31384 Federal Register / Vol. 87, No. 100 / Tuesday, May 24, 2022 / Rules and Regulations 

35The 2007 ‘‘Energy Conservation Standards 

Rulemaking Peer Review Report’’ is available at the 

following website: www.energy.gov/eere/buildings/ 

downloads/energy-conservation-standardsrulemaking-peer-review-report-0. (Last accessed 

Feb. 21, 2022.) 

36The December 2021 NAS report is available at 

www.nationalacademies.org/our-work/review-ofmethods-for-setting-building-and-equipmentperformance-standards. (Last accessed Feb. 21, 

2022.) 

Bulletin is to enhance the quality and 

credibility of the Government’s 

scientific information. Under the 

Bulletin, the energy conservation 

standards rulemaking analyses are 

‘‘influential scientific information,’’ 

which the Bulletin defines as ‘‘scientific 

information the agency reasonably can 

determine will have, or does have, a 

clear and substantial impact on 

important public policies or private 

sector decisions.’’ 70 FR 2664, 2667. 

In response to OMB’s Bulletin, DOE 

conducted formal peer reviews of the 

energy conservation standards 

development process and the analyses 

that are typically used and prepared a 

report describing that peer review.35

Generation of this report involved a 

rigorous, formal, and documented 

evaluation using objective criteria and 

qualified and independent reviewers to 

make a judgment as to the technical/ 

scientific/business merit, the actual or 

anticipated results, and the productivity 

and management effectiveness of 

programs and/or projects. Because 

available data, models, and 

technological understanding have 

changed since 2007, DOE has engaged 

with the National Academy of Sciences 

(‘‘NAS’’) to review DOE’s analytical 

methodologies to ascertain whether 

modifications are needed to improve the 

Department’s analyses. DOE is in the 

process of evaluating the resulting 

December 2021 NAS report.36

M. Congressional Notification 

As required by 5 U.S.C. 801, DOE will 

report to Congress on the promulgation 

of this final determination prior to its 

effective date. The report will state that 

it has been determined that the final 

determination is not a ‘‘major rule’’ as 

defined by 5 U.S.C. 804(2). 

VII. Approval of the Office of the 

Secretary 

The Secretary of Energy has approved 

publication of this final determination. 

Signing Authority 

This document of the Department of 

Energy was signed on May 18, 2022, by 

Kelly J. Speakes-Backman, Principal 

Deputy Assistant Secretary for Energy 

Efficiency and Renewable Energy, 

pursuant to delegated authority from the 

Secretary of Energy. That document 

with the original signature and date is 

maintained by DOE. For administrative 

purposes only, and in compliance with 

requirements of the Office of the Federal 

Register, the undersigned DOE Federal 

Register Liaison Officer has been 

authorized to sign and submit the 

document in electronic format for 

publication, as an official document of 

the Department of Energy. This 

administrative process in no way alters 

the legal effect of this document upon 

publication in the Federal Register. 

Signed in Washington, DC, on May 18, 

2022. 

Treena V. Garrett, 

Federal Register Liaison Officer, U.S. 

Department of Energyl 

[FR Doc. 2022–11128 Filed 5–23–22; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1071; Project 

Identifier AD–2021–01055–E; Amendment 

39–22044; AD 2022–10–06] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2017–18– 

14, which applied to certain Rolls-Royce 

Corporation (RRC) 250 model turboshaft 

engines. AD 2017–18–14 required 

repetitive visual inspections and 

fluorescent penetrant inspections (FPIs) 

of the 3rd-stage turbine wheel and 

removal from service of the 4th-stage 

turbine wheel. This AD was prompted 

by in-service turbine blade failures that 

resulted in the loss of power and engine 

in-flight shutdowns. This AD requires 

replacement of the 3rd-stage and 4thstage turbine wheels. This AD also 

revises the applicability to include an 

additional turboshaft engine model. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective June 28, 

2022. 

ADDRESSES: For service information 

identified in this final rule, contact 

Rolls-Royce Corporation, 450 South 

Meridian Street, Mail Code NB–01–06, 

Indianapolis, IN 46225; phone: (317) 

230–2720; email: HelicoptCustSupp@

Rolls-Royce.com; website: www.rollsroyce.com. You may view this service 

information at the Airworthiness 

Products Section, Operational Safety 

Branch, FAA, 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–2021–1071; 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: 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. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2017–18–14, 

Amendment 39–19023 (82 FR 42443, 

September 8, 2017), (AD 2017–18–14). 

AD 2017–18–14 applied to certain RRC 

250–C20, –C20B, –C20F, –C20J, –C20R, 

–C20R/1, –C20R/2, –C20R/4, –C20W, 

–C300/A1, and –C300/B1 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. The NPRM 

published in the Federal Register on 

January 14, 2022 (87 FR 2365). The 

NPRM was prompted by in-service 

turbine blade failures that resulted in 

the loss of power and engine in-flight 

shutdowns. Since the FAA issued AD 

2017–18–14, the manufacturer 

redesigned the 3rd-stage turbine wheel. 

The manufacturer published RollsRoyce Alert Commercial Engine Bulletin 

(CEB) CEB A–1428/CEB A–72–4111 

(single document), which describes 

procedures for replacement of the 3rdstage turbine wheel, P/N 23065818, with 

the new increased blade fillet 3rd-stage 

turbine wheel, P/N M250–10473. 

Additionally, the FAA determined that 

the RRC 250–C20C (T63–A–720) model 

turboshaft engine is also susceptible to 

the unsafe condition. In the NPRM, the 

FAA proposed to require replacement of 

the 3rd-stage and 4th-stage turbine 


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Federal Register / Vol. 87, No. 100 / Tuesday, May 24, 2022 / Rules and Regulations 31385 

wheels. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

two commenters. The commenters were 

an anonymous commenter and RRC. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Comments on Part Availability and 

Costs 

The anonymous commenter stated 

that RRC does not have the inventory to 

supply engine shops with the 3rd-stage 

and 4th-stage turbine wheels proposed 

for replacement in the NPRM. The 

commenter requested that RRC provide 

credit to its customers for unused time 

on 3rd-stage and 4th-stage turbine 

wheels and reasoned that customers 

paid for the full life of the 3rd-stage and 

4th-stage turbine wheels, not a partial 

life, which now requires replacement at 

full price. The commenter also stated 

that the part cost estimates in the NPRM 

for the 3rd-stage and 4th-stage turbine 

wheels are inaccurate and should 

indicate an estimated cost of $22,929.15 

and $18,926.59 to reflect Aviall and 

Boeing’s prices, respectively. The 

commenter noted that they have found 

performing FPIs on the 3rd-stage and 

4th-stage turbine wheels result in 

serviceable conditions compared to the 

previous configurations that were 

beyond serviceable. The commenter 

expressed that the proposed 

requirements in the NPRM would be a 

financial burden on RRC’s customers, 

considering the current market 

instability. 

The FAA disagrees that the 

manufacturer will not have sufficient 

inventory, which would prevent 

compliance with this AD. Prior to 

publishing the NPRM, the FAA 

confirmed with RRC that there would be 

adequate inventory for operators to 

replace the 3rd-stage and 4th-stage 

turbine wheels. In response to this 

comment, the FAA confirmed with RRC 

that the 3rd-stage and 4th-stage turbine 

wheels are available at a 50% 

discounted price. Additionally, RRC 

indicated that suppliers will also 

provide the discounted price. The FPI of 

3rd-stage turbine wheels was an interim 

action until redesigned parts became 

available. While FPI reduces the risk of 

a blade failure, the unsafe condition is 

addressed by replacing the 3rd-stage 

turbine wheel with the revised design. 

The FAA did not change this AD as a 

result of the comments. 

Request To Update Service Information 

RRC requested that the FAA revise the 

Related Service Information paragraph 

of this AD to reference Rolls-Royce Alert 

CEB CEB A–1428/CEB A–72–4111 

(single document), Revision 2, dated 

December 8, 2021. RRC reasoned that 

since the three Rolls-Royce bulletins 

were submitted to the FAA in support 

of the NPRM, Rolls-Royce has published 

Revision 2 of Rolls-Royce Alert CEB 

CEB A–1428/CEB A–72–4111 (single 

document). 

The FAA agrees. The FAA has 

updated the Related Service Information 

paragraph of this AD to reference RollsRoyce Alert CEB CEB A–1428/CEB A– 

72–4111 (single document), Revision 2, 

dated December 8, 2021. 

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, and any other changes 

described previously, this AD is 

adopted as proposed in the NPRM. 

None of the changes will increase the 

economic burden on any operator. 

Related Service Information 

The FAA reviewed Rolls-Royce Alert 

CEB CEB A–1428/CEB A–72–4111 

(single document), Revision 2, dated 

December 8, 2021. This Alert CEB 

describes procedures for replacing the 

3rd-stage turbine wheel, P/N 23065818, 

with the new increased blade fillet 3rdstage turbine wheel, P/N M250–10473. 

The FAA reviewed Rolls-Royce Alert 

CEB CEB–A–1422/CEB–A–72–4108 

(single document), Original Issue, dated 

September 13, 2017. This Alert CEB 

describes procedures for replacing 4thstage turbine wheel, P/N 23055944, with 

the new increased blade fillet 4th-stage 

turbine wheel, P/N M250–10445. 

The FAA also reviewed Rolls-Royce 

Alert Service Bulletin (SB) RR300–A– 

72–024, Original Issue, dated September 

13, 2017. This Alert SB describes 

procedures for replacing the 4th-stage 

turbine wheel, P/N RR30000240, with 

the new increased blade fillet 4th-stage 

turbine wheel, P/N RR30000494. 

Costs of Compliance 

The FAA estimates that this AD 

affects 3,769 engines installed on 

helicopters of U.S. registry. The FAA 

estimates that 3,041 3rd-stage turbine 

wheels and 3,769 4th-stage turbine 

wheels will require replacement. 

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 

Replace 3rd-stage turbine wheel, 

P/N 23065818.

3 work-hours × $85 per hour = 

$255.

$11,170 $11,425 $34,743,425 (3,041 engines). 

Replace 4th-stage turbine wheel, 

P/N 23055944 or RR30000240.

3 work-hours × $85 per hour = 

$255.

8,928 9,183 $34,610,727 (3,769 engines). 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some of the 

costs of this AD may be covered under 

warranty, thereby reducing the cost 

impact on affected operators. 

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 


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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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