33494 Federal Register / Vol. 86, No. 120 / Friday, June 25, 2021 / Rules and Regulations 

AMS is committed to complying with 

the E-Government Act, to promote the 

use of the internet and other 

information technologies to provide 

increased opportunities for citizen 

access to Government information and 

services, and for other purposes. 

Analysis of Comments 

An interim final rule was published 

in the Federal Register on February 24, 

2021, providing a 60-day comment 

period that ended April 26, 2021. This 

rule will adopt most of the changes in 

the interim final rule. One comment was 

received requesting a change to section 

1206.34 Procedures, concerning what 

constitutes a quorum at a Board 

meeting. Section 1206.34 was changed 

due to the reduction of the Board from 

21 to 18, a decrease in quorum 

requirements was necessary, and 

therefore, changed from 11 to at least 10 

of the 18 Board members are present. 

The commenter stated that this is 

problematic when the Board is not at 

full capacity and recommends a quorum 

at Board meetings be when at least one 

more than half of the voting members 

are present. USDA believes that this 

comment has merit and is revising 

section 1206.34 Procedures to specify 

that a quorum at a Board meeting exists 

when at least one more than half of the 

voting members are present. 

In addition, USDA made a correction 

to section 1206.43 Exemptions to clarify 

a change that was made inadvertently 

exempting domestic first handlers when 

the intent was to simply remove frozen 

mangos as a covered commodity. 

Therefore, the section has been 

corrected to exempt first handlers or 

importers of less than 500,000 pounds 

of mangos per calendar year, and 

domestically exported mangos. 

After consideration of all relevant 

matters presented, including comments, 

the referendum vote and other available 

information, it is hereby found that 

finalizing the interim final rule, with the 

changes below, as published in the 

Federal Register [86 FR 11094] on 

February 24, 2021, will tend to 

effectuate the purposes of the 1996 Act. 

List of Subjects in 7 CFR Part 1206 

Administrative practice and 

procedure, Advertising, Consumer 

information, Marketing agreements, 

Mango promotion, Reporting and 

recording requirements. 

Accordingly, the interim final rule 

amending 7 CFR part 1206, which was 

published in the February 24, 2021, 

Federal Register [86 FR 11094], is 

adopted as final with the following 

changes: 

PART 1206—MANGO RESEARCH, 

PROMOTION, AND INFORMATION 

ORDER 

■ 1. The authority citation for 7 CFR 

part 1206 continues to read as follows: 

Authority: 7 U.S.C. 7411–7425 and 7 

U.S.C. 7401. 

■ 2. In § 1206.34, revise paragraph (a) to 

read as follows: 

§ 1206.34 Procedure. 

(a) At a Board meeting, it will be 

considered a quorum when at least one 

more than half of the voting members 

are present. 

* * * * * 

■ 3. In § 1206.43, revise paragraph (a) to 

read as follows: 

§ 1206.43 Exemptions. 

(a) Any first handler or importer of 

less than 500,000 pounds of mangos per 

calendar year may claim an exemption 

from the assessments required under 

§ 1206.42. Mangos produced 

domestically and exported from the 

United States may annually claim an 

exemption from the assessments 

required under § 1206.42. 

* * * * * 

Erin Morris, 

Associate Administrator, Agricultural 

Marketing Service. 

[FR Doc. 2021–13317 Filed 6–24–21; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0850; Project 

Identifier AD–2020–00288–E; Amendment 

39–21569; AD 2021–11–07] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

General Electric Company (GE) GEnx– 

1B64, 1B64/P1, –1B64/P2, –1B67, 

–1B67/P1, –1B67/P2, –1B70, –1B70/75/ 

P1, –1B70/75/P2, –1B70/P1, –1B70/P2, 

–1B70C/P1, –1B70C/P2, –1B74/75/P1, 

–1B74/75/P2, –1B76/P2, –1B76A/P2, 

–2B67, –2B67/P, and –2B67B model 

turbofan engines. This AD was 

prompted by a finding during an 

inspection by the manufacturer that two 

stages 6–10 compressor rotor spools in 

the high-pressure compressor (HPC) 

assembly were damaged at similar 

locations. Additionally, the 

manufacturer reported that certain 

stages 6–10 compressor rotor spool webs 

did not undergo a required fluorescent 

penetrant inspection (FPI) during 

production. This AD requires inspection 

of the stages 6–10 compressor rotor 

spool and, depending on the results of 

the inspection, replacement of the stages 

6–10 compressor rotor spool. The FAA 

is issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective July 30, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 30, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

General Electric Company, 1 Neumann 

Way, Cincinnati, OH 45215; phone: 

(513) 552–3272; email: 

aviation.fleetsupport@ae.ge.com; 

website: 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 (781) 238– 

7759. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0850. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0850; or in person at Docket 

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

Monday through Friday, except Federal 

holidays. The AD docket contains this 

final rule, any comments received, and 

other information. The address for 

Docket Operations is U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Mehdi Lamnyi, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7743; fax: (781) 238– 

7199; email: Mehdi.Lamnyi@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain GE GEnx–1B and 

GEnx–2B model turbofan engines. The 


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NPRM published in the Federal 

Register on September 24, 2020 (85 FR 

60103). The NPRM was prompted by a 

report from the manufacturer that an 

inspection had found two stages 6–10 

compressor rotor spools in the HPC 

assembly damaged at similar locations 

on the webs. The subsequent 

investigation determined that tool marks 

were created during the manufacturing 

process. In addition, the manufacturer 

also reported that certain stages 6–10 

compressor rotor spool webs did not 

undergo a required FPI during 

production. 

In the NPRM, the FAA proposed to 

require inspection of the stages 6–10 

compressor rotor spool. Operators of 

certain affected GEnx–1B or GEnx–2B 

model turbofan engines have already 

completed acceptable inspections of the 

aft web of stage 6, stage 7, and stage 8 

of the stages 6–10 compressor rotor 

spool. The FAA proposed to require 

operators of those affected engines to 

complete the inspection of the stages 6– 

10 compressor rotor spool no later than 

the next engine shop visit. The FAA 

proposed to require all other remaining 

affected GEnx–1B and GEnx–2B model 

turbofan engines to complete this 

inspection by the next engine shop visit, 

before the stages 6–10 compressor rotor 

spools accumulate 6,500 cycles since 

new, or before further flight if 6,500 

cycles since new has already been 

accumulated as of the effective date of 

this AD. Depending on the results of the 

inspection, the FAA proposed to require 

replacement of the stages 6–10 

compressor rotor spool with a part 

eligible for installation. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

seven commenters. The commenters 

were American Airlines (American), GE 

Aviation, Japan Airlines, Nippon Cargo 

Airlines (NCA), the Air Line Pilots 

Association, International, United 

Airlines Engineering, and Boeing 

Commercial Airplanes. Three 

commenters supported the proposed 

rule without change. One commenter 

requested that the FAA add a term to 

the Definitions paragraph of the 

proposed rule, and use the latest version 

of the service information. Three 

commenters requested certain 

clarifications or changes to the Required 

Actions and Previous Credit sections. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Clarify Rejectable 

Indication 

GE Aviation requested that the FAA 

define the term ‘‘rejectable indication’’ 

to avoid confusion in the event an 

indication is found during inspection. 

GE Aviation requested that the FAA 

define rejectable indication as an 

indication that does not meet the 

serviceable or repairable limits defined 

in the special procedure referenced in 

GE GEnx–1B Service Bulletin (SB) 72– 

0472 R02, dated November 5, 2020 

(GEnx–1B SB 72–0472) and GE GEnx– 

2B SB 72–0415 R02, dated November 5, 

2020 (GEnx–2B SB 72–0415). 

The FAA agrees to define a ‘‘rejectable 

indication’’ as used in paragraph (g)(2) 

of the Required Actions section of this 

AD and added the definition in 

paragraph (h), Definitions, of this AD. 

Request To Clarify Acceptance of 

Reworked Parts 

American requested that the FAA 

clarify paragraph (g)(2) and paragraph 

(i), Credit for Previous Actions, 

regarding installation of parts that 

initially failed inspection with a 

rejectable indication but were later 

reworked and found acceptable. 

American stated that GE has been 

accepting parts that were reworked 

using GE Subtask 72–00–00–210–012 in 

the GEnx–1B EM 72–00–00, Special 

Procedure 023, in accordance with 

approved GE Departure 

Recommendations. 

The FAA disagrees. Paragraph (g)(2) 

of this AD requires that if during an 

inspection, a stages 6–10 compressor 

rotor spool is found to have a rejectable 

indication, as defined in paragraph (h) 

of this AD, then the stages 6–10 

compressor rotor spool must be 

removed from service. If the stages 6–10 

compressor rotor spool is subsequently 

repaired or reworked, operators would 

need to submit an alternative methods 

of compliance (AMOC) request to the 

FAA to allow use of the repaired or 

reworked stages 6–10 compressor rotor 

spool. 

Request To Revise References to 

Service Bulletin 

GE Aviation requested that the FAA 

update the specified service information 

by referencing Revision 2 of GE GEnx– 

1B SB 72–0472 and GE GEnx–2B SB 72– 

0415. GE noted that Revision 2 of these 

SBs had not been issued at the time of 

publication of the NPRM. 

The FAA agrees and has updated this 

AD to reference GEnx–1B SB 72–0472 

R02 and GEnx–2B SB 72–0415 R02, 

both dated November 5, 2020. This 

change to this AD imposes no additional 

burden on operators. 

Request To Revise Previous Credit 

Japan Airlines requested that the FAA 

grant credit for the borescope inspection 

(BSI) or eddy current inspection (ECI) 

required by paragraph (g)(1) of this AD 

if inspections were previously 

performed in accordance with GE 

GEnx–1B SB 72–0472 R01, dated July 

24, 2020. 

The FAA agrees and has updated 

paragraph (i), Credit for Previous 

Actions, to allow credit for inspections 

performed using GE GEnx–1B SB 72– 

0472 R01, dated July 24, 2020 or GE 

GEnx–2B SB 72–0415 R01, dated July 

24, 2020, as applicable. 

Request for Reference Date 

Clarification 

NCA requested that the FAA clarify 

the meaning of ‘‘previously undergone’’ 

in paragraph (g)(1)(ii) of this AD. NCA 

commented that one of its engines 

underwent an inspection during an 

engine shop visit using GEnx–2B SB 72– 

0385 R02, dated July 29, 2019 and GE 

GEnx–2B SB 72–0398 R00, dated 

October 30, 2019, before the effective 

date of this AD but after publication of 

GEnx–2B SB 72–0415 R01. NCA noted 

that the reference to ‘‘previously 

undergone’’ means that it has been 

implemented in accordance with SB in 

the past without any specific timeframe, 

so it is not clear if the NCA’s engine can 

apply the no cycles since new (CSN) 

limit. 

The FAA clarified paragraph (g)(1)(i) 

and (ii) of this AD by removing the 

phrase ‘‘previously undergone’’ and 

referring instead to engines that have 

undergone inspections ‘‘before the 

effective date of this AD.’’ 

Change to Compliance Time 

The FAA updated Table 1 to 

paragraph (g)(1) of this AD by allowing 

operators 100 flight cycles to perform 

the inspections required by paragraph 

(g)(1) of this AD when an engine has a 

stages 6–10 compressor rotor spool with 

6,400 CSN or greater as of the effective 

date of this AD. This change allows 

operators a grace period to complete the 

required inspections without 

unnecessary grounding of airplanes and 

still meets the safety intent of this AD. 

Conclusion 

The FAA reviewed the relevant data, 

considered any comments received, and 

determined that air safety requires 

adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. Except for minor editorial 

changes and any other changes 

described previously, this AD is 

adopted as proposed in the NPRM. 


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None of the changes will increase the 

economic burden on any operator. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed GE GEnx–1B 

Service Bulletin (SB) 72–0472 R02, 

dated November 5, 2020 (GEnx–1B SB 

72–0472) and GE GEnx–2B SB 72–0415 

R02, dated November 5, 2020 (GEnx–2B 

SB 72–0415). 

GEnx–1B SB 72–0472 describes 

procedures for performing a BSI or an 

ECI of stage 6, stage 7, and stage 8 webs, 

web transitions, and bore faces of the 

stages 6–10 compressor rotor spool for 

GEnx-1B model turbofan engines. 

GEnx–1B SB 72–0472 also provides the 

affected part and serial numbers of the 

stages 6–10 compressor rotor spools 

installed on GEnx–1B model turbofan 

engines. 

GEnx–2B SB 72–0415 describes 

procedures for performing a BSI or an 

ECI of stage 6, stage 7, and stage 8 webs, 

web transitions, and bore faces of the 

stages 6–10 compressor rotor spool for 

GEnx-2B model turbofan engines. 

GEnx–2B SB 72–0415 also provides the 

affected part and serial numbers of the 

stages 6–10 compressor rotor spools 

installed on GEnx-2B model turbofan 

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. 

Other Related Service Information 

The FAA also reviewed Subtask 72– 

31–45–160–002 of TASK 72–31–45– 

200–807 in GE GEnx–1B Engine Manual 

05–21–00, Life Limits 001 Mandatory 

Inspections, Rev. 31 dated, January 31, 

2020; and Subtask 72–31–45–160–002 

of TASK 72–31–45–200–801 in GE 

GEnx–2B Engine Manual 05–21–00, Life 

Limits 001 Mandatory Inspections, Rev. 

24 dated, January 31, 2020. The 

Subtasks provide guidance on 

performing the ECI on the stages 6–10 

compressor rotor spool on GE GEnx–1B 

and GEnx–2B model turbofan engines. 

The FAA also reviewed the following 

GE SBs: GEnx–1B SB 72–0448 R00, 

dated July 29, 2019 (GEnx–1B SB 72– 

0448); GEnx–1B SB 72–0460 R00, dated 

October 30, 2019 (GEnx–1B SB 72– 

0460); GEnx–2B SB 72–0385 R02, dated 

July 29, 2019 (GEnx–2B SB 72–0385); 

and GEnx–2B SB 72–0398 R00, dated 

October 30, 2019 (GEnx–2B SB 72– 

0398). 

GEnx–1B SB 72–0448 describes 

procedures for performing a BSI or an 

ECI of the stage 8 aft web of the HPC 

stages 6–10 rotor spool for GEnx–1B 

model turbofan engines. GEnx–1B SB 

72–0460 describes procedures for 

performing a BSI or an ECI of the stage 

6 and stage 7 aft web of the HPC stages 

6–10 rotor spool for GEnx–1B model 

turbofan engines. 

GEnx–2B SB 72–0385 describes 

procedures for performing a BSI or an 

ECI of the stage 8 aft web of the HPC 

stages 6–10 spool for GEnx–2B model 

turbofan engines. GEnx–2B SB 72–0398 

describes procedures for performing a 

BSI or an ECI of the stage 6 and stage 

7 aft web of the HPC stages 6–10 rotor 

spool for GEnx–2B model turbofan 

engines. 

Costs of Compliance 

The FAA estimates that this AD 

affects 268 engines installed on 

airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

BSI of GEnx–1B stage 6, stage 7, and stage 

8 webs, web transitions and bore faces of 

the stages 6–10 compressor rotor spool.

6 work-hours × $85 per hour = $510 ............. $0 $510 $89,760 

BSI of GEnx–2B stage 6, stage 7, and stage 

8 webs, web transitions and bore faces of 

the stages 6–10 compressor rotor spool.

6 work-hours × $85 per hour = $510 ............. 0 510 46,920 

The FAA estimates the following 

costs to do any necessary replacements 

that would be required based on the 

results of the inspection. The agency has 

no way of determining the number of 

aircraft that might need these 

replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace the stages 6–10 compressor rotor spool ....... 64 work-hours × $85 per hour = $5,440 ...................... $1,018,600 $1,024,040 

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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 


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(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2021–11–07 General Electric Company: 

Amendment 39–21569; Docket No. 

FAA–2020–0850; Project Identifier AD– 

2020–00288–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 30, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to: 

(1) General Electric Company (GE) GEnx– 

1B64, GEnx–1B64/P1, GEnx–1B64/P2, GEnx– 

1B67, GEnx–1B67/P1, GEnx–1B67/P2, GEnx– 

1B70, GEnx–1B70/75/P1, GEnx–1B70/75/P2, 

GEnx–1B70/P1, GEnx–1B70/P2, GEnx– 

1B70C/P1, GEnx–1B70C/P2, GEnx–1B74/75/ 

P1, GEnx–1B74/75/P2, GEnx–1B76/P2, 

GEnx–1B76A/P2 model turbofan engines 

with stages 6–10 compressor rotor spools in 

the high-pressure compressor (HPC) 

assembly with the following part numbers 

(P/N) installed: 

(i) P/N 2357M30G01, P/N 2357M30G02, 

P/N 2439M35G01, P/N 2439M35G02, or P/N 

2445M40G02, all serial numbers (S/Ns); 

(ii) P/N 2610M90G01 with the S/Ns listed 

in paragraph 4., APPENDIX—A, Table 1 of 

the GE GEnx–1B Service Bulletin (SB) 72– 

0472 R02, dated November 5, 2020 (GEnx–1B 

SB 72–0472); and 

(iii) P/N 2628M56G01 with the S/Ns listed 

in paragraph 4., APPENDIX—A, Table 2 or 

Table 3 of GEnx–1B SB 72–0472. 

(2) GEnx–2B67, GEnx–2B67/P, GEnx– 

2B67B model turbofan engines with the 

following stages 6–10 compressor rotor 

spools P/Ns installed: 

(i) P/N 2357M30G02, P/N 2439M35G02, or 

P/N 2445M40G02, all S/Ns; 

(ii) P/N 2340M36G01 with S/Ns listed in 

paragraph 4., APPENDIX—A, Table 1 of GE 

GEnx–2B SB 72–0415 R02, dated November 

5, 2020 (GEnx–2B SB 72–0415); and 

(iii) P/N 2628M56G01 with S/Ns listed in 

paragraph 4., APPENDIX—A, Table 2 or 

Table 3 of GEnx–2B SB 72–0415. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section. 

(e) Unsafe Condition 

This AD was prompted by a finding during 

an inspection that two stages 6–10 

compressor rotor spools were damaged at 

similar locations. In addition, the 

manufacturer reported that certain stages 6– 

10 compressor rotor spool webs did not 

undergo a required fluorescent penetrant 

inspection (FPI) during production. The FAA 

is issuing this AD to prevent failure of the 

compressor rotor spool. The unsafe 

condition, if not addressed, could result in 

uncontained release of debris, 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 and GEnx–2B 

model turbofan engines, before exceeding the 

compliance time in Table 1 to paragraph 

(g)(1) of this AD, perform a borescope 

inspection (BSI) or eddy current inspection 

(ECI) of the stage 6, stage 7, and stage 8 webs, 

web transitions, and bore faces of the stages 

6–10 compressor rotor spool in accordance 

with the Accomplishment Instructions, 

paragraph 3, of GEnx–1B SB 72–0472 (for 

GEnx–1B models) or the Accomplishment 

Instructions, paragraph 3, of GEnx–2B SB 72– 

0415 (for GEnx–2B models). 

TABLE 1 TO PARAGRAPH (g)(1) 

Cycles Since New (CSN) accumulated on the 

stages 6–10 compressor rotor spool Compliance time 

Less than 6,400 CSN .......................................... Next engine shop visit or before the stages 6–10 compressor rotor spool accumulates 6,500 

CSN, whichever occurs first after the effective date of this AD. 

6,400 CSN or greater .......................................... Within 100 flight cycles after the effective date of this AD. 

(i) For GEnx–1B model turbofan engines, 

except those identified in paragraph 4, 

APPENDIX—A, Table 3 of SB 72–0472, if, 

before the effective date of this AD, the 

engines have undergone inspections of the aft 

web of stage 6, stage 7, and stage 8 of the 

stages 6–10 compressor rotor spool using 

both GE GEnx–1B SB 72–0448 R00, dated 

July 29, 2019, and GE GEnx–1B SB 72–0460 

R00, dated October 30, 2019, regardless of the 

CSN accumulated on the stages 6–10 

compressor rotor spool, perform the 

inspection required by paragraph (g)(1) of 

this AD no later than the next engine shop 

visit after the effective date of this AD. 

(ii) For GEnx–2B model turbofan engines, 

except those identified in paragraph 4., 

APPENDIX—A, Table 3 of SB 72–0415, if, 

before the effective date of this AD, the 

engines have undergone inspections of the aft 

web of stage 6, stage 7, and stage 8 of the 

stages 6–10 compressor rotor spool using 

both GE GEnx–2B SB 72–385 R02, dated July 

29, 2019, and GE GEnx–2B SB 72–0398 R00, 

dated October 30, 2019, regardless of the CSN 

accumulated on the stages 6–10 compressor 

rotor spool, perform the inspection required 

by paragraph (g)(1) of this AD no later than 

the next engine shop visit after the effective 

date of this AD. 

(2) For all affected GEnx–1B and GEnx–2B 

model turbofan engines, during the 

inspections required by paragraph (g)(1) of 

this AD, if a rejectable indication is found, 

before further flight, remove the stages 6–10 

compressor rotor spool from service and 

replace it with a part eligible for installation. 

(h) Definitions 

(1) For the purpose 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 that the separation of engine 

flanges solely for the purposes of 

transportation of the engine without 

subsequent engine maintenance does not 

constitute an engine shop visit. 

(2) For the purpose of this AD, a rejectable 

indication is: 

(i) A BSI indication that does not meet the 

BSI serviceable or repairable limits 

referenced in the Accomplishment 

Instructions, paragraph 3.A.(1)(a)2, of GEnx– 

1B SB 72–0472, or paragraph 3.A.(1)(a)2 of 

GEnx–2B SB 72–0415, and the affected part 

has not undergone a subsequent ECI; or 

(ii) A BSI indication that does not meet the 

BSI serviceable or repairable limits 

referenced in the Accomplishment 

Instructions, paragraph 3.A.(1)(a)2, of GEnx– 

1B SB 72–0472, or paragraph 3.A.(1)(a)2 of 

GEnx–2B SB 72–0415, and the affected part 

has undergone a subsequent ECI in which the 

indication did not meet the ECI serviceable 

or repairable limits referenced in the 


lotter on DSK11XQN23PROD with RULES1
33498 Federal Register / Vol. 86, No. 120 / Friday, June 25, 2021 / Rules and Regulations 

Accomplishment Instructions, paragraph 

3.A.(1)(b) of GEnx–1B SB 72–0472, or 

paragraph 3.A.(1)(b) of GEnx–2B SB 72–0415; 

or 

(iii) An ECI indication that does not meet 

the serviceable or repairable limits referenced 

in the Accomplishment Instructions, 

paragraph 3.A.(1)(b) of GEnx–1B SB 72–0472, 

or paragraph 3.A.(1)(b) of GEnx–2B SB 72– 

0415. 

(i) Credit for Previous Actions 

(1) For affected GEnx–1B model turbofan 

engines, you may take credit for the BSI or 

ECI required by paragraph (g)(1) of this AD, 

if you performed an ECI of the stages 6–10 

compressor rotor spool webs, web 

transitions, and bore faces before the effective 

date of this AD using Subtask 72–31–45– 

160–002 of TASK 72–31–45–200–807 in GE 

GEnx–1B Engine Manual 05–21–00, Life 

Limits 001 Mandatory Inspections, Rev. 31, 

dated January 31, 2020, or earlier, and no 

rejectable indications were found. 

(2) For affected GEnx–2B model turbofan 

engines, you may take credit for the BSI or 

ECI required by paragraph (g)(1) of this AD, 

if you performed and ECI of the stages 6–10 

compressor rotor spool webs, web 

transitions, and bore faces before the effective 

date of this AD using Subtask 72–31–45– 

160–002 of TASK 72–31–45–200–801 in GE 

GEnx–2B Engine Manual 05–21–00, Life 

Limits 001 Mandatory Inspections, Rev. 24, 

dated January 31, 2020, or earlier, and no 

rejectable indications were found. 

(3) For affected GEnx–1B model turbofan 

engines, you may take credit for the BSI or 

ECI required by paragraph (g)(1) of this AD, 

if you performed that inspection before the 

effective date of this AD using GE GEnx–1B 

Service Bulletin (SB) 72–0472 R00, dated 

April 24, 2020, or GE GEnx–1B SB 72–0472 

R01, dated July 24, 2020, and no rejectable 

indications were found. 

(4) For affected GEnx–2B model turbofan 

engines, you may take credit for the BSI or 

ECI required by paragraph (g)(1) of this AD, 

if you performed that inspection before the 

effective date of this AD using GE GEnx–2B 

SB 72–0415 R00, dated April 24, 2020, or GE 

GEnx–2B SB 72–0415 R01, dated July 24, 

2020, and no rejectable indications were 

found. 

(j) 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 Related Information. You may 

email your request 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. 

(k) Related Information 

For more information about this AD, 

contact Mehdi Lamnyi, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

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

238–7743; fax: (781) 238–7199; email: 

Mehdi.Lamnyi@faa.gov. 

(l) 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) GE GEnx–1B Service Bulletin (SB) 72– 

0472 R02, dated November 5, 2020. 

(ii) GE GEnx–2B SB 72–0415 R02, dated 

November 5, 2020. 

(3) For General Electric Company 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: www.ge.com. 

(4) You may view this service information 

at FAA, Airworthiness Products Section, 

Operational Safety Branch, 1200 District 

Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call (781) 238–7759. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

email: fedreg.legal@nara.gov, or go to: 

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

ibr-locations.html. 

Issued on May 19, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–13424 Filed 6–24–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0512; Project 

Identifier MCAI–2020–01621–R; Amendment 

39–21627; AD 2021–13–21] 

RIN 2120–AA64 

Airworthiness Directives; Leonardo 

S.p.a. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Leonardo S.p.a. Model AB139, AW139, 

and AW189 helicopters. This AD was 

prompted by a report of the in-flight 

failure of one of the three stainless steel 

external rings bonded to the main rotor 

swashplate boot. This AD requires 

repetitive inspections of these stainless 

steel external rings for corrosion, cracks, 

and the condition of the adhesive that 

bonds the rings to the main rotor 

swashplate boot, and corrective action if 

necessary, as specified in a European 

Union Aviation Safety Agency (EASA) 

AD, which is incorporated by reference. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD becomes effective July 

12, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 12, 2021. 

The FAA must receive comments on 

this AD by August 9, 2021. 

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 EASA material incorporated by 

reference (IBR) in this AD, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 

8999 000; email ADs@easa.europa.eu; 

internet www.easa.europa.eu EASA, 

Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 

8999 000; email ADs@easa.europa.eu; 

internet www.easa.europa.eu. You may 

find this IBR material on the EASA 

website at https://ad.easa.europa.eu. 

You may view the EASA material at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. For information on the 

availability of the EASA material at the 

FAA, call (817) 222–5110. The EASA 

material is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0512. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0512; or in person at Docket 


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