DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-1185; Project Identifier AD-2021-00339-E;
Amendment 39-22040; AD 2022-10-02]
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: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2002-03-
01, which applied to certain Honeywell International, Inc. (Honeywell)
T53 model turboshaft engines. AD 2002-03-01 required 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. 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. This AD requires 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 issuing this AD to address the unsafe condition on these
products.

DATES: This AD is effective June 28, 2022.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 28,
2022.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of March
21, 2002 (67 FR 6857, February 14, 2002).

ADDRESSES: For service information identified in this final rule,
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. It is also available at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-1185.

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 final rule, any
comments received, and other information. The address for Docket
Operations is U.S. Department of Transportation, Docket Operations, M-
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: 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:

Background

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2002-03-01, Amendment 39-12642 (67 FR 6857,
February 14, 2002), (AD 2002-03-01). AD 2002-03-01 applied to 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. The NPRM
published in the Federal Register on January 24, 2022 (87 FR 3470). The
NPRM was prompted by reports indicating 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. In the NPRM, the FAA proposed to
continue to 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. In the NPRM, the FAA also
proposed to expand the applicability to include Honeywell T5317A-1 and
T5317BCV model turboshaft engines.

Discussion of Final Airworthiness Directive

Comments

The FAA received comments from an individual commenter. The
following presents the comments received on the NPRM and the FAA's
response to each comment.

Request To Withdraw the NPRM

An individual commenter commented that both the NPRM and the AD
being superseded [AD 2002-03-01] are redundant based on the service
bulletins Honeywell published addressing the unsafe condition. The
commenter suggested that if a new AD is published, the AD should
include language allowing operators already in compliance to remain in
compliance until the next due time. The commenter added that the
changes in the NPRM seem more appropriate for an AD revision than that
of publishing a new AD since the reference material and unsafe
condition remain unchanged. Additionally, the commenter suggested that
the justification for the NPRM, based on the introduction of Honeywell
T5317A-1 and T5317BCV model turboshaft engines, is inaccurate as both
series are already included in the Honeywell service bulletins.
The FAA disagrees with withdrawing the NPRM. Issuance of this AD is
necessary in order to mandate the required actions on the affected
engines to address the unsafe condition. Service information
incorporated by reference under 1 CFR part 51 in AD 2002-03-01 is also
incorporated by reference in this AD. The required actions for certain
engine models continue to be required by this AD. As a result,
operators who accomplished the required actions in AD 2002-03-01 before
the effective date of this AD, are in compliance with paragraph (g)(1)
of this AD based on paragraph (f) Compliance, which requires operators
to comply with this AD within the compliance times specified, unless
already done. Therefore, for operators that already complied with
paragraph (g)(1) of this AD prior to the effective date, the next
repetitive special vibration test of the engine must be accomplished
before exceeding the specified flight hours in paragraph (g)(2) of this
AD. Since the effective date of AD 2002-03-01, Honeywell published
Honeywell Service Bulletin (SB) T53-0147, dated May 29, 2007, and
Honeywell Maintenance Manual Temporary Revision (TR) No. 165, dated
July 29, 2020, which specify procedures for performing the initial and
repetitive special vibration tests on Honeywell T5317A-1 and T5317BCV
model turboshaft engines. Regarding the request to revise AD 2002-03-01
instead of issuing this superseding AD, the method to revise AD 2002-
03-01 is through superseding it, which this AD does.

Revision to the Required Actions

Since the NPRM published, the FAA determined the need to remove the
Definitions paragraph from this AD and instead, revise the required
actions in paragraph (g)(1) of this AD. In the NPRM, the FAA proposed
to define a ``reduction gearbox assembly eligible for installation'' as
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. In the NPRM, the FAA also proposed to define an
``engine eligible for installation'' as 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. Both of these proposed definitions
would have required operators to first perform a special vibration test
on the engine or reduction gearbox assembly before further flight after
installation. In lieu of these definitions, the FAA revised paragraph
(g)(1) of this AD to require a special vibration test before further
flight for a newly installed engine or newly installed reduction gearbox assembly.
The FAA also revised the proposed action in paragraph (g)(3) by
removing reference to those previously defined terms in the proposal
and removing the proposed actions in paragraphs (g)(4) and (5) of the
NPRM.

Conclusion

The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting the AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, this
AD is adopted as proposed in the NPRM. None of the changes will
increase the economic burden on any operator.

Related Service Information Under 1 CFR Part 51

The FAA reviewed AlliedSignal, Inc. 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, Inc. 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 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.
The FAA reviewed AlliedSignal, Inc. 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, Inc. 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, Inc. 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, Inc. SB
T5313B/17-0100, dated November 19, 1999; AlliedSignal, Inc. SB T53-L-
13B-0100, Revision 2, dated May 11, 1999; AlliedSignal, Inc. SB T53-L-
703-0100, Revision 2, dated May 11, 1999; AlliedSignal, Inc. SB T5311A/
B-0100, dated January 20, 2000; and AlliedSignal, Inc. 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, Inc. 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, Inc. 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, Inc. 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, Inc. 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.

Costs of Compliance

The FAA estimates that this AD affects 150 engines installed on
helicopters of U.S. registry.
The FAA estimates the following costs to comply with this AD:

Estimated Costs

The FAA estimates the following costs to do any necessary
replacement that would be required based on the results of the special
vibration test. The agency has no way of determining the number of
aircraft that might need this replacement:

On-Condition Costs

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 has determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 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: