Proposed Rule2026-21008
Airworthiness Directives; Baykar Piaggio Aerospace S.p.A. (Type Certificate Previously Held by Piaggio Aviation S.p.A.) Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
October 14, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt a new airworthiness directive (AD) for certain Baykar Piaggio Aerospace S.p.A. (Piaggio) Model P-180 airplanes. This proposed AD was prompted by a report of corrosion and cracks found around the head of attaching fasteners on main wing lower skin external reinforcement doublers. This proposed AD would require repetitive high frequency eddy current (HFEC) inspections of the lower skin reinforcement and, depending on findings, corrective action. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 91 Issue 197 (Wednesday, October 14, 2026)</title>
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[Federal Register Volume 91, Number 197 (Wednesday, October 14, 2026)]
[Proposed Rules]
[Pages 65144-65147]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-21008]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-11809; Project Identifier MCAI-2024-00028-A]
RIN 2120-AA64
Airworthiness Directives; Baykar Piaggio Aerospace S.p.A. (Type
Certificate Previously Held by Piaggio Aviation S.p.A.) Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Baykar Piaggio Aerospace S.p.A. (Piaggio) Model P-180
airplanes. This proposed AD was prompted by a report of corrosion and
cracks found around the head of attaching fasteners on main wing lower
skin external reinforcement doublers. This proposed AD would require
repetitive high frequency eddy current (HFEC) inspections of the lower
skin reinforcement and, depending on findings, corrective action. The
FAA is proposing this AD to address the unsafe condition on these
products.
DATES: The FAA must receive comments on this NPRM by November 30, 2026.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> Mail: U.S. Department of Transportation, Docket
Operations, M-91, West Building Fifth Floor, Room W58-213, 1200 New
Jersey Avenue SE, Washington, DC 20590.
<bullet> Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2026-11809; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this NPRM, the mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
street address for Docket Operations is listed above.
Material Incorporated by Reference:
<bullet> For Piaggio Aerospace material identified in this proposed
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: <a href="/cdn-cgi/l/email-protection#e69283858e888f85878a95939696899492a6968f8781818f89878394899596878583c88f92"><span class="__cf_email__" data-cfemail="7f0b1a1c1711161c1e130c0a0f0f100d0b3f0f161e181816101e1a0d100c0f1e1c1a51160b">[email protected]</span></a>.
<bullet> 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.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (816) 329-4059; email: <a href="/cdn-cgi/l/email-protection#c7a3a8b2a0e9b5b2a3a8abb7af87a1a6a6e9a0a8b1"><span class="__cf_email__" data-cfemail="50343f25377e2225343f3c2038103631317e373f26">[email protected]</span></a>.
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
<a href="http://regulations.gov">regulations.gov</a>, 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
[[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 <a href="http://regulations.gov">regulations.gov</a> 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:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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HFEC inspection................. 50 work-hours x $1,000 (per $5,250 (per $73,500 (per
$85 per hour = inspection). inspection). inspection).
$4,250 (per
inspection).
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On-Condition Costs
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Action Labor cost Parts cost Cost per product
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Corrosion removal (within the 10 work-hours x $85 per $1,000 (per repair).... $1,850 (per repair).
structural repair manual limits). hour = $850 (per
repair).
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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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[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:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 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.
Table 1 to Paragraph (h)(1)--Compliance Times
------------------------------------------------------------------------
Compliance time (hours
time-in-service (TIS)
or calendar time,
Group whichever occurs first Interval
after the effective
date of this AD)
------------------------------------------------------------------------
1............................. Within 1,900 hours TIS 1,900 hours TIS
or 46 months. or 50 months,
whichever
occurs first.
2............................. A or B, whichever 660 hours TIS or
occurs later: 25 months,
(A) Within 220 hours whichever
TIS or 9 months. occurs first.
(B) Within 660 hours
TIS or 25 months
since first
embodiment of Piaggio
SB 80-0482 Rev. 13.
------------------------------------------------------------------------
(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
[[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: <a href="/cdn-cgi/l/email-protection#4b0a0604080b2d2a2a652c243d"><span class="__cf_email__" data-cfemail="296864666a694f4848074e465f">[email protected]</span></a>. 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:
<a href="/cdn-cgi/l/email-protection#85e1eaf0e2abf7f0e1eae9f5edc5e3e4e4abe2eaf3"><span class="__cf_email__" data-cfemail="4d2922382a633f382922213d250d2b2c2c632a223b">[email protected]</span></a>.
(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: <a href="/cdn-cgi/l/email-protection#720617111a1c1b11131e010702021d000632021b1315151b1d1317001d01021311175c1b06"><span class="__cf_email__" data-cfemail="e89c8d8b8086818b89849b9d9898879a9ca89881898f8f8187898d9a879b98898b8dc6819c">[email protected]</span></a>.
(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 <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#f89e8ad691968b889d9b8c919796b896998a99d69f978e"><span class="__cf_email__" data-cfemail="88eefaa6e1e6fbf8edebfce1e7e6c8e6e9fae9a6efe7fe">[email protected]</span></a>.
Issued on October 9, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2026-21008 Filed 10-13-26; 8:45 am]
BILLING CODE 4910-13-P
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