SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments using a method listed under ADDRESSES . Include “Docket No. FAA-2026-11809; Project Identifier MCAI-2024-00028-A” at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this proposal because of those comments.

Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this NPRM.

CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as “PROPIN.” The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Doug Rudolph, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking.

Background

The European Union Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2024-0006, dated January 9, 2024 (EASA AD 2024-0006) (also referred to as the MCAI), to correct an unsafe condition on certain Piaggio Model P-180 airplanes. The MCAI states a report of an occurrence of corrosion and cracks ( printed page 65145) was found around the heads of attaching fasteners on main wing lower skin external reinforcement doublers during scheduled maintenance on a Piaggio Model P-180 airplane. This condition, if not detected and corrected, could reduce the structural integrity of the main wing with consequent reduced control of the airplane. To address this unsafe condition, Piaggio issued material providing instructions for repetitive HFEC inspections of the affected parts and, depending on findings, accomplishment of corrective action.

You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA-2026-11809.

Material Incorporated by Reference Under 1 CFR Part 51

The FAA reviewed Piaggio Aerospace Service Bulletin 80-0494 Rev. 1, dated November 30, 2023. This material specifies procedures for repetitive HFEC inspections on the main wing lower skin external reinforcement doublers, and corrective actions for the parts with evidence of corrosion and cracks. Corrective actions include, depending on inspection findings, repairing or contacting Piaggio to obtain an approved repair design approval sheet.

The FAA also reviewed Piaggio Aerospace Service Bulletin 80-0482 Rev. 13, dated January 27, 2026. This material specifies weight and balance updates and identifies updates to the effectivity of manufacturer's serial numbers affected by the weight and balance updates.

The FAA also reviewed Subject 51-10-40, Allowable Damage, Piaggio Aerospace Structural Repair Manual, Report No. 180-MAN-0250-1106, Issue D0, dated November 2, 2021. This material specifies identifying what is considered allowable minor damage (not critical to affect flight safety or performance) to primary and secondary structures that may be corrected by a simple procedure.

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.

FAA's Determination

These products have been approved by the civil aviation authority of another country and are approved for operation in the United States. Pursuant to the FAA's bilateral agreement with this State of Design Authority, that authority has notified the FAA of the unsafe condition described in the MCAI and material referenced above. The FAA is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design.

Proposed AD Requirements in This NPRM

This proposed AD would require accomplishing the actions specified in the material already described.

Costs of Compliance

The FAA estimates that this AD, if adopted as proposed, would affect 14 airplanes of U.S. registry.

The FAA estimates the following costs to comply with this proposed AD:

The costs for any repair that would be required by the proposed AD (including repairs for corrosion found outside the limits of the structural repair manual) would vary from airplane to airplane. Therefore, the FAA has no way of determining the cost estimate for such repairs

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

The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:

(1) Is not a “significant regulatory action” under Executive Order 12866,

(2) Would not affect intrastate aviation in Alaska, and

(3) Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

( printed page 65146)

The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

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:

Baykar Piaggio Aerospace S.p.A. (Type Certificate Previously Held by Piaggio Aviation S.p.A.): Docket No. FAA-2026-11809; Project Identifier MCAI-2024-00028-A.

(a) Comments Due Date

The FAA must receive comments on this airworthiness directive (AD) by November 30, 2026.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Baykar Piaggio Aerospace S.p.A. (type certificate previously held by Piaggio Aviation S.p.A.) (Piaggio) Model P-180 airplanes, certificated in any category, manufacturer serial numbers 1032, 1036, 1037, 1039, 1040, 1043, 1063, 1065, 1074, 1079, 1089, 1106, 1108 and 1112.

(d) Subject

Joint Aircraft System Component (JASC) Code 5730, Wing, Plates/Skins.

(e) Unsafe Condition

This AD was prompted by a report of corrosion and cracks found around the heads of attaching fasteners on main wing lower skin external reinforcement doublers. The FAA is issuing this AD to address this unsafe condition. The unsafe condition, if not addressed, could reduce the structural integrity of the main wing with reduced control of the airplane.

(f) Compliance

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

(g) Definitions

For the purpose of this AD:

(1) An “affected part” is a main wing lower skin external reinforcement doubler, having part number (P/N) 80-212457-001 (left-hand) or P/N 80-212457-002 (right-hand).

(2) The “material” is Piaggio Aerospace Service Bulletin (SB) 80-0494 Rev. 1, dated November 30, 2023 (Piaggio SB 80-0494 Rev. 1).

(3) “Group 1” airplanes are those on which, on the effective date of this AD, Piaggio Aerospace Service Bulletin 80-0482 Rev.13, dated January 27, 2026 (Piaggio SB 80-0482 Rev. 13) is not embodied, but on which, before the effective date of this AD, Piaggio SB 80-0482 Rev. 13 has been embodied and later removed.

(4) “Group 2” airplanes are those on which, on the effective date of this AD, Piaggio SB 80-0482 Rev. 13 is embodied.

(5) “Group 3” airplanes are those on which, on the effective date of this AD, Piaggio SB 80-0482 Rev. 13 has never been embodied.

(6) The “High Frequency Eddy Current (HFEC) inspection” is for the affected parts (lower skin reinforcement) of an airplane in accordance with the instructions in Section 2.B.(13) of Piaggio SB 80-0494 Rev. 1.

(7) “Repairable Corrosion” is corrosion identified as “repairable” in Subject 51-10-40, Allowable Damage, Piaggio Aerospace Structural Repair Manual, Report No. 180-MAN-0250-1106, Issue D0, dated November 2, 2021, except corrosion around the heads of the attaching fasteners of affected parts.

(h) Required Actions

(1) For Group 1 and Group 2 airplanes: Before exceeding the compliance time and, thereafter, at intervals not to exceed the values as defined in table 1 of this AD, as applicable, accomplish an HFEC inspection, as defined in this AD.

(2) If, during any inspection required by paragraph (h)(1) of this AD, repairable corrosion, as defined in this AD, is detected, before next flight, accomplish a repair in accordance with the instructions of steps 2.B.(15) through (19), and C.(20) of Piaggio SB 80-0494 Rev. 1.

(3) If, during any inspection required by paragraph (h)(1) of this AD, any discrepancy other than repairable corrosion is detected on an airplane, before next flight, contact either the Manager, International Validation Branch, FAA; European Union Aviation Safety Agency (EASA); or Piaggio's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature and, within the compliance time defined therein, accomplish that repair accordingly, including any post-repair follow-on action(s), as applicable.

(4) Accomplishment of corrective actions on an airplane, as required by paragraph (h)(2) or (3) of this AD, as applicable, does not constitute terminating action for the repetitive inspections required by paragraph (h)(1) of this AD for that airplane, unless otherwise specified in the approved repair instructions.

(5) For Group 1 airplanes: From the effective date of this AD, it is allowed to embody Piaggio SB 80-0482 Rev. 13, on an airplane, provided that, before next flight after that modification, an HFEC inspection, as defined in this AD, and, depending on findings, corrective action(s) as required by paragraph (h)(2) or (3) of this AD, as applicable, are accomplished on that airplane. After that modification, the airplane is effectively considered to be in Group 2, and HFEC inspections must be accomplished on that airplane as required by this AD for Group 2 airplanes.

(6) For Group 2 airplanes: From the effective date of this AD, following removal of Piaggio SB 80-0482 Rev. 13 from an airplane, that airplane is effectively considered to be in Group 1, and HFEC inspections must be accomplished on that airplane as required by this AD for Group 1 airplanes.

(7) For Group 3 airplanes: From the effective date of this AD, it is allowed to embody Piaggio SB 80-0482 Rev. 13 on an airplane, provided that, within 660 hours TIS or 25 months after that modification, whichever occurs first, an HFEC inspection, as defined in this AD, and, depending on findings, corrective action(s) as required by paragraph (h)(2) or (3) of this AD, as applicable, are accomplished on that airplane. After that modification, the airplane is effectively considered to be in Group 2, and HFEC inspections must be accomplished on that airplane as required by this AD for Group 2 airplanes.

(i) 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 ( printed page 65147) request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (j) of this AD and email to: AMOC@faa.gov. 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

For more information about this AD, contact Doug Rudolph, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (816) 329-4059; email: doug.rudolph@faa.gov.

(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) Piaggio Aerospace Service Bulletin 80-0482 Rev. 13, dated January 27, 2026.

(ii) Piaggio Aerospace Service Bulletin 80-0494 Rev. 1, dated November 30, 2023.

(iii) Subject 51-10-40, Allowable Damage, Piaggio Aerospace Structural Repair Manual, Report No. 180-MAN-0250-1106, Issue D0, dated November 2, 2021.

(3) For Piaggio Aerospace material identified in this AD, contact Baykar Piaggio Aerospace S.p.A., P180 Customer Support, via Pionieri e Aviatori d'Italia, snc—16154 Genoa, Italy; phone: +39 331 679 74 93; email: technicalsupport@piaggioaerospace.it.

(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.