31386 Federal Register / Vol. 87, No. 100 / Tuesday, May 24, 2022 / Rules and Regulations 

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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by: 

■ a. Removing Airworthiness Directive 

2017–18–14, Amendment 39–19023 (82 

FR 42443, September 8, 2017); and 

■ b. Adding the following new 

airworthiness directive: 

2022–10–06 Rolls-Royce Corporation: 

Amendment 39–22044; Docket No. 

FAA–2021–1071; Project Identifier AD– 

2021–01055–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective June 28, 2022. 

(b) Affected ADs 

This AD replaces AD 2017–18–14, 

Amendment 39–19023 (82 FR 42443, 

September 8, 2017). 

(c) Applicability 

This AD applies to Rolls-Royce 

Corporation (RRC) 250–C20, 250–C20B, 250– 

C20C (T63–A–720), 250–C20F, 250–C20J, 

250–C20R, 250–C20R/1, 250–C20R/2, 250– 

C20R/4, 250–C20W, 250–C300/A1, and 250– 

C300/B1 model turboshaft engines with 

either a 3rd-stage turbine wheel, part number 

(P/N) 23065818, or a 4th-stage turbine wheel, 

P/N 23055944 or RR30000240, installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by in-service 

turbine blade failures that resulted in the loss 

of power and engine in-flight shutdowns. 

The FAA is issuing this AD to prevent failure 

of the 3rd-stage and 4th-stage turbine blades. 

The unsafe condition, if not addressed, could 

result in damage to the engine and damage 

to the aircraft. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within 1,775 hours since last visual 

inspection and fluorescent penetrant 

inspection (FPI), or at the next engine shop 

visit, whichever occurs first after the effective 

date of this AD, remove: 

(i) 3rd-stage turbine wheel, P/N 23065818, 

and replace with a part eligible for 

installation. 

(ii) 4th-stage turbine wheel, P/N 23055944, 

and replace with a part eligible for 

installation. 

(2) Within 2,025 hours since last visual 

inspection and FPI, or at the next engine 

shop visit, whichever occurs first after the 

effective date of this AD, remove 4th-stage 

turbine wheel, P/N RR30000240, and replace 

with a part eligible for installation. 

(h) Definitions 

(1) For this purpose of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance in which the 

turbine module is separated from the exhaust 

collector, the gas-producer-support is 

separated from the power-turbine-support, or 

there is separation of pairs of major mating 

engine flanges, except that the separation of 

engine flanges solely for the purposes of 

transportation without subsequent engine 

maintenance does not constitute an engine 

shop visit. 

(2) For the purpose of this AD, a ‘‘part 

eligible for installation’’ is a 3rd-stage turbine 

wheel or 4th-stage turbine wheel that does 

not have a P/N listed in the Applicability, 

paragraph (c), of this AD. 

(i) Special Flight Permit 

A special flight permit may be issued in 

accordance with 14 CFR 21.197 and 21.199 

to permit a one-time non-revenue ferry flight 

to operate the airplane to a maintenance 

facility where the engine can be removed 

from service. This ferry flight must be 

performed with only essential flight crew. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Chicago ACO, 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 (k) of this AD. 

(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. 

(k) Related Information 

For more information about this AD, 

contact John Tallarovic, Aviation Safety 

Engineer, Chicago ACO, FAA, 2300 E Devon 

Avenue, Des Plaines, IL 60018; phone: (847) 

294–8180; email: john.m.tallarovic@faa.gov. 

(l) Material Incorporated by Reference 

None. 

Issued on May 3, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–11084 Filed 5–23–22; 8:45 am] 

BILLING CODE 4910–13–P 

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. 

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. 


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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 


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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

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Special vibration test of the engine ................ 4 work-hours × $85 per hour = $340 ............. $0 $340 $51,000 

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

Action Labor cost Parts cost Cost per 

product 

Replace the reduction gearbox assembly .................... 40 work-hours × $85 per hour = $3,400 ...................... $48,000 $51,400 

Replace the engine ...................................................... 24 work-hours × $85 per hour = $2,040 ...................... 250,577 252,617 

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 


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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. 

§ 39.13 [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: 

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. 

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, 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: 9-ANMLAACO-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. 

(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: jeffrey.chang@faa.gov. 

(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). 


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(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: fr.inspection@nara.gov, 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] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Parts 43, 65, and 147 

[Docket No.: FAA–2021–0237; Amdt. Nos. 

43–52, 65–63, 147–9] 

RIN 2120–AL67 

Aviation Maintenance Technician 

Schools 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Interim final rule; request for 

comments. 

SUMMARY: This final rule establishes 

regulations that conform with the 

Aircraft Certification, Safety, and 

Accountability Act, which sets forth 

statutory requirements to implement 

regulations for maintenance technician 

training. Consistent with the statute, 

this final rule adopts new requirements 

for issuing aviation maintenance 

technician school (AMTS) certificates 

and associated ratings and the general 

operating rules for the holders of those 

certificates and ratings. 

DATES: This rule is effective September 

21, 2022, except for amendatory 

instructions 6 and 9, which are effective 

August 1, 2023. Comments must be 

received on or before June 23, 2022. The 

incorporation by reference of certain 

publications listed in this rule is 

approved by the Director of the Federal 

Register as of September 21, 2022. 

ADDRESSES: You may send comments 

identified by docket number FAA– 

2021–0237 using any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

www.regulations.gov and follow the 

online instructions for sending your 

comments electronically. 

• Mail: Send comments to Docket 

Operations, M–30; U.S. Department of 

Transportation (DOT), 1200 New Jersey 

Avenue SE, Room W12–140, West 

Building Ground Floor, Washington, DC 

20590–0001. 

• Hand Delivery or Courier: Take 

comments to Docket Operations in 

Room W12–140 of the West Building 

Ground Floor at 1200 New Jersey 

Avenue SE, Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

• Fax: Fax comments to Docket 

Operations at 202–493–2251. 

Privacy: In accordance with 5 U.S.C. 

553(c), DOT solicits comments from the 

public to better inform its rulemaking 

process. DOT posts these comments, 

without edit, including any personal 

information the commenter provides, to 

www.regulations.gov, as described in 

the system of records notice (DOT/ALL– 

14 FDMS), which can be reviewed at 

www.dot.gov/privacy. 

Docket: Background documents or 

comments received may be read at 

www.regulations.gov at any time. 

Follow the online instructions for 

accessing the docket or visit Docket 

Operations in Room W12–140 of the 

West Building Ground Floor at 1200 

New Jersey Avenue SE, Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this 

action, contact Tanya Glines, Aircraft 

Maintenance Division, Federal Aviation 

Administration, 800 Independence 

Avenue SW, Washington, DC 20591; 

telephone (202) 380–5896; email 

Tanya.Glines@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Authority for This Rulemaking 

The FAA’s authority to issue rules on 

aviation safety is found in Title 49 of the 

United States Code. 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. 

This rulemaking is promulgated 

under the authority described in Title 

49, Subtitle VII, Part A, Subpart I, 

Chapter 401, Section 40113 (prescribing 

general authority of the Administrator of 

the FAA, with respect to aviation safety 

duties and powers, to prescribe 

regulations); and Subpart III, Chapter 

447, Sections 44701 (general authority 

of the Administrator to prescribe 

regulations and minimum standards in 

the interest of safety for inspecting, 

servicing, and overhauling aircraft, 

engines, propellers, and appliances, 

including for other practices, methods, 

and procedures necessary for safety in 

air commerce); 44702 (authority of the 

Administrator to issue air agency 

certificates); 44703 (authority of the 

Administrator to issue airman 

certificates); 44707 (authority of the 

Administrator to examine and rate air 

agencies, including civilian schools 

giving instruction in repairing, altering, 

and maintaining aircraft, aircraft 

engines, propellers, and appliances, on 

the adequacy of instruction, the 

suitability and airworthiness of 

equipment, and the competency of 

instructors); and 44709 (authority of the 

Administrator to amend, modify, 

suspend, and revoke air agency and 

other FAA-issued certificates). 

This rule is further promulgated 

under Section 135 of the Aircraft 

Certification, Safety, and Accountability 

Act in Public Law 116–260, the 

Consolidated Appropriations Act of 

2021. Section 135, titled ‘‘Promoting 

Aviation Regulations for Technical 

Training,’’ provides the requirements 

and terms of this rule. 

Good Cause for Immediate Adoption 

Section 553(b)(3)(B) of the 

Administrative Procedure Act (APA) (5 

U.S.C.) authorizes agencies to dispense 

with notice and comment procedures 

for rules when the agency, for ‘‘good 

cause,’’ finds that those procedures are 

‘‘impracticable, unnecessary, or contrary 

to the public interest.’’ Under this 

section, an agency, upon finding good 

cause, may issue a final rule without 

seeking comment prior to the 

rulemaking. 

The FAA finds good cause under 5 

U.S.C. 553(b)(3)(B) to waive prior notice 

and the opportunity for public comment 

because such procedures would be 

unnecessary and contrary to the public 

interest. On December 27, 2020, 

Congress passed the Consolidated 

Appropriations Act (Pub. L. 116–260), 

which includes the Aircraft 

Certification, Safety, and Accountability 

Act (the ‘‘Act’’). In Section 135 of the 

Act, titled ‘‘Promoting Aviation 

Regulations for Technical Training,’’ 


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