Airworthiness Directives; Bell Textron Canada Limited (Type Certificate Previously Held by Bell Helicopter Textron Canada Limited) Helicopters, 69161-69164 [2022-25030]
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Federal Register / Vol. 87, No. 222 / Friday, November 18, 2022 / Rules and Regulations
Instructions, Part B, paragraphs (82) through
(86), (88), and (104) of Piaggio SB 80–0405.
(2) If, as part of the corrective actions
required by paragraph (g)(1) of this AD, you
repaired areas of the fuselage skin but did not
replace the panels, do the following:
(i) Within 60 days after completing the
actions required by paragraph (g)(1) of this
AD, report the inspection results, including
the information specified in the Confirmation
Slip attached to Piaggio SB 80–0405, to
Piaggio at technicalsupport@
piaggioaerospace.it; and
(ii) Repeat the requirements of paragraph
(g)(1) of this AD at intervals not to exceed
660 hours time-in-service (TIS) or 26 months,
whichever occurs first.
(3) If, as part of the corrective actions
required by paragraph (g)(1) of this AD, you
replaced the panels, within 60 days after
completing the actions required by paragraph
(g)(1) of this AD, report the inspection
results, including the information specified
in the Confirmation Slip attached to Piaggio
SB 80–0405, to Piaggio at technicalsupport@
piaggioaerospace.it.
(4) If, during all of the inspections required
by paragraph (g)(1) of this AD, there is no
corrosion and no primer inconsistencies, no
further action is required by this AD.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the International Validation
Branch, mail it to the address identified in
paragraph (i)(1) of this AD or email to: 9AVS-AIR-730-AMOC@faa.gov. If mailing
information, also submit information by
email.
(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.
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(i) Related Information
(1) For more information about this AD,
contact Mike Kiesov, Aviation Safety
Engineer, FAA, General Aviation & Rotorcraft
Section, International Validation Branch, 901
Locust, Room 301, Kansas City, MO 64106;
phone: (816) 329–4144; email: mike.kiesov@
faa.gov.
(2) Refer to EASA AD 2021–0104, dated
April 15, 2021, for more information. This
EASA AD may be found in the AD docket at
regulations.gov under Docket No. FAA–
2022–0599.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
VerDate Sep<11>2014
15:59 Nov 17, 2022
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(i) Piaggio Service Bulletin 80–0405,
Revision 0, dated March 15, 2021.
(ii) Piaggio Service Bulletin 80–0405,
Revision 0, Errata Corrige No. 1, dated March
24, 2021.
(3) For service information identified in
this AD, contact Piaggio Aviation S.p.A.,
P180 Customer Support, via Pionieri e
Aviatori d’Italia, snc—16154 Genoa, Italy;
phone: +39 331 679 74 93; email:
technicalsupport@piaggioaerospace.it.
(4) You may view this service information
at FAA, Airworthiness Products Section,
Operational Safety Branch, 901 Locust,
Kansas City, MO 64106. For information on
the availability of this material at the FAA,
call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email: fr.inspection@nara.gov, or go to:
www.archives.gov/federal-register/cfr/ibrlocations.html.
DATES:
Issued on October 20, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
AGENCY:
Examining the AD Docket
You may examine the AD docket at
regulations.gov by searching for and
locating Docket No. FAA–2022–0286; 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.
FOR FURTHER INFORMATION CONTACT:
Payman Soltani, Aerospace Engineer,
Airframe Section, Los Angeles ACO
Branch, Compliance & Airworthiness
Division, FAA, 3960 Paramount Blvd.,
Lakewood, CA 90712; telephone (562)
627–5313; email payman.soltani@
faa.gov.
SUPPLEMENTARY INFORMATION:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for Bell
Textron Canada Limited (type certificate
previously held by Bell Helicopter
Textron Canada Limited) Model 206L,
206L–1, 206L–3, and 206L–4 helicopters
with a certain part-numbered main rotor
(M/R) blade installed under
Supplemental Type Certificate (STC)
SR02684LA. This AD was prompted by
delamination of M/R blades. This AD
requires a repetitive inspection for
delamination, and depending on the
results, removing the M/R blade from
service and reporting certain
information. The FAA is issuing this AD
to address the unsafe condition on these
products.
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to Bell Textron Canada Limited
Model 206L, 206L–1, 206L–3, and
206L–4 helicopters with a certain partnumbered M/R blade installed under
STC SR02684LA. The NPRM published
in the Federal Register on March 24,
2022 (87 FR 16652). The NPRM was
prompted by testing by Van Horn
Aviation, LLC (Van Horn), which
revealed the potential for delamination
in M/R blade part number (P/N)
20633000–101. Delaminations were
then confirmed by inspection of inservice M/R blades. Testing by Van
Horn confirmed that the 90° plies fail in
spanwise tension (normal to the fiber
[FR Doc. 2022–25029 Filed 11–17–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–0286; Project
Identifier AD–2021–01081–R; Amendment
39–22223; AD 2022–22–08]
RIN 2120–AA64
Airworthiness Directives; Bell Textron
Canada Limited (Type Certificate
Previously Held by Bell Helicopter
Textron Canada Limited) Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
PO 00000
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This AD is effective December
23, 2022.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 23, 2022.
ADDRESSES: For service information
identified in this final rule, contact
Dean Rosenlof, Van Horn Aviation, LLC,
1510 West Drake Drive, Tempe, AZ,
85283, United States; phone: (480) 483–
4202; email: dean@
vanhornaviation.com. You may view
this service information at the FAA,
Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177. For information on the
availability of this material at the FAA,
call (817) 222–5110. It is also available
at regulations.gov by searching for and
locating Docket No. FAA–2022–0286.
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Federal Register / Vol. 87, No. 222 / Friday, November 18, 2022 / Rules and Regulations
direction) at the inboard end of the
weight receptacle near M/R blade
station 186.0. Delamination then
propagates outboard from M/R blade
station 186.0 at the interface between
the 0° and 90° plies. According to Van
Horn, fatigue testing has shown that the
delamination initiates almost
immediately and progresses slowly in a
stable, predictable manner. The
delamination has been found to develop
first on the lower surface and grow
outboard from the inboard end of the
weight receptacle and forward of the
balance weight pocket. After
approximately 4 to 6 inches growth of
the delamination on the lower surface,
a similar delamination becomes
detectable on the M/R blade upper
surface. Should the delaminations
continue to grow to the point of static
overload, the receptacle could depart
the M/R blade. In the NPRM, the FAA
proposed to require, at specified
intervals, removing the affected M/R
blade, drawing rectangular inspection
areas ‘‘Zone 1’’ and ‘‘Zone 2’’ with a
permanent marker, tap inspecting the
inspection areas for delamination,
marking and measuring the length of
any delamination, and depending on the
results, removing the M/R blade from
service. The NPRM also proposed to
require reporting certain information to
Van Horn. The FAA is issuing this AD
to address the unsafe condition on these
products.
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from
one commenter, Van Horn. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
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Request for Changes to the
Measurements of Inspection Areas
Van Horn stated that the M/R blade
stations indicated for inspections are
incorrect in the proposed AD and
requested the FAA revise the required
actions to change the M/R blade stations
for ‘‘Zone 1’’ and ‘‘Zone 2.’’ However,
the measurements Van Horn included in
the comment in the AD docket to correct
the M/R blade stations for ‘‘Zone 1’’ and
‘‘Zone 2’’ were also incorrect. Van Horn
then contacted the FAA to correct these
measurements; a record of this ex parte
contact is included in the AD docket.
For information on locating the docket,
see ‘‘Examining the AD Docket.’’
According to Van Horn’s revised
comments, ‘‘Zone 1’’ described in the
NPRM as M/R blade stations 186.0 and
191.0, beginning 1.1 inches from the
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15:59 Nov 17, 2022
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leading edge of the M/R blade to 4.9
inches from the leading edge of the M/
R blade should be revised to M/R blade
stations 185.75 and 192.75, or measured
from the tip end of the M/R blade
between 36.25 inches and 29.25 inches
beginning 1.2 inches from the leading
edge of the M/R blade to 5.0 inches from
the leading edge of the M/R blade.
‘‘Zone 2’’ described in the NPRM as M/
R blade stations 186.0 and 191.0 should
be revised to M/R blade stations 185.9
and 192.9, or measured from the tip end
of the M/R blade between 36.1 inches
and 29.1 inches.
The FAA agrees and has revised this
AD accordingly.
Request for a Change to the Service
Bulletin Cited in Note 1
Van Horn proposed that Note 1 to
paragraph (g)(2)(i) cite Van Horn Service
Bulletin Notice No. 33000–4R4, dated
March 31, 2022 (SB33000–4R4) rather
than Van Horn Service Bulletin Notice
No. 33000–4R3, dated November 8,
2021 (SB 33000–4R3).
The FAA partially agrees. The FAA
appreciates that the latest revision of
that service bulletin is SB33000–4R4;
however, the portions of that service
bulletin that are specified in the
proposed AD are identical in SB33000–
4R3 and SB33000–4R4. Accordingly, the
FAA has made updates throughout the
Required Actions paragraph to allow
both SB33000–4R3 and SB33000–4R4 in
this final rule.
Request for a Reference to Additional
Service Information in Note 1
Van Horn proposed edits in Note 1 to
paragraph (g)(2)(i) to refer to the Van
Horn Instructions for Continued
Airworthiness, ICA Manual No. VMM–
MR–206L–501, Revision N/C, dated
May 24, 2018, for a blade configuration
drawing.
The FAA disagrees because it does
not provide information that could be
helpful for operators to comply with
this AD.
Request for Additional Tap Hammer
Tool
Van Horn also requested the FAA
revise the list of tap hammers in
paragraph (g)(2)(iii) of the proposed AD
to add Van Horn Aviation Tap Hammer
P/N VHACS0003 to the list of tap
hammers.
The FAA agrees and has revised this
AD as requested.
Conclusion
The FAA reviewed the relevant data,
considered any comments received, and
determined that air safety requires
adopting this AD as proposed.
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Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products. Except for minor editorial
changes, and any other changes
described previously, this AD is
adopted as proposed in the NPRM.
None of the changes will increase the
economic burden on any operator.
Related Service Information Under 1
CFR Part 51
The FAA reviewed SB 33000–4R3 and
SB 33000–4R4. This service information
specifies procedures to identify ‘‘Zone
1’’ and ‘‘Zone 2’’ inspection areas,
accomplish repetitive visual and tap
inspections of the zones to detect and
monitor the growth of any delamination,
and depending on the results, remove
the M/R blade from service and contact
Van Horn. SB 33000–4R3 applies to M/
R blade P/N 20633000–101 serial
numbers A012 through A104. SB
33000–4R4 expanded the applicability
to include M/R blade P/N 20633000–
101 with serial numbers A007, A008,
and A009; these serial-numbered parts
were included in the NPRM’s
applicability.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Differences Between This AD and the
Service Information
This AD requires using certain partnumbered composite tap hammers,
whereas SB 33000–4R3 and SB 33000–
4R4 do not. SB 33000–4R3 and SB
33000–4R4 specify procedures to
visually inspect the M/R blade, whereas
this AD does not. If there is any
delamination in the upper surface
inspection zone (‘‘Zone 1’’), this AD
requires removing the M/R blade from
service, whereas SB 33000–4R3 and SB
33000–4R4 do not specify procedures
for this condition.
Interim Action
The FAA considers this AD to be an
interim action. The inspection reports
that are required by this AD will enable
the FAA to obtain better insight into the
unsafe condition. If final action is later
identified, the FAA might consider
further rulemaking.
Costs of Compliance
The FAA estimates that this AD will
affect 23 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.
Removing, tap inspecting, and reinstalling an M/R blade will take about
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4.5 work-hours for an estimated cost of
$383 per M/R blade, per inspection
cycle and up to $8,809 for the U.S. fleet
per M/R blade, per inspection cycle.
Replacing an M/R blade will take about
4 work-hours and parts will cost about
$71,500 per M/R blade for a total of
$71,840 per M/R blade. Reporting
information to Van Horn will take about
1 work-hour for an estimated cost of $85
per report.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to a penalty for failure to comply with
a collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a currently valid
OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public
reporting for this collection of
information is estimated to take
approximately 1 hour per response,
including the time for reviewing
instructions, searching existing data
sources, gathering and maintaining the
data needed, and completing and
reviewing the collection of information.
All responses to this collection of
information are mandatory. Send
comments regarding this burden
estimate or any other aspect of this
collection of information, including
suggestions for reducing this burden to:
Information Collection Clearance
Officer, Federal Aviation
Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177–1524.
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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.
15:59 Nov 17, 2022
Jkt 259001
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
Authority for This Rulemaking
VerDate Sep<11>2014
Regulatory Findings
2022–22–08 Bell Textron Canada Limited
(Type Certificate Previously Held by Bell
Helicopter Textron Canada Limited):
Amendment 39–22223; Docket No.
FAA–2022–0286; Project Identifier AD–
2021–01081–R.
(a) Effective Date
This airworthiness directive (AD) is
effective December 23, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bell Textron Canada
Limited (type certificate previously held by
Bell Helicopter Textron Canada Limited)
Model 206L, 206L–1, 206L–3, and 206L–4
helicopters, certificated in any category, with
main rotor (M/R) blade part number (P/N)
20633000–101 with serial number A007,
A008, A009, or A012 through A104
inclusive, installed under Supplemental
Type Certificate SR02684LA.
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69163
(d) Subject
Joint Aircraft System Component (JASC)
Code: 6210, Main Rotor Blades.
(e) Unsafe Condition
This AD was prompted by reports of
delamination of M/R blades. The FAA is
issuing this AD to address delamination of an
M/R blade initiating in the 90° plies at the
lower inboard end of the weight pocket
receptacle. The unsafe condition, if not
addressed, could result in reduced structural
integrity of the M/R blade, excessive
vibration, and subsequent loss of control of
the helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Accomplish the actions required by
paragraph (g)(2) of this AD at the following
compliance time, whichever occurs later:
(i) Before the M/R blade accumulates 400
total hours time-in-service (TIS) or 2,400
engine starts since initial installation on any
helicopter, whichever occurs first; or
(ii) Within 100 hours TIS after the effective
date of this AD.
(2) Remove each M/R blade from the
helicopter, place it on a flat, stable surface,
and accomplish the following:
(i) Use a permanent marker to draw
rectangular inspection ‘‘Zone 1’’ on the upper
surface of the M/R blade at M/R blade
stations 185.75 and 192.75, or measured from
the tip end of the M/R blade between 36.25
inches and 29.25 inches, beginning 1.2
inches from the leading edge of the M/R
blade to 5.0 inches from the leading edge of
the M/R blade. Draw lines from the inboard
end to the outboard end to connect each end
at 1.2 inches and 5.0 inches. Draw parallel
lines from the inboard end of the inspection
zone to the outboard end of the inspection
zone, with the lines spaced 0.50 inch apart.
Note 1 to paragraph (g)(2)(i): This note
applies to paragraphs (g)(2)(i) and (ii) of this
AD. Figure 4 of Van Horn Aviation, LLC,
Service Bulletin Notice No. 33000–4R3,
dated November 8, 2021 (SB 33000–4R3),
and Van Horn Aviation, LLC, Service
Bulletin Notice No. 33000–4R4, dated March
31, 2022 (SB 33000–4R4) depict ‘‘Zone 1’’
and ‘‘Zone 2.’’
(ii) Use a permanent marker to draw
rectangular inspection ‘‘Zone 2’’ on the lower
surface of the M/R blade at M/R blade
stations 185.9 and 192.9, or measured from
the tip end of the M/R blade between
36.1inches and 29.1 inches, beginning from
the forward edge of the weight receptacle
pocket and extending 1 inch in the direction
towards the leading edge of the M/R blade.
Draw lines from the inboard end to the
outboard end to connect each end at the
weight receptacle pocket and 1 inch forward
of the weight receptacle pocket. Draw
parallel lines from the inboard end of the
inspection zone to the outboard end of the
inspection zone, with the lines spaced 0.50
inch apart.
(iii) Using composite tap hammer Abaris
Training Tap Hammer P/N ABATH, HeatCon
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Tap Hammer P/N HCS1104–01, Brown Tool
Composite Tap Hammer P/N BAT–CTH8,
MATCO Tools Composite Tap Hammer P/N
T4BAT–CTH8, or Van Horn Aviation Tap
Hammer P/N VHACS0003, tap inspect the
areas within ‘‘Zone 1’’ and ‘‘Zone 2’’ for any
delamination by following Tap Inspect
Balance Receptacle, paragraph A.(4) of SB
33000–4R3 or SB 33000–4R4. Where SB
33000–4R3 and SB 33000–4R4 specify to
mark the location where the delamination
starts, use a permanent marker.
(iv) If there are any marks where the
delamination starts, connect the marks
indicating the delamination location and
measure the length at the farthest point from
the inboard end of the inspection area.
(v) If there is any delamination in the lower
surface inspection zone (‘‘Zone 2’’) that is 6.0
or more inches in length or if there is any
delamination in the upper surface inspection
zone (‘‘Zone 1’’), before further flight, remove
the M/R blade from service.
(3) Thereafter repeat the actions required
by paragraph (g)(2) of this AD at intervals not
to exceed 400 hours TIS or 2,400 engine
starts, whichever occurs first.
(4) If there is any delamination, within 30
days after accomplishing the actions required
by paragraphs (g)(1) or (3) of this AD, report
each delamination size and location, and the
total hours TIS and total engine starts since
initial installation of the M/R blade, to Mr.
Dean Rosenlof, Van Horn Aviation, LLC,
1510 West Drake Drive, Tempe, AZ 85283, or
by email to info@vanhornaviation.com.
(i) Van Horn Aviation, LLC, Service
Bulletin Notice No. 33000–4R3, dated
November 8, 2021.
(ii) Van Horn Aviation, LLC, Service
Bulletin Notice No. 33000–4R4, dated March
31, 2022.
(3) For Van Horn Aviation, LLC, service
information identified in this AD, contact
Dean Rosenlof, Van Horn Aviation, LLC,
1510 West Drake Drive, Tempe, AZ, 85283,
United States; phone: (480) 483–4202; email:
dean@vanhornaviation.com.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email: fr.inspection@nara.gov, or go to:
www.archives.gov/federal-register/cfr/ibrlocations.html.
(h) Alternative Methods of Compliance
(AMOCs)
Federal Aviation Administration
(1) The Manager, Los Angeles ACO 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 (i) of this
AD. Information may be emailed to: 9-ANMLAACO-AMOC-REQUESTS@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.
14 CFR Part 71
(i) Related Information
For more information about this AD,
contact Payman Soltani, Aerospace Engineer,
Airframe Section, Los Angeles ACO Branch,
Compliance & Airworthiness Division, FAA,
3960 Paramount Blvd., Lakewood, CA 90712;
telephone (562) 627–5313; email
payman.soltani@faa.gov.
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(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
VerDate Sep<11>2014
15:59 Nov 17, 2022
Jkt 259001
Issued on October 21, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–25030 Filed 11–17–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
[Docket No. FAA–2022–0711; Airspace
Docket No. 21–ANM–64]
RIN 2120–AA66
Amendment of Class E Airspace;
Colorado Plains Regional Airport, CO.
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: This action modifies the Class
E airspace designated as a surface area,
modifies the Class E airspace extending
upward from 700 feet above the surface,
and removes the Class E airspace
extending upward from 1,200 feet above
the surface at Colorado Plains Regional
Airport, CO. Additionally, this action
makes several administrative
modifications to update the airport’s
existing Class E airspace legal
descriptions. These actions will support
the safety and management of
instrument flight rule (IFR) operations at
the airport.
DATES: Effective 0901 UTC, February 23,
2023. The Director of the Federal
Register approves this incorporation by
reference under Title 1 CFR part 51,
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
subject to the annual revision of FAA
Order JO 7400.11, Airspace
Designations and Reporting Points, and
publication of conforming amendments.
ADDRESSES: FAA Order JO 7400.11G,
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
Avenue SW, Washington, DC 20591;
telephone: (202) 267–8783.
FOR FURTHER INFORMATION CONTACT:
Nathan A Chaffman, Federal Aviation
Administration, Western Service Center,
Operations Support Group, 2200 S
216th Street, Des Moines, WA 98198;
telephone (206) 231–3460.
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 would
modify the Class E airspace at Colorado
Plains Regional Airport, CO, to support
IFR operations at the airport.
History
The FAA published a notice of
proposed rulemaking (NPRM) in the
Federal Register for FAA–2022–0711
(87 FR 45723; July 29, 2022) to modify
the Class E airspace designated as a
surface area, modify the Class E airspace
extending upward from 700 feet above
the surface, remove the Class E airspace
extending upward from 1,200 feet above
the surface, and make administrative
changes to the Class E legal
descriptions. Interested parties were
invited to participate in this rulemaking
effort by submitting written comments
on the proposal to the FAA. No
comments were received.
Subsequent to publication of the
NPRM in the Federal Register, the FAA
identified a discrepancy with the
proposed Class E2 legal description. The
airport name is removed from the
description, as it is in the second line
of the header and duplication is not
necessary.
E:\FR\FM\18NOR1.SGM
18NOR1
]]>Agencies
[Federal Register Volume 87, Number 222 (Friday, November 18, 2022)]
[Rules and Regulations]
[Pages 69161-69164]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-25030]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0286; Project Identifier AD-2021-01081-R;
Amendment 39-22223; AD 2022-22-08]
RIN 2120-AA64
Airworthiness Directives; Bell Textron Canada Limited (Type
Certificate Previously Held by Bell Helicopter Textron Canada Limited)
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Bell Textron Canada Limited (type certificate previously held by Bell
Helicopter Textron Canada Limited) Model 206L, 206L-1, 206L-3, and
206L-4 helicopters with a certain part-numbered main rotor (M/R) blade
installed under Supplemental Type Certificate (STC) SR02684LA. This AD
was prompted by delamination of M/R blades. This AD requires a
repetitive inspection for delamination, and depending on the results,
removing the M/R blade from service and reporting certain information.
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 a certain publication listed in this AD as of December 23,
2022.
ADDRESSES: For service information identified in this final rule,
contact Dean Rosenlof, Van Horn Aviation, LLC, 1510 West Drake Drive,
Tempe, AZ, 85283, United States; phone: (480) 483-4202; email:
[email protected]. You may view this service information at the
FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood
Pkwy., Room 6N-321, Fort Worth, TX 76177. For information on the
availability of this material at the FAA, call (817) 222-5110. It is
also available at regulations.gov by searching for and locating Docket
No. FAA-2022-0286.
Examining the AD Docket
You may examine the AD docket at regulations.gov by searching for
and locating Docket No. FAA-2022-0286; 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.
FOR FURTHER INFORMATION CONTACT: Payman Soltani, Aerospace Engineer,
Airframe Section, Los Angeles ACO Branch, Compliance & Airworthiness
Division, FAA, 3960 Paramount Blvd., Lakewood, CA 90712; telephone
(562) 627-5313; email [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to Bell Textron Canada
Limited Model 206L, 206L-1, 206L-3, and 206L-4 helicopters with a
certain part-numbered M/R blade installed under STC SR02684LA. The NPRM
published in the Federal Register on March 24, 2022 (87 FR 16652). The
NPRM was prompted by testing by Van Horn Aviation, LLC (Van Horn),
which revealed the potential for delamination in M/R blade part number
(P/N) 20633000-101. Delaminations were then confirmed by inspection of
in-service M/R blades. Testing by Van Horn confirmed that the 90[deg]
plies fail in spanwise tension (normal to the fiber
[[Page 69162]]
direction) at the inboard end of the weight receptacle near M/R blade
station 186.0. Delamination then propagates outboard from M/R blade
station 186.0 at the interface between the 0[deg] and 90[deg] plies.
According to Van Horn, fatigue testing has shown that the delamination
initiates almost immediately and progresses slowly in a stable,
predictable manner. The delamination has been found to develop first on
the lower surface and grow outboard from the inboard end of the weight
receptacle and forward of the balance weight pocket. After
approximately 4 to 6 inches growth of the delamination on the lower
surface, a similar delamination becomes detectable on the M/R blade
upper surface. Should the delaminations continue to grow to the point
of static overload, the receptacle could depart the M/R blade. In the
NPRM, the FAA proposed to require, at specified intervals, removing the
affected M/R blade, drawing rectangular inspection areas ``Zone 1'' and
``Zone 2'' with a permanent marker, tap inspecting the inspection areas
for delamination, marking and measuring the length of any delamination,
and depending on the results, removing the M/R blade from service. The
NPRM also proposed to require reporting certain information to Van
Horn. The FAA is issuing this AD to address the unsafe condition on
these products.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from one commenter, Van Horn. The
following presents the comments received on the NPRM and the FAA's
response to each comment.
Request for Changes to the Measurements of Inspection Areas
Van Horn stated that the M/R blade stations indicated for
inspections are incorrect in the proposed AD and requested the FAA
revise the required actions to change the M/R blade stations for ``Zone
1'' and ``Zone 2.'' However, the measurements Van Horn included in the
comment in the AD docket to correct the M/R blade stations for ``Zone
1'' and ``Zone 2'' were also incorrect. Van Horn then contacted the FAA
to correct these measurements; a record of this ex parte contact is
included in the AD docket. For information on locating the docket, see
``Examining the AD Docket.'' According to Van Horn's revised comments,
``Zone 1'' described in the NPRM as M/R blade stations 186.0 and 191.0,
beginning 1.1 inches from the leading edge of the M/R blade to 4.9
inches from the leading edge of the M/R blade should be revised to M/R
blade stations 185.75 and 192.75, or measured from the tip end of the
M/R blade between 36.25 inches and 29.25 inches beginning 1.2 inches
from the leading edge of the M/R blade to 5.0 inches from the leading
edge of the M/R blade. ``Zone 2'' described in the NPRM as M/R blade
stations 186.0 and 191.0 should be revised to M/R blade stations 185.9
and 192.9, or measured from the tip end of the M/R blade between 36.1
inches and 29.1 inches.
The FAA agrees and has revised this AD accordingly.
Request for a Change to the Service Bulletin Cited in Note 1
Van Horn proposed that Note 1 to paragraph (g)(2)(i) cite Van Horn
Service Bulletin Notice No. 33000-4R4, dated March 31, 2022 (SB33000-
4R4) rather than Van Horn Service Bulletin Notice No. 33000-4R3, dated
November 8, 2021 (SB 33000-4R3).
The FAA partially agrees. The FAA appreciates that the latest
revision of that service bulletin is SB33000-4R4; however, the portions
of that service bulletin that are specified in the proposed AD are
identical in SB33000-4R3 and SB33000-4R4. Accordingly, the FAA has made
updates throughout the Required Actions paragraph to allow both
SB33000-4R3 and SB33000-4R4 in this final rule.
Request for a Reference to Additional Service Information in Note 1
Van Horn proposed edits in Note 1 to paragraph (g)(2)(i) to refer
to the Van Horn Instructions for Continued Airworthiness, ICA Manual
No. VMM-MR-206L-501, Revision N/C, dated May 24, 2018, for a blade
configuration drawing.
The FAA disagrees because it does not provide information that
could be helpful for operators to comply with this AD.
Request for Additional Tap Hammer Tool
Van Horn also requested the FAA revise the list of tap hammers in
paragraph (g)(2)(iii) of the proposed AD to add Van Horn Aviation Tap
Hammer P/N VHACS0003 to the list of tap hammers.
The FAA agrees and has revised this AD as requested.
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, and
any other changes described previously, this AD is adopted as proposed
in the NPRM. None of the changes will increase the economic burden on
any operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed SB 33000-4R3 and SB 33000-4R4. This service
information specifies procedures to identify ``Zone 1'' and ``Zone 2''
inspection areas, accomplish repetitive visual and tap inspections of
the zones to detect and monitor the growth of any delamination, and
depending on the results, remove the M/R blade from service and contact
Van Horn. SB 33000-4R3 applies to M/R blade P/N 20633000-101 serial
numbers A012 through A104. SB 33000-4R4 expanded the applicability to
include M/R blade P/N 20633000-101 with serial numbers A007, A008, and
A009; these serial-numbered parts were included in the NPRM's
applicability.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Differences Between This AD and the Service Information
This AD requires using certain part-numbered composite tap hammers,
whereas SB 33000-4R3 and SB 33000-4R4 do not. SB 33000-4R3 and SB
33000-4R4 specify procedures to visually inspect the M/R blade, whereas
this AD does not. If there is any delamination in the upper surface
inspection zone (``Zone 1''), this AD requires removing the M/R blade
from service, whereas SB 33000-4R3 and SB 33000-4R4 do not specify
procedures for this condition.
Interim Action
The FAA considers this AD to be an interim action. The inspection
reports that are required by this AD will enable the FAA to obtain
better insight into the unsafe condition. If final action is later
identified, the FAA might consider further rulemaking.
Costs of Compliance
The FAA estimates that this AD will affect 23 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.
Removing, tap inspecting, and re-installing an M/R blade will take
about
[[Page 69163]]
4.5 work-hours for an estimated cost of $383 per M/R blade, per
inspection cycle and up to $8,809 for the U.S. fleet per M/R blade, per
inspection cycle. Replacing an M/R blade will take about 4 work-hours
and parts will cost about $71,500 per M/R blade for a total of $71,840
per M/R blade. Reporting information to Van Horn will take about 1
work-hour for an estimated cost of $85 per report.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to take
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, and completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Send comments regarding this burden estimate
or any other aspect of this collection of information, including
suggestions for reducing this burden to: Information Collection
Clearance Officer, Federal Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177-1524.
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:
2022-22-08 Bell Textron Canada Limited (Type Certificate Previously
Held by Bell Helicopter Textron Canada Limited): Amendment 39-22223;
Docket No. FAA-2022-0286; Project Identifier AD-2021-01081-R.
(a) Effective Date
This airworthiness directive (AD) is effective December 23,
2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bell Textron Canada Limited (type certificate
previously held by Bell Helicopter Textron Canada Limited) Model
206L, 206L-1, 206L-3, and 206L-4 helicopters, certificated in any
category, with main rotor (M/R) blade part number (P/N) 20633000-101
with serial number A007, A008, A009, or A012 through A104 inclusive,
installed under Supplemental Type Certificate SR02684LA.
(d) Subject
Joint Aircraft System Component (JASC) Code: 6210, Main Rotor
Blades.
(e) Unsafe Condition
This AD was prompted by reports of delamination of M/R blades.
The FAA is issuing this AD to address delamination of an M/R blade
initiating in the 90[deg] plies at the lower inboard end of the
weight pocket receptacle. The unsafe condition, if not addressed,
could result in reduced structural integrity of the M/R blade,
excessive vibration, and subsequent loss of control of the
helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Accomplish the actions required by paragraph (g)(2) of this
AD at the following compliance time, whichever occurs later:
(i) Before the M/R blade accumulates 400 total hours time-in-
service (TIS) or 2,400 engine starts since initial installation on
any helicopter, whichever occurs first; or
(ii) Within 100 hours TIS after the effective date of this AD.
(2) Remove each M/R blade from the helicopter, place it on a
flat, stable surface, and accomplish the following:
(i) Use a permanent marker to draw rectangular inspection ``Zone
1'' on the upper surface of the M/R blade at M/R blade stations
185.75 and 192.75, or measured from the tip end of the M/R blade
between 36.25 inches and 29.25 inches, beginning 1.2 inches from the
leading edge of the M/R blade to 5.0 inches from the leading edge of
the M/R blade. Draw lines from the inboard end to the outboard end
to connect each end at 1.2 inches and 5.0 inches. Draw parallel
lines from the inboard end of the inspection zone to the outboard
end of the inspection zone, with the lines spaced 0.50 inch apart.
Note 1 to paragraph (g)(2)(i): This note applies to paragraphs
(g)(2)(i) and (ii) of this AD. Figure 4 of Van Horn Aviation, LLC,
Service Bulletin Notice No. 33000-4R3, dated November 8, 2021 (SB
33000-4R3), and Van Horn Aviation, LLC, Service Bulletin Notice No.
33000-4R4, dated March 31, 2022 (SB 33000-4R4) depict ``Zone 1'' and
``Zone 2.''
(ii) Use a permanent marker to draw rectangular inspection
``Zone 2'' on the lower surface of the M/R blade at M/R blade
stations 185.9 and 192.9, or measured from the tip end of the M/R
blade between 36.1inches and 29.1 inches, beginning from the forward
edge of the weight receptacle pocket and extending 1 inch in the
direction towards the leading edge of the M/R blade. Draw lines from
the inboard end to the outboard end to connect each end at the
weight receptacle pocket and 1 inch forward of the weight receptacle
pocket. Draw parallel lines from the inboard end of the inspection
zone to the outboard end of the inspection zone, with the lines
spaced 0.50 inch apart.
(iii) Using composite tap hammer Abaris Training Tap Hammer P/N
ABATH, HeatCon
[[Page 69164]]
Tap Hammer P/N HCS1104-01, Brown Tool Composite Tap Hammer P/N BAT-
CTH8, MATCO Tools Composite Tap Hammer P/N T4BAT-CTH8, or Van Horn
Aviation Tap Hammer P/N VHACS0003, tap inspect the areas within
``Zone 1'' and ``Zone 2'' for any delamination by following Tap
Inspect Balance Receptacle, paragraph A.(4) of SB 33000-4R3 or SB
33000-4R4. Where SB 33000-4R3 and SB 33000-4R4 specify to mark the
location where the delamination starts, use a permanent marker.
(iv) If there are any marks where the delamination starts,
connect the marks indicating the delamination location and measure
the length at the farthest point from the inboard end of the
inspection area.
(v) If there is any delamination in the lower surface inspection
zone (``Zone 2'') that is 6.0 or more inches in length or if there
is any delamination in the upper surface inspection zone (``Zone
1''), before further flight, remove the M/R blade from service.
(3) Thereafter repeat the actions required by paragraph (g)(2)
of this AD at intervals not to exceed 400 hours TIS or 2,400 engine
starts, whichever occurs first.
(4) If there is any delamination, within 30 days after
accomplishing the actions required by paragraphs (g)(1) or (3) of
this AD, report each delamination size and location, and the total
hours TIS and total engine starts since initial installation of the
M/R blade, to Mr. Dean Rosenlof, Van Horn Aviation, LLC, 1510 West
Drake Drive, Tempe, AZ 85283, or by email to
[email protected].
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles ACO 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 (i) of this AD. Information may
be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(i) Related Information
For more information about this AD, contact Payman Soltani,
Aerospace Engineer, Airframe Section, Los Angeles ACO Branch,
Compliance & Airworthiness Division, FAA, 3960 Paramount Blvd.,
Lakewood, CA 90712; telephone (562) 627-5313; email
[email protected].
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Van Horn Aviation, LLC, Service Bulletin Notice No. 33000-
4R3, dated November 8, 2021.
(ii) Van Horn Aviation, LLC, Service Bulletin Notice No. 33000-
4R4, dated March 31, 2022.
(3) For Van Horn Aviation, LLC, service information identified
in this AD, contact Dean Rosenlof, Van Horn Aviation, LLC, 1510 West
Drake Drive, Tempe, AZ, 85283, United States; phone: (480) 483-4202;
email: [email protected].
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email: [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on October 21, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-25030 Filed 11-17-22; 8:45 am]
BILLING CODE 4910-13-P
