Federal Register / Vol. 90, No. 5 / Wednesday, January 8, 2025 / Rules and Regulations 1359 

addressed, could result in fuel leaking from 

the electrical grounding receptacles. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Within 36 months after the effective date 

of this AD, do the actions specified in 

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

accordance with Gulfstream GVII–G500 

Customer Bulletin No. 089 or Gulfstream 

GVII–G600 Customer Bulletin No. 058, both 

dated November 28, 2023, as applicable. 

(1) Do borescope inspections for cracking 

and corrosion of the interior walls of the 

grounding receptacle casing and do all 

applicable corrective actions before further 

flight. 

(2) Remove the ‘‘GROUND HERE’’ decal/ 

stencil from the grounding receptacles and 

apply epoxy over the ground receptacle area 

to permanently disable the grounding 

receptacles. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, East Certification 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 

certification office, send it to the attention of 

the person identified in paragraph (i) of this 

AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(3) For material that contains steps that are 

labeled as Required for Compliance (RC), the 

provisions of paragraphs (h)(3)(i) and (ii) of 

this AD apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(i) Related Information 

For more information about this AD, 

contact Brandon Ellis, Aviation Safety 

Engineer, FAA, 1701 Columbia Avenue, 

College Park, GA 30337; phone: 404–474– 

5535; email: 9-ASO-ATLACO-ADs@faa.gov. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the material listed in this paragraph under 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use this material as 

applicable to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Gulfstream GVII–G500 Customer 

Bulletin No. 089, dated November 28, 2023. 

(ii) Gulfstream GVII–G600 Customer 

Bulletin No. 058, dated November 28, 2023. 

(3) For Gulfstream material identified in 

this AD, contact Gulfstream Aerospace 

Corporation, Technical Publications Dept., 

P.O. Box 2206, Savannah, GA 31402–2206; 

telephone 800–810–4853; email pubs@

gulfstream.com; website gulfstream.com/en/ 

customer-support. 

(4) You may view this material at the FAA, 

Airworthiness Products Section, Operational 

Safety Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 

(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 December 4, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2025–00138 Filed 1–7–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2024; Project 

Identifier MCAI–2024–00140–T; Amendment 

39–22907; AD 2024–25–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Defense and Space S.A. (Formerly 

Known as Construcciones 

Aeronauticas, S.A.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus Defense and Space S.A. Model 

CN–235, CN–235–200, and CN–235–300 

airplanes. This AD was prompted by a 

torn bulkhead seal found jamming the 

nose landing gear (NLG) emergency 

cable pulley. Due to the similarity of 

design, the main landing gear (MLG) 

emergency cable pulley could be 

exposed to the same failure mode. This 

AD requires repetitive inspections and 

corrective actions for damage of affected 

bulkhead seals and retainer rings, and 

repetitive replacement of affected parts, 

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 is effective February 12, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 12, 2025. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–2024; 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 EASA material identified for 

this AD, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, 

Germany; telephone +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 material at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available at regulations.gov 

under Docket No. FAA–2024–2024. 

FOR FURTHER INFORMATION CONTACT: 

Shahram Daneshmandi, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; phone: 

206–231–3220; email: 

shahram.daneshmandi@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 all Airbus Defense and Space 

S.A. (formerly known as Construcciones 

Aeronauticas, S.A.) Model CN–235, CN– 

235–200, and CN–235–300 airplanes. 

The NPRM published in the Federal 

Register on August 20, 2024 (89 FR 

67332). The NPRM was prompted by 

AD 2024–0054, dated February 26, 2024 

(EASA AD 2024–0054) (also referred to 

as the MCAI) issued by the European 

Union Aviation Safety Agency (EASA), 

which is the Technical Agent for the 

Member States of the European Union. 


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1360 Federal Register / Vol. 90, No. 5 / Wednesday, January 8, 2025 / Rules and Regulations 

The MCAI states a torn bulkhead seal 

was found jamming the NLG emergency 

cable pulley. Due to the similarity of 

design, the MLG emergency cable pulley 

could be exposed to the same failure 

mode. 

In the NPRM, the FAA proposed to 

require repetitive inspections and 

corrective actions for damage of affected 

bulkhead seals and retainer rings, and 

repetitive replacement of affected parts, 

as specified in EASA AD 2024–0054. 

The FAA is issuing this AD to address 

a jammed emergency cable pulley, 

which could prevent the emergency 

extension of the landing gears when 

required, causing damage to the airplane 

and possible injury to occupants. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2024–2024. 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the cost to the public. 

Conclusion 

This product has been approved by 

the aviation authority of another 

country and is 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 this 

product. 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. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

EASA AD 2024–0054 specifies 

procedures for repetitive general visual 

inspections for any type of damage of 

the bulkhead seals and the retainer 

rings, and, depending on findings, 

replacement. EASA AD 2024–0054 also 

requires repetitive replacement of 

affected parts. This material is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Costs of Compliance 

The FAA estimates that this AD 

affects 10 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per product Cost on U.S. operators 

Up to 7 work-hours × $85 per hour = $595 per 

inspection/replacement cycle.

$365 per replacement cycle ... Up to $960 per inspection/replacement cycle.Up to $9,600 per inspection/ 

replacement cycle. 

The FAA estimates the following 

costs to do any necessary on-condition 

action that would be required based on 

the results of any required actions. The 

FAA has no way of determining the 

number of aircraft that might need this 

on-condition action: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per product 

2 work-hours × $85 per hour = $170 .............................................................................................................. $365 $535 

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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2024–25–05 Airbus Defense and Space S.A. 

(Formerly Known as Construcciones 

Aeronauticas, S.A.): Amendment 39– 


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Federal Register / Vol. 90, No. 5 / Wednesday, January 8, 2025 / Rules and Regulations 1361 

22907; Docket No. FAA–2024–2024; 

Project Identifier MCAI–2024–00140–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective February 12, 2025. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Defense and 

Space S.A. (formerly known as 

Construcciones Aeronauticas, S.A.) Model 

CN–235, CN–235–200, and CN–235–300 

airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Unsafe Condition 

This AD was prompted by a torn bulkhead 

seal found jamming the nose landing gear 

emergency cable pulley. Due to the similarity 

of design, the main landing gear emergency 

cable pulley could be exposed to the same 

failure mode. The FAA is issuing this AD to 

address this potential unsafe condition, 

which could prevent the emergency 

extension of the landing gears when required, 

causing damage to the airplane and possible 

injury to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraphs (h) and 

(i) of this AD: Comply with all required 

actions and compliance times specified in, 

and in accordance with, European Union 

Aviation Safety Agency (EASA) AD 2024– 

0054, dated February 26, 2024 (EASA AD 

2024–0054). 

(h) Exceptions to EASA AD 2024–0054 

(1) Where EASA AD 2024–0054 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where paragraph 3.1.1 of the Alert 

Operators Transmission (AOT) specified in 

EASA AD 2024–0054, states ‘‘each year (1 

Year between 8 and 10 Years since 

component installation) since the 

inspection,’’ this AD requires replacing that 

text with ‘‘within one year after the last 

inspection’’. 

(3) This AD does not adopt the ‘‘Remarks’’ 

section of EASA AD 2024–0054. 

(i) No Reporting Requirement 

Although the material referenced in EASA 

AD 2024–0054 specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

(j) 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 (k) of this AD. Information may be 

emailed to: AMOC@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 EASA; or Airbus Defense 

and Space S.A.’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(k) Additional Information 

For more information about this AD, 

contact Shahram Daneshmandi, Aviation 

Safety Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; phone: 206– 

231–3220; email: shahram.daneshmandi@

faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the material listed in this paragraph under 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use this material as 

applicable to do the actions required by this 

AD, unless this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2024–0054, dated February 26, 

2024. 

(ii) [Reserved] 

(3) For EASA material identified in this 

AD, contact EASA, Konrad-Adenauer-Ufer 3, 

50668 Cologne, Germany; telephone +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 material at the FAA, 

Airworthiness Products Section, Operational 

Safety Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 

(5) You may view this material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

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

ibr-locations or email fr.inspection@nara.gov. 

Issued on December 4, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2025–00146 Filed 1–7–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–0755; Project 

Identifier AD–2023–00521–E; Amendment 

39–22909; AD 2024–25–07] 

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 

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 engines. This 

AD was prompted by a manufacturer 

evaluation that determined a lower life 

limit may be necessary for certain stages 

6–10 compressor rotor spools than 

allowed by the engine shop manual 

(ESM). This AD requires a one-time 

inspection of the stages 6–10 spools for 

previously accomplished blend repairs, 

a one-time inspection of the blend 

repairs on the stages 6–10 spools for 

compliance with the updated allowable 

limits, and replacement if necessary. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective February 12, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 12, 2025. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–0755; 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 GE material identified in this 

AD, contact GE, 1 Neumann Way, 

Cincinnati, OH 45215; phone: (513) 


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