This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

89627 

Vol. 88, No. 248 

Thursday, December 28, 2023 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–2401; Project 

Identifier AD–2023–01278–E] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines, LLC Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2022–19–15, which applies to certain 

International Aero Engines, LLC (IAE 

LLC) Model PW1100G series engines; 

and AD 2023–16–07, which applies to 

certain IAE LLC Model PW1100G series 

engines and PW1400G series engines. 

AD 2022–19–15 requires an angled 

ultrasonic inspection (AUSI) of the 

high-pressure turbine (HPT) 1st-stage 

disk and HPT 2nd-stage disk, and 

replacement if necessary. AD 2023–16– 

07 requires an AUSI of the HPT 1ststage hub (also known as the HPT 1ststage disk) and HPT 2nd-stage hub (also 

known as the HPT 2nd-stage disk) for 

cracks, and replacement if necessary, 

which is terminating action for AD 

2022–19–15. Since the FAA issued 

those two ADs, an investigation 

determined an increased risk of powder 

metal anomalies for all powder metal 

parts in certain powder metal 

production campaigns, which are 

susceptible to failure significantly 

earlier than previously determined. This 

proposed AD would retain the AUSI 

requirement for certain HPT 1st-stage 

and HPT 2nd-stage hubs from AD 2023– 

16–07. This proposed AD would also 

require performing an AUSI of the HPT 

1st-stage hub, HPT 2nd-stage hub, highpressure compressor (HPC) 7th-stage 

integrally bladed rotor (IBR–7), and HPC 

8th-stage integrally bladed rotor (IBR–8) 

for cracks and replacement if necessary. 

This proposed AD would also require 

accelerated replacement of the HPC 

IBR–7, HPC IBR–8, HPC rear hub, HPT 

1st-stage hub, HPT 1st-stage air seal, 

HPT 1st-stage blade retaining plate, HPT 

2nd-stage hub, HPT 2nd-stage blade 

retaining plate, and HPT 2nd-stage rear 

seal. 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 January 17, 

2024. 

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 

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. 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–2401; 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. 

Material Incorporated by Reference: 

• For Pratt & Whitney (PW) service 

information identified in this NPRM, 

contact International Aero Engines, LLC, 

400 Main Street, East Hartford, CT 

06118; phone: (860) 565–0140; email: 

help24@pw.utc.com; website: 

connect.prattwhitney.com. 

• 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. 

FOR FURTHER INFORMATION CONTACT: 

Carol Nguyen, Aviation Safety Engineer, 

FAA, 2200 South 216th Street, Des 

Moines, WA 98198; phone: (781) 238– 

7655; email: carol.nguyen@faa.gov. 

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–2023–2401; Project Identifier AD– 

2023–01278–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 

regulations.gov, including any personal 

information you provide. The agency 

will also post a report summarizing each 

substantive verbal contact received 

about this NPRM. 

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 Carol Nguyen, 

Aviation Safety Engineer, FAA, 2200 

South 216th Street, Des Moines, WA 

98198. 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 2022–19–15, 

Amendment 39–22184 (87 FR 59660, 

October 3, 2022; corrected October 24, 

2022 (87 FR 64156)) (AD 2022–19–15), 


khammond on DSKJM1Z7X2PROD with PROPOSALS
89628 Federal Register / Vol. 88, No. 248 / Thursday, December 28, 2023 / Proposed Rules 

for certain IAE LLC Model PW1122G– 

JM, PW1124G1–JM, PW1124G–JM, 

PW1127G1–JM, PW1127GA–JM, 

PW1127G–JM, PW1129G–JM, 

PW1130G–JM, PW1133GA–JM, and 

PW1133G–JM engines. AD 2022–19–15 

was prompted by an analysis of an event 

involving an International Aero Engines 

AG V2533–A5 model turbofan engine, 

which experienced an uncontained 

failure of an HPT 1st-stage disk that 

resulted in high-energy debris 

penetrating the engine cowling. AD 

2022–19–15 requires performing an 

AUSI of the HPT 1st-stage disk and HPT 

2nd-stage disk and, depending on the 

results of the inspections, replacing the 

HPT 1st-stage disk or HPT 2nd-stage 

disk. The agency issued AD 2022–19–15 

to prevent failure of the HPT 1st-stage 

disk and HPT 2nd-stage disk. 

Since the FAA issued AD 2022–19– 

15, an Airbus Model A320neo airplane 

powered by IAE LLC Model 

PW1127GA–JM engines experienced a 

failure of the HPC IBR–7 that resulted in 

an engine shutdown and an aborted 

take-off. Following this event, the 

manufacturer conducted a records 

review of production and field-returned 

parts and then re-evaluated their 

engineering analysis methodology. The 

new analysis identified HPT 1st-stage 

hubs and HPT 2nd-stage hubs that are 

susceptible to failure significantly 

earlier than previously determined. On 

August 4, 2023, PW issued service 

information with procedures for an 

AUSI to detect cracks and prevent 

premature failure. The manufacturer’s 

updated analysis also identified 

PW1400G series engines that contain 

HPT 1st-stage hubs and HPT 2nd-stage 

hubs that are also subject to the unsafe 

condition. The FAA determined that the 

new service information necessitated 

action much earlier than the compliance 

time mandated in AD 2022–19–15 and 

that the additional engines should also 

be subject to these actions. As a result, 

the FAA issued AD 2023–16–07, 

Amendment 39–22526 (88 FR 56999, 

August 22, 2023) (AD 2023–16–07) for 

certain IAE LLC Model PW1122G–JM, 

PW1124G1–JM, PW1124G–JM, 

PW1127G–JM, PW1127G1–JM, 

PW1127GA–JM, PW1129G–JM, 

PW1130G–JM, PW1133G–JM, 

PW1133GA–JM, PW1428G–JM, 

PW1428GA–JM, PW1428GH–JM, 

PW1431G–JM, PW1431GA–JM, and 

PW1431GH–JM engines. AD 2023–16– 

07 requires performing an AUSI of the 

HPT 1st-stage hub (also known as the 

HPT 1st-stage disk) and HPT 2nd-stage 

hub (also known as the HPT 2nd-stage 

disk) for cracks and, depending on the 

results of the inspections, replacing the 

HPT 1st-stage hub or HPT 2nd-stage 

hub, which was terminating action for 

the requirements of AD 2022–19–15. 

The FAA issued AD 2023–16–07 to 

prevent failure of the HPT 1st-stage hub 

and HPT 2nd-stage hub. 

Actions Since the Previous ADs Were 

Issued 

Since the FAA issued AD 2023–16– 

07, additional manufacturer analysis 

found that the failure of the HPC IBR– 

7 was caused by a powder metal 

anomaly, similar in nature to the 

anomalies outlined in AD 2022–19–15. 

The analysis also concluded that there 

is an increased risk of failure for 

additional powder metal parts in certain 

powder metal production campaigns, 

specifically the HPC IBR–7 and HPC 

IBR–8, and that all affected parts are 

susceptible to failure significantly 

earlier than previously determined. The 

condition, if not addressed, could result 

in uncontained hub failure, release of 

high-energy debris, damage to the 

engine, damage to the airplane, and loss 

of the airplane. 

Previous NPRM 

To address the unsafe condition, the 

FAA issued an NPRM (Docket No. 

FAA–2023–2237; Project Identifier AD– 

2023–01057–E) to supersede AD 2022– 

19–15 and AD 2023–16–07, which was 

published in the Federal Register on 

December 12, 2023 (88 FR 86088). 

However, since that NPRM was issued, 

the FAA has received information from 

PW that an error was inadvertently 

included in the NPRM compliance 

times for some of the HPT 1st-stage and 

2nd-stage hubs, which would have 

required removal significantly later than 

necessary. Because the removal 

timeframe needed to be shortened, the 

FAA determined it is necessary to 

withdraw the NPRM and issue a new 

NPRM for the unsafe condition with the 

correct compliance times. 

The FAA received comments on the 

previous NPRM (Docket No. FAA– 

2023–2237; Project Identifier AD–2023– 

01057–E), which will be copied to 

Docket No. FAA–2023–2401 and 

addressed in the final rule. 

Since the requirements in this 

proposed AD are similar to those 

proposed in the withdrawn NPRM, and 

because the comment period on the 

withdrawn NPRM was 30 days, we have 

good cause to make the comment period 

for this proposed AD 20 days. 

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 the following 

service information: 

• PW Alert Service Bulletin (ASB) 

PW1000G–C–72–00–0224–00A–930A– 

D, Issue No: 001, dated November 3, 

2023, which specifies procedures for 

performing an AUSI for cracks on 

affected HPC IBR–7 and HPC IBR–8; 

• PW ASB PW1000G–C–72–00– 

0225–00A–930A–D Issue No: 001, dated 

November 3, 2023, which specifies 

procedures for performing an AUSI for 

cracks on affected HPT 1st-stage hubs 

and HPT 2nd-stage hubs; 

• PW SI NO. 198F–23, dated 

November 3, 2023, which specifies the 

list of affected HPT 1st-stage hubs and 

HPT 2nd-stage hubs, identified by part 

number and serial number, installed on 

certain IAE LLC engines. 

• PW Service Bulletin PW1000G–C– 

72–00–0188–00A–930A–D, Issue No: 

002, dated July 8, 2022, which was 

previously approved for incorporation 

by reference on November 7, 2022 (87 

FR 59660, October 3, 2022; corrected 

October 24, 2022 (87 FR 64156)). This 

service information specifies procedures 

for performing an AUSI for cracks on 

affected HPT 1st-stage hubs and HPT 

2nd-stage hubs; 

• PW Special Instruction (SI) NO. 

149F–23, dated August 4, 2023, which 

was previously approved for 

incorporation by reference on August 

28, 2023 (88 FR 56999, August 22, 

2023). This service information specifies 

the list of affected HPT 1st-stage hubs 

and HPT 2nd-stage hubs, identified by 

part number and serial number, 

installed on certain IAE LLC engines; 

and 

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. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would retain none 

of the requirements of AD 2022–19–15, 

however, it would retain certain 

requirements of AD 2023–16–07. This 

proposed AD would require performing 

an AUSI of the HPT 1st-stage hub and 

HPT 2nd-stage hub and replacing as 

necessary. This proposed AD would 

also require performing an AUSI of the 

HPC IBR–7 and HPC IBR–8 for cracks 

and replacing as necessary. This 

proposed AD would also require 

accelerated replacement of the HPC 

IBR–7, HPC IBR–8, HPC rear hub, HPT 


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Federal Register / Vol. 88, No. 248 / Thursday, December 28, 2023 / Proposed Rules 89629 

1st-stage hub, HPT 1st-stage air seal, 

HPT 1st-stage blade retaining plate, HPT 

2nd-stage hub, HPT 2nd-stage blade 

retaining plate, and HPT 2nd-stage rear 

seal. 

Interim Action 

The FAA considers this proposed AD 

to be an interim action. The unsafe 

condition is still under investigation by 

the manufacturer and, depending on the 

results of that investigation, the FAA 

may consider further rulemaking action. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 430 

engines installed on airplanes of U.S. 

registry. The FAA estimates that 366 

engines would need replacement of the 

HPT 1st-stage hub; 351 engines would 

need replacement of the HPT 2nd-stage 

hub; 408 engines would need 

replacement of the HPC IBR–7; 368 

engines would need replacement of the 

HPC IBR–8; 283 engines would need 

replacement of the HPC rear hub; and 

206 engines would need replacement of 

the HPT 1st-stage air seal, HPT 1st-stage 

blade retaining plate, HPT 2nd-stage 

blade retaining plate, and HPT 2ndstage rear seal. 

The FAA estimates the following 

costs to comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost 

Parts cost 

(average pro-rated 

cost) 

Cost per 

product 

Cost on U.S. 

operators 

AUSI of HPT 1st-stage hub, HPT 2nd-stage 

hub, HPC IBR–7, and HPC IBR–8 for 

cracks.

80 work-hours × $85 per hour = $6,800 ...... $0 $6,800 $2,924,000 

Replace HPT 1st-stage hub ......................... 10 work-hours × $85 per hour = $850 ......... 56,000 56,850 20,807,100 

Replace HPT 2nd-stage hub ........................ 10 work-hours × $85 per hour = $850 ......... 62,000 62,850 22,060,350 

Replace HPC IBR–7 ..................................... 10 work-hours × $85 per hour = $850 ......... 82,000 82,850 33,802,800 

Replace HPC IBR–8 ..................................... 10 work-hours × $85 per hour = $850 ......... 93,000 93,850 34,536,800 

Replace HPC rear hub ................................. 10 work-hours × $85 per hour = $850 ......... 132,000 132,850 37,596,550 

Replace HPT 1st-stage air seal, HPT 1ststage blade retaining plate, HPT 2ndstage blade retaining plate, and HPT 2ndstage rear seal.20 work-hours × $85 per hour = $1,700 ...... 35,000 36,700 7,560,200 

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 

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. 

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 

■ 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 

2022–19–15, Amendment 39–22184 (87 

FR 64156, October 24, 2022; corrected 

October 24, 20 (87 FR 64156)); and 

Airworthiness Directive 2023–16–07, 

Amendment 39–22526 (88 FR 56999, 

August 22, 2023); and 

■ b. Adding the following new 

airworthiness directive: 

International Aero Engines, LLC: Docket No. 

FAA–2023–2401; Project Identifier AD– 

2023–01278–E. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by January 17, 

2024. 

(b) Affected ADs 

(1) This AD replaces AD 2022–19–15, 

Amendment 39–22184 (87 FR 64156, October 

24, 2022; corrected October 24, 20 (87 FR 

64156)). 

(2) This AD replaces AD 2023–16–07, 

Amendment 39–22526 (88 FR 56999, August 

22, 2023) (AD 2023–16–07). 

(c) Applicability 

This AD applies to International Aero 

Engines, LLC (IAE LLC) Model PW1122G– 

JM, PW1124G1–JM, PW1124G–JM, 

PW1127G–JM, PW1127G1–JM, PW1127GA– 

JM, PW1129G–JM, PW1130G–JM, PW1133G– 

JM, PW1133GA–JM, PW1428G–JM, 

PW1428GA–JM, PW1428GH–JM, PW1431G– 

JM, PW1431GA–JM, and PW1431GH–JM 

engines. 


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89630 Federal Register / Vol. 88, No. 248 / Thursday, December 28, 2023 / Proposed Rules 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section; 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by an analysis of 

an event involving an IAE LLC Model 

PW1127GA–JM engine, which experienced 

failure of a high-pressure compressor (HPC) 

7th-stage integrally bladed rotor (IBR–7) that 

resulted in an engine shutdown and aborted 

takeoff. The FAA is issuing this AD to failure 

of the high-pressure turbine (HPT) 1st-stage 

hub, HPT 2nd-stage hub, HPC IBR–7, and 

HPC 8th-stage integrally bladed rotor (IBR–8). 

The unsafe condition, if not addressed, could 

result in uncontained hub failure, release of 

high-energy debris, damage to the engine, 

damage to the airplane, and loss of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections From AD 2023–16– 

07, With No Changes 

(1) This paragraph restates the 

requirements of paragraph (g)(1) of AD 2023– 

16–07. For Group 1 and Group 2 engines 

with an installed HPT 1st-stage hub having 

part number (P/N) 30G7301 and a serial 

number (S/N) listed in Tables 1, 2, 3, or 4 of 

PW Special Instruction (SI) NO. 149F–23, 

dated August 4, 2023 (PW SI NO. 149F–23), 

within 30 days after August 28, 2023 (the 

effective date of AD 2023–16–07), perform an 

AUSI of the HPT 1st-stage hubs for cracks in 

accordance with the Accomplishment 

Instructions, paragraph 9.A. or 9.B., as 

applicable, of Pratt & Whitney (PW) Service 

Bulletin PW1000G–C–72–00–0188–00A– 

930A–D, Issue No: 002, dated July 8, 2022 

(PW1000G–C–72–00–0188–00A–930A–D, 

Issue 002). 

(2) This paragraph restates the 

requirements of paragraph (g)(2) of AD 2023– 

16–07. For Group 1 and Group 2 engines 

with an installed HPT 2nd-stage hub having 

P/N 30G6602 and an S/N listed in Tables 1, 

2, 3, or 4 of PW SI NO. 149F–23, within 30 

days after August 28, 2023 (the effective date 

of AD 2023–16–07), perform an AUSI of the 

HPT 2nd-stage hubs for cracks in accordance 

with the Accomplishment Instructions, 

paragraph 9.C. or 9.D., as applicable, of 

PW1000G–C–72–00–0188–00A–930A–D, 

Issue 002. 

(h) New Required Actions 

(1) For Group 1 and Group 2 engines with 

an installed HPC IBR–7 having part number 

(P/N) 30G2307 or 30G4407 or an installed 

HPC IBR–8 having P/N, 30G5608, 30G5908 or 

30G8908, at the next HPC engine shop visit 

and thereafter at every HPC engine shop visit, 

perform an angled ultrasonic scan inspection 

(AUSI) of the affected HPC IBR–7 or HPC 

IBR–8, as applicable, for cracks in accordance 

with the Accomplishment Instructions, 

paragraph 4.E.(1) or 4.E.(2), of PW Alert 

Service Bulletin (ASB) PW1000G–C–72–00– 

0224–00A–930A–D, Issue No: 001, dated 

November 3, 2023. 

(2) For Group 1 and Group 2 engines with 

an installed HPT 1st-stage hub having P/N 

30G7301 or an HPT 2nd-stage hub having P/ 

N 30G6602, before exceeding the applicable 

compliance time in Table 1 to paragraph 

(h)(2) of this AD, except as required by 

paragraphs (g)(1) and (2) and paragraph (h)(6) 

of this AD, perform an AUSI of the affected 

HPT 1st-stage hub or HPT 2nd-stage hub, as 

applicable, for cracks in accordance with the 

Accomplishment Instructions, paragraph 

1.D.(7)(a) or 1.D.(7)(b) of PW ASB PW1000G– 

C–72–00–0225–00A–930A–D Issue No: 001, 

dated November 3, 2023 (PW ASB 

PW1000G–C–72–00–0225–00A–930A–D). 

Thereafter, repeat the AUSI at the applicable 

interval in Table 1 to paragraph (h)(2) of this 

AD. 

TABLE 1 TO PARAGRAPH (h)(2)—AUSI COMPLIANCE TIMES

Engine 

group 

AUSI performed prior 

to effective date of 

this AD 

Compliance time Repetitive interval 

1 ......... No ............................. Before accumulating 3,800 cycles since new (CSN) or 

within 100 flight cycles (FCs) after the effective date 

of this AD, whichever occurs later.

Thereafter at each HPT engine shop visit or before 

exceeding 3,800 FCs from the last AUSI of the affected hub, whichever occurs first. 

1 ......... Yes ........................... At the next HPT engine shop visit, not to exceed 

3,800 FCs since the previous AUSI, or within 100 

FCs after the effective date of this AD, whichever 

occurs later.

Thereafter at each HPT engine shop visit or before 

exceeding 3,800 FCs from the last AUSI of the affected hub, whichever occurs first. 

2 ......... No ............................. Before accumulating 2,800 CSN or within 100 FCs 

after the effective date of this AD, whichever occurs 

later.

Thereafter at each HPT engine shop visit or before 

exceeding 2,800 FCs from the last angled AUSI of 

the affected hub, whichever occurs first. 

2 ......... Yes ........................... At the next HPT engine shop visit, not to exceed 

2,800 FCs since the previous AUSI, or within 100 

FCs after the effective date of this AD, whichever 

occurs later.

Thereafter at each HPT engine shop visit or before 

exceeding 2,800 FCs from the last AUSI of the affected hub, whichever occurs first. 

(3) For Group 1 and Group 2 engines with 

an installed part listed in Table 2 to 

paragraph (h)(3) of this AD, at the next HPT 

engine shop visit not to exceed the applicable 

cyclic limit specified in Table 2 to paragraph 

(h)(3) of this AD, or 100 FCs after the 

effective date of the AD, whichever occurs 

later, except as required by paragraphs (h)(5) 

and (7) of this AD, remove the affected part 

from service and replace with a part eligible 

for installation. 

TABLE 2 TO PARAGRAPH (h)(3)—PART REPLACEMENT COMPLIANCE TIMES

Engine 

group 

AUSI performed prior to 

effective date of this AD Part name Part number Cyclic limit 

1 ............... Yes ................................ HPT 1st-stage hub ........ 30G4201 or 30G6201 ... 3,800 FCs since last AUSI. 

No .................................. HPT 1st-stage hub ........ 30G4201 or 30G6201 ... 3,800 CSN. 

Yes ................................ HPT 2nd-stage hub ....... 30G3902 or 30G5502 ... 3,800 FCs since last AUSI or 7,000 CSN whichever comes first. 

No .................................. HPT 2nd-stage hub ....... 30G3902 or 30G5502 ... 3,800 CSN. 

2 ............... Yes ................................ HPT 1st-stage hub ........ 30G4201 or 30G6201 ... 2,800 FCs since last AUSI. 

No .................................. HPT 1st-stage hub ........ 30G4201 or 30G6201 ... 2,800 CSN. 

Yes ................................ HPT 2nd-stage hub ....... 30G3902 or 30G5502 ... 2,800 FCs since last AUSI or 5,000 CSN whichever comes first. 

No .................................. HPT 2nd-stage hub ....... 30G3902 or 30G5502 ... 2,800 CSN. 


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Federal Register / Vol. 88, No. 248 / Thursday, December 28, 2023 / Proposed Rules 89631 

(4) For Group 1 and Group 2 engines with 

an installed part listed in Table 3 to 

paragraph (h)(4) of this AD, before exceeding 

the applicable compliance times specified in 

Table 3 to paragraph (h)(4) of this AD, 

remove the affected part from service and 

replace with a part eligible for installation. 

TABLE 3 TO PARAGRAPH (h)(4)—PART REPLACEMENT COMPLIANCE TIMES

Engine 

group Part name Part number Compliance time 

1 and 2 .... HPC rear hub ... 30G4008 ............................ At the next HPC shop visit or HPT shop visit, whichever occurs first after the effective date of this AD. 

1 and 2 .... HPT 1st-stage 

front air seal.

30G3994 or 30G4674 ........ At the next HPT engine shop visit. 

HPT 2nd-stage 

rear air seal.

30G2452.

HPT 1st-stage 

blade retaining plate.

30G2446.

HPT 2nd-stage 

blade retaining plate.

30G2447.

1 .............. HPC rear hub ... 30G8208 ............................ Before accumulating 7,000 CSN or within 100 FCs after the effective date of this 

AD, whichever occurs later. 

HPC IBR–7 ...... 30G2307 or 30G4407.

HPC IBR–8 ...... 30G5608 or 30G5908 or 

30G8908.

HPT 1st-stage 

hub.

30G7301.

HPT 2nd-stage 

hub.

30G6602.

2 .............. HPC rear hub ... 30G8208 ............................ Before accumulating 5,000 CSN or within 100 FCs after the effective date of this 

AD, whichever occurs later. 

HPC IBR–7 ...... 30G2307 or 30G4407.

HPC IBR–8 ...... 30G5608 or 30G5908 or 

30G8908.

HPT 1st-stage 

hub.

30G7301.

HPT 2nd-stage 

hub.

30G6602.

(5) For Group 1 and Group 2 engines with 

an installed HPT 1st-stage hub having P/N 

30G6201 or an HPT 2nd-stage hub having P/ 

N 30G5502 and an S/N listed in Tables 1, 2, 

3, or 4 of PW SI NO. 149F–23 that has not 

had an AUSI performed before the effective 

date of this AD, before further flight, remove 

the affected hub from service. 

(6) For Group 1 and Group 2 engines with 

an installed HPT 1st-stage hub having P/N 

30G7301 or an HPT 2nd-stage hub having P/ 

N 30G6602 with an S/N listed in Tables 1, 

2, 3, or 4 of PW SI NO. 198F–23, dated 

November 3, 2023, within 100 FC after the 

effective date of this AD, perform an AUSI of 

the affected hub for cracks in accordance 

with the Accomplishment Instructions, 

paragraph 1.D.(7)(a) or 1.D.(7)(b) of PW ASB 

PW1000G–C–72–00–0225–00A–930A–D. 

(7) For Group 1 and Group 2 engines with 

an installed HPT 1st-stage hub having P/N 

30G6201 or an HPT 2nd-stage hub having P/ 

N 30G5502 with an S/N listed in Tables 1, 

2, 3, or 4 of PW SI NO. 198F–23, dated 

November 3, 2023, within 100 FC after the 

effective date of this AD, remove the hub 

from service and replace with a part eligible 

for installation. 

(8) If any crack is found during any 

inspection required by this AD, before further 

flight, remove the affected part from service 

and replace with a part eligible for 

installation. 

(9) If an affected part has accumulated 100 

FCs or less since the last AUSI, reinspection 

is not required provided that the part was not 

damaged during removal from the engine. 

(i) Definitions 

(1) For the purposes of this AD, ‘‘Group 1 

engines’’ are IAE LLC Model PW1122G–JM, 

PW1124G1–JM, PW1124G–JM, PW1127G– 

JM, PW1127G1–JM, and PW1127GA–JM 

engines. 

(2) For the purposes of this AD, ‘‘Group 2 

engines’’ are IAE LLC Model PW1129G–JM, 

PW1130G–JM, PW1133G–JM, PW1133GA– 

JM, PW1428G–JM, PW1428GA–JM, 

PW1428GH–JM, PW1431G–JM, PW1431GA– 

JM, and PW1431GH–JM engines. 

(3) For the purposes of this AD, an ‘‘HPC 

engine shop visit’’ is the induction of an 

engine into the shop for maintenance 

involving the separation of the H-flange. 

(4) For the purposes of this AD, an ‘‘HPT 

engine shop visit’’ is the induction of an 

engine into the shop for maintenance 

involving the separation of the M-flange. 

(5) For the purposes of this AD, a ‘‘part 

eligible for installation’’ is: 

(i) An HPC IBR–7 having P/N 30G2307 or 

30G4407, that has passed the AUSI required 

by paragraph (h)(1) of this AD or later 

approved P/N. 

(ii) An HPC IBR–8 having, P/N 30G5608, 

30G5908, or 30G8908 that has passed the 

AUSI required by paragraph (h)(1) of this AD 

or later approved P/N. 

(iii) An HPT 1st-stage hub having P/N 

30G7301 that has passed the AUSI required 

by paragraph (h)(2) of this AD or later 

approved P/N. 

(iv) An HPT 2nd-stage hub having P/N 

30G6602 that has passed the AUSI required 

by paragraph (h)(2) of this AD or later 

approved P/N. 

(v) An HPC rear hub, P/N 30G8208 or later 

approved P/N. 

(vi) An HPT 1st-stage front air seal, P/N 

30G4617 or later approved P/N. 

(vii) An HPT 2nd-stage rear air seal, P/N 

30G4811 or later approved P/N. 

(viii) An HPT 1st-stage blade retaining 

plate, P/N 30G6059, 31G0018 or later 

approved P/N. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (g)(1) and (2) 

of this AD, if those actions were performed 

before the effective date of this AD using PW 

Service Bulletin PW1000G–C–72–00–0188– 

00A–930A–D, Issue No: 001, dated 

September 13, 2021. This service information 

is not incorporated by reference in this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, AIR–520 Continued 

Operational Safety 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 


khammond on DSKJM1Z7X2PROD with PROPOSALS
89632 Federal Register / Vol. 88, No. 248 / Thursday, December 28, 2023 / Proposed Rules 

appropriate. If sending information directly 

to the manager of the AIR–520 Continued 

Operational Safety Branch, send it to the 

attention of the person identified in 

paragraph (l)(1) 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. 

(l) Additional Information 

(1) For more information about this AD, 

contact Carol Nguyen, Aviation Safety 

Engineer, FAA, 2200 South 216th Street, Des 

Moines, WA 98198; phone: (781) 238–7655; 

email: carol.nguyen@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(6) and (7) of this AD. 

(m) 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 [DATE 35 DAYS AFTER 

PUBLICATION OF THE FINAL RULE]. 

(i) Pratt & Whitney (PW) Alert Service 

Bulletin PW1000G–C–72–00–0224–00A– 

930A–D, Issue No: 001, dated November 3, 

2023. 

(ii) PW Alert Service Bulletin PW1000G– 

C–72–00–0225–00A–930A–D, Issue No: 001, 

dated November 3, 2023. 

(iii) PW Special Instruction NO. 198F–23, 

dated November 3, 2023. 

(4) The following service information was 

approved for IBR on August 28, 2023 (88 FR 

56999, August 22, 2023). 

(i) PW Special Instruction NO. 149F–23, 

dated August 4, 2023. 

(ii) [Reserved] 

(5) The following service information was 

approved for IBR on November 7, 2022 (87 

FR 59660, October 3, 2022; corrected October 

24, 2022 (87 FR 64156)). 

(i) PW Service Bulletin PW1000G–C–72– 

00–0188–00A–930A–D, Issue No: 002, dated 

July 8, 2022. 

(ii) [Reserved] 

(6) For PW service information identified 

in this AD, contact International Aero 

Engines, LLC, 400 Main Street, East Hartford, 

CT 06118; phone: (860) 565–0140; email: 

help24@pw.utc.com; website: 

connect.prattwhitney.com. 

(7) 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. 

(8) You may view this material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

visit: www.archives.gov/federal-register/cfr/ 

ibr-locations or email: fr.inspection@

nara.gov. 

Issued on December 21, 2023. 

Caitlin Locke, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–28693 Filed 12–22–23; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–2237; Project 

Identifier AD–2023–01057–E] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines, LLC Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Proposed rule; withdrawal. 

SUMMARY: The FAA is withdrawing a 

notice of proposed rulemaking (NPRM) 

that proposed to supersede 

Airworthiness Directive (AD) 2022–19– 

15, which applies to certain 

International Aero Engines, LLC (IAE 

LLC) Model PW1100G series engines; 

and AD 2023–16–07, which applies to 

certain IAE LLC Model PW1100G series 

engines and PW1400G series engines. 

AD 2022–19–15 requires an angled 

ultrasonic inspection (AUSI) of the 

high-pressure turbine (HPT) 1st-stage 

disk and HPT 2nd-stage disk, and 

replacement if necessary. AD 2023–16– 

07 requires an AUSI of the HPT 1ststage hub (also known as the HPT 1ststage disk) and HPT 2nd-stage hub (also 

known as the HPT 2nd-stage disk) for 

cracks, and replacement if necessary, 

which is terminating action for AD 

2022–19–15. The NPRM was prompted 

by a manufacturer investigation that 

determined an increased risk of powder 

metal anomalies for all powder metal 

parts in certain powder metal 

production campaigns, which are 

susceptible to failure significantly 

earlier than previously determined. The 

NPRM would have retained the AUSI 

requirement for certain HPT 1st-stage 

and HPT 2nd-stage hubs from AD 2023– 

16–07. The NPRM would also have 

required performing an AUSI of the HPT 

1st-stage hub, HPT 2nd-stage hub, highpressure compressor (HPC) 7th-stage 

integrally bladed rotor (IBR–7), and HPC 

8th-stage integrally bladed rotor (IBR–8) 

for cracks and replacement if necessary. 

The NPRM would also have required 

accelerated replacement of the HPC 

IBR–7, HPC IBR–8, HPC rear hub, HPT 

1st-stage hub, HPT 1st-stage air seal, 

HPT 1st-stage blade retaining plate, HPT 

2nd-stage hub, HPT 2nd-stage blade 

retaining plate, and HPT 2nd-stage rear 

seal. Since issuance of the NPRM, the 

FAA has received information that an 

error was inadvertently included in the 

compliance times for some of the HPT 

1st-stage and 2nd-stage hubs, which 

would have required removal 

significantly later than necessary. 

Accordingly, the NPRM is withdrawn. 

DATES: As of December 28, 2023, the 

proposed rule, which was published in 

the Federal Register on December 12, 

2023 (88 FR 86088), is withdrawn. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov by searching 

for and locating Docket No. FAA–2023– 

2237; 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 AD action, 

the NPRM, any comments received, and 

other information. The street address for 

Docket Operations is Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Carol Nguyen, Aviation Safety Engineer, 

FAA, 2200 South 216th Street, Des 

Moines, WA 98198; phone: (781) 238– 

7655; email: carol.nguyen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued an NPRM that 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

certain IAE LLC Model PW1122G–JM, 

PW1124G1–JM, PW1124G–JM, 

PW1127G–JM, PW1127G1–JM, 

PW1127GA–JM, PW1129G–JM, 

PW1130G–JM, PW1133G–JM, 

PW1133GA–JM, PW1428G–JM, 

PW1428GA–JM, PW1428GH–JM, 

PW1431G–JM, PW1431GA–JM, and 

PW1431GH–JM engines. The NPRM was 

published in the Federal Register on 

December 12, 2023 (88 FR 86088). The 

NPRM was prompted by an analysis of 

an event involving an IAE LLC Model 

PW1127GA–JM engine, which 

experienced failure of a HPC IBR–7 that 

resulted in an engine shutdown and 

aborted takeoff; and the FAA’s 

determination to supersede AD 2022– 

19–15, Amendment 39–22184 (87 FR 

59660, October 3, 2022; corrected 

October 24, 2022 (87 FR 64156)) (AD 

2022–19–15), and AD 2023–16–07, 

Amendment 39–22526 (88 FR 56999, 

August 22, 2023) (AD 2023–16–07). The 

NPRM proposed to retain the AUSI 

requirement for certain HPT 1st-stage 

and HPT 2nd-stage hubs from AD 2023– 

16–07. The NPRM also proposed to 

require performing an AUSI of the HPT 


khammond on DSKJM1Z7X2PROD with PROPOSALS