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

1038 

Vol. 89, No. 6 

Tuesday, January 9, 2024 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–2523; Project 

Identifier AD–2023–01086–E] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Pratt & Whitney (PW) Model 

PW1519G, PW1521G, PW1521GA, 

PW1521G–3, PW1524G, PW1524G–3, 

PW1525G, PW1525G–3, PW1919G, 

PW1921G, PW1922G, PW1923G, and 

PW1923G–A engines. This proposed AD 

was prompted by an updated analysis of 

an event involving an International Aero 

Engines, LLC (IAE LLC) Model 

PW1127GA–JM engine, which 

experienced a high-pressure compressor 

(HPC) 7th-stage integrally bladed rotor 

(IBR–7) separation that resulted in an 

engine shutdown and aborted takeoff. 

This proposed AD would require 

performing an angled ultrasonic 

inspection (AUSI) of certain highpressure turbine (HPT) 1st-stage hubs, 

HPT 2nd-stage hubs, and HPC 8th-stage 

disks for cracks and, depending on the 

results of the inspections, replacing the 

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

hubs, or HPC 8th-stage disks. This 

proposed AD would also require 

accelerated replacement of certain HPC 

7th-stage rotors, HPC 8th-stage disks, 

HPC rear hubs, HPT 1st-stage hubs, HPT 

2nd-stage hubs, HPT 1st-stage air seals, 

HPT 2nd-stage air seals, HPT 1st-stage 

blade retaining plates, and HPT 2ndstage blade retaining plates. 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 February 8, 

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–2023–2523; 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 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. 

• 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–2023–2523; Project Identifier AD– 

2023–01086–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 this proposal 

because of those comments. 

The FAA has been informed that PW 

has done some outreach with affected 

operators regarding the proposed 

corrective actions for this unsafe 

condition. As a result, affected operators 

are already aware of the proposed 

corrective actions and, in some cases, 

have already begun planning for 

replacement of the affected parts. 

Therefore, the FAA has determined that 

a 30-day comment period is appropriate 

given the particular circumstances 

related to the proposed correction of 

this unsafe condition. 

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. 


khammond on DSKJM1Z7X2PROD with PROPOSALS
Federal Register / Vol. 89, No. 6 / Tuesday, January 9, 2024 / Proposed Rules 1039 

Background 

On December 24, 2022, 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 aborted take-off. Following this 

event, the manufacturer conducted a 

records review of production and fieldreturned parts and re-evaluated their 

engineering analysis methodology. The 

new analysis found that the failure of 

the HPC IBR–7 was caused by a nickel 

powdered metal anomaly, similar in 

nature to an anomaly previously 

observed. The analysis also concluded 

that there is an increased risk of failure 

for additional nickel powdered metal 

parts in certain nickel powdered metal 

production campaigns, and these parts 

are susceptible to failure much earlier 

than previously determined. As a result, 

the FAA is proposing additional AUSIs 

for certain affected nickel powdered 

metal parts and removal from service of 

certain affected nickel powdered metal 

parts. Certain PW Model PW1519G, 

PW1521G, PW1521GA, PW1521G–3, 

PW1524G, PW1524G–3, PW1525G, 

PW1525G–3, PW1919G, PW1921G, 

PW1922G, PW1923G, and PW1923G–A 

engines are among the products affected 

by this condition. This condition, if not 

addressed, could result in uncontained 

disk failure, release of high-energy 

debris, damage to the engine, damage to 

the airplane, and possible loss of the 

airplane. 

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–A–72–00–0196–00A–930A– 

D, Issue No: 002, dated November 30, 

2023, and PW ASB PW1000G–A–72– 

00–0141–00B–930A–D, Issue No: 002, 

dated November 30, 2023. This service 

information specifies a list of affected 

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

hubs that are identified by serial 

number (S/N) and installed on certain 

PW engines; and instructions for 

performing an AUSI on affected HPT 

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

• PW ASB PW1000G–A–72–00– 

0197–00A–930A–D, Issue No: 004, 

dated November 30, 2023, and PW ASB 

PW1000G–A–72–00–0142–00B–930A– 

D, Issue No: 004, dated November 30, 

2023. This service information specifies 

a list of affected HPC 8th-stage disks 

that are identified by S/N and installed 

on certain PW engines; and instructions 

for performing an AUSI on affected HPC 

8th-stage disks. 

• PW ASB PW1000G–A–72–00– 

0204–00A–930A–D Issue No: 001, dated 

November 30, 2023, and PW ASB 

PW1000G–A–72–00–0150–00B–930A–D 

Issue No: 001, dated November 30, 

2023, which specifies procedures for 

performing repetitive AUSIs on affected 

HPC 8th-stage disks. 

• PW ASB PW1000G–A–72–00– 

0205–00A–930A–D, Issue No: 001, 

dated November 30, 2023, and PW ASB 

PW1000G–A–72–00–0151–00B–930A– 

D, Issue No: 001, dated November 30, 

2023, which specify procedures for 

performing repetitive AUSIs on affected 

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

hubs. 

• PW Special Instruction No. 240F– 

23, dated November 30, 2023, which 

specifies a list of affected HPT 1st-stage 

hubs and HPT 2nd-stage hubs that are 

identified by S/N and installed on 

certain PW engines. 

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 require 

performing an AUSI of certain HPT 1ststage hubs, HPT 2nd-stage hubs, and 

HPC 8th-stage disks for cracks and, 

depending on the results of the 

inspections, replacing the HPT 1st-stage 

hubs, HPT 2nd-stage hubs, or HPC 8thstage disks. This proposed AD would 

also require accelerated replacement of 

certain HPC 7th-stage rotors, HPC 8thstage disks, HPC rear hubs, HPT 1ststage air seals, HPT 2nd-stage air seals, 

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

hubs, HPT 1st-stage blade retaining 

plates, and HPT 2nd-stage blade 

retaining plates. 

Interim Action 

The FAA considers this AD to be an 

interim action. This 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 160 

engines would need the AUSI of the 

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

and HPC 8th-stage disk; 218 engines 

would need replacement of the HPT 1ststage hub; 226 engines would need 

replacement of the HPT 2nd-stage hub; 

231 engines would need replacement of 

the HPC 7th-stage rotor; 231 engines 

would need replacement of the HPC 

8th-stage disk; 231 engines would need 

replacement of the HPC rear hub; 231 

engines would need replacement of the 

HPT 1st-stage air seal; 233 engines 

would need replacement of the HPT 

2nd-stage air seal; 232 engines would 

need replacement of the HPT 1st-stage 

blade retaining plate; and 231 engines 

would need replacement of the HPT 

2nd-stage blade retaining plate. 

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 

Perform AUSI of HPT 1st-stage hub, HPT 2ndstage hub, and HPC 8th-stage disk.60 work-hours × $85 per hour = $5,100 .... $0 $5,100 $816,000 

Replace HPT 1st-stage hub ..................................... 10 work-hours × $85 per hour = $850 ....... 49,500 50,350 10,976,300 

Replace HPT 2nd-stage hub .................................... 10 work-hours × $85 per hour = $850 ....... 25,500 26,350 5,955,100 

Replace HPC 7th-stage rotor ................................... 10 work-hours × $85 per hour = $850 ....... 48,000 48,850 11,284,350 

Replace HPC 8th-stage disk .................................... 10 work-hours × $85 per hour = $850 ....... 35,500 36,350 8,396,850 

Replace HPC rear hub ............................................. 10 work-hours × $85 per hour = $850 ....... 83,000 83,850 19,369,350 

Replace HPT 1st-stage air seal ............................... 10 work-hours × $85 per hour = $850 ....... 21,000 21,850 5,047,350 

Replace HPT 2nd-stage air seal .............................. 10 work-hours × $85 per hour = $850 ....... 36,000 36,850 8,586,050 

Replace HPT 1st-stage blade retaining plate .......... 10 work-hours × $85 per hour = $850 ....... 34,000 34,850 8,085,200 


khammond on DSKJM1Z7X2PROD with PROPOSALS
1040 Federal Register / Vol. 89, No. 6 / Tuesday, January 9, 2024 / Proposed Rules 

ESTIMATED COSTS—Continued 

Action Labor cost 

Parts cost 

(average 

pro-rated cost) 

Cost per 

product 

Cost on U.S. 

operators 

Replace HPT 2nd-stage blade retaining plate ......... 10 work-hours × $85 per hour = $850 ....... 13,000 13,850 3,199,350 

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 this 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 adding 

the following new airworthiness 

directive: 

Pratt & Whitney: Docket No. FAA–2023– 

2523; Project Identifier AD–2023–01086– 

E. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by February 8, 

2024. 

(b) Affected ADs 

None. 

(c) Applicability 

Pratt & Whitney (PW) Model PW1519G, 

PW1521G, PW1521GA, PW1521G–3, 

PW1524G, PW1524G–3, PW1525G, 

PW1525G–3, PW1919G, PW1921G, 

PW1922G, PW1923G, and PW1923G–A 

engines. 

(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 updated 

analysis of an event involving an 

International Aero Engines, LLC Model 

PW1127GA–JM engine, which experienced a 

high-pressure compressor (HPC) 7th-stage 

integrally bladed rotor separation that 

resulted in an engine shutdown and aborted 

takeoff. The FAA is issuing this AD to 

prevent failure of the high-pressure turbine 

(HPT) 1st-stage hub, HPT 2nd-stage hub, and 

HPC 8th-stage disk. 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 possible loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For PW1500G engines with an installed 

HPC 8th-stage disk having part number (P/N) 

30G7208, at the next HPC engine shop visit, 

except as required by paragraph (g)(3) of this 

AD, perform an angled ultrasonic inspection 

(AUSI) of the affected HPC 8th-stage disk for 

cracks in accordance with the 

Accomplishment Instructions, paragraph 8., 

of PW Alert Service Bulletin (ASB) 

PW1000G–A–72–00–0197–00A–930A–D, 

Issue No: 004, dated November 30, 2023. 

(2) For PW1500G engines with an installed 

HPT 1st-stage hub having P/N 30G8501 or an 

installed HPT 2nd-stage hub having P/N 

30G7202, at the next engine shop visit, 

except as required by paragraph (g)(3) of this 

AD, perform an AUSI of the affected HPT 1ststage hub or HPT 2nd-stage hub, as 

applicable, for cracks in accordance with the 

Accomplishment Instructions, paragraph 8.A. 

or 8.B., of PW ASB PW1000G–A–72–00– 

0196–00A–930A–D, Issue No: 002, dated 

November 30, 2023. 

(3) For PW1500G engines with an installed 

part, P/N and serial number (S/N) listed in 

Table 1 to paragraph (g)(3) of this AD with 

no AUSI performed prior to the effective date 

of this AD, within the applicable compliance 

time listed in Table 1 to paragraph (g)(3) of 

this AD or within 100 flight cycles (FCs) after 

the effective date of this AD, whichever 

occurs later, perform an AUSI of the affected 

part for cracks in accordance with the 

applicable service bulletin listed in Table 1 

to paragraph (g)(3) of this AD. 

TABLE 1 TO PARAGRAPH (g)(3)—AUSI COMPLIANCE TIMES

Part Applicable S/N listing Compliance time Applicable service bulletin 

(see paragraph (m)(2) of this AD) 

HPC 8th-stage disk ....

P/N 30G7208 

Table 1 of PW ASB PW1000G–A–72–00– 

0197–00A–930A–D.

Next HPC engine shop visit not to 

exceed 10,000 part cycles since 

new (CSN).

Accomplishment Instructions, paragraph 8., of PW 

ASB PW1000G–A–72–00–0197–00A–930A–D. 

HPT 1st-stage hub .....

P/N 30G8501 

Table 2 of PW ASB PW1000G–A–72–00– 

0196–00A–930A–D.

Next engine shop visit not to exceed 

5,000 part CSN.

Accomplishment Instructions, paragraph 8.A. of PW 

ASB PW1000G–A–72–00–0196–00A–930A–D 


khammond on DSKJM1Z7X2PROD with PROPOSALS
Federal Register / Vol. 89, No. 6 / Tuesday, January 9, 2024 / Proposed Rules 1041 

TABLE 1 TO PARAGRAPH (g)(3)—AUSI COMPLIANCE TIMES—Continued 

Part Applicable S/N listing Compliance time Applicable service bulletin 

(see paragraph (m)(2) of this AD) 

HPT 2nd-stage hub ....

P/N 30G7202 

Table 3 of PW ASB PW1000G–A–72–00– 

0196–00A–930A–D.

Next engine shop visit not to exceed 

5,000 part CSN.

Accomplishment Instructions, paragraph 8.B, of PW 

ASB PW1000G–A–72–00–0196–00A–930A–D. 

HPT 1st-stage hub .....

P/N 30G8501 

Table 4 of PW ASB PW1000G–A–72–00– 

0196–00A–930A–D.

Next engine shop visit not to exceed 

4,000 part CSN.

Accomplishment Instructions, paragraph 8.A, of PW 

ASB PW1000G–A–72–00–0196–00A–930A–D. 

HPT 2nd-stage hub ....

P/N 30G7202 

Table 5 of PW ASB PW1000G–A–72–00– 

0196–00A–930A–D.

Next engine shop visit not to exceed 

4,000 part CSN.

Accomplishment Instructions, paragraph 8.B., of PW 

ASB PW1000G–A–72–00–0196–00A–930A–D. 

(4) Thereafter at each piece-part exposure 

of the affected part for PW1500G engines 

with an installed HPC 8th-stage disk having 

P/N 30G7208, an installed HPT 1st-stage hub 

having P/N 30G8501, or an installed HPT 

2nd-stage hub having P/N 30G7202, do the 

following: 

(i) Perform an AUSI of the affected HPC 

8th-stage disk for cracks in accordance with 

the Accomplishment Instructions, paragraph 

5.B., PW ASB PW1000G–A–72–00–0204– 

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

30, 2023. 

(ii) Perform an AUSI of the affected HPT 

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

applicable, for cracks in accordance with the 

Accomplishment Instructions, paragraph 7.A. 

or 7.B., of PW ASB PW1000G–A–72–00– 

0205–00A–930A–D, Issue No: 001, dated 

November 30, 2023. 

(5) For PW1900G engines with an installed 

HPC 8th-stage disk having P/N 30G7208, at 

the next HPC engine shop visit, except as 

required by paragraph (g)(7) of this AD, 

perform an AUSI of the affected HPC 8thstage disk for cracks in accordance with the 

Accomplishment Instructions, paragraph 8., 

of Pratt & Whitney PW ASB PW1000G–A– 

72–00–0142–00B–930A–D, Issue No: 004, 

dated November 30, 2023. 

(6) For PW1900G engines with an installed 

HPT 1st-stage hub having P/N 30G8501 or an 

installed HPT 2nd-stage hub having P/N 

30G7202, at the next engine shop visit, 

except as required by paragraph (g)(7) of this 

AD, perform an AUSI of the affected HPT 1ststage hub and HPT 2nd-stage hub, as 

applicable, for cracks in accordance with the 

Accomplishment Instructions, paragraph 8.A. 

or 8.B., of PW ASB PW1000G–A–72–00– 

0141–00B–930A–D, Issue No: 002, dated 

November 30, 2023. 

(7) For PW1900G engines with an installed 

part, P/N and S/N listed in Table 2 to 

paragraph (g)(7) of this AD, with no AUSI 

performed prior to the effective date of this 

AD, within the compliance time listed in 

Table 2 to paragraph (g)(7) of this AD or 

within 100 FCs after the effective date of this 

AD, whichever occurs later, perform an AUSI 

of the affected parts for cracks in accordance 

with the applicable service bulletin listed in 

Table 2 to paragraph (g)(7) of this AD. 

TABLE 2 TO PARAGRAPH (g)(7)—AUSI COMPLIANCE TIMES

Part Table S/N is listed in Compliance time Applicable service bulletin 

(see paragraph (m)(2) of this AD) 

HPC 8th-stage disk 

having P/N 30G7208.

Table 1 of PW ASB PW1000G–A–72–00– 

0142–00B–930A–D.

Next HPC engine shop visit not to 

exceed 10,000 part CSN.

Accomplishment Instructions, paragraph 8., of PW 

ASB PW1000G–A–72–00–0142–00B–930A–D. 

HPT 1st-stage hub 

having P/N 30G8501.

Table 2 of PW ASB PW1000G–A–72–00– 

0141–00B–930A–D.

Next engine shop visit not to exceed 

5,000 part CSN.

Accomplishment Instructions, paragraph 8.A., of PW 

ASB PW1000G–A–72–00–0141–00B–930A–D. 

HPT 2nd-stage hub 

having P/N 30G7202.

Table 3 of PW ASB PW1000G–A–72–00– 

0141–00B–930A–D.

Next engine shop visit not to exceed 

5,000 part CSN.

Accomplishment Instructions, paragraph 8.B, of PW 

ASB PW1000G–A–72–00–0141–00B–930A–D. 

HPT 1st-stage hub 

having P/N 30G8501.

Table 4 of PW ASB PW1000G–A–72–00– 

0141–00B–930A–D.

Next engine shop visit not to exceed 

4,000 part CSN.

Accomplishment Instructions, paragraph 8.A., of PW 

ASB PW1000G–A–72–00–0141–00B–930A–D. 

HPT 2nd-stage hub 

having P/N 30G7202.

Table 5 of PW ASB PW1000G–A–72–00– 

0141–00B–930A–D.

Next engine shop visit not to exceed 

4,000 part CSN.

Accomplishment Instructions, paragraph 8.B., of PW 

ASB PW1000G–A–72–00–0141–00B–930A–D. 

(8) Thereafter at each piece-part exposure 

of the affected part for PW1900G engines 

with an installed HPC 8th-stage disk having 

P/N 30G7208, or an installed HPT 1st-stage 

hub having P/N 30G8501, or an installed 

HPT 2nd-stage hub having P/N 30G7202, do 

the following: 

(i) Perform an AUSI of the affected HPC 

8th-stage disk for cracks in accordance with 

the Accomplishment Instructions, paragraph 

5.B., of PW ASB PW1000G–A–72–00–0150– 

00B–930A–D, Issue No: 001, dated November 

30, 2023. 

(ii) Perform an AUSI of the affected HPT 

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

applicable, for cracks in accordance with the 

Accomplishment Instructions, paragraph 7.A. 

or 7.B., of PW ASB PW1000G–A–72–00– 

0151–00B–930A–D, Issue No: 001, dated 

November 30, 2023. 

(9) If any crack is found during the 

inspections required by paragraph (g) of this 

AD, before further flight, remove the affected 

part from service and replace with a part 

eligible for installation. 

(10) For engines with an installed part and 

P/N listed in Table 3 to paragraph (g)(10) of 

this AD having 3,300 CSN or less on the 

effective date of this AD, before the part 

accumulates 4,000 CSN or at the next engine 

shop visit after the effective date of this AD, 

whichever occurs first, remove the part from 

service and replace with a part eligible for 

installation. 

TABLE 3 TO PARAGRAPH (g)(10)— 

PART NUMBERS

Part name P/N 

HPC 7th-stage rotor ................................ 30G3307 

HPC 8th-stage disk ................................. 30G3248 

HPC rear hub .......................................... 30G2902 

HPT 1st-stage hub .................................. 30G5701 

HPT 2nd-stage hub ................................. 30G5002 

HPT 1st-stage air seal ............................ 30G3132 

HPT 2nd-stage air seal ........................... 30G3451 

HPT 1st-stage blade retaining plate ....... 30G1692 

HPT 2nd-stage blade retaining plate ...... 30G1698 

(11) For engines with an installed part and 

P/N listed in Table 3 to paragraph (g)(10) of 

this AD having more than 3,300 CSN on the 

effective date of this AD, at the next engine 

shop visit or within 700 FCs after the 

effective date of this AD, whichever occurs 

first, remove the part from service and 

replace it with a part eligible for installation. 

(12) For engines with an installed HPT 1ststage hub having P/N 30G8501 or an installed 

HPT 2nd-stage hub having P/N 30G7202 and 

an S/N listed in Table 1 of PW Special 

Instruction (SI) No. 240F–23, dated 

November 30, 2023, within 100 FCs from the 

effective date of this AD, remove the hub 

from service and replace it with a part 

eligible for installation. 

(13) 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. 

(h) Installation Prohibition 

After the effective date of this AD, do not 

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

30G8501 or an HPT 2nd-stage hub having P/ 

N 30G7202 and an S/N listed in Table 1 of 

PW SI No. 240F–23, dated November 30, 

2023, in any engine. 

(i) Definitions 

(1) For the purposes of this AD, 

‘‘PW1500G’’ engines are PW Model 

PW1519G, PW1521G, PW1521GA, 

PW1521G–3, PW1524G, PW1524G–3, 

PW1525G, and PW1525G–3 engines. 


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1042 Federal Register / Vol. 89, No. 6 / Tuesday, January 9, 2024 / Proposed Rules 

(2) For the purposes of this AD, 

‘‘PW1900G’’ engines are PW Model 

PW1919G, PW1921G, PW1922G, PW1923G, 

and PW1923G–A engines. 

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

eligible for installation’’ is: 

(i) Any HPC 7th-stage rotor, P/N 30G5307 

or later approved P/N. 

(ii) Any HPC 8th-stage disk, P/N 30G7208, 

that has passed the AUSI required by 

paragraph (g) of this AD or later approved 

P/N. 

(iii) Any HPC rear hub, P/N 30G7308 or 

later approved P/N. 

(iv) Any HPT 1st-stage hub, P/N 30G8501, 

that has passed the AUSI required by 

paragraph (g) of this AD or later approved 

P/N. 

(v) Any HPT 2nd-stage hub, P/N 30G7202, 

that has passed the AUSI required by 

paragraph (g) of this AD or later approved 

P/N. 

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

30G5195 or later approved P/N. 

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

30G5196 or later approved P/N. 

(viii) Any HPT 1st-stage blade retaining 

plate, P/N 30G5193 or later approved P/N. 

(ix) Any HPT 2nd-stage blade retaining 

plate, P/N 30G5194 or later approved P/N. 

(4) For the purposes of this AD, a ‘‘piecepart exposure’’ is when the part is 

disassembled from the rotor assembly. 

(5) For the purposes of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges, except for the following situations, 

which do not constitute an engine shop visit. 

(i) The separation of engine flanges solely 

for the purposes of transportation without 

subsequent engine maintenance. 

(ii) Fan case maintenance or replacement. 

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

engine shop visit’’ is when the HPC rotor 

assembly is removed from the engine. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

initial AUSI of the HPC 8th-stage disk, HPT 

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

specified in paragraph (g)(1), (2), (4) and (5) 

of this AD, if the initial AUSI was performed 

before the effective date of this AD using the 

following service information; 

(1) PW ASB PW1000G–A–72–00–0196– 

00A–930A–D, Issue No: 001, dated March 16, 

2023; or 

(2) PW ASB PW1000G–A–72–00–0197– 

00A–930A–D, Issue No: 001, dated March 22, 

2023; or 

(3) PW ASB PW1000G–A–72–00–0197– 

00A–930A–D, Issue No: 002, dated June 19, 

2023; or 

(4) PW ASB PW1000G–A–72–00–0197– 

00A–930A–D, Issue No: 003, dated August 

14, 2023; or 

(5) PW ASB PW1000G–A–72–00–0141– 

00B–930A–D, Issue No: 001, dated March 16, 

2023; or 

(6) PW ASB PW1000G–A–72–00–0142– 

00B–930A–D, Issue No: 001, dated March 22, 

2023; or 

(7) PW ASB PW1000G–A–72–00–0142– 

00B–930A–D, Issue No: 002, dated June 19, 

2023.; or 

(8) PW ASB PW1000G–A–72–00–0142– 

00B–930A–D, Issue No: 003, dated August 

14, 2023. 

(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 

appropriate. If sending information directly 

to the manager of 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)(3) and (4) 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. 

(i) Pratt & Whitney (PW) Alert Service 

Bulletin (ASB) PW1000G–A–72–00–0141– 

00B–930A–D, Issue No: 002, dated November 

30, 2023. 

(ii) PW ASB PW1000G–A–72–00–0142– 

00B–930A–D, Issue No: 004, dated November 

30, 2023. 

(iii) PW ASB PW1000G–A–72–00–0150– 

00B–930A–D Issue No:001, dated November 

30, 2023. 

(iv) PW ASB PW1000G–A–72–00–0151– 

00B–930A–D, Issue No: 001, dated November 

30, 2023. 

(v) PW ASB PW1000G–A–72–00–0196– 

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

30, 2023. 

(vi) PW ASB PW1000G–A–72–00–0197– 

00A–930A–D, Issue No: 004, dated November 

30, 2023. 

(vii) PW ASB PW1000G–A–72–00–0204– 

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

30, 2023. 

(viii) PW ASB PW1000G–A–72–00–0205– 

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

30, 2023. 

(ix) PW Special Instruction No. 240F–23, 

dated November 30, 2023. 

(3) 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. 

(4) 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. 

(5) 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 27, 2023. 

Caitlin Locke, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–00309 Filed 1–5–24; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Part 53 

[REG–142338–07] 

RIN 1545–BI33 

Taxes on Taxable Distributions From 

Donor Advised Funds Under Section 

4966 

AGENCY: Internal Revenue Service (IRS), 

Treasury 

ACTION: Notice of proposed rulemaking; 

extension of comment period. 

SUMMARY: This document extends the 

period to submit comments or to request 

a public hearing for a notice of proposed 

rulemaking (REG–142338–07) that was 

published in the Federal Register on 

Tuesday, November 14, 2023. The 

proposed regulations relate to excise 

taxes on taxable distributions made by 

a sponsoring organization from a donor 

advised fund, and on the agreement of 

certain fund managers to the making of 

such distributions. 

DATES: The period to submit written or 

electronic comments for the notice of 

proposed rulemaking published on 

November 14, 2023 (88 FR 77922) or to 

request a public hearing is extended 

from January 16, 2024, to February 15, 

2024. 

ADDRESSES: Commenters are strongly 

encouraged to submit public comments 

electronically. Submit electronic 

submissions via the Federal 

eRulemaking Portal at 

www.regulations.gov (indicate IRS and 

REG–142338–07) by following the 

online instructions for submitting 

comments. Once submitted to the 

Federal eRulemaking Portal, comments 

cannot be edited or withdrawn. The 

Department of the Treasury (Treasury 


khammond on DSKJM1Z7X2PROD with PROPOSALS