2025-15-10: Horizontal Stabilizer 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: a. Removing Airworthiness Directive 2023-25-03, Amendment 39-22630 (88 FR 90085, December 29, 2023); and b. Adding the following new airworthiness directive: 2025-15-10 Piaggio Aviation S.p.A.: Amendment 39-23097; Docket No. FAA-2025-0013; Project Identifier MCAI-2024-00375-A. (a) Effective Date This airworthiness directive (AD) is effective September 3, 2025. (b) Affected ADs This AD replaces AD 2023-25-03, Amendment 39-22630 (88 FR 90085, December 29, 2023). (c) Applicability This AD applies to Piaggio Aviation S.p.A. Model P-180 airplanes, serial numbers (S/Ns) 1002, 1004 through 1234 inclusive, 3001 through 3012 inclusive, and 3016, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 5510, Horizontal Stabilizer Structure. (e) Unsafe Condition This AD was prompted by a report of corrosion on the various aluminum alloy reinforcements in the horizontal stabilizer (HS) central box caused by a humid environment inside the box from water ingress and/or condensation. The FAA is issuing this AD to address this condition. The unsafe condition, if not addressed, could result in reduced structural integrity of the HS and loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Within the applicable compliance time specified in table 1 to paragraph (g)(1) of this AD, do a detailed inspection of the HS central box for corrosion, in accordance with step (8), of Part A, of the Accomplishment Instructions in Piaggio Aerospace Service Bulletin 80-0489, Revision 2, dated November 30, 2022 (Piaggio SB 80-0489, Revision 2), except you are not required to record any images. Table 1 to Paragraph ( g )(1)-HS Central Box One Time Inspection P-180 serial No. Compliance time (hours Time-in-Service (TIS) or calendar time, whichever occurs first after February 2, 2024 (the effective date of AD 2023-25-03)) 1002; and 1034 through 3016 inclusive Within 220 hours TIS or 13 months after February 2, 2024 (the effective date of AD 2023-25-03). 1004 through 1033 inclusive Within 320 hours TIS or 13 months after February 2, 2024 (the effective date of AD 2023-25-03). (2) If, during the inspection required by paragraph (g)(1) of this AD, any corrosion is detected, 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), for an assessment of the corrosion level (level 1, 2, or 3). Note 1 to paragraph (g)(2): Appendix 1, Inspection Results Form, in Piaggio SB 80-0489, Revision 2, may be used when contacting the FAA, EASA, or Piaggio's EASA DOA. (3) If level 1 corrosion is found during the inspection required by paragraph (g)(1) of this AD, no further action is required by this AD. (4) If level 2 corrosion is found during the inspection required by paragraph (g)(1) of this AD, do the action in either paragraph (g)(4)(i) or (ii) of this AD. (i) Before further flight, replace the HS assembly or repair the HS assembly in accordance with instructions from either the Manager, International Validation Branch, FAA; EASA; or Piaggio's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (ii) Within 400 hours TIS or 12 months, whichever occurs first after the inspection required by paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 400 hours TIS or 12 months, whichever occurs first after the most recent inspection, repeat the inspection required by paragraph (g)(1) of this AD. In addition, inspect the internal composite structure of the HS central box for surface cracks, distortion, and damage. After each repetitive inspection, before further flight, assess the inspection findings as required by paragraph (g)(2) of this AD. If it is determined that the level 2 corrosion has worsened since the last inspection; or if any surface cracks, distortion, or damage is found during any inspection; before further flight, replace the HS assembly or repair the HS assembly in accordance with instructions from either the Manager, International Validation Branch, FAA; EASA; or Piaggio's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. These inspections must be repeated at intervals not to exceed 400 hours TIS or 12 months, whichever occurs first after the most recent inspection. (5) If level 3 corrosion is found during the inspection required by paragraph (g)(1) of this AD, do the actions required by paragraph (g)(5)(i) or (ii) of this AD. (i) Before further flight after the inspection required by paragraph (g)(1) of this AD, replace the HS assembly or repair the HS assembly in accordance with instructions from either the Manager, International Validation Branch, FAA; EASA; or Piaggio's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (ii) Within 200 hours TIS or 6 months, whichever occurs first after the inspection required by paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 200 hours TIS or 6 months, whichever occurs first after the most recent inspection, repeat the inspection required by paragraph (g)(1) of this AD. In addition, inspect the internal composite structure of the HS central box for surface cracks, distortion, and damage. After each repetitive inspection, before further flight, assess the inspection findings as required by paragraph (g)(2) of this AD. If it is determined that the level 3 corrosion has worsened since the last inspection; or if any surface cracks, distortion, or damage is found; before further flight, replace the HS assembly or repair the HS assembly in accordance with instructions from either the Manager, International Validation Branch, FAA; EASA; or Piaggio's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. These inspections must be repeated at intervals not to exceed 200 hours TIS or 6 months, whichever occurs first after the most recent inspection, until a maximum of 660 hours TIS or 13 months, whichever occurs first after the inspection required by paragraph (g)(1) of this AD, at which time the HS assembly must be repaired or replaced. (6) Repair or replacement of the HS assembly is terminating action for the repetitive inspections required by paragraphs (g)(4)(ii) and (g)(5)(ii) of this AD. (h) Credit for Previous Actions You may take credit for the actions required by paragraphs (g)(1) through (5) of this AD if you performed those actions before February 2, 2024 (the effective date of AD 2023-25-03) using Piaggio Aerospace Service Bulletin 80-0489, Revision 1, dated May 13, 2022. (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 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, mail it to the address identified in paragraph (j) of this AD or email to: AMOC@faa.gov. If mailing information, also submit information by email. 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 William McCully, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (404) 474-5548; email: william.mccully@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 the AD specifies otherwise. (3) The following material was approved for IBR on February 2, 2024 (88 FR 90085, December 29, 2023). (i) Piaggio Aerospace Service Bulletin 80-0489, Revision 2, dated November 30, 2022. (ii) [Reserved] (4) For Piaggio material identified in this AD, contact Piaggio Aviation 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. (5) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (817) 222-5110. (6) 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 25, 2025. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2025-14390 Filed 7-29-25; 8:45 am]BILLING CODE 4910-13-P