Airworthiness Directives; Honeywell International, Inc. (Type Certificate Previously Held by AlliedSignal, Inc. and Textron Lycoming) Turboshaft Engines, 3470-3475 [2022-01238]
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Federal Register / Vol. 87, No. 15 / Monday, January 24, 2022 / Proposed Rules
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[FR Doc. 2022–00849 Filed 1–21–22; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–1185; Project
Identifier AD–2021–00339–E]
RIN 2120–AA64
Airworthiness Directives; Honeywell
International, Inc. (Type Certificate
Previously Held by AlliedSignal, Inc.
and Textron Lycoming) Turboshaft
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
2002–03–01, which applies to all
Honeywell International, Inc.
(Honeywell) T53 model turboshaft
engines. AD 2002–03–01 requires initial
and repetitive special vibration tests of
the engine, and if necessary replacement
with a serviceable reduction gearbox
assembly, or a serviceable engine before
further flight. Since the FAA issued AD
2002–03–01, the FAA received reports
that two additional Honeywell model
turboshaft engines, not captured in AD
2002–03–01, are also subject to
SUMMARY:
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Federal Register / Vol. 87, No. 15 / Monday, January 24, 2022 / Proposed Rules
tachometer drive spur gear failures due
to vibration loads. This proposed AD
would require initial and repetitive
special vibration tests of the engine and,
depending on the results, replacement
of either the reduction gearbox assembly
or the engine. The FAA is proposing
this AD to address the unsafe condition
on these products.
DATES: The FAA must receive comments
on this proposed AD by March 10, 2022.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE, Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Honeywell
International, Inc., 111 South 34th
Street, Phoenix, AZ 85034; phone: (800)
601–3099; fax: (602) 365 5577; website:
https://myaerospace.honeywell.com/
wps/portal. You may view this service
information at the FAA, Airworthiness
Products Section, Operational Safety
Branch, 1200 District Avenue,
Burlington, MA 01803. For information
on the availability of this material at the
FAA, call (817) 222–5110.
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Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–1185; 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, any comments received, and
other information. The street address for
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Jeffrey Chang, Aviation Safety Engineer,
Los Angeles ACO Branch, FAA, 3960
Paramount Boulevard, Lakewood, CA
90712; phone: (562) 627–5263; fax: (562)
627–5210; email: jeffrey.chang@faa.gov.
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–2021–1185; Project Identifier AD–
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2021–00339–E’’ 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 the 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 we receive about this proposed
AD.
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 Jeffrey Chang,
Aviation Safety Engineer, Los Angeles
ACO Branch, FAA, 3960 Paramount
Boulevard, Lakewood, CA 90712. Any
commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
Background
The FAA issued AD 2002–03–01,
Amendment 39–12642 (67 FR 6857,
February 14, 2002) (AD 2002–03–01) for
all Honeywell (formerly AlliedSignal,
Inc. and Textron Lycoming) T5311A,
T5311B, T5313B, T5317A, T5317B, and
former military T53–L–11, T53–L–11A,
T53–L–11B, T53–L–11C, T53–L–11D,
T53–L–11A S/SA, T53–L–13B, T53–L–
13B S/SA, T53–L–13B S/SB, and T53–
L–703 model turboshaft engines. AD
2002–03–01 was prompted by reports of
tachometer drive spur gear failure,
resulting in potential engine overspeed,
loss of power turbine speed (N2)
instrument panel indication, and hard
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landings. AD 2002–03–01 requires
initial and repetitive special vibration
tests of the engine and, for engines that
fail the special vibration tests,
replacement of the gearbox assembly or
engine before further flight. The agency
issued AD 2002–03–01 to prevent
excessive vibrations produced by the
reduction gearbox assembly that could
cause failure of the tachometer drive
spur gear.
Actions Since AD 2002–03–01 Was
Issued
Since the FAA issued AD 2002–03–
01, the FAA received reports that
Honeywell T5317A–1 and T5317BCV
model turboshaft engines are subject to
the same unsafe condition identified in
AD 2002–03–01, tachometer drive spur
gear failures due to vibration loads.
These model turboshaft engines were
not included in the applicability of AD
2002–03–01. The FAA and Honeywell
determined that the Honeywell
T5317A–1 engine model was
inadvertently left out of the
applicability of AD 2002–03–01 and the
Honeywell T5317BCV engine model
was introduced into production after the
publication of AD 2002–03–01.
FAA’s Determination
The FAA is issuing this NPRM after
determining that the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design.
Related Service Information Under 1
CFR Part 51
The FAA reviewed AlliedSignal
Aerospace Service Bulletin (SB)
T5311A/B–0100, dated January 20,
2000. This SB specifies procedures for
performing a special vibration check on
Honeywell T5311A and T5311B model
turboshaft engines.
The FAA reviewed AlliedSignal
Aerospace SB T5313B/17–0100, dated
November 19, 1999. This SB specifies
procedures for performing a special
vibration check on Honeywell T5313B,
T5317A, and T5317B model turboshaft
engines.
The FAA reviewed Honeywell SB
T53–0147, dated May 29, 2007. This SB
specifies procedures for performing a
special vibration check on Honeywell
T5317A–1 model turboshaft engines.
The FAA reviewed Honeywell
Maintenance Manual Temporary
Revision (TR) No. 165, dated July 29,
2020. This TR specifies procedures for
performing a special vibration check on
Honeywell T5313B, T5317A, T5317A–1,
T5317B, and T5317BCV model
turboshaft engines.
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The FAA reviewed AlliedSignal
Aerospace SB T53–L–11–0100, Revision
2, dated January 20, 2000. This SB
specifies procedures for performing a
special vibration check on Honeywell
T53–L–11, –11A, –11B, –11C, –11D, and
–11A S/SA model turboshaft engines.
The FAA reviewed AlliedSignal
Aerospace SB T53–L–13B–0100,
Revision 2, dated May 11, 1999. This SB
specifies procedures for performing a
special vibration check on Honeywell
T53–L–13B, –13B S/SA, and –13B S/SB
model turboshaft engines.
The FAA reviewed AlliedSignal
Aerospace SB T53–L–703–0100,
Revision 2, dated May 11, 1999. This SB
specifies procedures for performing a
special vibration check on Honeywell
T53–L–703 model turboshaft engines.
The Director of the Federal Register
approved AlliedSignal Aerospace SB
T5313B/17–0100, dated November 19,
1999; AlliedSignal Aerospace SB T53–
L–13B–0100, Revision 2, dated May 11,
1999; AlliedSignal Aerospace SB T53–
L–703–0100, Revision 2, dated May 11,
1999; AlliedSignal Aerospace SB
T5311A/B–0100, dated January 20,
2000; and AlliedSignal Aerospace SB
T53–L–11–0100, Revision 2, dated
January 20, 2000, for incorporation by
reference as of March 21, 2002 (67 FR
6857, February 14, 2002). 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 ADDRESSES.
Other Related Service Information
The FAA reviewed AlliedSignal
Aerospace SB T5311/T53–L–11–0103,
dated January 20, 2000. This SB
specifies procedures for replacing the
reduction gearbox assembly on
Honeywell T5311A and T5311B model
turboshaft engines and Honeywell T53–
L–11, –11A, –11B, –11C, –11D, and
–11A S/SA model turboshaft engines.
The FAA reviewed AlliedSignal
Aerospace SB T5313B/17–0103, dated
November 19, 1999. This SB specifies
procedures for replacing the reduction
gearbox assembly on Honeywell
T5313B, T5317A, and T5317B model
turboshaft engines.
The FAA reviewed AlliedSignal
Aerospace SB T53–L–13B–0103,
Revision 4, dated November 2, 1999.
This SB specifies procedures for
replacing the reduction gearbox
assembly on Honeywell T53–L–13B,
–13B S/SA, and –13B S/SB model
turboshaft engines.
The FAA reviewed AlliedSignal
Aerospace SB T53–L–703–0103,
Revision 4, dated November 2, 1999.
This SB specifies procedures for
replacing the reduction gearbox
assembly on Honeywell T53–L–703
model turboshaft engines.
Proposed AD Requirements in This
NPRM
This proposed AD would retain all of
the requirements of AD 2002–03–01.
This proposed AD would require initial
and repetitive special vibration tests of
the engine and, depending on the
results, replacement of either the
reduction gearbox assembly or the
engine. This proposed AD would also
expand the applicability to include
Honeywell T5317A–1 and T5317BCV
model turboshaft engines.
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 150
engines installed on helicopters of U.S.
registry.
The FAA estimates the following
costs to comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Special vibration test of the engine ................
4 work-hours × $85 per hour = $340 .............
The FAA estimates the following
costs to do any necessary replacement
that would be required based on the
Cost per
product
Parts cost
results of the proposed special vibration
test. The agency has no way of
$0
$340
Cost on
U.S. operators
$51,000
determining the number of aircraft that
might need this replacement:
ON-CONDITION COSTS
Action
Labor cost
Replace the reduction gearbox assembly ....................
Replace the engine ......................................................
40 work-hours × $85 per hour = $3,400 ......................
24 work-hours × $85 per hour = $2,040 ......................
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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
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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
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Parts cost
$48,000
250,577
Cost per
product
$51,400
252,617
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 the 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.
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Federal Register / Vol. 87, No. 15 / Monday, January 24, 2022 / Proposed Rules
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
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
2002–03–01, Amendment 39–12642 (67
FR 6857, February 14, 2002); and
■ b. Adding the following new
airworthiness directive:
■
■
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Honeywell International Inc. (Type
Certificate previously held by
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(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by March 10,
2022.
(b) Affected ADs
This AD replaces AD 2002–03–01,
Amendment 39–12642 (67 FR 6857, February
14, 2002).
(c) Applicability
1. The authority citation for part 39
continues to read as follows:
■
§ 39.13
AlliedSignal, Inc. and Textron
Lycoming): Docket No. FAA–2021–1185;
Project Identifier AD–2021–00339–E.
This AD applies to Honeywell
International, Inc. (Type Certificate
previously held by AlliedSignal, Inc. and
Textron Lycoming) T5311A, T5311B,
T5313B, T5317A, T5317A–1, T5317B,
T5317BCV, and former military T53–L–11,
T53–L–11A, T53–L–11B, T53–L–11C, T53–
L–11D, T53–L–11A S/SA, T53–L–13B, T53–
L–13B S/SA, T53–L–13B S/SB, and T53–L–
703 model turboshaft engines.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7600, Engine Controls.
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(e) Unsafe Condition
This AD was prompted by reports of
tachometer drive spur gear failure, resulting
in potential engine overspeed, loss of power
turbine speed (N2) instrument panel
indication, and hard landings. The FAA is
issuing this AD to prevent excessive
vibrations produced by the reduction gearbox
assembly that could cause failure of the
tachometer drive spur gear. The unsafe
condition, if not addressed, could result in
failure of the engine, loss of thrust control,
and damage to the aircraft.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Within 100 flight hours (FHs) after the
effective date of this AD, perform an initial
special vibration test of the engine using the
service information, as applicable to the
engine model, listed in Table 1 to paragraph
(g)(1) of this AD.
BILLING CODE 4910–13–P
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BILLING CODE 4910–13–C
(2) Thereafter, within the following
compliance times, perform repetitive special
vibration tests of the engine:
(i) For engines that have tachometer drive
spur gear part number (P/N) 1–070–062–04
installed, perform a repetitive special
vibration test before exceeding 500 FHs since
the last special vibration test.
(ii) For engines that have tachometer drive
spur gear P/N 1–070–062–06 installed,
perform a repetitive special vibration test
before exceeding 1,000 FHs since the last
special vibration test.
(3) If, during any special vibration test
required by paragraph (g)(1) or (2) of this AD,
an engine exceeds the 0.2 inches per second
(IPS) limit for any peak RPM/frequency
bands, perform one of the following:
(i) Before further flight, replace the
reduction gearbox assembly with a reduction
gearbox assembly eligible for installation; or
(ii) Before further flight, replace the engine
with an engine eligible for installation.
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(4) After replacing the reduction gearbox
assembly or engine, as required by paragraph
(3)(i) or (ii) of this AD, before further flight,
perform an initial special vibration test of the
engine using the service information, as
applicable to the engine model, listed in
Table 1 to paragraph (g)(1) of this AD.
(5) If, during the special vibration test
required by paragraph (g)(4) of this AD, an
engine exceeds the 0.2 IPS limit for any peak
within the RPM/frequency bands, before
further flight, replace the reduction gearbox
assembly or the engine.
(h) Definitions
(1) For the purpose of this AD, a
‘‘reduction gearbox assembly eligible for
installation’’ is a new, zero hour reduction
gearbox assembly or an overhauled reduction
gearbox assembly with tachometer drive spur
gear P/N 1–070–062–04 or P/N 1–070–062–
06 that does not exceed the 0.2 IPS limit for
any peak within the RPM/frequency bands
during the administered special vibration
test.
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(2) For the purpose of this AD, an ‘‘engine
eligible for installation’’ is an engine with
tachometer drive spur gear P/N 1–070–062–
04 or P/N 1–070–062–06 that does not exceed
the 0.2 IPS limit for any peak within the
RPM/frequency bands during the
administered special vibration test.
(i) No Reporting Requirement
The reporting requirements in the
Accomplishment Instructions, paragraph 3.A.
or paragraph 11.F, of the service information,
as applicable to the engine model, listed in
Table 1 to paragraph (g)(1) of this AD, are not
required by this AD.
(j) 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
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information directly to the manager of the
certification office, send it to the attention of
the person identified in paragraph (k)(1) of
this AD. Information may be emailed to: 9ANM-LAACO-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.
(3) AMOCs approved for AD 2002–03–01
(67 FR 6857, February 14, 2002) are approved
as AMOCs for the corresponding provisions
of this AD.
received at one of the addresses
provided below, no later than 5 p.m. on
March 25, 2022.
ADDRESSES: You may submit comments,
identified by RIN 0955–AA04, by any of
the following methods (please do not
submit duplicate comments). Because of
staff and resource limitations, we cannot
accept comments by facsimile (FAX)
transmission.
Federal eRulemaking Portal: Follow
the instructions for submitting
comments. Attachments should be in
(k) Related Information
Microsoft Word, Microsoft Excel, or
Adobe PDF; however, we prefer
(1) For more information about this AD,
contact Jeffrey Chang, Aviation Safety
Microsoft Word. https://
Engineer, Los Angeles ACO Branch, FAA,
www.regulations.gov.
3960 Paramount Boulevard, Lakewood, CA
Regular, Express, or Overnight Mail:
90712; phone: (562) 627–5263; fax: (562)
Department of Health and Human
627–5210; email: jeffrey.chang@faa.gov.
Services, Office of the National
(2) For service information identified in
Coordinator for Health Information
this AD, contact Honeywell International,
Technology, Attention: Request for
Inc., 111 South 34th Street, Phoenix, AZ
Information: Electronic Prior
85034; phone: (800) 601–3099; fax: (602) 365
Authorization Standards,
5577; website: https://
myaerospace.honeywell.com/wps/portal. You Implementation Specifications, and
may view this referenced service information Certification Criteria, Mary E. Switzer
at the FAA, Airworthiness Products Section,
Building, Mail Stop: 7033A, 330 C
Operational Safety Branch, 1200 District
Street SW, Washington, DC 20201.
Avenue, Burlington, MA 01803. For
Please submit one original and two
information on the availability of this
copies.
material at the FAA, call (817) 222–5110.
Hand Delivery or Courier: Office of
Issued on January 18, 2022.
the National Coordinator for Health
Lance T. Gant,
Information Technology, Attention:
Director, Compliance & Airworthiness
Request for Information: Electronic Prior
Division, Aircraft Certification Service.
Authorization Standards,
[FR Doc. 2022–01238 Filed 1–21–22; 8:45 am]
Implementation Specifications, and
BILLING CODE 4910–13–P
Certification Criteria, Mary E. Switzer
Building, Mail Stop: 7033A, 330 C
Street SW, Washington, DC 20201.
Please submit one original and two
DEPARTMENT OF HEALTH AND
copies. (Because access to the interior of
HUMAN SERVICES
the Mary E. Switzer Building is not
Office of the Secretary
readily available to persons without
Federal Government identification,
45 CFR Part 170
commenters are encouraged to leave
their comments in the mail drop slots
RIN–0955–AA04
located in the main lobby of the
building.)
Request for Information: Electronic
Inspection of Public Comments: All
Prior Authorization Standards,
comments received before the close of
Implementation Specifications, and
the comment period will be available for
Certification Criteria
public inspection, including any
AGENCY: Office of the National
personally identifiable or confidential
Coordinator for Health IT, Health and
business information that is included in
Human Services (HHS).
a comment. Please do not include
anything in your comment submission
ACTION: Request for information
that you do not wish to share with the
SUMMARY: This request for information
general public. Such information
seeks input from the public regarding
includes, but is not limited to: A
electronic prior authorization standards, person’s social security number; date of
implementation specifications, and
birth; driver’s license number; state
certification criteria that could be
identification number or foreign country
adopted within the ONC Health IT
equivalent; passport number; financial
Certification Program. Responses to this account number; credit or debit card
Request for Information will be used to
number; any personal health
inform potential future rulemaking.
information; or any business
information that could be considered
DATES: To be assured consideration,
written or electronic comments must be proprietary. We will post all comments
VerDate Sep<11>2014
17:07 Jan 21, 2022
Jkt 256001
PO 00000
Frm 00026
Fmt 4702
Sfmt 4702
3475
that are received before the close of the
comment period at https://
www.regulations.gov.
Docket: For access to the docket to
read background documents or
comments received, go to https://
www.regulations.gov or the Department
of Health and Human Services, Office of
the National Coordinator for Health
Information Technology, Mary E.
Switzer Building, Mail Stop: 7033A, 330
C Street SW, Washington, DC 20201
(call ahead to the contact listed below
to arrange for inspection).
FOR FURTHER INFORMATION CONTACT: Alex
Baker, Office of Policy, Office of the
National Coordinator for Health
Information Technology, 202–260–2048.
SUPPLEMENTARY INFORMATION:
I. Background
For purposes of this Request for
Information (RFI), prior authorization
generally refers to rules imposed by
healthcare payers that require approval
for a medication, procedure, device, or
other medical service be obtained prior
to payment for the item or service. Prior
authorization requirements are
established by payers to help control
costs and ensure payment accuracy by
verifying that an item or service is
medically necessary, meets coverage
criteria, and is consistent with standards
of care. Stakeholders have stated that
diverse payer policies, provider
workflow challenges, and technical
barriers create an environment in which
the prior authorization process is a
source of burden for patients, providers,
and payers; a cause of burnout for
providers; and a health risk for patients
when it delays their care.1
ONC’s Strategy on Reducing
Regulatory and Administrative Burden
Relating to the Use of Health IT and
EHRs,2 released in 2020, identified
challenges associated with the prior
authorization process, including: (i)
Difficulty in determining whether an
item or service requires prior
authorization; (ii) difficulty in
determining payer-specific prior
authorization requirements for those
items and services; (iii) inefficient use of
provider and staff time to navigate
communications channels such as fax,
telephone, and various web portals; and
1 For additional discussion of administrative
burden associated with the prior authorization
process, see the CMS Interoperability and Prior
Authorization proposed rule at 85 FR 82606.
2 Office of the National Coordinator for Health
Information Technology. Strategy on Reducing
Regulatory and Administrative Burden Relating to
the Use of Health IT and EHRs [PDF file]. February
2020. Retrieved from https://www.healthit.gov/
sites/default/files/page/2020-02/BurdenReport_
0.pdf.
E:\FR\FM\24JAP1.SGM
24JAP1
]]>Agencies
[Federal Register Volume 87, Number 15 (Monday, January 24, 2022)]
[Proposed Rules]
[Pages 3470-3475]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-01238]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-1185; Project Identifier AD-2021-00339-E]
RIN 2120-AA64
Airworthiness Directives; Honeywell International, Inc. (Type
Certificate Previously Held by AlliedSignal, Inc. and Textron Lycoming)
Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2002-03-01, which applies to all Honeywell International, Inc.
(Honeywell) T53 model turboshaft engines. AD 2002-03-01 requires
initial and repetitive special vibration tests of the engine, and if
necessary replacement with a serviceable reduction gearbox assembly, or
a serviceable engine before further flight. Since the FAA issued AD
2002-03-01, the FAA received reports that two additional Honeywell
model turboshaft engines, not captured in AD 2002-03-01, are also
subject to
[[Page 3471]]
tachometer drive spur gear failures due to vibration loads. This
proposed AD would require initial and repetitive special vibration
tests of the engine and, depending on the results, replacement of
either the reduction gearbox assembly or the engine. The FAA is
proposing this AD to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by March 10,
2022.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Honeywell
International, Inc., 111 South 34th Street, Phoenix, AZ 85034; phone:
(800) 601-3099; fax: (602) 365 5577; website: https://myaerospace.honeywell.com/wps/portal. You may view this service
information at the FAA, Airworthiness Products Section, Operational
Safety Branch, 1200 District Avenue, Burlington, MA 01803. For
information on the availability of this material at the FAA, call (817)
222-5110.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-1185; 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, any comments
received, and other information. The street address for Docket
Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Jeffrey Chang, Aviation Safety
Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount Boulevard,
Lakewood, CA 90712; phone: (562) 627-5263; fax: (562) 627-5210; 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-2021-1185; Project Identifier
AD-2021-00339-E'' 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
the 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 we receive about this proposed AD.
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
Jeffrey Chang, Aviation Safety Engineer, Los Angeles ACO Branch, FAA,
3960 Paramount Boulevard, Lakewood, CA 90712. Any commentary that the
FAA receives which is not specifically designated as CBI will be placed
in the public docket for this rulemaking.
Background
The FAA issued AD 2002-03-01, Amendment 39-12642 (67 FR 6857,
February 14, 2002) (AD 2002-03-01) for all Honeywell (formerly
AlliedSignal, Inc. and Textron Lycoming) T5311A, T5311B, T5313B,
T5317A, T5317B, and former military T53-L-11, T53-L-11A, T53-L-11B,
T53-L-11C, T53-L-11D, T53-L-11A S/SA, T53-L-13B, T53-L-13B S/SA, T53-L-
13B S/SB, and T53-L-703 model turboshaft engines. AD 2002-03-01 was
prompted by reports of tachometer drive spur gear failure, resulting in
potential engine overspeed, loss of power turbine speed (N2) instrument
panel indication, and hard landings. AD 2002-03-01 requires initial and
repetitive special vibration tests of the engine and, for engines that
fail the special vibration tests, replacement of the gearbox assembly
or engine before further flight. The agency issued AD 2002-03-01 to
prevent excessive vibrations produced by the reduction gearbox assembly
that could cause failure of the tachometer drive spur gear.
Actions Since AD 2002-03-01 Was Issued
Since the FAA issued AD 2002-03-01, the FAA received reports that
Honeywell T5317A-1 and T5317BCV model turboshaft engines are subject to
the same unsafe condition identified in AD 2002-03-01, tachometer drive
spur gear failures due to vibration loads. These model turboshaft
engines were not included in the applicability of AD 2002-03-01. The
FAA and Honeywell determined that the Honeywell T5317A-1 engine model
was inadvertently left out of the applicability of AD 2002-03-01 and
the Honeywell T5317BCV engine model was introduced into production
after the publication of AD 2002-03-01.
FAA's Determination
The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Related Service Information Under 1 CFR Part 51
The FAA reviewed AlliedSignal Aerospace Service Bulletin (SB)
T5311A/B-0100, dated January 20, 2000. This SB specifies procedures for
performing a special vibration check on Honeywell T5311A and T5311B
model turboshaft engines.
The FAA reviewed AlliedSignal Aerospace SB T5313B/17-0100, dated
November 19, 1999. This SB specifies procedures for performing a
special vibration check on Honeywell T5313B, T5317A, and T5317B model
turboshaft engines.
The FAA reviewed Honeywell SB T53-0147, dated May 29, 2007. This SB
specifies procedures for performing a special vibration check on
Honeywell T5317A-1 model turboshaft engines.
The FAA reviewed Honeywell Maintenance Manual Temporary Revision
(TR) No. 165, dated July 29, 2020. This TR specifies procedures for
performing a special vibration check on Honeywell T5313B, T5317A,
T5317A-1, T5317B, and T5317BCV model turboshaft engines.
[[Page 3472]]
The FAA reviewed AlliedSignal Aerospace SB T53-L-11-0100, Revision
2, dated January 20, 2000. This SB specifies procedures for performing
a special vibration check on Honeywell T53-L-11, -11A, -11B, -11C, -
11D, and -11A S/SA model turboshaft engines.
The FAA reviewed AlliedSignal Aerospace SB T53-L-13B-0100, Revision
2, dated May 11, 1999. This SB specifies procedures for performing a
special vibration check on Honeywell T53-L-13B, -13B S/SA, and -13B S/
SB model turboshaft engines.
The FAA reviewed AlliedSignal Aerospace SB T53-L-703-0100, Revision
2, dated May 11, 1999. This SB specifies procedures for performing a
special vibration check on Honeywell T53-L-703 model turboshaft
engines.
The Director of the Federal Register approved AlliedSignal
Aerospace SB T5313B/17-0100, dated November 19, 1999; AlliedSignal
Aerospace SB T53-L-13B-0100, Revision 2, dated May 11, 1999;
AlliedSignal Aerospace SB T53-L-703-0100, Revision 2, dated May 11,
1999; AlliedSignal Aerospace SB T5311A/B-0100, dated January 20, 2000;
and AlliedSignal Aerospace SB T53-L-11-0100, Revision 2, dated January
20, 2000, for incorporation by reference as of March 21, 2002 (67 FR
6857, February 14, 2002). 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
ADDRESSES.
Other Related Service Information
The FAA reviewed AlliedSignal Aerospace SB T5311/T53-L-11-0103,
dated January 20, 2000. This SB specifies procedures for replacing the
reduction gearbox assembly on Honeywell T5311A and T5311B model
turboshaft engines and Honeywell T53-L-11, -11A, -11B, -11C, -11D, and
-11A S/SA model turboshaft engines.
The FAA reviewed AlliedSignal Aerospace SB T5313B/17-0103, dated
November 19, 1999. This SB specifies procedures for replacing the
reduction gearbox assembly on Honeywell T5313B, T5317A, and T5317B
model turboshaft engines.
The FAA reviewed AlliedSignal Aerospace SB T53-L-13B-0103, Revision
4, dated November 2, 1999. This SB specifies procedures for replacing
the reduction gearbox assembly on Honeywell T53-L-13B, -13B S/SA, and -
13B S/SB model turboshaft engines.
The FAA reviewed AlliedSignal Aerospace SB T53-L-703-0103, Revision
4, dated November 2, 1999. This SB specifies procedures for replacing
the reduction gearbox assembly on Honeywell T53-L-703 model turboshaft
engines.
Proposed AD Requirements in This NPRM
This proposed AD would retain all of the requirements of AD 2002-
03-01. This proposed AD would require initial and repetitive special
vibration tests of the engine and, depending on the results,
replacement of either the reduction gearbox assembly or the engine.
This proposed AD would also expand the applicability to include
Honeywell T5317A-1 and T5317BCV model turboshaft engines.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 150 engines installed on helicopters of U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Special vibration test of the engine.. 4 work-hours x $85 per $0 $340 $51,000
hour = $340.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary
replacement that would be required based on the results of the proposed
special vibration test. The agency has no way of determining the number
of aircraft that might need this replacement:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replace the reduction gearbox assembly........ 40 work-hours x $85 per hour = $48,000 $51,400
$3,400.
Replace the engine............................ 24 work-hours x $85 per hour = 250,577 252,617
$2,040.
----------------------------------------------------------------------------------------------------------------
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 above, I certify that the 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.
[[Page 3473]]
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:
0
a. Removing Airworthiness Directive 2002-03-01, Amendment 39-12642 (67
FR 6857, February 14, 2002); and
0
b. Adding the following new airworthiness directive:
Honeywell International Inc. (Type Certificate previously held by
AlliedSignal, Inc. and Textron Lycoming): Docket No. FAA-2021-1185;
Project Identifier AD-2021-00339-E.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by March 10, 2022.
(b) Affected ADs
This AD replaces AD 2002-03-01, Amendment 39-12642 (67 FR 6857,
February 14, 2002).
(c) Applicability
This AD applies to Honeywell International, Inc. (Type
Certificate previously held by AlliedSignal, Inc. and Textron
Lycoming) T5311A, T5311B, T5313B, T5317A, T5317A-1, T5317B,
T5317BCV, and former military T53-L-11, T53-L-11A, T53-L-11B, T53-L-
11C, T53-L-11D, T53-L-11A S/SA, T53-L-13B, T53-L-13B S/SA, T53-L-13B
S/SB, and T53-L-703 model turboshaft engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7600, Engine
Controls.
(e) Unsafe Condition
This AD was prompted by reports of tachometer drive spur gear
failure, resulting in potential engine overspeed, loss of power
turbine speed (N2) instrument panel indication, and hard landings.
The FAA is issuing this AD to prevent excessive vibrations produced
by the reduction gearbox assembly that could cause failure of the
tachometer drive spur gear. The unsafe condition, if not addressed,
could result in failure of the engine, loss of thrust control, and
damage to the aircraft.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Within 100 flight hours (FHs) after the effective date of
this AD, perform an initial special vibration test of the engine
using the service information, as applicable to the engine model,
listed in Table 1 to paragraph (g)(1) of this AD.
BILLING CODE 4910-13-P
[[Page 3474]]
[GRAPHIC] [TIFF OMITTED] TP24JA22.000
BILLING CODE 4910-13-C
(2) Thereafter, within the following compliance times, perform
repetitive special vibration tests of the engine:
(i) For engines that have tachometer drive spur gear part number
(P/N) 1-070-062-04 installed, perform a repetitive special vibration
test before exceeding 500 FHs since the last special vibration test.
(ii) For engines that have tachometer drive spur gear P/N 1-070-
062-06 installed, perform a repetitive special vibration test before
exceeding 1,000 FHs since the last special vibration test.
(3) If, during any special vibration test required by paragraph
(g)(1) or (2) of this AD, an engine exceeds the 0.2 inches per
second (IPS) limit for any peak RPM/frequency bands, perform one of
the following:
(i) Before further flight, replace the reduction gearbox
assembly with a reduction gearbox assembly eligible for
installation; or
(ii) Before further flight, replace the engine with an engine
eligible for installation.
(4) After replacing the reduction gearbox assembly or engine, as
required by paragraph (3)(i) or (ii) of this AD, before further
flight, perform an initial special vibration test of the engine
using the service information, as applicable to the engine model,
listed in Table 1 to paragraph (g)(1) of this AD.
(5) If, during the special vibration test required by paragraph
(g)(4) of this AD, an engine exceeds the 0.2 IPS limit for any peak
within the RPM/frequency bands, before further flight, replace the
reduction gearbox assembly or the engine.
(h) Definitions
(1) For the purpose of this AD, a ``reduction gearbox assembly
eligible for installation'' is a new, zero hour reduction gearbox
assembly or an overhauled reduction gearbox assembly with tachometer
drive spur gear P/N 1-070-062-04 or P/N 1-070-062-06 that does not
exceed the 0.2 IPS limit for any peak within the RPM/frequency bands
during the administered special vibration test.
(2) For the purpose of this AD, an ``engine eligible for
installation'' is an engine with tachometer drive spur gear P/N 1-
070-062-04 or P/N 1-070-062-06 that does not exceed the 0.2 IPS
limit for any peak within the RPM/frequency bands during the
administered special vibration test.
(i) No Reporting Requirement
The reporting requirements in the Accomplishment Instructions,
paragraph 3.A. or paragraph 11.F, of the service information, as
applicable to the engine model, listed in Table 1 to paragraph
(g)(1) of this AD, are not required by this AD.
(j) 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
[[Page 3475]]
information directly to the manager of the certification office,
send it to the attention of the person identified in paragraph
(k)(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.
(3) AMOCs approved for AD 2002-03-01 (67 FR 6857, February 14,
2002) are approved as AMOCs for the corresponding provisions of this
AD.
(k) Related Information
(1) For more information about this AD, contact Jeffrey Chang,
Aviation Safety Engineer, Los Angeles ACO Branch, FAA, 3960
Paramount Boulevard, Lakewood, CA 90712; phone: (562) 627-5263; fax:
(562) 627-5210; email: [email protected].
(2) For service information identified in this AD, contact
Honeywell International, Inc., 111 South 34th Street, Phoenix, AZ
85034; phone: (800) 601-3099; fax: (602) 365 5577; website: https://myaerospace.honeywell.com/wps/portal. You may view this referenced
service information at the FAA, Airworthiness Products Section,
Operational Safety Branch, 1200 District Avenue, Burlington, MA
01803. For information on the availability of this material at the
FAA, call (817) 222-5110.
Issued on January 18, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-01238 Filed 1-21-22; 8:45 am]
BILLING CODE 4910-13-P
