[Federal Register Volume 87, Number 100 (Tuesday, May 24, 2022)]
[Rules and Regulations]
[Pages 31386-31391]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-11059]


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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; 
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.

[[Page 31387]]


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: 
<a href="/cdn-cgi/l/email-protection#3f555a59594d5a46115c575e51587f595e5e11585049"><span class="__cf_email__" data-cfemail="d9b3bcbfbfabbca0f7bab1b8b7be99bfb8b8f7beb6af">[email protected]</span></a>.

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

[[Page 31388]]

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
----------------------------------------------------------------------------------------------------------------
                                                                                     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 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

[[Page 31389]]

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

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:

2022-10-02 Honeywell International Inc. (Type Certificate previously 
held by AlliedSignal, Inc. and Textron Lycoming): Amendment 39-
22040; Docket No. FAA-2021-1185; Project Identifier AD-2021-00339-E.

(a) Effective Date

    This airworthiness directive (AD) is effective June 28, 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, or before further flight for a newly installed engine or 
newly installed reduction gearbox assembly, 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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[GRAPHIC] [TIFF OMITTED] TR24MY22.000

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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, before further 
flight, remove the reduction gearbox assembly or the engine from 
service.

(h) 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.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, FAA, has the authority 
to approve AMOCs for this AD, if requested using the procedures 
found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your 
request to your principal inspector or local Flight Standards 
District Office, as appropriate. If sending information directly to 
the manager of the certification office, send it to the attention of 
the person identified in paragraph (j) of this AD. Information may 
be emailed to: <a href="/cdn-cgi/l/email-protection#142d39555a5939585555575b3955595b57394671656171676067547275753a737b62"><span class="__cf_email__" data-cfemail="30091d717e7d1d7c7171737f1d717d7f731d6255414555434443705651511e575f46">[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.

(j) Related Information

    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#751f10131307100c5b161d141b12351314145b121a03"><span class="__cf_email__" data-cfemail="523837343420372b7c313a333c35123433337c353d24">[email protected]</span></a>.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
June 28, 2022.
    (i) Honeywell Service Bulletin (SB) T53-0147, dated May 29, 
2007.
    (ii) Honeywell Maintenance Manual Temporary Revision No. 165, 
dated July 29, 2020.
    (4) The following service information was approved for IBR on 
March 21, 2002 (67 FR 6857, February 14, 2002).

[[Page 31391]]

    (i) AlliedSignal, Inc. SB T5311A/B-0100, dated January 20, 2000.
    (ii) AlliedSignal, Inc. SB T5313B/17-0100, dated November 19, 
1999.
    (iii) AlliedSignal, Inc. SB T53-L-11-0100, Revision 2, dated 
January 20, 2000.
    (iv) AlliedSignal, Inc. SB T53-L-13B-0100, Revision 2, dated May 
11, 1999.
    (v) AlliedSignal, Inc. SB T53-L-703-0100, Revision 2, dated May 
11, 1999.
    (5) 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.
    (6) You may view this service information at 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: <a href="/cdn-cgi/l/email-protection#91f7e3bff8ffe2e1f4f2e5f8feffd1fff0e3f0bff6fee7"><span class="__cf_email__" data-cfemail="6e081c4007001d1e0b0d1a0701002e000f1c0f40090118">[email protected]</span></a>, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on May 5, 2022.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2022-11059 Filed 5-23-22; 8:45 am]
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