97492 Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Rules and Regulations 

(i) Boeing Alert Service Bulletin MD11– 

78A017, Revision 1, dated June 4, 2024. 

(ii) [Reserved] 

(3) For Boeing material identified in this 

AD, contact Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 110– 

SK57, Seal Beach, CA 90740–5600; telephone 

562–797–1717; website myboeingfleet.com. 

(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 November 19, 2024. 

Peter A. White, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2024–28780 Filed 12–6–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2134; Project 

Identifier MCAI–2024–00125–T; Amendment 

39–22894; AD 2024–24–04] 

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 superseding 

Airworthiness Directive (AD) 2018–18– 

09, which applied to all Airbus Defense 

and Space S.A. Model CN–235, CN– 

235–100, CN–235–200, and CN–235– 

300 airplanes; and certain Model C–295 

airplanes. AD 2018–18–09 required a 

detailed inspection of the upper and 

lower lugs of each horizontal stabilizerto-fuselage rear attachment fitting, 

repair if necessary, and a report of 

findings. This AD was prompted by 

reports of new occurrences of cracking. 

This AD requires repetitive inspections, 

as specified in a European Union 

Aviation Safety Agency (EASA) AD, 

which is incorporated by reference. This 

AD also revises the applicability. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective January 13, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 13, 2025. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–2134; 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 in this 

AD, contact EASA, Konrad-AdenauerUfer 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–2024–2134. 

FOR FURTHER INFORMATION CONTACT: 

Shahram Daneshmandi, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; 

telephone 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 to supersede AD 2018–18–09, 

Amendment 39–19388 (83 FR 45041, 

September 5, 2018) (AD 2018–18–09). 

AD 2018–18–09 applied to all Airbus 

Defense and Space S.A. Model CN–235, 

CN–235–100, CN–235–200, and CN– 

235–300 airplanes; and certain Model 

C–295 airplanes. AD 2018–18–09 

required a detailed inspection of the 

upper and lower lugs of each horizontal 

stabilizer-to-fuselage rear attachment 

fitting, repair if necessary, and a report 

of findings. The FAA issued AD 2018– 

18–09 to address cracking, which could 

lead to reduced structural integrity of 

the lugs on the horizontal stabilizer-tofuselage rear attachment fittings. The 

unsafe condition, if not addressed, 

could result in lug or fitting failure, and 

could result in reduced controllability 

of the airplane. 

The NPRM published in the Federal 

Register on August 30, 2024 (89 FR 

70582). The NPRM was prompted by 

AD 2024–0049, dated February 20, 

2024, issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union (EASA AD 2024– 

0049) (also referred to as the MCAI). The 

MCAI states that since EASA AD 2017– 

0218, dated November 8, 2017, was 

issued, new occurrences of cracking 

were reported and the manufacturer 

issued new material to provide 

instructions for repetitive highfrequency eddy current (HFEC) 

inspections for cracking of the affected 

part for all airplanes. 

In the NPRM, the FAA proposed to 

require repetitive inspections, as 

specified in EASA AD 2024–0049. The 

NPRM also proposed to revise the 

applicability. The FAA is issuing this 

AD to address cracking, which could 

lead to reduced structural integrity of 

the lugs on the horizontal stabilizer-tofuselage rear attachment fittings and 

consequent lug or fitting failure, and 

could result in reduced controllability 

of the airplane. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2024–2134. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from a 

commenter who supported the NPRM 

without change. 

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, considered 

the comment 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 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 2024–0049 specifies 

procedures for repetitive HFEC 

inspections for discrepancies (including 

cracking, rework, and sharp corner 

radii) of the upper and lower lugs of 


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Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Rules and Regulations 97493 

each horizontal stabilizer-to-fuselage 

rear attachment fitting and contacting 

the manufacturer for corrective actions. 

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 14 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

New actions .... Up to 15 work-hours × $85 per hour = $1,275 ................... None .............. Up to $1,275 ......................... Up to $17,850. 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition actions specified in 

this AD. 

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: 

■ a. Removing Airworthiness Directive 

(AD) 2018–18–09, Amendment 39– 

19388 (83 FR 45041, September 5, 

2018); and 

■ b. Adding the following new AD: 

2024–24–04 Airbus Defense and Space S.A. 

(Formerly known as Construcciones 

Aeronauticas, S.A.): Amendment 39– 

22894; Docket No. FAA–2024–2134; 

Project Identifier MCAI–2024–00125–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 13, 2025. 

(b) Affected ADs 

This AD replaces AD 2018–18–09, 

Amendment 39–19388 (83 FR 45041, 

September 5, 2018) (AD 2018–18–09). 

(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, CN–235–300, and C– 

295 airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by a report that 

cracks were found on the horizontal 

stabilizer-to-fuselage rear attachment fitting. 

The FAA is issuing this AD to address 

cracking, which could lead to reduced 

structural integrity of the lugs on the 

horizontal stabilizer-to-fuselage rear 

attachment fittings. The unsafe condition, if 

not addressed, could result in lug or fitting 

failure, and could result in reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, European Union Aviation 

Safety Agency (EASA) AD 2024–0049, dated 

February 20, 2024 (EASA AD 2024–0049). 

(h) Exceptions to EASA AD 2024–0049 

(1) Where paragraph (1) of EASA AD 2024– 

0049 specifies to do the initial inspection 

within certain compliance times, for this AD, 

accomplish the initial inspection at the time 

specified in paragraph (h)(1)(i) or (ii) of this 

AD, whichever occurs later. 

(i) At the applicable compliance time 

specified in paragraph (1) of EASA AD 2024– 

0049. 

(ii) Within 50 flight cycles or 50 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

(2) Where paragraph (1) of EASA AD 2024– 

0049 specifies ‘‘thereafter, at intervals as 

defined in paragraph 3.1.1 of the AOT,’’ this 

AD requires replacing that text with 

‘‘thereafter, at intervals not to exceed the 

intervals defined in paragraph 3.1.1 of the 

AOT.’’ 

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

section of EASA AD 2024–0049. 

(4) Where paragraph (2) of EASA AD 2024– 

0049 specifies ‘‘If, during any inspection as 

required by paragraph (1) of this AD, 

discrepancies are detected, as defined in the 

AOT, before next flight, contact Airbus DS 

for approved corrective action instructions 

and accomplish those instructions 

accordingly,’’ this AD requires replacing that 

text with ‘‘If, during any inspection as 

required by paragraph (1) of this AD, any 

discrepancy is detected, the discrepancy 

must be repaired before further flight 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 DOA-authorized signature.’’ 


ddrumheller on DSK120RN23PROD with RULES1
97494 Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Rules and Regulations 

(i) No Reporting Requirement 

Although the material referenced in EASA 

AD 2024–0049 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; telephone 

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 

(IBR) 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 2024–0049, dated February 20, 

2024. 

(ii) [Reserved] 

(3) For EASA AD 2024–0049, 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-locationsoremailfr.inspection@nara.gov. 

Issued on November 21, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–28787 Filed 12–6–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1053; Project 

Identifier AD–2023–00164–T; Amendment 

39–22891; AD 2024–24–01] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 757–200, 

–200CB, and –200PF series airplanes. 

This AD was prompted by a crack 

growth analysis, which indicated that 

current inspections are not adequate to 

detect cracks in certain sections of the 

upper frame at the frame splice between 

certain stringers before a single frame 

fails. This AD requires an inspection or 

records review for existing repairs, 

repetitive inspections for cracks of the 

upper frame at the frame splices 

between certain stringers in certain 

sections, and applicable on-condition 

actions. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective January 13, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 13, 2025. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–1053, 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 Boeing material identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster 

Blvd., MC 110–SK57, Seal Beach, CA 

90740–5600; telephone 562–797–1717; 

website myboeingfleet.com. 

• 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–2023–1053. 

FOR FURTHER INFORMATION CONTACT: 

Wayne Ha, Aviation Safety Engineer, 

FAA, 2200 South 216th Street, Des 

Moines, WA 98198; phone: 562–627– 

5238; email: wayne.ha@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 The Boeing Company 

Model 757–200, –200CB, and –200PF 

series airplanes. The NPRM published 

in the Federal Register on July 24, 2023 

(88 FR 47402). The NPRM was 

prompted by a crack growth analysis, 

which indicated that current 

inspections are not adequate to detect 

cracks in certain sections of the upper 

frame at the frame splice between 

certain stringers before a single frame 

fails. In the NPRM, the FAA proposed 

to require an inspection or records 

review for existing repairs, repetitive 

inspections for cracks of the upper 

frame at the frame splices between 

certain stringers in certain sections, and 

applicable on-condition actions. 

The FAA issued a supplemental 

notice of proposed rulemaking (SNPRM) 

to amend 14 CFR part 39 by adding an 

AD that would apply to certain The 

Boeing Company Model 757–200, 

–200CB, and –200PF series airplanes. 

The SNPRM published in the Federal 

Register on April 22, 2024 (89 FR 

29274). The SNPRM was prompted by a 

determination that the repetitive 

inspection intervals for airplanes that 

were modified by Aviation Partners 

Boeing (APB) supplemental type 

certificate (STC) ST01518SE needed to 

be revised. The SNPRM proposed to 

require the actions specified in the 

NPRM, with certain revised compliance 

times. 

The FAA is issuing this AD to address 

cracking at the upper frames common to 

the splice at stringers S–13 to S–14, 

which could interact with fuselage skin 

cracking at the stringer S–14 lap splice. 

This unsafe condition, if not addressed, 

could result in the inability of a 

principal structural element to sustain 


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