Airworthiness Directive · Amendment 39-23097 · Horizontal stabilizer structure
Piaggio Aviation S.p.A. Airplanes
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.
The FAA is superseding Airworthiness Directive (AD) 2023-25- 03, which applied to certain Piaggio Aviation S.p.A. (Piaggio) Model P- 180 airplanes. AD 2023-25-03 required a one-time detailed inspection of the horizontal stabilizer (HS) central box for corrosion; an assessment of the corrosion level; and depending on the determination, repetitive detailed inspections of the HS central box for corrosion and the internal composite structure for surface cracks, distortion, and damage; and repair or replacement of the HS assembly. Repair or replacement of the HS assembly was terminating action for the repetitive inspections. Since the FAA issued AD 2023-25-03, it was determined that AD 2023-25-03 imposed an unintended restriction that is not in the mandatory continuing airworthiness information (MCAI). This AD retains certain actions of AD-2023-25-03 and removes the unintended restriction. The FAA is issuing this AD to address the unsafe condition on these products.
(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.
| 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.
