Federal Register / Vol. 87, No. 105 / Wednesday, June 1, 2022 / Proposed Rules 33071 

more than one-eighth inch in greatest 

dimension; 

(g) Poorly developed kernel; and 

(h) Shriveling when the surface of the 

kernel is very conspicuously wrinkled. 

■ 63. Add § 51.1452 to read as follows: 

§ 51.1452 Serious damage. 

Serious damage means any specific 

defect described in this section; or an 

equally objectionable variation of any 

one of these defects, or any other defect, 

or any combination of defects, which 

seriously detracts from the appearance 

or the edible or marketing quality of the 

individual portion of kernel or of the lot 

as a whole. The following defects shall 

be considered as serious damage: 

(a) Adhering material from inside the 

shell when attached to more than onehalf of the surface on one side of the 

half-kernel or piece; 

(b) Any plainly visible mold; 

(c) Dark kernel spots when more than 

three are on the kernel, or when any 

dark kernel spot or the aggregate of two 

or more spots affect an area of more than 

10 percent of the surface of the halfkernel or piece; 

(d) Dark skin discoloration, darker 

than ‘‘dark brown,’’ when covering more 

than one-fourth of the surface of the 

half-kernel or piece; 

(e) Decay affecting any portion of the 

kernel; 

(f) Insects, web, or frass or any 

distinct evidence of insect feeding on 

the kernel; 

(g) Internal discoloration, which is 

dark gray, dark brown, or black and 

extends more than one-third the length 

of the half-kernel or piece; 

(h) Rancidity when the kernel is 

distinctly rancid to the taste. Staleness 

of flavor shall not be classed as 

rancidity; and 

(i) Undeveloped kernel. 

■ 64. Add § 51.1453 to read as follows: 

§ 51.1453 Rancidity. 

Rancidity refers to the tendency of the 

oil in a pecan kernel to become tainted 

as a result of oxidation or hydrolysis. 

While there is no definitive measure to 

determine rancidity, the tendency of the 

kernel to become rancid can be 

evaluated by testing the kernel’s 

peroxide and free-fatty acid values. 

Peroxide values should be less than 5 

mEq/kg and free fatty acid should be 

less than 1%. 

■ 65. Add an undesignated center 

heading and § 51.1454 to read as 

follows: 

Metric Conversion Table 

§ 51.1454 Metric conversion table. 

TABLE 1 TO § 51.1454 

Inches Millimeters 

(mm) 

32/64 ..................................... 12.7 

28/64 ..................................... 11.1 

24/64 ..................................... 9.5 

20/64 ..................................... 7.9 

16/64 ..................................... 6.4 

12/64 ..................................... 4.8 

8/64 ....................................... 3.2 

6/64 ....................................... 2.4 

5/64 ....................................... 2.0 

4/64 ....................................... 1.6 

Erin Morris, 

Associate Administrator, Agricultural 

Marketing Service. 

[FR Doc. 2022–10856 Filed 5–31–22; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0467; Project 

Identifier AD–2022–00174–E] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company 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 General Electric Company (GE) 

GEnx–1B and GEnx–2B model turbofan 

engines. This proposed AD was 

prompted by the detection of meltrelated freckles in the forgings and 

billets, which may reduce the life of 

certain compressor discharge pressure 

(CDP) seals, interstage seals, highpressure turbine (HPT) rotor stage 2 

disks, and stages 6–10 compressor rotor 

spools. This proposed AD would require 

revising the airworthiness limitations 

section (ALS) of the applicable GEnx– 

1B and GEnx–2B Engine Manual (EM) 

and the operator’s existing approved 

maintenance program or inspection 

program, as applicable, to incorporate 

reduced life limits for these parts. 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 July 18, 2022. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

https://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact General Electric 

Company, 1 Neumann Way, Cincinnati, 

OH 45215; phone: (513) 552–3272; 

email: aviation.fleetsupport@ae.ge.com; 

website: https://www.ge.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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0467; or in person at Docket 

Operations between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

NPRM, any comments received, and 

other information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Alexei Marqueen, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7178; email: 

Alexei.T.Marqueen@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–2022–0467; Project Identifier AD– 

2022–00174–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. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 


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11.35, the FAA will post all comments 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact 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 Alexei Marqueen, 

Aviation Safety Engineer, ECO Branch, 

FAA, 1200 District Avenue, Burlington, 

MA 01803. 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 was notified by the engine 

manufacturer of the detection of meltrelated freckles in the forgings and 

billets, which may reduce the life of 

certain CDP seals, interstage seals, HPT 

rotor stage 2 disks, and stages 6–10 

compressor rotor spools (life-limited 

parts (LLPs)) on GEnx–1B54/P2, GEnx– 

1B58/P2, GEnx–1B64/P2, GEnx–1B67/ 

P2, GEnx–1B70/P2, GEnx–1B70C/P2, 

GEnx–1B70/72/P2, GEnx–1B70/75/P2, 

GEnx–1B74/75/P2, GEnx–1B75/P2, 

GEnx–1B76/P2, GEnx–1B76A/P2, and 

GEnx–1B78/P2 (GEnx–1B) and GEnx– 

2B67, GEnx–2B67B, and GEnx–2B67/P 

(GEnx–2B) model turbofan engines. The 

manufacturer’s investigation determined 

that, as a result of such freckles forming 

in the forgings and billets, certain LLPs 

may have undetected subsurface 

anomalies that developed during the 

manufacturing process, resulting in 

reduced material properties and a lower 

fatigue life capability. Reduced material 

properties may cause premature LLP 

fracture, which could result in 

uncontained debris release. As a result 

of its investigation, the manufacturer 

determined the need to reduce the life 

limits of certain LLPs. To reflect these 

reduced life limits, the manufacturer 

revised the ALS of the affected GEnx– 

1B and GEnx–2B EMs. The FAA is 

proposing to require operators to update 

the ALS of the applicable GEnx–1B and 

GEnx–2B EM with the reduced life 

limits for certain LLPs. This condition, 

if not addressed, could result in 

uncontained debris release, damage to 

the engine, and damage to 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 

The FAA reviewed GE GEnx–1B 

Service Bulletin (SB) 72–0484 R00, 

dated August 11, 2021, and GE GEnx– 

2B SB 72–0423 R00, dated August 11, 

2021. These SBs, differentiated by 

engine model, provide the reduced life 

limits for certain LLPs. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require 

revising the ALS of the applicable 

GEnx–1B and GEnx–2B EM and the 

operator’s existing approved 

maintenance program or inspection 

program, as applicable, to incorporate 

reduced life limits for certain LLPs. 

Differences Between This Proposed AD 

and the Service Information 

GE GEnx–2B Service Bulletin (SB) 

72–0423 R00, dated August 11, 2021, 

uses the term ‘‘HPT stage 2 disk’’ to 

describe HPT stage 2 disk P/N 

2383M86P02, while this proposed AD 

uses the term ‘‘HPT rotor stage 2 disk.’’ 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 390 

engines installed on airplanes of U.S. 

registry. 

The FAA estimates the following 

costs to comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Revise ALS of EM and the operator’s existing 

approved maintenance or inspection program.

1 work-hour × $85 per hour = $85 ................. $0 $85 $33,150 

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. 


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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: 

General Electric Company: Docket No. FAA– 

2022–0467; Project Identifier AD–2022– 

00174–E. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by July 18, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company (GE) GEnx–1B54/P2, GEnx–1B58/ 

P2, GEnx–1B64/P2, GEnx–1B67/P2, GEnx– 

1B70/P2, GEnx–1B70C/P2, GEnx–1B70/72/ 

P2, GEnx–1B70/75/P2, GEnx–1B74/75/P2, 

GEnx–1B75/P2, GEnx–1B76/P2, GEnx– 

1B76A/P2, GEnx–1B78/P2, GEnx–2B67, 

GEnx–2B67B, and GEnx–2B67/P model 

turbofan engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section, and JASC Code 7250, Turbine 

Section. 

(e) Unsafe Condition 

This AD was prompted by the detection of 

melt-related freckles in the forgings and 

billets, which may reduce the life of certain 

compressor discharge pressure (CDP) seals, 

interstage seals, high-pressure turbine (HPT) 

rotor stage 2 disks, and stages 6–10 

compressor rotor spools. The FAA is issuing 

this AD to prevent failure of the CDP seal, 

interstage seal, HPT rotor stage 2 disk, and 

stages 6–10 compressor rotor spool. The 

unsafe condition, if not addressed, could 

result in uncontained debris release, damage 

to the engine, and damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For all affected GEnx–1B model 

turbofan engines, within 90 days after the 

effective date of this AD, revise the 

airworthiness limitations section (ALS) of the 

existing GEnx–1B Engine Manual (EM) and 

the operator’s existing approved maintenance 

program or inspection program, as 

applicable, by inserting the following 

information into the applicable table for their 

respective part numbers: 

(i) For stages 6–10 compressor rotor spool 

part number (P/N) 2628M56G01, insert the 

information in Table 1 to paragraph (g)(1)(i) 

of this AD. 

TABLE 1 TO PARAGRAPH (g)(1)(i)—STAGES 6–10 COMPRESSOR ROTOR SPOOL P/N 2628M56G01 

Part name Part No. Life cycles 

–1B54/P2 

Life cycles 

–1B58/P2 

–1B64/P2 

–1B67/P2 

–1B70/P2 

Life cycles 

–1B70C/P2 

Life cycles 

–1B70/72/P2 

–1B70/75/P2 

–1B74/75/P2 

–1B75/P2 

Life cycles 

–1B76/P2 

Life cycles 

–1B76A/P2 

Life cycles 

–1B78/P2 

Spool, Stage 6–10 2628M56G01 For part serial numbers 

NOT listed in GEnx–1B SB 72– 

0484, latest revision.

17,000 17,000 15,000 15,000 14,600 12,200 14,600 

Spool, Stage 6–10 2628M56G01 For part serial numbers 

listed in Table 1 of GEnx–1B SB 

72–0484, latest revision.

10,300 10,300 10,300 10,300 8,500 8,500 8,500 

Spool, Stage 6–10 2628M56G01 For part serial numbers 

listed in Table 2 of GEnx–1B SB 

72–0484, latest revision.

5,700 5,700 5,700 5,700 4,800 4,800 4,800 

(ii) For CDP seal P/N 2383M82P03, insert 

the information in Table 2 to paragraph 

(g)(1)(ii) of this AD. 

TABLE 2 TO PARAGRAPH (g)(1)(ii)—CDP SEAL P/N 2383M82P03 

Part name Part No. Life cycles 

–1B54/P2 

Life cycles 

–1B58/P2 

–1B64/P2 

–1B67/P2 

–1B70/P2 

Life cycles 

–1B70C/P2 

Life cycles 

–1B70/72/P2 

–1B70/75/P2 

–1B74/75/P2 

–1B75/P2 

Life cycles 

–1B76/P2 

Life cycles 

–1B76A/P2 

Life cycles 

–1B78/P2 

Seal, CDP ............. 2383M82P03 For part serial numbers 

NOT listed in GEnx–1B SB 72– 

0484, latest revision.

20,000 20,000 15,000 15,000 15,000 15,000 15,000 

Seal, CDP ............. 2383M82P03 For part serial numbers 

listed in Table 3 of GEnx–1B SB 

72–0484, latest revision.

6,100 6,100 6,100 6,100 5,300 5,300 5,300 

Seal, CDP ............. 2383M82P03 For part serial numbers 

listed in Table 4 of GEnx–1B SB 

72–0484, latest revision.

13,400 13,400 13,400 13,400 9,300 9,300 9,300 

Seal, CDP ............. 2383M82P03 For part serial numbers 

listed in Table 5 of GEnx–1B SB 

72–0484, latest revision.

3,600 3,600 3,600 3,600 2,900 2,900 2,900 

(iii) For interstage seal P/N 2383M85P04, 

insert the information in Table 3 to paragraph 

(g)(1)(iii) of this AD. 


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TABLE 3 TO PARAGRAPH (g)(1)(iii)—INTERSTAGE SEAL P/N 2383M85P04 

Part name Part No. Life cycles 

–1B54/P2 

Life cycles 

–1B58/P2 

–1B64/P2 

–1B67/P2 

–1B70/P2 

Life cycles 

–1B70C/P2 

Life cycles 

–1B70/72/P2 

–1B70/75/P2 

–1B74/75/P2 

–1B75/P2 

Life cycles 

–1B76/P2 

Life cycles 

–1B76A/P2 

Life cycles 

–1B78/P2 

Seal, Interstage ..... 2383M85P04 For part serial numbers 

NOT listed in GEnx–1B SB 72– 

0484, latest revision.

17,000 15,000 15,000 15,000 14,200 14,800 14,200 

Seal, Interstage ..... 2383M85P04 For part serial numbers 

listed in Table 6 of GEnx–1B SB 

72–0484, latest revision.

10,500 10,500 10,500 10,500 6,400 6,400 6,400 

Seal, Interstage ..... 2383M85P04 For part serial numbers 

listed in Table 7 of GEnx–1B SB 

72–0484, latest revision.

15,000 15,000 15,000 15,000 10,500 10,500 10,500 

Seal, Interstage ..... 2383M85P04 For part serial numbers 

listed in Table 8 of GEnx–1B SB 

72–0484, latest revision.

5,500 5,500 5,500 5,500 2,800 2,800 2,800 

(iv) For HPT rotor stage 2 disk P/N 

2383M86P02, insert the information in Table 

4 to paragraph (g)(1)(iv) of this AD. 

TABLE 4 TO PARAGRAPH (g)(1)(iv)—HPT ROTOR STAGE 2 DISK P/N 2383M86P02 

Part name Part No. Life cycles 

–1B54/P2 

Life cycles 

–1B58/P2 

–1B64/P2 

–1B67/P2 

–1B70/P2 

Life cycles 

–1B70C/P2 

Life cycles 

–1B70/72/P2 

–1B70/75/P2 

–1B74/75/P2 

–1B75/P2 

Life cycles 

–1B76/P2 

Life cycles 

–1B76A/P2 

Life cycles 

–1B78/P2 

Disk, Stage 2 ........ 2383M86P02 For part serial numbers 

NOT listed in GEnx–1B SB 72– 

0484, latest revision.

12,100 12,100 10,400 10,400 9,500 6,800 9,500 

Disk, Stage 2 ........ 2383M86P02 For part serial numbers 

listed in Table 9 of GEnx–1B SB 

72–0484, latest revision.

6,900 6,900 6,900 6,900 5,100 5,100 5,100 

Disk, Stage 2 ........ 2383M86P02 For part serial numbers 

listed in Table 10 of GEnx–1B SB 

72–0484, latest revision.

10,400 10,400 10,400 10,400 7,500 6,800 7,500 

Disk, Stage 2 ........ 2383M86P02 For part serial numbers 

listed in Table 11 of GEnx–1B SB 

72–0484, latest revision.

3,800 3,800 3,800 3,800 3,000 3,000 3,000 

(2) For all affected GEnx–2B model 

turbofan engines, within 90 days after the 

effective date of this AD, revise the ALS of 

the existing GEnx–2B EM and the operator’s 

existing approved maintenance program or 

inspection program, as applicable, by 

inserting the following information into the 

applicable table for their respective part 

numbers: 

(i) For stages 6–10 compressor rotor spool 

P/N 2628M56G01, insert the information in 

Table 5 to paragraph (g)(2)(i) of this AD. 

TABLE 5 TO PARAGRAPH (g)(2)(i)—STAGES 6–10 COMPRESSOR ROTOR SPOOL P/N 2628M56G01 

Part name Part No. Life cycles 

–2B67 

Life cycles 

–2B67B 

Life cycles 

–2B67/P 

Spool, Stage 6–10 .... 2628M56G01 For part serial numbers NOT listed in GEnx–2B SB 

72–0423, latest revision.

........................ ........................ 11,100 

Spool, Stage 6–10 .... 2628M56G01 For part serial numbers listed in Table 1 of GEnx–2B 

SB 72–0423, latest revision.

........................ ........................ 10,300 

Spool, Stage 6–10 .... 2628M56G01 For part serial numbers listed in Table 2 of GEnx–2B 

SB 72–0423, latest revision.

........................ ........................ 5,700 

(ii) For CDP seal P/N 2383M82P03, insert 

the information in Table 6 to paragraph 

(g)(2)(ii) of this AD. 

TABLE 6 TO PARAGRAPH (g)(2)(ii)—CDP SEAL P/N 2383M82P03 

Part name Part No. Life cycles 

–2B67 

Life cycles 

–2B67B 

Life cycles 

–2B67/P 

Seal, CDP ................. 2383M82P03 For part serial numbers NOT listed in GEnx–2B SB 

72–0423, latest revision.

........................ ........................ 15,000 


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TABLE 6 TO PARAGRAPH (g)(2)(ii)—CDP SEAL P/N 2383M82P03—Continued 

Part name Part No. Life cycles 

–2B67 

Life cycles 

–2B67B 

Life cycles 

–2B67/P 

Seal, CDP ................. 2383M82P03 For part serial numbers listed in Table 3 of GEnx–2B 

SB 72–0423, latest revision.

........................ ........................ 6,100 

Seal, CDP ................. 2383M82P03 For part serial numbers listed in Table 4 of GEnx–2B 

SB 72–0423, latest revision.

........................ ........................ 13,400 

Seal, CDP ................. 2383M82P03 For part serial numbers listed in Table 5 of GEnx–2B 

SB 72–0423, latest revision.

........................ ........................ 3,600 

(iii) For interstage seal P/N 2383M85P04, 

insert the information in Table 7 to paragraph 

(g)(2)(iii) of this AD. 

TABLE 7 TO PARAGRAPH (g)(2)(iii)—INTERSTAGE SEAL P/N 2383M85P04 

Part name Part No. Life cycles 

–2B67 

Life cycles 

–2B67B 

Life cycles 

–2B67/P 

Seal, Interstage ........ 2383M85P04 For part serial numbers NOT listed in GEnx–2B SB 

72–0423, latest revision.

........................ ........................ 15,000 

Seal, Interstage ........ 2383M85P04 For part serial numbers listed in Table 6 of GEnx–2B 

SB 72–0423, latest revision.

........................ ........................ 10,500 

Seal, Interstage ........ 2383M85P04 For part serial numbers listed in Table 7 of GEnx–2B 

SB 72–0423, latest revision.

........................ ........................ 15,000 

Seal, Interstage ........ 2383M85P04 For part serial numbers listed in Table 8 of GEnx–2B 

SB 72–0423, latest revision.

........................ ........................ 5,500 

(iv) For HPT rotor stage 2 disk P/N 

2383M86P02, insert the information in Table 

8 to paragraph (g)(2)(iv) of this AD. 

TABLE 8 TO PARAGRAPH (g)(2)(iv)—HPT ROTOR STAGE 2 DISK P/N 2383M86P02 

Part name Part No. Life cycles 

–2B67 

Life cycles 

–2B67B 

Life cycles 

–2B67/P 

Disk, Stage 2 ............ 2383M86P02 For part serial numbers NOT listed in GEnx–2B SB 

72–0423, latest revision.

........................ ........................ 13,300 

Disk, Stage 2 ............ 2383M86P02 For part serial numbers listed in Table 9 of GEnx–2B 

SB 72–0423, latest revision.

........................ ........................ 6,900 

Disk, Stage 2 ............ 2383M86P02 For part serial numbers listed in Table 10 of GEnx–2B 

SB 72–0423, latest revision.

........................ ........................ 10,400 

Disk, Stage 2 ............ 2383M86P02 For part serial numbers listed in Table 11 of GEnx–2B 

SB 72–0423, latest revision.

........................ ........................ 3,800 

(3) After performing the actions required 

by paragraphs (g)(1) and (2) of this AD, 

except as provided in paragraph (h) of this 

AD, no alternative life limits may be 

approved for the affected parts. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO Branch, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the certification office, 

send it to the attention of the person 

identified in paragraph (i)(1) of this AD and 

email to: ANE-AD-AMOC@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(i) Related Information 

(1) For more information about this AD, 

contact Alexei Marqueen, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: (781) 

238–7178; email: Alexei.T.Marqueen@

faa.gov. 

(2) For service information identified in 

this AD, contact General Electric Company, 

1 Neumann Way, Cincinnati, OH 45215; 

phone: (513) 552–3272; email: 

aviation.fleetsupport@ae.ge.com; website: 

https://www.ge.com. You may view this 

referenced service information at the FAA, 

Airworthiness Products Section, Operational 

Safety Branch, 1200 District Avenue, 

Burlington, MA 01803. For information on 

the availability of this material at the FAA, 

call (817) 222–5110. 

Issued on May 12, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–11354 Filed 5–31–22; 8:45 am] 

BILLING CODE 4910–13–P 


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