2026-01-05: Wings

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. 2. The FAA amends § 39.13 by adding the following new airworthiness directive: 2026-01-05 The Boeing Company: Amendment 39-23233; Docket No. FAA-2025-0744; Project Identifier AD-2024-00586-T. (a) Effective Date This airworthiness directive (AD) is effective February 20, 2026. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 757-200 and -300 series airplanes, certificated in any category, as specified in paragraph 1.A.1 of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by an operator reporting a crack on a Model 757-200 airplane equipped with Aviation Partners Boeing scimitar blended winglets. The FAA is issuing this AD to address the potential for cracking on the right- or left-wing lower stringer L-8 or L-6 vertical web flange at a fastener common to the reinforcement strap. The unsafe condition, if not addressed, could result in the inability of a principal structural element to sustain limit loads, which could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Except as specified in paragraphs (h) and (i) of this AD: At the applicable times specified in paragraph 1.E., "Compliance," of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, do all applicable actions identified as "RC" (required for compliance) in, and in accordance with, the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024. (h) Exceptions to Service Bulletin Specifications (1) Where the Compliance Time columns of the tables in "Compliance" paragraph of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, refer to the original issue date of this Service Bulletin, this AD requires using the effective date of this AD. (2) Where Table 2 and Table 3 of the "Compliance" paragraph of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, specify Action 1 without a compliance time, for this AD, the compliance time is before 9,500 flight cycles after the blended winglet installation, within 3,000 flight cycles after the effective date of this AD, or within 24 months after the effective date of this AD, whichever occurs later. (3) Where Table 5 and Table 6 of the "Compliance" paragraph of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, specify Action 1 without a compliance time, for this AD, the compliance time is before 8,000 flight cycles after the blended winglet installation, within 3,000 flight cycles after the effective date of this AD, or within 24 months after the effective date of this AD, whichever occurs later. (4) Where Table 9 and Table 10 of the "Compliance" paragraph of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, specify Action 1 without a compliance time, for this AD, the compliance time is before 9,500 flight cycles after the blended winglet installation, within 3,000 flight cycles after the effective date of this AD, or within 22 months after the effective date of this AD, whichever occurs later. (5) Where Table 12 and Table 13 of the "Compliance" paragraph of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, specify Action 1 without a compliance time, for this AD, the compliance time is before 8,000 flight cycles after the blended winglet installation, within 3,000 flight cycles after the effective date of this AD, or within 22 months after the effective date of this AD, whichever occurs later. (6) Where Condition 2 of Table 6 in the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, includes "remove crack" as part of the actions, the action "remove crack" is not required by this AD for Condition 2 of Table 6. (7) Where Action 2 of Condition 4.2 in Table 3 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, does not include a method of compliance for the inspection, for this AD, the method of compliance is Figure 3 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024. (8) Where Action 2 of Condition 4.2 in Table 6 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, does not include a method of compliance for the inspection, for this AD, the method of compliance is Figure 8 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024. (9) Where flag notes (b) and (c) of Figure 3 and Figure 8 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, specify doing a surface high frequency eddy current (HFEC) inspection of the applicable lower stringer vertical web flange "around each of the four fasteners for any crack", this AD requires replacing that text with "around each fastener, including any washers or freeze plug retainer washers (washer removal is not required) for any crack". (10) Where Step 4 of Figure 3 and Figure 8 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, specifies applying both BMS 5-45 and BMS 5-168 sealants, this AD requires application of either BMS 5-45 or BMS 5-168 sealant. (11) Where flag note (b) of Figure 5 and Figure 10 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, specifies "Maximum hole diameter 0.80 inch", this AD requires replacing that text with "Maximum hole diameter 0.80 inch. Do an open-hole HFEC inspection of the hole in the stringer in accordance with 757 NDT Manual Part 6, 51-00-04, 51-00-11, or 51-00-16". (12) Where flag note (e) of Figure 6 and Figure 11 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, specifies "The retainer washer must have 0.15-0.20 inch overlap with the freeze plug", this AD requires replacing that text with "The retainer washer must have a 0.15-0.20-inch radius greater than the freeze plug". (13) Where Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, specifies contacting Aviation Partners Boeing for repair instructions: This AD requires repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (i) No Reporting Requirement Although Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024, specifies to report existing repairs, this AD does not require any report. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, West 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 (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) Except as specified by paragraph (g) of this AD: For material that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (j)(2)(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. (k) Additional Information For more information about this AD, contact Sarah Illg, Aviation Safety Engineer, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone: 206-231-3517; email: Sarah.A.Illg@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) Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024. (ii) [Reserved] (3) For Aviation Partners Boeing material identified in this AD, contact Aviation Partners Boeing, 2811 South 102nd St., Suite 200, Seattle, WA 98168; phone 206-830-7699; email leng@aviationpartners.com; website aviationpartnersboeing.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 January 12, 2026. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026-00838 Filed 1-15-26; 8:45 am]BILLING CODE 4910-13-P