Airworthiness Directives; The Boeing Company Airplanes, 12452-12455 [2025-04319]

Download as PDF 12452 Federal Register / Vol. 90, No. 51 / Tuesday, March 18, 2025 / Rules and Regulations instructions in paragraphs, including subparagraphs under those paragraphs, not identified 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 instructions identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to instructions identified as RC require approval of an AMOC. (j) Additional Information For more information about this AD, contact Dan Rodina, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206–231–3225; email: dan.rodina@faa.gov. (k) 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 2024–0058R2, dated October 4, 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 material on the EASA website ad.easa.europa.eu. (4) You may view this material 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. (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 March 6, 2025. Peter A. White, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2025–04334 Filed 3–17–25; 8:45 am] khammond on DSK9W7S144PROD with RULES BILLING CODE 4910–13–P VerDate Sep<11>2014 15:45 Mar 17, 2025 Jkt 265001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–2315; Project Identifier AD–2023–00537–T; Amendment 39–22988; AD 2025–05–16] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737–800 series airplanes. This AD was prompted by a determination that the compliance time for the initial ultrasonic inspection required by AD 2019–11–06 is insufficient for certain airplanes. This AD requires reducing the compliance time for the ultrasonic inspection of the skin under the drag link assembly. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 22, 2025. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 22, 2025. ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2024–2315; 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–2024–2315. FOR FURTHER INFORMATION CONTACT: Owen Bley-Male, Aviation Safety SUMMARY: PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206– 231–3992; email: owen.f.bley-male@ 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 737–800 series airplanes. The NPRM published in the Federal Register on September 25, 2024 (89 FR 78260). The NPRM was prompted by a determination that the compliance time for the initial ultrasonic inspection required by AD 2019–11–06, Amendment 39–19652 (84 FR 27193, June 12, 2019) (AD 2019–11–06), is insufficient for Model 737–800 series airplanes that have been modified to a freighter configuration using Boeing Drawing 800A0003. In the NPRM, the FAA proposed to require reducing the compliance time for the ultrasonic inspection of the skin under the drag link assembly. The FAA is issuing this AD to address cracking found in the station (STA) 540 bulkhead chord and skin, which could result in the inability of a primary structural element to sustain limit load. The unsafe condition, if not addressed, could result in possible rapid decompression and loss of structural integrity of the airplane. Discussion of Final Airworthiness Directive Comments The FAA received comments from Boeing and an individual, who supported the NPRM without change. The FAA received comments from Aviation Partners Boeing (APB) and an individual who supported the NPRM and had additional comments. The following presents the comments received on the NPRM and the FAA’s response to each comment. Limited Organization Designation Authorization (ODA) Approvals APB stated that Boeing does not have a delegation to approve repairs in areas affected by the split scimitar winglet configuration of Supplemental Type Certificate (STC) ST00830SE. APB also commented that approval by The Boeing Company Organization Designation Authorization (ODA), as specified in paragraph (j)(3) of the proposed AD, may not be given for an alternative method of compliance (AMOC) for alternative inspections and corrective actions in those areas, but such approval must be obtained as specified in paragraph (j)(1) of the proposed AD. E:\FR\FM\18MRR1.SGM 18MRR1 Federal Register / Vol. 90, No. 51 / Tuesday, March 18, 2025 / Rules and Regulations APB added that Boeing retains approval delegation for findings related to fuselage structures affected by the proposed rule. The FAA acknowledges and concurs with APB’s assertions. However, no change to this AD is necessary. Paragraphs (g)(1) and (2) of this AD state that AMOC approval be obtained using a method approved in accordance with the procedures specified in ‘‘paragraph (j)’’ of this AD, and does not limit approvals to the provisions of paragraph (j)(1) or (3) of this AD. Therefore, AMOC approval in accordance with paragraphs (j)(1) or (3) of this AD would be provided based on whether the actions needing an AMOC apply to the APB design or the Boeing design. Effect of Winglets on Accomplishment of the Proposed Actions APB stated that accomplishing STC ST00830SE does not affect the actions specified in the proposed AD. The FAA concurs with the commenter. The FAA has redesignated paragraph (c) of the proposed AD as paragraph (c)(1) of this AD and added paragraph (c)(2) to this AD to state that installation of STC ST00830SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE is installed, a ‘‘change in product’’ AMOC approval request is not necessary to comply with the requirements of 14 CFR 39.17. considered an acceptable AMOC. The individual reasoned that clear and specific guidelines for AMOCs would provide greater clarity and consistency, helping to ensure that any AMOC would meet safety standards. The FAA agrees to clarify. The AMOC process is outlined in 14 CFR 39.17 and 39.19, which specify that any AMOC request must include the specific actions proposed to address the unsafe condition, and that the proposed actions must provide an acceptable level of safety. AMOCs may be requested under the provisions of paragraph (j) of this AD. An AMOC may be applicable only to a specific airplane (e.g., to repair cracks) or to an entire fleet (e.g., to use revised service information). The FAA has therefore determined that adding additional AMOC guidelines or criteria to this AD is unnecessary. The FAA has not changed this AD in this regard. 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. None of the changes will increase the economic burden on any operator. Terminating Action for Certain Requirements of AD 2019–11–06 Request for More Detailed AMOC Criteria An individual suggested including more detailed criteria for what would be Accomplishing the actions required by this AD replaces the corresponding 12453 initial ultrasonic inspections and oncondition actions required by paragraph (g) of AD 2019–11–06 for Model 737– 800 series airplanes converted to a freighter configuration using Boeing Drawing 800A0003 only. Material Incorporated by Reference Under 1 CFR Part 51 The FAA reviewed Boeing Alert Service Bulletin 737–53A1368, dated February 27, 2018. This material specifies an ultrasonic inspection of the skin under the drag link assembly and repair for any cracks; repetitive inspections for any cracks, including ultrasonic inspections, high frequency eddy current inspections, low frequency eddy current inspections, and detailed inspections; and a preventative modification if no crack is found. The FAA also reviewed Boeing 737– 800BCF Airworthiness Limitations, D140A006, Revision L, dated April 1, 2021. This material contains required inspections for principal structural element items. Section 5.2.1 of this material identifies the airplanes affected by this AD. 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 18 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Action Labor cost Initial inspection ..... Up to 23 work-hours × $85 per hour = Up to $1,955. The FAA estimates the following costs to do any on-condition actions that Cost per product Parts cost $0 Cost on U.S. operators Up to $1,955 .......... would be required based on the results of the inspection. The agency has no Up to $35,190. way of determining the number of airplanes that might need these actions: ESTIMATED COSTS FOR ON-CONDITION ACTIONS Labor cost Parts cost khammond on DSK9W7S144PROD with RULES Up to 56 work-hours × $85 per hour = Up to $4,760 .................................................. 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: VerDate Sep<11>2014 15:45 Mar 17, 2025 Jkt 265001 $24,020 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 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 Cost per product Up to $28,780. 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. E:\FR\FM\18MRR1.SGM 18MRR1 12454 Federal Register / Vol. 90, No. 51 / Tuesday, March 18, 2025 / Rules and Regulations 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 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(f), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2025–05–16 The Boeing Company: Amendment 39–22988; Docket No. FAA–2024–2315; Project Identifier AD– 2023–00537–T. khammond on DSK9W7S144PROD with RULES (a) Effective Date This airworthiness directive (AD) is effective April 22, 2025. (b) Affected ADs This AD affects AD 2019–11–06, Amendment 39–19652 (84 FR 27193, June 12, 2019) (AD 2019–11–06). (c) Applicability (1) This AD applies to The Boeing Company Model 737–800 series airplanes, certificated in any category, that have been converted to a freighter configuration using Boeing Drawing 800A0003 before April 1, 2021, and are identified as Group A in VerDate Sep<11>2014 15:45 Mar 17, 2025 Jkt 265001 (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a determination that the compliance time for the initial ultrasonic inspection of the skin under the drag link assembly required by AD 2019–11– 06 must be reduced for certain airplanes. The FAA is issuing this AD to address cracking found in the station (STA) 540 bulkhead chord and skin, which could result in the inability of a primary structural element to sustain limit load. The unsafe condition, if not addressed, could result in possible rapid decompression and loss of structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: § 39.13 Section 5.2.1, ‘‘Effectivity,’’ of Boeing 737– 800BCF Airworthiness Limitations, D140A006, Revision L, dated April 1, 2021. Note 1 to paragraph (c)(1): Airplanes with a 737–800BCF designation are Model 737– 800 series airplanes that have been converted to a freighter configuration using Boeing Drawing 800A0003. (2) Installation of Supplemental Type Certificate (STC) ST00830SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (g) Required Actions (1) For airplanes identified as Group 1, Configuration 2, 3, 4, or 5, or as Group 5 in Boeing Alert Service Bulletin 737–53A1368, dated February 27, 2018: At the compliance time specified in paragraph (g)(1)(i), (ii), (iii), or (iv) of this AD, whichever occurs last, perform an ultrasonic inspection of the skin under the drag link assembly in accordance with the Accomplishment Instructions, Part 2, of Boeing Alert Service Bulletin 737– 53A1368, dated February 27, 2018. Do all applicable on-condition actions for the Part 2 inspection at the times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1368, dated February 27, 2018, except where Boeing Alert Service Bulletin 737–53A1368, dated February 27, 2018, specifies contacting Boeing for repair instructions, this AD requires doing the repair using a method approved in accordance with paragraph (j) of this AD. (i) Before the airplane accumulates 17,000 total flight cycles. (ii) Within 5,000 flight cycles after July 17, 2019 (the effective date of AD 2019–11–06). (iii) Within 12 months after the effective date of this AD. (iv) Within 1,000 flight cycles after the effective date of this AD. (2) For airplanes identified as Group 1, Configuration 1, 3, or 4 in Boeing Alert Service Bulletin 737–53A1368, dated PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 February 27, 2018: At the compliance time specified in paragraph (g)(2)(i), (ii), (iii), or (iv) of this AD, whichever occurs last, perform an ultrasonic inspection of the repair tripler under the drag link assembly in accordance with the Accomplishment Instructions, Part 6, of Boeing Alert Service Bulletin 737–53A1368, dated February 27, 2018. Do all applicable on-condition actions for the Part 6 inspection at the times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1368, dated February 27, 2018, except where Boeing Alert Service Bulletin 737–53A1368, dated February 27, 2018, specifies contacting Boeing for repair instructions, this AD requires doing the repair using a method approved in accordance with paragraph (j) of this AD. (i) Before the airplane accumulates 30,000 total flight cycles. (ii) Within 5,000 flight cycles after July 17, 2019 (the effective date of AD 2019–11–06). (iii) Within 12 months after the effective date of this AD. (iv) Within 1,000 flight cycles after the effective date of this AD. (i) Terminating Action for Certain Requirements of AD 2019–11–06 Accomplishing the actions required by this AD replaces the corresponding initial ultrasonic inspections and on-condition actions required by paragraph (g) of AD 2019–11–06 for Model 737–800 series airplanes converted to a freighter configuration using Boeing Drawing 800A0003 only. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, AIR–520, Continued Operational Safety 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 (k) of this AD. Information may be emailed to: AMOC@ faa.gov. (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) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by The Boeing Company Organization Designation Authorization (ODA) that has been authorized by the Manager, AIR–520, Continued Operational Safety Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (k) Related Information For more information about this AD, contact Owen Bley-Male, Aviation Safety Engineer, FAA, 2200 South 216th St., Des E:\FR\FM\18MRR1.SGM 18MRR1 Federal Register / Vol. 90, No. 51 / Tuesday, March 18, 2025 / Rules and Regulations Moines, WA 98198; phone: 206–231–3992; email: owen.f.bley-male@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 the AD specifies otherwise. (i) Boeing 737–800BCF Airworthiness Limitations, D140A006, Revision L, dated April 1, 2021. (ii) Boeing Alert Service Bulletin 737– 53A1368, dated February 27, 2018. (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 March 7, 2025. Peter A. White, Deputy Director, Integrated Certificate Management Division,Aircraft Certification Service. [FR Doc. 2025–04319 Filed 3–17–25; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–2330; Project Identifier MCAI–2024–00393–T; Amendment 39–22983; AD 2025–05–11] RIN 2120–AA64 Airworthiness Directives; ATR—GIE Avions de Transport Régional Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all ATR—GIE Avions de Transport Régional Model ATR42 and ATR72 airplanes. This AD was prompted by a report of a manufacturing defect identified in the lavatory fire extinguisher. This defect could potentially result in leakage at the eutectic tip, leading to a loss of pressure in the cylinder, making fire khammond on DSK9W7S144PROD with RULES SUMMARY: VerDate Sep<11>2014 15:45 Mar 17, 2025 Jkt 265001 extinguishing capabilities ineffective. This AD requires an inspection (i.e., weight check) and replacement, as applicable, of certain lavatory compartment fire extinguishers, and also prohibits the installation of affected 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 April 22, 2025. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 22, 2025. ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2024–2330; 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–2024–2330. 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 by adding an AD that would apply to all Model ATR42–200, ATR42– 300, ATR42–320, and ATR42–500 airplanes; and Model ATR72–101, ATR72–102, ATR72–201, ATR72–202, ATR72–211, ATR72–212, and ATR72– PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 12455 212A airplanes. The NPRM published in the Federal Register on October 10, 2024 (89 FR 82190). The NPRM was prompted by AD 2024–0132, dated July 9, 2024, issued by EASA, which is the Technical Agent for the Member States of the European Union (EASA AD 2024– 0132) (also referred to as the MCAI). The MCAI states a manufacturing defect was identified in the lavatory fire extinguisher. This defect could potentially result in leakage at the eutectic tip, leading to a loss of pressure in the cylinder, making fire extinguishing capabilities ineffective. This condition, if not detected and corrected, in combination with fire in the lavatory waste bin, could result in the propagation of an uncontrolled fire. In the NPRM, the FAA proposed to require an inspection (i.e., weight check) and replacement, as applicable, of certain lavatory compartment fire extinguishers, as specified in EASA AD 2024–0132. The NPRM also proposed to prohibit the installation of affected parts, as specified in EASA AD 2024– 0132. The FAA is issuing this AD to address the unsafe condition on these products. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2024–2330. Discussion of Final Airworthiness Directive Comments The FAA received a comment from Air Line Pilots Association, International (ALPA) who supported the NPRM without change. The FAA received additional comments from an individual. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Revise Applicability An individual requested that the FAA exclude certain airplanes from the proposed AD. The commenter stated the proposed AD is redundant if an aircraft has at least one additional fire extinguisher on board. The commenter stated that if the AD was narrowly written, it would not apply to aircraft that have at least one non-affected fire extinguisher on the aircraft and that while the proposed AD prioritizes safety, it is highly burdensome. The commenter stated that the AD should be inapplicable to aircraft that have multiple fire extinguishers. The FAA disagrees with this request. The AD requires inspection and replacement of a specific lavatory fire extinguisher with a known manufacturing defect. In addition, 14 E:\FR\FM\18MRR1.SGM 18MRR1

Agencies

[Federal Register Volume 90, Number 51 (Tuesday, March 18, 2025)]
[Rules and Regulations]
[Pages 12452-12455]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-04319]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-2315; Project Identifier AD-2023-00537-T; 
Amendment 39-22988; AD 2025-05-16]
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 737-800 series airplanes. This AD was 
prompted by a determination that the compliance time for the initial 
ultrasonic inspection required by AD 2019-11-06 is insufficient for 
certain airplanes. This AD requires reducing the compliance time for 
the ultrasonic inspection of the skin under the drag link assembly. The 
FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective April 22, 2025.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 22, 
2025.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2024-2315; 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-2024-2315.

FOR FURTHER INFORMATION CONTACT: Owen Bley-Male, Aviation Safety 
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-
231-3992; email: [email protected].

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 737-800 series airplanes. The NPRM published in the 
Federal Register on September 25, 2024 (89 FR 78260). The NPRM was 
prompted by a determination that the compliance time for the initial 
ultrasonic inspection required by AD 2019-11-06, Amendment 39-19652 (84 
FR 27193, June 12, 2019) (AD 2019-11-06), is insufficient for Model 
737-800 series airplanes that have been modified to a freighter 
configuration using Boeing Drawing 800A0003. In the NPRM, the FAA 
proposed to require reducing the compliance time for the ultrasonic 
inspection of the skin under the drag link assembly. The FAA is issuing 
this AD to address cracking found in the station (STA) 540 bulkhead 
chord and skin, which could result in the inability of a primary 
structural element to sustain limit load. The unsafe condition, if not 
addressed, could result in possible rapid decompression and loss of 
structural integrity of the airplane.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from Boeing and an individual, who 
supported the NPRM without change.
    The FAA received comments from Aviation Partners Boeing (APB) and 
an individual who supported the NPRM and had additional comments. The 
following presents the comments received on the NPRM and the FAA's 
response to each comment.

Limited Organization Designation Authorization (ODA) Approvals

    APB stated that Boeing does not have a delegation to approve 
repairs in areas affected by the split scimitar winglet configuration 
of Supplemental Type Certificate (STC) ST00830SE. APB also commented 
that approval by The Boeing Company Organization Designation 
Authorization (ODA), as specified in paragraph (j)(3) of the proposed 
AD, may not be given for an alternative method of compliance (AMOC) for 
alternative inspections and corrective actions in those areas, but such 
approval must be obtained as specified in paragraph (j)(1) of the 
proposed AD.

[[Page 12453]]

APB added that Boeing retains approval delegation for findings related 
to fuselage structures affected by the proposed rule.
    The FAA acknowledges and concurs with APB's assertions. However, no 
change to this AD is necessary. Paragraphs (g)(1) and (2) of this AD 
state that AMOC approval be obtained using a method approved in 
accordance with the procedures specified in ``paragraph (j)'' of this 
AD, and does not limit approvals to the provisions of paragraph (j)(1) 
or (3) of this AD. Therefore, AMOC approval in accordance with 
paragraphs (j)(1) or (3) of this AD would be provided based on whether 
the actions needing an AMOC apply to the APB design or the Boeing 
design.

Effect of Winglets on Accomplishment of the Proposed Actions

    APB stated that accomplishing STC ST00830SE does not affect the 
actions specified in the proposed AD.
    The FAA concurs with the commenter. The FAA has redesignated 
paragraph (c) of the proposed AD as paragraph (c)(1) of this AD and 
added paragraph (c)(2) to this AD to state that installation of STC 
ST00830SE does not affect the ability to accomplish the actions 
required by this AD. Therefore, for airplanes on which STC ST00830SE is 
installed, a ``change in product'' AMOC approval request is not 
necessary to comply with the requirements of 14 CFR 39.17.

Request for More Detailed AMOC Criteria

    An individual suggested including more detailed criteria for what 
would be considered an acceptable AMOC. The individual reasoned that 
clear and specific guidelines for AMOCs would provide greater clarity 
and consistency, helping to ensure that any AMOC would meet safety 
standards.
    The FAA agrees to clarify. The AMOC process is outlined in 14 CFR 
39.17 and 39.19, which specify that any AMOC request must include the 
specific actions proposed to address the unsafe condition, and that the 
proposed actions must provide an acceptable level of safety. AMOCs may 
be requested under the provisions of paragraph (j) of this AD. An AMOC 
may be applicable only to a specific airplane (e.g., to repair cracks) 
or to an entire fleet (e.g., to use revised service information). The 
FAA has therefore determined that adding additional AMOC guidelines or 
criteria to this AD is unnecessary. The FAA has not changed this AD in 
this regard.

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. None of the changes will increase the economic burden on 
any operator.

Terminating Action for Certain Requirements of AD 2019-11-06

    Accomplishing the actions required by this AD replaces the 
corresponding initial ultrasonic inspections and on-condition actions 
required by paragraph (g) of AD 2019-11-06 for Model 737-800 series 
airplanes converted to a freighter configuration using Boeing Drawing 
800A0003 only.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Service Bulletin 737-53A1368, dated 
February 27, 2018. This material specifies an ultrasonic inspection of 
the skin under the drag link assembly and repair for any cracks; 
repetitive inspections for any cracks, including ultrasonic 
inspections, high frequency eddy current inspections, low frequency 
eddy current inspections, and detailed inspections; and a preventative 
modification if no crack is found.
    The FAA also reviewed Boeing 737-800BCF Airworthiness Limitations, 
D140A006, Revision L, dated April 1, 2021. This material contains 
required inspections for principal structural element items. Section 
5.2.1 of this material identifies the airplanes affected by this AD.
    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 18 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
            Action                    Labor cost          Parts cost    Cost per  product        operators
----------------------------------------------------------------------------------------------------------------
Initial inspection............  Up to 23 work-hours x               $0  Up to $1,955.....  Up to $35,190.
                                 $85 per hour = Up to
                                 $1,955.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any on-condition 
actions that would be required based on the results of the inspection. 
The agency has no way of determining the number of airplanes that might 
need these actions:

                Estimated Costs for On-Condition Actions
------------------------------------------------------------------------
            Labor cost                Parts cost      Cost per product
------------------------------------------------------------------------
Up to 56 work-hours x $85 per hour         $24,020  Up to $28,780.
 = Up to $4,760.
------------------------------------------------------------------------

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.

[[Page 12454]]

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

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2025-05-16 The Boeing Company: Amendment 39-22988; Docket No. FAA-
2024-2315; Project Identifier AD-2023-00537-T.

(a) Effective Date

    This airworthiness directive (AD) is effective April 22, 2025.

(b) Affected ADs

    This AD affects AD 2019-11-06, Amendment 39-19652 (84 FR 27193, 
June 12, 2019) (AD 2019-11-06).

(c) Applicability

    (1) This AD applies to The Boeing Company Model 737-800 series 
airplanes, certificated in any category, that have been converted to 
a freighter configuration using Boeing Drawing 800A0003 before April 
1, 2021, and are identified as Group A in Section 5.2.1, 
``Effectivity,'' of Boeing 737-800BCF Airworthiness Limitations, 
D140A006, Revision L, dated April 1, 2021.

    Note 1 to paragraph (c)(1): Airplanes with a 737-800BCF 
designation are Model 737-800 series airplanes that have been 
converted to a freighter configuration using Boeing Drawing 
800A0003.

    (2) Installation of Supplemental Type Certificate (STC) 
ST00830SE does not affect the ability to accomplish the actions 
required by this AD. Therefore, for airplanes on which STC ST00830SE 
is installed, a ``change in product'' alternative method of 
compliance (AMOC) approval request is not necessary to comply with 
the requirements of 14 CFR 39.17.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by a determination that the compliance time 
for the initial ultrasonic inspection of the skin under the drag 
link assembly required by AD 2019-11-06 must be reduced for certain 
airplanes. The FAA is issuing this AD to address cracking found in 
the station (STA) 540 bulkhead chord and skin, which could result in 
the inability of a primary structural element to sustain limit load. 
The unsafe condition, if not addressed, could result in possible 
rapid decompression and loss of structural integrity of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) For airplanes identified as Group 1, Configuration 2, 3, 4, 
or 5, or as Group 5 in Boeing Alert Service Bulletin 737-53A1368, 
dated February 27, 2018: At the compliance time specified in 
paragraph (g)(1)(i), (ii), (iii), or (iv) of this AD, whichever 
occurs last, perform an ultrasonic inspection of the skin under the 
drag link assembly in accordance with the Accomplishment 
Instructions, Part 2, of Boeing Alert Service Bulletin 737-53A1368, 
dated February 27, 2018. Do all applicable on-condition actions for 
the Part 2 inspection at the times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1368, dated 
February 27, 2018, except where Boeing Alert Service Bulletin 737-
53A1368, dated February 27, 2018, specifies contacting Boeing for 
repair instructions, this AD requires doing the repair using a 
method approved in accordance with paragraph (j) of this AD.
    (i) Before the airplane accumulates 17,000 total flight cycles.
    (ii) Within 5,000 flight cycles after July 17, 2019 (the 
effective date of AD 2019-11-06).
    (iii) Within 12 months after the effective date of this AD.
    (iv) Within 1,000 flight cycles after the effective date of this 
AD.
    (2) For airplanes identified as Group 1, Configuration 1, 3, or 
4 in Boeing Alert Service Bulletin 737-53A1368, dated February 27, 
2018: At the compliance time specified in paragraph (g)(2)(i), (ii), 
(iii), or (iv) of this AD, whichever occurs last, perform an 
ultrasonic inspection of the repair tripler under the drag link 
assembly in accordance with the Accomplishment Instructions, Part 6, 
of Boeing Alert Service Bulletin 737-53A1368, dated February 27, 
2018. Do all applicable on-condition actions for the Part 6 
inspection at the times specified in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 737-53A1368, dated February 27, 
2018, except where Boeing Alert Service Bulletin 737-53A1368, dated 
February 27, 2018, specifies contacting Boeing for repair 
instructions, this AD requires doing the repair using a method 
approved in accordance with paragraph (j) of this AD.
    (i) Before the airplane accumulates 30,000 total flight cycles.
    (ii) Within 5,000 flight cycles after July 17, 2019 (the 
effective date of AD 2019-11-06).
    (iii) Within 12 months after the effective date of this AD.
    (iv) Within 1,000 flight cycles after the effective date of this 
AD.

(i) Terminating Action for Certain Requirements of AD 2019-11-06

    Accomplishing the actions required by this AD replaces the 
corresponding initial ultrasonic inspections and on-condition 
actions required by paragraph (g) of AD 2019-11-06 for Model 737-800 
series airplanes converted to a freighter configuration using Boeing 
Drawing 800A0003 only.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, AIR-520, Continued Operational Safety 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 (k) 
of this AD. Information may be emailed to: [email protected].
    (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) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by The Boeing Company Organization Designation 
Authorization (ODA) that has been authorized by the Manager, AIR-
520, Continued Operational Safety Branch, FAA, to make those 
findings. To be approved, the repair method, modification deviation, 
or alteration deviation must meet the certification basis of the 
airplane, and the approval must specifically refer to this AD.

(k) Related Information

    For more information about this AD, contact Owen Bley-Male, 
Aviation Safety Engineer, FAA, 2200 South 216th St., Des

[[Page 12455]]

Moines, WA 98198; phone: 206-231-3992; email: [email protected].

(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 the AD specifies otherwise.
    (i) Boeing 737-800BCF Airworthiness Limitations, D140A006, 
Revision L, dated April 1, 2021.
    (ii) Boeing Alert Service Bulletin 737-53A1368, dated February 
27, 2018.
    (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 [email protected].

    Issued on March 7, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division,Aircraft 
Certification Service.
[FR Doc. 2025-04319 Filed 3-17-25; 8:45 am]
BILLING CODE 4910-13-P
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