AD 2026-06-05 Airworthiness Directives; Baykar Piaggio Aerospace S.p.A. (Type Certificate Previously Held by Piaggio Aviation S.p.A.) Airplanes

Models named: P-180. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Baykar Piaggio Aerospace S.p.A. (type certificate previously held by Piaggio Aviation S.p.A.) Model P-180 airplanes, manufacturer serial numbers 1002, 1004 through 3016, and 3018, certificated in any category.

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

(1) Within the applicable compliance time specified in table 1 to paragraph (g)(1) of this AD and thereafter at intervals not to exceed 660 hours time-in-service (TIS) or 26 months, whichever occurs first, do the applicable repetitive visual and non-destructive testing (NDT) inspections of the parts of the vertical stabilizer assembly for evidence of damage to the protective finish, corrosion, and cracking, in accordance with section 2.B, PART A, items (i) through (vii) as applicable, of Piaggio Aerospace Service Bulletin (SB) 80-0493, Revision 0, dated November 21, 2024 (Piaggio Aerospace SB 80-0493, Rev. 0). Where Piaggio Aerospace SB 80-0493, Rev. 0, states that subsequent inspections shall be performed in accordance with the aircraft maintenance manual inspection program chapter 05-20-00, this AD does not require those actions. Table 1 to Paragraph ( g )(1)—Compliance Times P-180 Serial No. Compliance time (hours TIS or calendar time, whichever occurs first after the effective date of this AD) 1002, 1004 through 3016 Within 220 hours TIS or 13 months. 3018 Within 660 hours TIS or 26 months. (2) Within the applicable compliance time specified in table 1 to paragraph (g)(1) of this AD, do the applicable one-time NDT inspections of the parts of the vertical stabilizer assembly for evidence of damage to the protective finish, corrosion and cracking, in accordance with section 2.B, PART A, items (viii) and (ix), as applicable, of Piaggio Aerospace SB 80-0493, Rev. 0. (3) If, during any inspection required by paragraph (g)(1) or (2) of this AD any corrosion or cracking is found, before further flight, accomplish the applicable corrective action(s), including post-repair inspections, in accordance with the instructions of section 2.B, PART B, of Piaggio Aerospace SB 80-0493, Rev. 0. (4) Where the Accomplishment Instructions, section 2.B, PART B, step (49) of Piaggio SB 80-0493, Rev. 0, state to contact Piaggio to obtain an approved repair design approval sheet (RDAS) and accomplish that repair accordingly including post-repair follow-on actions(s), as applicable, before further flight, contact either the Manager, International Validation Branch, FAA; European Union Aviation Safety Agency (EASA); or Piaggio's EASA Design Organization Approval (DOA) for approved repair instructions and, within the compliance time specified therein, accomplish those instructions accordingly, including post-repair follow-on action(s), as applicable. If approved by the DOA, the approval must include the DOA-authorized signature.

This AD was prompted by reports of corrosion and cracks affecting the vertical stabilizer. The FAA is issuing this AD to address this unsafe condition. The unsafe condition, if not addressed, could result in reduced structural integrity of the vertical stabilizer and the rudder with consequent reduced control of the airplane.

None.