Proposed Rule2026-09771
Airworthiness Directives; Pilatus Aircraft Ltd. 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
May 15, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is revising a notice of proposed rulemaking (NPRM) that would have applied to certain Pilatus Aircraft Ltd. (Pilatus) Model PC-12 airplanes. This action revises the NPRM by changing the applicability. The FAA is proposing this airworthiness directive (AD) to address the unsafe condition on these products. Since these actions would impose an additional burden over those in the NPRM for different airplanes, the FAA is requesting comments on this SNPRM.
Full Text
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<title>Federal Register, Volume 91 Issue 94 (Friday, May 15, 2026)</title>
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[Federal Register Volume 91, Number 94 (Friday, May 15, 2026)]
[Proposed Rules]
[Pages 27878-27881]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-09771]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-0018; Project Identifier MCAI-2025-01384-A]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (SNPRM).
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SUMMARY: The FAA is revising a notice of proposed rulemaking (NPRM)
that would have applied to certain Pilatus Aircraft Ltd. (Pilatus)
Model PC-12 airplanes. This action revises the NPRM by changing the
applicability. The FAA is proposing this airworthiness directive (AD)
to address the unsafe condition on these products. Since these actions
would impose an additional burden over those in the NPRM for different
airplanes, the FAA is requesting comments on this SNPRM.
DATES: The FAA must receive comments on this SNPRM by June 29, 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-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
[[Page 27879]]
<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-2026-0018; 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 SNPRM, 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 European Union Aviation Safety Agency (EASA) material
identified in this proposed AD, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; phone: +49 221 8999 000; email:
<a href="/cdn-cgi/l/email-protection#befffacdfedbdfcddf90dbcbccd1cedf90dbcb"><span class="__cf_email__" data-cfemail="5213162112373321337c3727203d22337c3727">[email protected]</span></a>; website: easa.europa.eu. You may find this material
on the EASA website at ad.easa.europa.eu. It is also available at
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2026-0018.
<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#2e4a415b49005c5b4a41425e466e484f4f00494158"><span class="__cf_email__" data-cfemail="1d7972687a336f687972716d755d7b7c7c337a726b">[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 the ADDRESSES section. Include ``Docket No. FAA-2026-0018;
Project Identifier MCAI-2025-01384-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 again revise 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 SNPRM.
Confidential Business Information
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 SNPRM 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 SNPRM, 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 SNPRM. 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 FAA issued an NPRM to amend 14 CFR part 39 by adding an AD that
would have applied to certain Pilatus Model PC-12 airplanes. The NPRM
was published in the Federal Register on January 21, 2026 (91 FR 2512).
The NPRM was prompted by EASA AD 2025-0182, dated August 25, 2025 (EASA
AD 2025-0182) (also referred to as the MCAI), issued by EASA, which is
the Technical Agent for the Member States of the European Union, to
correct an unsafe condition on certain Pilatus Model PC-12/47E
airplanes. The MCAI states that there was a report that the emergency
exit door could not be opened from inside an airplane. Further
investigation revealed that incorrect installation of the passenger
service unit (PSU) trim panel, which is installed above the emergency
exit door, could block the opening of the emergency exit if the PSU
trim panel is positioned too far inboard. This condition, if not
addressed, could prevent the opening of the emergency door, which could
result in injury to occupants during an emergency evacuation.
In the NPRM, the FAA proposed to require a visual inspection of the
PSU trim panel for dual lock fastener tapes and modification if dual
lock fastener tapes are not installed. The NPRM also proposed to
prohibit the installation of affected parts.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2026-0018.
Actions Since the NPRM Was Issued
Since the FAA issued the NPRM, the FAA has determined that the
applicability of the NPRM referenced the incorrect airplane model.
Therefore, this proposed AD revises the NPRM to correct the affected
airplane from Model PC-12 to Model PC-12/47E. The FAA is proposing this
AD to address the unsafe condition on these products.
Comments
The FAA received a comment from the Air Line Pilots Association,
International. The commenter supported the NPRM without change.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed EASA AD 2025-0182, which specifies procedures for
modifying the PSU trim panel if dual lock fastener tapes are not
installed. EASA AD 2025-0182 also prohibits the installation of an
affected part. EASA AD 2025-0182 also refers to instructions to
determine whether dual lock fastener tapes are installed on a PSU trim
panel. 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 referenced above. The FAA is issuing this SNPRM
after determining that the unsafe condition described previously is
likely to exist or develop on other products of the same type design.
Certain changes described above expand the scope of the NPRM. As a
result, it is necessary to reopen the comment period to provide
additional opportunity for the public to comment on this SNPRM.
Proposed AD Requirements in This SNPRM
This proposed AD would require accomplishing the actions specified
in the material already described, except for any differences
identified as exceptions in the regulatory text of this proposed AD.
See ``Differences Between this SNPRM and the MCAI'' for a
[[Page 27880]]
discussion of the general differences included in this proposed AD.
Differences Between This SNPRM and the MCAI
Where paragraph (1) of EASA AD 2025-0182 does not specify an
inspection to determine whether dual lock fastener tapes are installed
on a PSU trim panel, for this proposed AD an inspection would be
required in accordance with section B. Part 1 of the material
referenced in EASA AD 2025-0182 to determine whether an airplane has
the dual lock fastener tapes installed on a PSU trim panel and is
either a Group 1 or Group 2 airplane as defined in EASA AD 2025-0182.
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA developed a process to use some civil aviation
authority (CAA) ADs as the primary source of information for compliance
with requirements for corresponding FAA ADs. The FAA has since
coordinated with other manufacturers and CAAs to use this process. As a
result, the FAA proposes to incorporate by reference EASA AD 2025-0182
in the FAA final rule. This proposed AD would, therefore, require
compliance with EASA AD 2025-0182 in its entirety through that
incorporation, except for any differences identified as exceptions in
the regulatory text of this proposed AD. Using common terms that are
the same as the heading of a particular section in EASA AD 2025-0182
does not mean that operators need comply only with that section. For
example, where the AD requirement refers to ``all required actions and
compliance times,'' compliance with this AD requirement is not limited
to the section titled ``Required Action(s) and Compliance Time(s)'' in
EASA AD 2025-0182. Material required by EASA AD 2025-0182 for
compliance will be available at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-
2026-0018 after the FAA final rule is published.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 276 airplanes of U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspect PSU trim panel................ 1 work-hour x $85 per $0 $85 $23,460
hour = $85.
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The FAA estimates the following costs to do any necessary
modification that would be required based on the results of the
proposed inspection. The agency has no way of determining the number of
airplanes that might need this modification:
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Modify PSU trim panel......................... 2 work-hours x $85 per hour = $100 $270
$170.
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The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this
proposed AD may be covered under warranty, thereby reducing the cost
impact on affected operators.
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.
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:
[[Page 27881]]
Pilatus Aircraft Ltd.: Docket No. FAA-2026-0018; Project Identifier
MCAI-2025-01384-A.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by June 29, 2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Pilatus Aircraft Ltd. Model PC-12/47E
airplanes, manufacturer serial numbers 2001 through 2999,
certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) Code 2500, Cabin
Equipment/Furnishings.
(e) Unsafe Condition
This AD was prompted by a report that the emergency exit door
could not be opened from inside an airplane. The FAA is issuing this
AD to prevent the passenger service unit (PSU) trim panel from
blocking the opening of the emergency exit. The unsafe condition, if
not addressed, could prevent the opening of the emergency door,
which could result in injury to occupants during an emergency
evacuation.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Except as specified in paragraphs (h) and (i) of this AD: Comply
with all required actions and compliance times specified in, and in
accordance with, European Union Aviation Safety Agency (EASA) AD
2025-0182, dated August 25, 2025 (EASA AD 2025-0182).
(h) Exceptions to EASA AD 2025-0182
(1) Where EASA AD 2025-0182 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where paragraph (1) of EASA AD 2025-0182 does not specify an
inspection to determine whether dual lock fastener tapes are
installed on a PSU trim panel, for this AD an inspection is required
in accordance with section B. Part 1 of the material referenced in
EASA AD 2025-0182 to determine whether an airplane has the dual lock
fastener tapes installed on a PSU trim panel and is either a Group 1
or Group 2 airplane as defined in EASA AD 2025-0182.
(3) This AD does not adopt the ``Remarks'' section of EASA AD
2025-0182.
(i) No Reporting Requirement
Although the material referenced in EASA AD 2025-0182 specifies
to submit certain information to the manufacturer, this AD does not
include that requirement.
(j) Alternative Methods of Compliance (AMOCs)
(1) 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 International Validation Branch, send it to the
attention of the person identified in paragraph (k) of this AD and
email to: <a href="/cdn-cgi/l/email-protection#fcbdb1b3bfbc9a9d9dd29b938a"><span class="__cf_email__" data-cfemail="20616d6f63604641410e474f56">[email protected]</span></a>.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office/certificate holding
district office.
(k) 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#e5818a9082cb9790818a89958da5838484cb828a93"><span class="__cf_email__" data-cfemail="b0d4dfc5d79ec2c5d4dfdcc0d8f0d6d1d19ed7dfc6">[email protected]</span></a>.
(l) 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) European Union Aviation Safety Agency (EASA) AD 2025-0182,
dated August 25, 2025.
(ii) [Reserved]
(3) For EASA material identified in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999
000; email: <a href="/cdn-cgi/l/email-protection#47060334072226342669223235283726692232"><span class="__cf_email__" data-cfemail="3d7c794e7d585c4e5c1358484f524d5c135848">[email protected]</span></a>; website: easa.europa.eu. You may
find this EASA AD on the EASA website at ad.easa.europa.eu.
(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#2244500c4b4c51524741564b4d4c624c4350430c454d54"><span class="__cf_email__" data-cfemail="7a1c08541314090a1f190e1315143a141b081b541d150c">[email protected]</span></a>.
Issued on May 12, 2026.
Paul R. Bernado,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2026-09771 Filed 5-14-26; 8:45 am]
BILLING CODE 4910-13-P
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