[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