Federal Register / Vol. 89, No. 15 / Tuesday, January 23, 2024 / Rules and Regulations 4181 

(ii) The sensing element has been tested 

and found to be serviceable as specified in 

paragraph (i) of this AD; and the sensing 

element has been marked on one face of one 

connector hex nut with one green mark, as 

specified in Figure 11 of Bombardier Service 

Bulletin 100–36–10, dated December 23, 

2022, or Bombardier Service Bulletin 350– 

36–003, dated December 23, 2022, as 

applicable (the figure is representative for all 

sensing elements). 

(2) For purposes of this AD, a serviceable 

part is a sensing element that is not an 

affected part. 

(h) Revision of the Existing Airplane Flight 

Manual (AFM) 

For airplane serial numbers 20001 through 

20457 inclusive and 20501 through 20906 

inclusive: Within 30 days after the effective 

date of this AD, revise the existing AFM to 

include the information specified in 

paragraphs (h)(1) and (2) of this AD, as 

applicable. 

(1) For airplane serial numbers 20001 

through 20457 inclusive: Section 05–42, Air 

Conditioning & Pressurization, Non-Normal 

Procedures Section, Bombardier Challenger 

300 AFM (Imperial Version), Publication No. 

CSP 100–1, Revision 71, dated November 9, 

2022. 

Note 1 to Paragraph (h)(1): For obtaining 

the procedures for Bombardier Challenger 

300 AFM (Imperial Version), Publication No. 

CSP 100–1, use Document Identification No. 

CH 300 AFM–I. 

(2) For airplane serial numbers 20501 

through 20906 inclusive: Section 05–42, 

Airconditioning & Pressurization, NonNormal Procedures Section, Bombardier 

Challenger 350 AFM, Publication No. CH 350 

AFM, Revision 37, dated November 9, 2022. 

Note 2 to Paragraph (h)(2): For obtaining 

the procedures for Bombardier Challenger 

350 AFM, Publication No. CH 350 AFM, use 

Document Identification No. CH 350 AFM. 

(i) Testing of Overheat Detection Sensing 

Elements 

For airplane serial numbers 20001 through 

20457 inclusive and 20501 through 20906 

inclusive: Within 7,500 flight cycles or 96 

months, whichever occurs first, from the 

effective date of this AD, test the overheat 

detection sensing elements to determine if 

they are serviceable, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 100–36–10, dated December 

23, 2022; or Bombardier Service Bulletin 

350–36–003, dated December 23, 2022, as 

applicable. 

(1) For each sensing element that is 

serviceable, before further flight, mark the 

sensing element with a witness mark in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

100–36–10, dated December 23, 2022; or 

Bombardier Service Bulletin 350–36–003, 

dated December 23, 2022; as applicable. 

(2) For each sensing element that is not 

serviceable, before further flight, replace the 

sensing element with a serviceable part in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

100–36–10, dated December 23, 2022; or 

Bombardier Service Bulletin 350–36–003, 

dated December 23, 2022; as applicable. 

(j) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an affected part on any 

airplane. 

(k) No Reporting Requirement 

Although Bombardier Service Bulletin 

100–36–10, dated December 23, 2022; and 

Bombardier Service Bulletin 350–36–003, 

dated December 23, 2022; specify to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

(l) Additional AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Validation 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 

responsible Flight Standards Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, mail it to the address identified in 

paragraph (m)(2) of this AD. Information may 

be emailed to: 9-AVS-NYACO-COS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the responsible Flight Standards Office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, International Validation 

Branch, FAA; or Transport Canada; or 

Bombardier, Inc.’s Transport Canada Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(m) Additional Information 

(1) Refer to Transport Canada AD CF– 

2023–09, dated February 14, 2023, for related 

information. This Transport Canada AD may 

be found in the AD docket at regulations.gov 

under Docket No. FAA–2023–1890. 

(2) For more information about this AD, 

contact Steven Dzierzynski, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 516– 

228–7300; email 9-avs-nyaco-cos@faa.gov. 

(n) 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 this AD specifies otherwise. 

(i) Bombardier Service Bulletin 100–36–10, 

dated December 23, 2022. 

(ii) Bombardier Service Bulletin 350–36– 

003, dated December 23, 2022. 

(iii) Section 05–42, Air Conditioning & 

Pressurization, Non-Normal Procedures 

Section, Bombardier Challenger 300 AFM 

(Imperial Version), Publication No. CSP 100– 

1, Revision 71, dated November 9, 2022. 

Note 3 to Paragraph (n)(2)(iii): For 

obtaining the procedures for Bombardier 

Challenger 300 AFM (Imperial Version), 

Publication No. CSP 100–1, use Document 

Identification No. CH 300 AFM–I. 

(iv) Section 05–42, Air Conditioning & 

Pressurization, Non-Normal Procedures 

Section, Bombardier Challenger 350 AFM, 

Publication No. CH 350 AFM, Revision 37, 

dated November 9, 2022. 

Note 4 to Paragraph (n)(2)(iv): For 

obtaining the procedures for Bombardier 

Challenger 350 AFM, Publication No. CH 350 

AFM, use Document Identification No. CH 

350 AFM. 

(v) Liebherr Service Bulletin CFD–F1958– 

26–01, dated May 6, 2022. 

(3) For Bombardier service information 

identified in this AD, contact Bombardier 

Business Aircraft Customer Response Center, 

400 Coˆte-Vertu Road West, Dorval, Que ́bec 

H4S 1Y9, Canada; telephone 514–855–2999; 

email ac.yul@aero.bombardier.com; website 

bombardier.com. 

(4) For Liebherr-Aerospace Toulouse SAS 

service information identified in this AD, 

contact Liebherr-Aerospace Toulouse SAS, 

408, Avenue des Etats-Unis—B.P.52010, 

31016 Toulouse Cedex, France; telephone 

+33 (0)5.61.35.28.28; fax +33 

(0)5.61.35.29.29; email techpub.toulouse@

liebherr.com; website liebherr.aero. 

(5) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 216th 

Street, Des Moines, WA. For information on 

the availability of this material at the FAA, 

call 206–231–3195. 

(6) You may view this material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

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

ibr-locations, or email fr.inspection@

nara.gov. 

Issued on December 21, 2023. 

Caitlin Locke, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–01170 Filed 1–22–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1811; Project 

Identifier MCAI–2023–00146–E; Amendment 

39–22654; AD 2024–01–03] 

RIN 2120–AA64 

Airworthiness Directives; GE Aviation 

Czech s.r.o. (Type Certificate 

Previously Held by WALTER Engines 

a.s., Walter a.s., and MOTORLET a.s.) 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2023–01– 


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4182 Federal Register / Vol. 89, No. 15 / Tuesday, January 23, 2024 / Rules and Regulations 

07 for all GE Aviation Czech s.r.o. 

(GEAC) (type certificate previously held 

by WALTER Engines a.s., Walter a.s., 

and MOTORLET a.s.) Model H75–100, 

H75–200, H80, H80–100, H80–200, 

H85–100, and H85–200 engines. AD 

2023–01–07 required revising the 

airworthiness limitations section (ALS) 

of the existing engine maintenance 

manual (EMM) and the operator’s 

existing approved maintenance or 

inspection program, as applicable, to 

incorporate updated coefficients and 

recalculate the cycles accumulated on 

critical parts. Since the FAA issued AD 

2023–01–07, the manufacturer revised 

the ALS of the EMM to introduce new 

and more restrictive airworthiness 

limitations and associated thresholds 

and intervals for life-limited parts, 

which prompted this AD action. This 

AD requires revising the ALS of the 

existing EMM and the operator’s 

existing approved engine maintenance 

or inspection program, as applicable, to 

incorporate new and more restrictive 

instructions and associated thresholds 

and intervals for life-limited parts, as 

specified in a European Union Aviation 

Safety Agency (EASA) AD, which is 

incorporated by reference (IBR). The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective February 27, 

2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 27, 2024. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–1811; 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, the mandatory 

continuing airworthiness information 

(MCAI), 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. 

Material Incorporated by Reference: 

• For service information identified 

in this final rule, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, 

Germany; phone: +49 221 8999 000; 

email: ADs@easa.europa.eu; website: 

easa.europa.eu. You may find this 

material on the EASA website at 

ad.easa.europa.eu. 

• 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 regulations.gov under 

Docket No. FAA–2023–1811. 

FOR FURTHER INFORMATION CONTACT: 

Barbara Caufield, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; phone: 

(781) 238–7146; email: 

barbara.caufield@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2023–01–07, 

Amendment 39–22301 (88 FR 2501, 

January 17, 2023; corrected February 3, 

2023 (88 FR 7355); corrected February 

16, 2023 (88 FR 10013)) (AD 2023–01– 

07). AD 2023–01–07 applied to GEAC 

Model H75–100, H75–200, H80, H80– 

100, H80–200, H85–100, and H85–200 

engines. AD 2023–01–07 required 

revising the ALS of the existing EMM 

and the operator’s existing approved 

maintenance or inspection program, as 

applicable, to incorporate the updated 

coefficients and recalculate the cycles 

accumulated on critical parts. The FAA 

issued AD 2023–01–07 to prevent 

failure of the engine. 

The NPRM published in the Federal 

Register on September 6, 2023 (88 FR 

60896). The NPRM was prompted by 

EASA AD 2023–0021, dated January 23, 

2023 (EASA AD 2023–0021) (also 

referred to as the MCAI), issued by 

EASA, which is Technical Agent for the 

Member States of the European Union. 

EASA AD 2023–0021 supersedes EASA 

AD 2022–0008. The MCAI states that 

the manufacturer revised the ALS to 

introduce new and more restrictive 

instructions and associated thresholds 

and intervals for life-limited parts. The 

MCAI also states that GEAC published 

an Alert Service Bulletin, ASB–H75–72– 

10–00–0062, ASB–H80–72–10–00–0107, 

ASB–H85–72–10–00–0051, ASB– 

M601F–72–10–00–0070, ASB–M601E– 

72–10–00–0120, ASB–M601D–72–10– 

00–0087 and ASB–M601Z–72–10–00– 

0069; Revision 1, dated January 20, 

2023, published as a single document, 

which provides instructions to 

determine the accumulated life of 

certain propeller shafts. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2023–1811. 

In the NPRM, the FAA proposed to 

require accomplishing the actions 

specified in the MCAI described 

previously, except for any differences 

identified as exceptions in the 

regulatory text of the proposed AD. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

These products have been approved 

by the aviation authority of another 

country and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with this 

State of Design Authority, it has notified 

the FAA of the unsafe condition 

described in the MCAI referenced 

above. The FAA reviewed the relevant 

data 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. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed EASA AD 2023– 

0021, which specifies procedures for 

operators to revise the ALS of the 

existing EMM and the operator’s 

existing approved engine maintenance 

or inspection program, as applicable, to 

incorporate new and more restrictive 

instructions and associated thresholds 

and intervals for life-limited parts, as 

applicable to each engine model. 

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 33 engines installed on airplanes 

of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 


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Federal Register / Vol. 89, No. 15 / Tuesday, January 23, 2024 / Rules and Regulations 4183 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Revise the ALS ................................................. 1 work-hours × $85 per hour = $85 ................. $0 $85 $2,805 

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 has determined that 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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by: 

■ a. Removing Airworthiness Directive 

2023–01–07, Amendment 39–22301 (88 

FR 2501, January 17, 2023; corrected 

February 3, 2023 (88 FR 7355); corrected 

February 16, 2023 (88 FR 10013)); and 

■ b. Adding the following new 

airworthiness directive: 

2024–01–03 GE Aviation Czech s.r.o. (Type 

Certificate Previously held by WALTER 

Engines a.s., Walter a.s., and 

MOTORLET a.s.): Amendment 39– 

22654; Docket No. FAA–2023–1811; 

Project Identifier MCAI–2023–00146–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective February 27, 2024. 

(b) Affected ADs 

This AD replaces AD 2023–01–07, 

Amendment 39–22301 (88 FR 2501, January 

17, 2023; corrected February 3, 2023 (88 FR 

7355); corrected February 16, 2023 (88 FR 

10013)). 

(c) Applicability 

This AD applies to GE Aviation Czech 

s.r.o. (type certificate previously held by 

WALTER Engines a.s., Walter a.s., and 

MOTORLET a.s.) Model H75–100, H75–200, 

H80, H80–100, H80–200, H85–100, and H85– 

200 engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7200, Engine (Turbine/Turboprop). 

(e) Unsafe Condition 

This AD was prompted by the 

manufacturer revising the airworthiness 

limitations section (ALS) of the existing 

engine maintenance manual (EMM) to 

introduce new and more restrictive 

airworthiness limitations and associated 

thresholds and intervals for life-limited parts. 

The FAA is issuing this AD to prevent failure 

of the engine. The unsafe condition, if not 

addressed, could result in uncontained 

release of a critical part, 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) Except as specified in paragraph (h) of 

this AD: Perform all required actions within 

the compliance times specified in, and in 

accordance with, European Union Aviation 

Safety Agency (EASA) AD 2023–0021, dated 

January 23, 2023 (EASA AD 2023–0021). 

(2) The action required by paragraph (g)(1) 

of this AD may be performed by the owner/ 

operator (pilot) holding at least a private pilot 

certificate and must be entered into the 

aircraft records showing compliance with 

this AD in accordance with 14 CFR 43.9(a) 

and 91.417(a)(2)(v). The record must be 

maintained as required by 14 CFR 91.417, 

121.380, or 135.439. 

(h) Exceptions to EASA AD 2023–0021 

(1) Where EASA AD 2023–0021 defines the 

AMP as ‘‘the approved Aircraft Maintenance 

Programme containing the tasks on the basis 

of which the scheduled maintenance is 

conducted to ensure the continuing 

airworthiness of each operated engine,’’ for 

this AD, replace that text with, ‘‘the aircraft 

maintenance program containing the tasks on 

the basis of which the scheduled 

maintenance is conducted to ensure the 

continuing airworthiness of each operated 

airplane.’’ 

(2) Where EASA AD 2023–0021 defines the 

ALS as ‘‘the Airworthiness Limitations 

Section of GEAC EMM No. 0983402 Revision 

25, dated November 21, 2022,’’ for this AD, 

replace that text with, ‘‘the airworthiness 

limitations section of GEAC EMM No. 

0983402 Revision 26, dated February 1, 

2023.’’ The ALS in Revision 26 of the EMM 

is unchanged from Revision 25 of the EMM. 

(3) Where EASA AD 2023–0021 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(4) Where paragraph (3) of EASA AD 2023– 

0021 specifies revising ‘‘the approved AMP 

within 12 months after the effective date of 

EASA AD 2023–0021,’’ replace that text with, 

‘‘the ALS of the existing approved engine 

maintenance or inspection program, as 

applicable, within 90 days after the effective 

date of this AD.’’ 

(5) This AD does not require compliance 

with paragraphs (1), (2), (4), and (5) of EASA 

AD 2023–0021. 

(6) This AD does not adopt the Remarks 

paragraph of EASA AD 2023–0021. 

(i) Provisions for Alternative Actions and 

Intervals 

After performing the actions required by 

paragraph (g) of this AD, no alternative 

actions and associated thresholds and 

intervals, including life limits, are allowed 

unless they are approved as specified in the 

provisions of the ‘‘Ref. Publications’’ section 

of EASA AD 2023–0021. 


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4184 Federal Register / Vol. 89, No. 15 / Tuesday, January 23, 2024 / Rules and Regulations 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Validation 

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 International Validation 

Branch, send it to the attention of the person 

identified in paragraph (k) 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. 

(k) Additional Information 

For more information about this AD, 

contact Barbara Caufield, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone: (781) 238– 

7146; email: barbara.caufield@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) European Union Aviation Safety Agency 

(EASA) AD 2023–0021, dated January 23, 

2023. 

(ii) [Reserved] 

(3) For EASA AD 2023–0021, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; phone: +49 221 8999 000; 

email: ADs@easa.europa.eu; website: 

easa.europa.eu. You may find this EASA AD 

on the EASA website at ad.easa.europa.eu. 

(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 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-locationsoremailfr.inspection@nara.gov. 

Issued on January 17, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–01218 Filed 1–22–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1647; Project 

Identifier AD–2023–00487–E; Amendment 

39–22650; AD 2023–26–07] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company 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) Model 

GE90–90B, GE90–94B, GE90–110B1, 

and GE90–115B engines. This AD was 

prompted by a manufacturer 

investigation that revealed certain highpressure turbine (HPT) stage 1 disks, 

HPT stage 2 disks, forward HPT rotor 

seals, interstage HPT seals, and stages 

7–9 compressor rotor spools were 

manufactured from powder metal 

material suspected to contain iron 

inclusion. This AD requires replacement 

of affected HPT stage 1 disks, HPT stage 

2 disks, forward HPT rotor seals, 

interstage HPT seals, and stages 7–9 

compressor rotor spools. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective February 27, 

2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 27, 2024. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–1647; 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. 

Material Incorporated by Reference: 

• 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@

ge.com; website: 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 regulations.gov under 

Docket No. FAA–2023–1647. 

FOR FURTHER INFORMATION CONTACT: 

Alexei Marqueen, Aviation Safety 

Engineer, FAA, 2200 South 216th Street, 

Des Moines, WA 98198; phone: (781) 

238–7178; 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 Model GE90–90B, 

GE90–94B, GE90–110B1, and GE90– 

115B engines. The NPRM published in 

the Federal Register on September 5, 

2023 (88 FR 60603). The NPRM was 

prompted by the manufacturer’s 

detection of iron inclusion in a turbine 

disk manufactured from the same 

powder metal material used to 

manufacture certain HPT stage 1 disks, 

HPT stage 2 disks, forward HPT rotor 

seals, interstage HPT seals, and stages 

7–9 compressor rotor spools for GE90– 

90B, GE90–94B, GE90–110B1, and 

GE90–115B engines. Further 

investigation by the manufacturer 

determined that the iron inclusion is 

attributed to deficiencies in the 

manufacturing process and may cause 

reduced material properties and a lower 

fatigue life capability, which may result 

in premature fracture and subsequent 

uncontained failure. The FAA was also 

informed that GE communicated with 

affected operators having affected HPT 

stage 1 and stage 2 disks identified in 

Table 1 to Paragraph (c) of this AD 

regarding the corrective action for this 

unsafe condition. As a result, affected 

operators are already aware of the 

corrective action and have already 

performed the actions required by this 

AD. Therefore, the FAA has determined 

that the compliance time to replace 

these affected HPT stage 1 and stage 2 

disks before further flight is appropriate. 

In the NPRM, the FAA proposed to 

require replacement of certain HPT 

stage 1 disks, HPT stage 2 disks, forward 

HPT rotor seals, interstage HPT seals, 

and stages 7–9 compressor rotor spools 

with parts 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 

five commenters. Commenters included 


khammond on DSKJM1Z7X2PROD with RULES