Proposed Rule2022-01238
Airworthiness Directives; Honeywell International, Inc. (Type Certificate Previously Held by AlliedSignal, Inc. and Textron Lycoming) Turboshaft Engines
Primary source
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Published
January 24, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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 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.
Full Text
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<title>Federal Register, Volume 87 Issue 15 (Monday, January 24, 2022)</title>
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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-01238]
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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).
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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:
<bullet> Federal eRulemaking Portal: Go to <a href="https://www.regulations.gov">https://www.regulations.gov</a>. Follow the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> 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.
<bullet> 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: <a href="https://myaerospace.honeywell.com/wps/portal">https://myaerospace.honeywell.com/wps/portal</a>. 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> 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:
<a href="/cdn-cgi/l/email-protection#08626d6e6e7a6d71266b6069666f486e6969266f677e"><span class="__cf_email__" data-cfemail="2d47484b4b5f4854034e454c434a6d4b4c4c034a425b">[email protected]</span></a>.
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
<a href="https://www.regulations.gov">https://www.regulations.gov</a>, 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
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Special vibration test of the engine.. 4 work-hours x $85 per $0 $340 $51,000
hour = $340.
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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
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Cost per
Action Labor cost Parts cost product
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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.
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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 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.
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(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: <a href="/cdn-cgi/l/email-protection#0d34204c434020414c4c4e42204c40424e205f687c78687e797e4d6b6c6c236a627b"><span class="__cf_email__" data-cfemail="477e6a06090a6a0b060604086a060a08046a15223632223433340721262669202831">[email protected]</span></a>.
(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: <a href="/cdn-cgi/l/email-protection#82e8e7e4e4f0e7fbace1eae3ece5c2e4e3e3ace5edf4"><span class="__cf_email__" data-cfemail="345e51525246514d1a575c555a53745255551a535b42">[email protected]</span></a>.
(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: <a href="https://myaerospace.honeywell.com/wps/portal">https://myaerospace.honeywell.com/wps/portal</a>. 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]
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