8178 Federal Register / Vol. 87, No. 30 / Monday, February 14, 2022 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0831; Project 

Identifier AD–2021–00712–E; Amendment 

39–21933; AD 2022–03–16] 

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– 

1B and GEnx–2B model turbofan 

engines. This AD was prompted by the 

manufacturer’s report of two findings of 

sheared compressor discharge pressure 

(CDP) bolts during engine shop visits. 

This AD requires initial and repetitive 

inspections of the CDP bolted joint and, 

depending on the findings, a piece part 

inspection of the stages 6–10 

compressor rotor spool, CDP seal, and 

high-pressure turbine (HPT) rotor stage 

1 disk. As a terminating action, this AD 

requires operators to reassemble the 

CDP bolted joint using a specific torque 

wrench. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective March 21, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 21, 2022. 

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 (817) 222– 

5110. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0831. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0831; 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: 

Alexei Marqueen, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7178; fax: (781) 238– 

7199; email: Alexei.T.Marqueen@

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 

NPRM published in the Federal 

Register on October 28, 2021 (86 FR 

59667). The NPRM was prompted by a 

report from the manufacturer of two 

findings of sheared CDP bolts at engine 

shop visits during disassembly of the 

CDP bolted joint on GEnx–1B70/75/P2 

and GEnx–2B67/P model turbofan 

engines. Subsequent investigation by 

the manufacturer determined that the 

fracture and liberation of the CDP bolts 

was caused by the inadvertent overtorque condition of the bolts during 

assembly and reassembly with a 

11C4525P01 torque fixture or during 

assembly with a 11C4629P01 torque 

wrench. In one finding, the fractured 

CDP bolt caused damage to the stages 6– 

10 compressor rotor spool, CDP seal, 

and HPT rotor stage 1 disk. In the 

NPRM, the FAA proposed to require 

initial and repetitive inspections of the 

CDP bolted joint and, depending on the 

findings, a piece part inspection of the 

stages 6–10 compressor rotor spool, CDP 

seal, and HPT rotor stage 1 disk. As a 

terminating action, the NPRM also 

proposed to require operators to 

reassemble the CDP bolted joint using a 

11C4888P01 torque wrench. 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 

four commenters. The commenters were 

American Airlines (American), The 

Boeing Company (Boeing), GE Aviation, 

and United Airlines Engineering (UAL 

Engineering). The following presents the 

comments received on the NPRM and 

the FAA’s response to each comment. 

Request To Add Engine Serial Numbers 

to Applicability Paragraph 

American requested that the FAA 

clarify paragraph (c), Applicability, by 

adding the affected engine serial 

numbers (S/Ns). American explained 

that operators do not have visibility to 

the engines that were assembled or 

reassembled by GE with the 

11C4525P01 torque fixture, or engines 

that were assembled with the 

11C4629P01 torque wrench. American 

noted that due to this lack of visibility, 

operators will need to rely on GE to 

provide the affected engine S/Ns, either 

in GEnx–1B Service Bulletin (SB) 72– 

0495 R00, dated May 11, 2021 (GEnx– 

1B SB 72–0495) or in response to an 

inquiry, which would place an 

excessive burden on the operators. 

The FAA disagrees with adding 

engine S/Ns to the Applicability 

paragraph of this AD. According to GE, 

each maintenance, repair and overhaul 

(MRO) shop will have a record of what 

date the new 11C4888P01 torque 

wrench was implemented for use, and 

any CDP bolted joint reassembled at an 

engine shop visit prior to that 

implementation date would have used 

the prior 11C4525P01 torque fixture. 

Thus, for engines that have had an 

engine shop visit, each operator will be 

able to determine if their engine is 

affected based on the date of the last 

engine shop visit and the date that the 

particular MRO shop implemented the 

new tool. For engines that have not had 

an engine shop visit, Paragraph 1.A, 

Table A of GEnx–1B SB 72–0495 and 

Paragraph 1.A, Table A of GE GEnx–2B 

SB 72–0433 R00, dated May 11, 2021 

define which engine S/Ns are affected 

based on production records. 

Request To Add Clarifying Language to 

Required Actions 

GE Aviation requested that the FAA 

update the language in paragraph (g)(2) 

of this AD to incorporate a reference to 

the terminating action contained in 

paragraph (h) of this AD. GE supported 

its request for change by explaining the 

additional reference will ensure clear 

understanding of the requirements. 

The FAA disagrees with updating 

paragraph (g)(2) of this AD to 

incorporate a reference to the 

terminating action in paragraph (h) of 

this AD. Referencing paragraph (h) 

within paragraph (g)(2) is unnecessary. 

Request To Add Language Requiring 

Accomplishment of Terminating Action 

UAL Engineering requested that the 

FAA incorporate the terminating action 

in paragraph (h) of this AD as a 

requirement in paragraph (g)(3) of this 


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Federal Register / Vol. 87, No. 30 / Monday, February 14, 2022 / Rules and Regulations 8179 

AD. UAL Engineering explained that 

requiring the terminating action within 

paragraph (g)(3) of this AD would 

eliminate any ambiguity involving the 

reassembly of the CDP bolted joint, 

which could potentially lead to the use 

of a non-conforming tool and additional 

repetitive inspections. 

The FAA disagrees with revising the 

required action as proposed by UAL 

Engineering. MRO shops no longer use 

the 11C4525P01 torque fixture. All MRO 

shops have implemented the use of the 

updated 11C4888P01 torque wrench. 

Therefore, if a piece part inspection is 

required pursuant to paragraph (g)(3) of 

this AD, the CDP bolted joint will be 

reassembled with the updated 

11C4888P01 torque wrench. The nonconforming tool will not be used, and 

therefore will not drive any additional 

repetitive inspections after a reassembly 

is performed following a piece part 

inspection. 

Support for the AD 

Boeing expressed support for the AD 

as written. 

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, this AD is adopted as proposed 

in the NPRM. 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 SB 

72–0495 R00, dated May 11, 2021 (GE 

GEnx–1B SB 72–0495) and GE GEnx–2B 

SB 72–0433 R00, dated May 11, 2021 

(GEnx–2B SB 72–0433). GEnx–1B SB 

72–0495 describes procedures for the 

inspection of the CDP bolted joint 

components on GEnx–1B model 

turbofan engines. GEnx–2B SB 72–0433 

describes procedures for the inspection 

of the CDP bolted joint components 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. 

Costs of Compliance 

The FAA estimates that this AD 

affects 320 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 

Inspection of CDP bolted joint ........................ 1 work-hour × $85 per hour = $85 ................. $0 $85 $27,200 

The FAA estimates the following 

costs to do any necessary additional 

inspections that would be required 

based on the results of the proposed 

inspection. The agency has no way of 

determining the number of aircraft that 

might need these inspections. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Piece part inspection of stages 6–10 compressor 

rotor spool.

56 work-hours × $85 per hour = $4,760 ...................... $0 $4,760 

Piece part inspection of CPD seal ............................... 22 work-hours × $85 per hour = $1,870 ...................... 0 1,870 

Piece part inspection of HPT rotor stage 1 disk .......... 59 work-hours × $85 per hour = $5,015 ...................... 0 5,015 

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: 

(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. 


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8180 Federal Register / Vol. 87, No. 30 / Monday, February 14, 2022 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2022–03–16 General Electric Company: 

Amendment 39–21933; Docket No. 

FAA–2021–0831; Project Identifier AD– 

2021–00712–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 21, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to 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, 

GEnx–2B67, GEnx–2B67B, and GEnx–2B67/P 

model turbofan engines with a compressor 

discharge pressure (CDP) bolted joint 

assembled or reassembled with the 

11C4525P01 torque fixture or assembled with 

the 11C4629P01 torque wrench. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by a report from 

the manufacturer of two findings of sheared 

CDP bolts during engine shop visits. The 

FAA is issuing this AD to prevent fracture of 

the CDP bolt. The unsafe condition, if not 

addressed, could result in 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) At the next engine shop visit after the 

effective date of this AD, perform an 

inspection of the CDP bolted joint for 

fractured or missing material using the 

Accomplishment Instructions, paragraph 

3.A.(2) of GE GEnx–1B Service Bulletin (SB) 

72–0495 R00, dated May 11, 2021 (GEnx–1B 

SB 72–0495) (for GEnx–1B models) or 

Accomplishment Instructions, paragraph 

3.A.(2) of GE GEnx–2B SB 72–0433 R00, 

dated May 11, 2021, (GEnx–2B SB 72–0433) 

(for GEnx–2B models). 

(2) Repeat the inspection required by 

paragraph (g)(1) of this AD at every engine 

shop visit. 

(3) If a fractured or missing bolt or nut is 

found during any inspection required by 

paragraph (g)(1) or (2) of this AD, before 

further flight, perform piece part inspections 

of the stages 6–10 compressor rotor spool, 

CDP seal, and high-pressure turbine rotor 

stage 1 disk in accordance with the 

Instructions for Continued Airworthiness. 

(h) Terminating Action 

As terminating action to the repetitive 

inspections required by paragraph (g)(2) of 

this AD, reassemble the CDP bolted joint 

using the 11C4888P01 torque wrench, in 

accordance with the Accomplishment 

Instructions, paragraph 3.B.(1) of GEnx–1B 

SB 72–0495 (for GEnx–1B models) or the 

Accomplishment Instructions, paragraph 

3.B.(1) of GEnx–2B SB 72–0433 (for GEnx–2B 

models). 

(i) Definition 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving a module 

exposure in which the mid fan shaft removal 

exposes the CDP bolted joint. 

(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 ECO Branch, send it to 

the attention of the person identified in 

paragraph (k) of this AD. 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 Alexei Marqueen, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

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

238–7178; fax: (781) 238–7199; email: 

Alexei.T.Marqueen@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) General Electric Company (GE) GEnx– 

1B Service Bulletin (SB) 72–0495 R00, dated 

May 11, 2021. 

(ii) GE GEnx–2B SB 72–0433 R00, dated 

May 11, 2021. 

(3) For GE 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 (817) 222–5110. 

(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: fr.inspection@nara.gov, or go to: 

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

ibr-locations.html. 

Issued on January 25, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–03040 Filed 2–11–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Bureau of Industry and Security 

15 CFR Part 744 

[Docket No. 220203–0039] 

RIN 0694–AI70 

Addition of Certain Entities to the 

Entity List 

AGENCY: Bureau of Industry and 

Security, Commerce. 

ACTION: Final rule. 

SUMMARY: This final rule amends the 

Export Administration Regulations 

(EAR) by adding seven entities under 

seven entries to the Entity List. These 

seven entities have been determined by 

the U.S. Government to be acting 

contrary to the foreign policy or national 

security interests of the United States 

and will be listed on the Entity List 

under the destinations of the People’s 

Republic of China (China), Pakistan, and 

the United Arab Emirates (UAE). This 

final rule also modifies four existing 

entries on the Entity List under the 

destination of China. 

DATES: This rule is effective February 

14, 2022. 

FOR FURTHER INFORMATION CONTACT: 

Chair, End-User Review Committee, 

Office of the Assistant Secretary for 

Export Administration, Bureau of 

Industry and Security, Department of 

Commerce, Phone: (202) 482–5991, 

Email: ERC@bis.doc.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

Entity List 

The Entity List (supplement no. 4 to 

part 744 of the EAR) identifies entities 

for which there is reasonable cause to 

believe, based on specific and 

articulable facts, that the entities have 

been involved, are involved, or pose a 

significant risk of being or becoming 

involved in activities contrary to the 

national security or foreign policy 

interests of the United States. The EAR 

(15 CFR parts 730–774) impose 

additional license requirements on, and 


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