Airworthiness Directives; Leonardo S.p.a. Helicopters, 26198-26201 [2021-09992]
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Federal Register / Vol. 86, No. 91 / Thursday, May 13, 2021 / Proposed Rules
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Would not affect intrastate
aviation in Alaska, and
(3) Would not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
■ a. Removing Airworthiness Directive
(AD) 2020–23–13, Amendment 39–
21330 (85 FR 73407, November 18,
2020), and
■ b. Adding the following new AD:
■
ATR—GIE Avions de Transport Re´gional:
Docket No. FAA–2021–0366; Project
Identifier MCAI–2021–00080–T.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by June 28,
2021.
(b) Affected ADs
This AD replaces AD 2020–23–13,
Amendment 39–21330 (85 FR 73407,
November 18, 2020) (AD 2020–23–13).
(c) Applicability
This AD applies to all ATR—GIE Avions
de Transport Re´gional Model ATR42–200,
–300, and –320 airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of
America Code 31, Instruments.
(e) Reason
This AD was prompted by false activation
of the stall warning system due to wiring
damage on the wire bundle between an angle
of attack (AOA) probe and the crew alerting
computer, and the development of a wiring
modification and aircraft flight manual
(AFM) update to address the unsafe
condition. The FAA is issuing this AD to
address this condition, which could result in
loss of control of the airplane during take-off
and landing phases.
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Jkt 253001
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, European Union Aviation
Safety Agency (EASA) AD 2021–0024, dated
January 19, 2021 (EASA AD 2021–0024).
(h) Exceptions to EASA AD 2021–0024
(1) Where EASA AD 2021–0024 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) Where EASA AD 2021–0024 refers to
‘‘the effective date of EASA AD 2020–0221,’’
this AD requires using December 3, 2020 (the
effective date of AD 2020–23–13).
(3) The ‘‘Remarks’’ section of EASA AD
2021–0024 does not apply to this AD.
(4) Paragraph (3) of EASA AD 2021–0024
specifies to report inspection results to
ATR—GIE Avions de Transport Re´gional
within a certain compliance time. For this
AD, report inspection results at the
applicable time specified in paragraph
(h)(4)(i) or (ii) of this AD.
(i) If the inspection was done on or after
December 3, 2020 (the effective date of AD
2020–23–13): Submit the report within 30
days after the inspection.
(ii) If the inspection was done before
December 3, 2020 (the effective date of AD
2020–23–13): Submit the report within 30
days after the effective date of this AD.
(5) Paragraphs (5) and (6) of EASA AD
2021–0024 specify amending ‘‘the applicable
AFM [aircraft flight manual] of that aeroplane
by inserting the AFM change provided in
Appendix 1 of this [EASA] AD,’’ but this AD
requires amending ‘‘the existing AFM and
applicable corresponding operational
procedures to incorporate the limitations and
procedures specified in Appendix 1 of EASA
AD 2021–0024.’’
(6) Where paragraphs (5) and (6) of EASA
AD 2021–0024 specify to ‘‘inform all flight
crews, and, thereafter, operate the aeroplane
accordingly,’’ this AD does not require those
actions as those actions are already required
by existing FAA operating regulations.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Large Aircraft
Section, 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 responsible Flight
Standards Office, as appropriate. If sending
information directly to the Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (j)(2) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the responsible
Flight Standards Office.
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(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Large Aircraft Section,
International Validation Branch, FAA; or
EASA; or ATR—GIE Avions de Transport
Re´gional’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(j) Related Information
(1) For information about EASA AD 2021–
0024, contact EASA, Konrad-Adenauer-Ufer
3, 50668 Cologne, Germany; telephone +49
221 8999 000; email ADs@easa.europa.eu;
Internet www.easa.europa.eu. You may find
this EASA AD on the EASA website at
https://ad.easa.europa.eu. You may view this
material at the FAA, Airworthiness Products
Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195. This
material may be found in the AD docket on
the internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0366.
(2) For more information about this AD,
contact Shahram Daneshmandi, Aerospace
Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198;
phone and fax: 206–231–3220; email:
shahram.daneshmandi@faa.gov.
Issued on May 7, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–10015 Filed 5–12–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0364; Project
Identifier MCAI–2020–00274–R]
RIN 2120–AA64
Airworthiness Directives; Leonardo
S.p.a. Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
Leonardo S.p.a. (Leonardo) Model
A109S and AW109SP helicopters with a
certain part-numbered vertical fin
vibration absorber installation installed.
This proposed AD would require
repetitive inspections of the vertical fin
vibration absorber installation and the
surrounding structure and depending on
SUMMARY:
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Federal Register / Vol. 86, No. 91 / Thursday, May 13, 2021 / Proposed Rules
the inspection results, removing certain
parts from service. This proposed AD
would also prohibit installing certain
part-numbered vertical fin vibration
absorber installations. This proposed
AD was prompted by a report of cracks
and damage detected on the vertical fin
absorber installation and surrounding
structure during scheduled inspections.
The actions of this proposed AD are
intended to address an unsafe condition
on these products.
DATES: The FAA must receive comments
on this proposed AD by June 28, 2021.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: (202) 493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed rule, contact Leonardo
S.p.a. Helicopters, Emanuele Bufano,
Head of Airworthiness, Viale G.Agusta
520, 21017 C.Costa di Samarate (Va)
Italy; telephone +39–0331–225074; fax
+39–0331–229046; or at https://
www.leonardocompany.com/en/home.
You may view the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0364; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this NPRM, the
European Union Aviation Safety Agency
(EASA) AD, any comments received,
and other information. The street
address for Docket Operations is listed
above.
FOR FURTHER INFORMATION CONTACT:
Kristin Bradley, Aerospace Engineer,
General Aviation & Rotorcraft Section,
International Validation Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
Kristin.Bradley@faa.gov.
SUPPLEMENTARY INFORMATION:
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Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2021–0364; Project Identifier
MCAI–2020–00274–R’’ at the beginning
of your comments. The most helpful
comments reference a specific portion of
the proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend this proposal
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to Kristin Bradley,
Aerospace Engineer, General Aviation &
Rotorcraft Section, International
Validation Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email
Kristin.Bradley@faa.gov. Any
commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
Background
EASA, which is the Technical Agent
for the Member States of the European
Union, issued EASA AD 2014–0150,
dated June 18, 2014 (EASA AD 2014–
0150), to correct an unsafe condition for
certain AgustaWestland S.p.A. (now
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26199
Leonardo S.p.a. Helicopters) (formerly
Agusta S.p.A.) Model A109S and
AW109SP helicopters, with absorber
part number (P/N) 109–B810–79–
101installed. EASA advises that during
a scheduled inspection on Model A109S
and AW109SP helicopters, cracks and
damage were detected on the vertical fin
vibration absorber installation and the
surrounding structure. EASA states
investigation results determined the
cracks and damage were likely related to
the design of the vertical fin vibration
absorber installation and incorrect
installation. Accordingly, EASA AD
2014–0150 required repetitive
inspections and removal of the affected
part.
After EASA AD 2014–0150 was
issued, EASA determined certain
helicopters were not included in the
applicability and may also be subject to
the unsafe condition. Accordingly,
EASA issued EASA AD 2019–0294,
dated December 4, 2019 (EASA AD
2019–0294), which supersedes EASA
AD 2014–0150. EASA AD 2019–0294
retains the requirements of EASA AD
2014–0150, and expands the
applicability, prohibits vertical fin
vibration absorber installation P/N 109–
B810–79–101 from being installed on
any helicopter, and considers removal
of the affected part to constitute
terminating action for the repetitive
inspections. EASA states this condition
if not detected and corrected could
affect the structural integrity of the
helicopter.
FAA’s Determination
These helicopters have been approved
by EASA and are approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the
European Union, EASA has notified the
FAA about the unsafe condition
described in its AD. The FAA is
proposing this AD after evaluating all
known relevant information and
determining that an unsafe condition is
likely to exist or develop on other
helicopters of the same type designs.
Related Service Information
The FAA reviewed AgustaWestland
S.p.A. Bollettino Technico (BT) No.
109S–58 for Model A109S helicopters,
and AgustaWestland S.p.A BT No.
109SP–074 for Model AW109SP
helicopters, each dated May 7, 2014.
This service information specifies
instructions for removing the vertical fin
vibration absorber installation,
inspecting the rib assembly and vertical
fin vibration absorber installation and
depending on the inspection results,
removing certain parts from service.
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Federal Register / Vol. 86, No. 91 / Thursday, May 13, 2021 / Proposed Rules
Proposed AD Requirements in This
NPRM
This proposed AD would require
within 30 hours time-in-service (TIS)
after the effective date of this AD, and
thereafter every 100 hours TIS,
removing the vertical fin vibration
absorber installation P/N 109–B810–79–
101, and using a mirror and light source,
inspecting the rib assembly and
depending on the inspection results,
removing certain parts from service.
This proposed AD would also require
inspecting the vertical fin vibration
absorber installation P/N 109–B810–79–
101 for hole elongation; for fretting
between the plate and the masses, and
in-between the masses; for fretting on
the doubler; and the bolts for scratches
and corrosion. Depending on the
inspection results, this proposed AD
would require removing the vertical fin
vibration absorber installation P/N 109–
B810–79–101 from service. This
proposed AD would also require, within
12 months TIS after the effective date of
this AD, unless already accomplished,
removing the vertical fin vibration
absorber installation P/N 109–B810–79–
101 from service. This proposed AD
would also prohibit installing an
affected part on any helicopter, and
would provide a terminating action for
the 100 hour TIS repetitive inspections.
Differences Between This Proposed AD
and the EASA AD
EASA AD 2019–0294 applies to
certain serial-numbered Model A109S
and AW109SP helicopters, whereas this
proposed AD would apply to all serialnumbered Model A109S and AW109SP
helicopters with a certain partnumbered vertical fin vibration absorber
installation installed.
Costs of Compliance
The FAA estimates that this proposed
AD would affect 96 helicopters of U.S.
Registry. The FAA estimates that
operators may incur the following costs
in order to comply with this proposed
AD. Labor costs are estimated at $85 per
work-hour.
Removing and inspecting the vertical
fin vibration absorber installation and
surrounding structure would take about
8 work-hours for an estimated cost of
$680 per helicopter per inspection cycle
and $65,280 for the U.S. fleet per
inspection cycle.
Replacing the rib assembly, shim,
doubler, and bracket would take about
16 work-hours and parts would cost
about $10,000 for an estimated cost of
$11,360 per helicopter.
According to Leonardo some of the
costs of this proposed AD may be
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Jkt 253001
covered under warranty, thereby
reducing the cost impact on affected
individuals. The FAA does not control
warranty coverage by Leonardo.
Accordingly, all costs are included in
this cost estimate.
■
Authority for This Rulemaking
§ 39.13
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: General requirements. Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
■
Regulatory Findings
The FAA determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed, I certify
this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
2. Would not affect intrastate aviation
in Alaska, and
3. Would not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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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.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
Leonardo S.p.a.: Docket No. FAA–2021–
0364; Project Identifier MCAI–2020–
00274–R.
(a) Comments Due
The FAA must receive comments on this
airworthiness directive (AD) by June 28,
2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Leonardo S.p.a. Model
A109S helicopters and AW109SP
helicopters, certificated in any category, with
vertical fin vibration absorber installation
part number (P/N) 109–B810–79–101
installed.
(d) Subject
Joint Aircraft Service Component (JASC)
Code: 2740, Stabilizer Control System.
(e) Unsafe Condition
This AD defines the unsafe condition as
cracks or damage on the vertical fin vibration
absorber installation and surrounding
structure. This condition could affect the
structural integrity of the helicopter and lead
to subsequent loss of control of the
helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Within 30 hours time-in-service (TIS)
after the effective date of this AD, and
thereafter at intervals not to exceed 100 hours
TIS:
(i) Remove the vertical fin vibration
absorber installation P/N 109–B810–79–101,
and using a mirror and light source, visually
inspect the rib assembly P/N 109–0372–53–
201 for hole elongation, fretting, and cracks.
If there is any hole elongation, fretting, or
cracks, before further flight, remove rib
assembly P/N 109–0372–53–201, shim P/N
109–0372–53–211, doubler P/N 109–0372–
53–213, and bracket P/N 109–0373–02–113
from service and replace with airworthy
parts.
(ii) Inspect the vertical fin vibration
absorber installation P/N 109–B810–79–101
for hole elongation; for fretting between the
plate and the masses and in-between the
masses; for fretting on doubler P/N 109–
0372–53–213; and the bolts for scratches and
corrosion. If there is any hole elongation;
fretting between the plate and the masses or
in-between the masses; fretting on doubler P/
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Federal Register / Vol. 86, No. 91 / Thursday, May 13, 2021 / Proposed Rules
N 109–0372–53–213; or bolts with scratches
or corrosion, before further flight, remove the
vertical fin vibration absorber installation P/
N 109–B810–79–101 from service.
(2) Within 12 months TIS after the effective
date of this AD unless already accomplished
per paragraph (g)(1)(ii) of this AD, remove the
vertical fin vibration absorber installation P/
N 109–B810–79–101 from service.
(3) As of the effective date of this AD, do
not install vertical fin vibration absorber
installation P/N 109–B810–79–101 on any
helicopter.
(4) Removing the vertical fin vibration
absorber installation P/N 109–B810–79–101
from service, as described in paragraphs
(g)(1)(ii) or (2) of this AD provides a
terminating action for the 100 hour TIS
repetitive inspections required by paragraph
(g)(1) of 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
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procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the International Validation
Branch, send it to the attention of the person
identified in paragraph (i)(1) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(i) Related Information
(1) For more information about this AD,
contact Kristin Bradley, Aerospace Engineer,
General Aviation & Rotorcraft Section,
International Validation Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email
Kristin.Bradley@faa.gov.
(2) For service information identified in
this AD, contact Leonardo S.p.a. Helicopters,
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26201
Emanuele Bufano, Head of Airworthiness,
Viale G.Agusta 520, 21017 C. Costa di
Samarate (Va) Italy; telephone +39–0331–
225074; fax +39–0331–229046; or at https://
www.leonardocompany.com/en/home. You
may view this referenced service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(3) The subject of this AD is addressed in
European Union Aviation Safety Agency
(EASA) AD 2019–0294, dated December 4,
2019. You may view the EASA AD on the
internet at https://www.regulations.gov in
Docket No. FAA–2021–0364.
Issued on May 6, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–09992 Filed 5–12–21; 8:45 am]
BILLING CODE 4910–13–P
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]]>Agencies
[Federal Register Volume 86, Number 91 (Thursday, May 13, 2021)]
[Proposed Rules]
[Pages 26198-26201]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-09992]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0364; Project Identifier MCAI-2020-00274-R]
RIN 2120-AA64
Airworthiness Directives; Leonardo S.p.a. Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for Leonardo S.p.a. (Leonardo) Model A109S and AW109SP helicopters with
a certain part-numbered vertical fin vibration absorber installation
installed. This proposed AD would require repetitive inspections of the
vertical fin vibration absorber installation and the surrounding
structure and depending on
[[Page 26199]]
the inspection results, removing certain parts from service. This
proposed AD would also prohibit installing certain part-numbered
vertical fin vibration absorber installations. This proposed AD was
prompted by a report of cracks and damage detected on the vertical fin
absorber installation and surrounding structure during scheduled
inspections. The actions of this proposed AD are intended to address an
unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by June 28,
2021.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: (202) 493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed rule, contact
Leonardo S.p.a. Helicopters, Emanuele Bufano, Head of Airworthiness,
Viale G.Agusta 520, 21017 C.Costa di Samarate (Va) Italy; telephone
+39-0331-225074; fax +39-0331-229046; or at https://www.leonardocompany.com/en/home. You may view the referenced service
information at the FAA, Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0364; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the European Union Aviation Safety Agency (EASA) AD, any
comments received, and other information. The street address for Docket
Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Kristin Bradley, Aerospace Engineer,
General Aviation & Rotorcraft Section, International Validation Branch,
FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-
5110; email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2021-0364; Project Identifier
MCAI-2020-00274-R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
Kristin Bradley, Aerospace Engineer, General Aviation & Rotorcraft
Section, International Validation Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817) 222-5110; email
[email protected]. Any commentary that the FAA receives which is
not specifically designated as CBI will be placed in the public docket
for this rulemaking.
Background
EASA, which is the Technical Agent for the Member States of the
European Union, issued EASA AD 2014-0150, dated June 18, 2014 (EASA AD
2014-0150), to correct an unsafe condition for certain AgustaWestland
S.p.A. (now Leonardo S.p.a. Helicopters) (formerly Agusta S.p.A.) Model
A109S and AW109SP helicopters, with absorber part number (P/N) 109-
B810-79-101installed. EASA advises that during a scheduled inspection
on Model A109S and AW109SP helicopters, cracks and damage were detected
on the vertical fin vibration absorber installation and the surrounding
structure. EASA states investigation results determined the cracks and
damage were likely related to the design of the vertical fin vibration
absorber installation and incorrect installation. Accordingly, EASA AD
2014-0150 required repetitive inspections and removal of the affected
part.
After EASA AD 2014-0150 was issued, EASA determined certain
helicopters were not included in the applicability and may also be
subject to the unsafe condition. Accordingly, EASA issued EASA AD 2019-
0294, dated December 4, 2019 (EASA AD 2019-0294), which supersedes EASA
AD 2014-0150. EASA AD 2019-0294 retains the requirements of EASA AD
2014-0150, and expands the applicability, prohibits vertical fin
vibration absorber installation P/N 109-B810-79-101 from being
installed on any helicopter, and considers removal of the affected part
to constitute terminating action for the repetitive inspections. EASA
states this condition if not detected and corrected could affect the
structural integrity of the helicopter.
FAA's Determination
These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA about the
unsafe condition described in its AD. The FAA is proposing this AD
after evaluating all known relevant information and determining that an
unsafe condition is likely to exist or develop on other helicopters of
the same type designs.
Related Service Information
The FAA reviewed AgustaWestland S.p.A. Bollettino Technico (BT) No.
109S-58 for Model A109S helicopters, and AgustaWestland S.p.A BT No.
109SP-074 for Model AW109SP helicopters, each dated May 7, 2014. This
service information specifies instructions for removing the vertical
fin vibration absorber installation, inspecting the rib assembly and
vertical fin vibration absorber installation and depending on the
inspection results, removing certain parts from service.
[[Page 26200]]
Proposed AD Requirements in This NPRM
This proposed AD would require within 30 hours time-in-service
(TIS) after the effective date of this AD, and thereafter every 100
hours TIS, removing the vertical fin vibration absorber installation P/
N 109-B810-79-101, and using a mirror and light source, inspecting the
rib assembly and depending on the inspection results, removing certain
parts from service. This proposed AD would also require inspecting the
vertical fin vibration absorber installation P/N 109-B810-79-101 for
hole elongation; for fretting between the plate and the masses, and in-
between the masses; for fretting on the doubler; and the bolts for
scratches and corrosion. Depending on the inspection results, this
proposed AD would require removing the vertical fin vibration absorber
installation P/N 109-B810-79-101 from service. This proposed AD would
also require, within 12 months TIS after the effective date of this AD,
unless already accomplished, removing the vertical fin vibration
absorber installation P/N 109-B810-79-101 from service. This proposed
AD would also prohibit installing an affected part on any helicopter,
and would provide a terminating action for the 100 hour TIS repetitive
inspections.
Differences Between This Proposed AD and the EASA AD
EASA AD 2019-0294 applies to certain serial-numbered Model A109S
and AW109SP helicopters, whereas this proposed AD would apply to all
serial-numbered Model A109S and AW109SP helicopters with a certain
part-numbered vertical fin vibration absorber installation installed.
Costs of Compliance
The FAA estimates that this proposed AD would affect 96 helicopters
of U.S. Registry. The FAA estimates that operators may incur the
following costs in order to comply with this proposed AD. Labor costs
are estimated at $85 per work-hour.
Removing and inspecting the vertical fin vibration absorber
installation and surrounding structure would take about 8 work-hours
for an estimated cost of $680 per helicopter per inspection cycle and
$65,280 for the U.S. fleet per inspection cycle.
Replacing the rib assembly, shim, doubler, and bracket would take
about 16 work-hours and parts would cost about $10,000 for an estimated
cost of $11,360 per helicopter.
According to Leonardo some of the costs of this proposed AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. The FAA does not control warranty coverage by Leonardo.
Accordingly, all costs are included in this cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed, I certify this proposed regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Would not affect intrastate aviation in Alaska, and
3. Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
Leonardo S.p.a.: Docket No. FAA-2021-0364; Project Identifier MCAI-
2020-00274-R.
(a) Comments Due
The FAA must receive comments on this airworthiness directive
(AD) by June 28, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Leonardo S.p.a. Model A109S helicopters and
AW109SP helicopters, certificated in any category, with vertical fin
vibration absorber installation part number (P/N) 109-B810-79-101
installed.
(d) Subject
Joint Aircraft Service Component (JASC) Code: 2740, Stabilizer
Control System.
(e) Unsafe Condition
This AD defines the unsafe condition as cracks or damage on the
vertical fin vibration absorber installation and surrounding
structure. This condition could affect the structural integrity of
the helicopter and lead to subsequent loss of control of the
helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Within 30 hours time-in-service (TIS) after the effective
date of this AD, and thereafter at intervals not to exceed 100 hours
TIS:
(i) Remove the vertical fin vibration absorber installation P/N
109-B810-79-101, and using a mirror and light source, visually
inspect the rib assembly P/N 109-0372-53-201 for hole elongation,
fretting, and cracks. If there is any hole elongation, fretting, or
cracks, before further flight, remove rib assembly P/N 109-0372-53-
201, shim P/N 109-0372-53-211, doubler P/N 109-0372-53-213, and
bracket P/N 109-0373-02-113 from service and replace with airworthy
parts.
(ii) Inspect the vertical fin vibration absorber installation P/
N 109-B810-79-101 for hole elongation; for fretting between the
plate and the masses and in-between the masses; for fretting on
doubler P/N 109-0372-53-213; and the bolts for scratches and
corrosion. If there is any hole elongation; fretting between the
plate and the masses or in-between the masses; fretting on doubler
P/
[[Page 26201]]
N 109-0372-53-213; or bolts with scratches or corrosion, before
further flight, remove the vertical fin vibration absorber
installation P/N 109-B810-79-101 from service.
(2) Within 12 months TIS after the effective date of this AD
unless already accomplished per paragraph (g)(1)(ii) of this AD,
remove the vertical fin vibration absorber installation P/N 109-
B810-79-101 from service.
(3) As of the effective date of this AD, do not install vertical
fin vibration absorber installation P/N 109-B810-79-101 on any
helicopter.
(4) Removing the vertical fin vibration absorber installation P/
N 109-B810-79-101 from service, as described in paragraphs
(g)(1)(ii) or (2) of this AD provides a terminating action for the
100 hour TIS repetitive inspections required by paragraph (g)(1) of
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, send
it to the attention of the person identified in paragraph (i)(1) of
this AD. Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(i) Related Information
(1) For more information about this AD, contact Kristin Bradley,
Aerospace Engineer, General Aviation & Rotorcraft Section,
International Validation Branch, FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone (817) 222-5110; email
[email protected].
(2) For service information identified in this AD, contact
Leonardo S.p.a. Helicopters, Emanuele Bufano, Head of Airworthiness,
Viale G.Agusta 520, 21017 C. Costa di Samarate (Va) Italy; telephone
+39-0331-225074; fax +39-0331-229046; or at https://www.leonardocompany.com/en/home. You may view this referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX
76177. For information on the availability of this material at the
FAA, call (817) 222-5110.
(3) The subject of this AD is addressed in European Union
Aviation Safety Agency (EASA) AD 2019-0294, dated December 4, 2019.
You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA-2021-0364.
Issued on May 6, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021-09992 Filed 5-12-21; 8:45 am]
BILLING CODE 4910-13-P
