy barrel
nut and the P/N of the new retainer being as applicable to the
affected tail boom attachment point. Regardless of the result of the
barrel nut inspection, remove the bolt from service and replace it
with a new bolt. Apply a coating of Aeriol ThixO #2 (3810-0) or
Aeriol ThixO SYN (3820-0) aviation grease to each bolt shank only.
Install the hardware set of each tail boom attachment point (nickel
alloy barrel nut, retainer, bolt, countersunk washer, and plain
washers). Torque each bolt by using the torque value information
identified in paragraph (g) of this AD. Repeat the actions required
by this paragraph for each failed tail boom attachment point, one
hardware set at a time.
(C) For Model 210 helicopters, visually inspect the removed
barrel nut for cracking, corrosion, and loss of tare torque. If the
barrel nut has any cracking, corrosion, or loss of tare toque,
before further flight, remove the barrel nut and retainer from
service and replace them with a new nickel alloy barrel nut P/N
NAS577C6A, NAS577C8A, or NAS577C9A, and new retainer P/N NAS578C6A,
NAS578C8A, or NAS578C9A, with the P/N of the new nickel alloy barrel
nut and the P/N of the new retainer being as applicable to the
affected tail boom attachment point. Regardless of the result of the
barrel nut inspection, remove the bolt from service and replace it
with a new bolt, apply a coating of Aeriol ThixO #2 (3810-0) or
Aeriol ThixO SYN (3820-0) aviation grease to each bolt shank only,
and torque each bolt by using the torque value information
identified in paragraph (g) of this AD. Repeat the actions required
by this paragraph for each failed tail boom attachment point, one
hardware set at a time.
(ii) After accumulating 1 hour TIS, but not to exceed 5 hours
TIS after accomplishing the actions required by paragraph (h)(3)(i)
of this AD, using the torque value information identified in
paragraph (g) of this AD as applicable to your model helicopter,
inspect the torque applied on each newly installed bolt. Thereafter,
repeat the torque inspection of those bolts after accumulating 1
hour TIS, but not to exceed 5 hours TIS, to determine if the torque
has stabilized. Do not exceed three torque inspections total for
those bolts and accomplish the actions required by paragraphs
(h)(2)(i) and (ii) of this AD.
(4) Within 5,000 hours TIS or 5 years after accomplishing the
actions required by paragraph (h)(1) of this AD, whichever occurs
first, and thereafter within intervals not to exceed 5,000 hours TIS
or 5 years, whichever occurs first, accomplish the actions required
by paragraphs (h)(4)(i) and (ii) of this AD.
(i) Accomplish the actions required by paragraphs (h)(1)(i),
(ii), or (iii) of this AD, as applicable to your model helicopter.
(ii) After accumulating 1 hour TIS, but not to exceed 5 hours
TIS after accomplishing the actions required by paragraph (h)(4)(i)
of this AD, using the torque value information identified in
paragraph (g) of this AD as applicable to your model helicopter,
inspect the torque applied on each bolt. Thereafter, repeat the
torque inspection of those bolts after accumulating 1 hour TIS, but
not to exceed 5 hours TIS, to determine if the torque has
stabilized. Do not exceed three torque inspections total for those
bolts and accomplish the actions required by paragraphs (h)(2)(i)
and (ii) of this AD.
(5) As of the effective date of this AD, do not install the
following parts identified in paragraphs (h)(5)(i) and (ii) of this
AD on any helicopter.
(i) For Model 204B helicopters: steel alloy nut P/N NAS679A,
NAS1291, or MS21042.
(ii) For Model 205A, 205A-1, 205B, and 210 helicopters: steel
alloy barrel nut P/N NAS577B9A, P/N NAS577B8A, or P/N NAS577B6A.
(i) Special Flight Permit
A one-time special flight permit may be issued in accordance
with 14 CFR 21.197 and 21.199 in order to fly to a maintenance area
to perform the required actions in this AD.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Central Certification 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 certification office, 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 Michael Perrin,
Aviation Safety Engineer, FAA, 1801 S Airport Road, Wichita, KS
67209; phone: (562) 627-5362; email: [email protected].
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the material listed in this paragraph
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as applicable to do the actions
required by this AD, unless the AD specifies otherwise.
(i) Bell Alert Service Bulletin 210-21-15, Revision A, dated
February 23, 2022.
(ii) [Reserved]
(3) For Bell material identified in this AD, contact Bell
Textron Inc., P.O. Box 482, Fort Worth, TX 76101; phone: (450) 437-
2862 or (800) 363-8023; fax: (450) 433-0272; email:
[email protected]; website: bellflight.com/support/contact-support.
(4) You may view this material at the FAA, Office of Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy., Fort Worth, TX
76177. For information on the availability
[[Page 80739]]
of this material at the FAA, call: (817) 222-5110.
(5) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].
Issued on September 27, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-22908 Filed 10-3-24; 8:45 am]
BILLING CODE 4910-13-P
