2026-15-05: Wing Structure

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: 2026-15-05 Textron Aviation Inc.: Amendment 39-23417; Docket No. FAA-2026-7223; Project Identifier AD-2026-00329-A. (a) Effective Date This airworthiness directive (AD) is effective August 10, 2026. (b) Affected ADs None. (c) Applicability This AD applies to Textron Aviation Inc. Model B300 and B300C airplanes, certificated in any category, identified in Textron Mandatory Service Letter MTL-57-04, Revision 1, dated March 27, 2025, including airplanes identified in paragraphs (c)(1) through (3) of this AD, except for any airplane that has had a wing evaluation performed by Textron Aviation Special Missions and been issued a serial number specific aircraft limitations manual and structural inspection and repair manual supplements. (1) Model B300 airplanes (heavy weight) having Kit 130-4402 installed (effective for serial numbers (S/Ns) FL-91, FL-381, FL-383, FL-387, FL-391 and on). (2) Model B300 (heavy weight) and B300C (non-extended range) airplanes having Kit 130-4030 installed (effective for S/Ns FL-381, FL-383 and on, and FM-12 and on). (3) Model B300 (increased gross weight with extended-range fuel tank) airplanes having Kit 130-4014 (effective for S/Ns FL-1 and on and FM-1 and on). (d) Subject Joint Aircraft System Component (JASC) Code 5700, Wing Structure. (e) Unsafe Condition This AD was prompted by the manufacturer's revision of the structural inspection and repair manual to introduce more restrictive inspection intervals for airplanes that are certified to or operating at a 16,500 pound (lb.) maximum takeoff weight (MTOW). The FAA is issuing this AD to prevent undetected cracks in the wing or wing supporting structure. The unsafe condition, if not addressed, could result in reduced structural integrity and consequent wing separation from the fuselage in flight. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions At the applicable compliance time specified in paragraphs (g)(1) through (3) of this AD, revise the Limitations Section of the existing aircraft maintenance manual or instructions for continued airworthiness and the existing maintenance or inspection program, as applicable, by incorporating the information identified in table 1 to paragraph (g) of this AD. (1) For airplanes that are certified to or operating at 16,500 lb. MTOW and with 3,800 hours total time-in-service (TTIS) or less: Before accumulating 3,800 hours TTIS or within 25 hours time-in-service (TIS) or 30 days after the effective date of this AD, whichever occurs later. (2) For airplanes that are certified to or operating at 16,500 lb. MTOW and with between 3,801 and 7,400 TTIS: Within 200 hours TIS or 6 months, whichever occurs first after the effective date of this AD. (3) For airplanes that are certified to or operating at 16,500 lb. MTOW and with more than 7,401 hours TTIS: Within 25 hours TIS or 30 days, whichever occurs first after the effective date of this AD. Table 1 to Paragraph ( g )-Revised Scheduled Component Replacement Time Limits Task No. Component Interval 57-00-00-9602 Wing to Fuselage Attach Angles (FL-1 through FL-175, FL-177; FM-1 through FM-9; unless Kit 101-1202-0001 is installed) 16,500 MTOW airplanes, replace every 2,500 hours. 57-00-00-9603 Wing to Fuselage Attach Angles (FL-176, FL-178 and after; FM-10 and after; and prior airplanes with Kit 101-1202-0001 installed) 16,500 MTOW airplanes, replace every 29,200 hours. 57-20-01-9600 Outboard Wing Structure (FL-1 through FL-125; FM-1 through FM-8; unless 101-110085-1 and -2 spar caps are installed) 16,500 MTOW airplanes, replace every 6,500 hours. There are no life limitation inspection tasks associated with the wing center section Wing Center Section (FL-126 and after; FM-9 and after; and prior airplanes with Kit 101-1200-0001 installed) The life is not limited provided the inspection programs defined in the listed maintenance manuals and the replacement schedule for the items listed below have been adhered to for continued airworthiness. King Air Series Structural Inspection and Repair Manual, P/N 98-39006, Revision D6. - Chapter 57-18-02 Super King Air Model B300/B300C Maintenance Manual, P/N 130-590031-11. - Chapter 5 - Chapter 57 Super King Air Model B300/B300C Fusion Maintenance Manual, P/N 434-590169-0009. - Chapter 5 - Chapter 57 There are no life limitation inspection tasks associated with the outboard wing structure. Outboard Wing Structure (FL-126 and after; FM-9 and after; and prior airplanes with 101-110085-1 and -2 spar caps installed) The life is not limited provided the inspection programs defined in the listed maintenance manuals and the replacement schedule for the items listed below have been adhered to for continued airworthiness. King Air Series Structural Inspection and Repair Manual, P/N 98-39006, Revision D6. - Chapter 57-18-02 Super King Air Model B300/B300C Maintenance Manual, P/N 130-590031-11. - Chapter 5 - Chapter 57 Super King Air Model B300/B300C Fusion Maintenance Manual, P/N 434-590169-0009. - Chapter 5 - Chapter 57 Note 1 to paragraph (g): Additional guidance for accomplishing the actions required by this AD can be found in Textron Super King Air B300/B300C Airworthiness Limitations Manual 130-590031-211G, Revision G0, dated April 29, 2026. (h) Provisions for Alternative Actions and Intervals After the action required by paragraph (g) of this AD has been performed, no alternative actions and associated thresholds and intervals are allowed unless they are approved as specified in the provisions of paragraph (i) of this AD. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Central 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 local Flight Standards District Office, as appropriate. If sending information directly to the manager of the Central Certification Branch, send it to the attention of the person identified in paragraph (j)(1) of this AD and email to: AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (j) Additional Information (1) For more information about this AD, contact Soban Saeed, Aviation Safety Engineer, FAA, 1801 South Airport Road, Wichita, KS 67209; phone: (316) 946-4123; email: CCB-COS@faa.gov. (2) Material identified in this AD that is not incorporated by reference is available at the address specified in paragraph (k)(3) of this AD. (k) 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) Textron Mandatory Service Letter MTL-57-04, Revision 1, dated March 27, 2025. (ii) [Reserved] (3) For Textron material identified in this AD, contact Textron, One Cessna Blvd., Wichita, KS, 67215; phone: (316) 517-9355; email: teamturboprop@txtav.com; website: txtav.com . (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 1100 Main, Kansas City, MO 64105. For information on the availability of this material at the FAA, call (817) 222-5110. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email fr.inspection@nara.gov . Issued on July 16, 2026. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026-15006 Filed 7-23-26; 8:45 am]BILLING CODE 4910-13-P