Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

[Federal Register Volume 91, Number 166 (Friday, August 28, 2026)]
[Rules and Regulations]
[Pages 55444-55446]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-17639]


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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; 
Amendment 39-23424; AD 2026-15-12]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Pilatus Aircraft Ltd. (Pilatus) Model PC-12/47E airplanes. This 
AD was prompted by a report that the emergency exit door could not be 
opened from inside an airplane. This AD requires modification of the 
passenger service unit (PSU) trim panel if dual lock fastener tapes are 
not installed. This AD also prohibits the installation of affected 
parts. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective October 2, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 2, 
2026.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov 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 final rule, the mandatory continuing airworthiness 
information (MCAI), any comments received, and other information. The 
address for Docket Operations is U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.
    Material Incorporated by Reference:
    <bullet> For European Union Aviation Safety Agency (EASA) material 
identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 
Cologne, Germany; phone: +49 221 8999 000; email: [email protected]; 
website: easa.europa.eu. You may find this material on the EASA website 
at ad.easa.europa.eu.
    <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. It is also available at regulations.gov under 
Docket No. FAA-2026-0018.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
phone: (816) 329-4059; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply 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 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 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.
    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

[[Page 55445]]

tapes are not installed. The NPRM also proposed to prohibit the 
installation of affected parts. The FAA is issuing this AD to address 
the unsafe condition on these products.
    The FAA issued a supplemental notice of proposed rulemaking (SNPRM) 
to amend 14 CFR part 39 by adding an AD that would apply to certain 
Pilatus Model PC-12/47E airplanes. The SNPRM was published in the 
Federal Register on May 15, 2026 (91 FR 27878). The SNPRM was prompted 
by the FAA's determination that the applicability of the NPRM 
referenced the incorrect airplane model. In the SNPRM, the FAA proposed 
to revise the NPRM to correct the affected airplane from Model PC-12 to 
Model PC-12/47E. The FAA is issuing this AD to address the unsafe 
condition on these products.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2026-0018.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from the Air Line Pilots Association, 
International. The commenter supported the SNPRM without change.

Changes to Final Rule Since Issuance of the SNPRM

    Since issuance of the SNPRM, the FAA has determined that the 
inspection proposed in the SNPRM is not necessary and the reference to 
the instructions in the definition of ``Affected part'' in EASA AD 
2025-0182 is adequate. This change also affects the Costs of Compliance 
section.

Conclusion

    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 reviewed the relevant 
data, considered any comments received, and determined that air safety 
requires adopting this AD as proposed. Accordingly, the FAA is issuing 
this AD to address the unsafe condition on these products. Except for 
minor editorial changes and any other changes described previously, 
this AD is adopted as proposed in the SNPRM. None of the changes will 
increase the economic burden on any operator.

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.

Costs of Compliance

    The FAA estimates that this AD affects 276 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                         Cost per   Cost on U.S.
                   Action                              Labor cost           Parts cost    product     operators
----------------------------------------------------------------------------------------------------------------
Modify PSU trim panel......................  2 work-hours x $85 per hour =        $100        $270       $74,520
                                              $170.
----------------------------------------------------------------------------------------------------------------

    The FAA has included all known costs in its cost estimate. 
According to the manufacturer, however, some of the costs of this 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

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will 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 Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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:
2026-15-12 Pilatus Aircraft Ltd.: Amendment 39-23424; Docket No. 
FAA-2026-0018; Project Identifier MCAI-2025-01384-A.

(a) Effective Date

    This airworthiness directive (AD) is effective October 2, 2026.

(b) Affected ADs

    None.

[[Page 55446]]

(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 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) 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: [email protected].
    (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: 
[email protected].

(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: [email protected]; 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 www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    Issued on August 26, 2026.
Christopher R. Parker,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2026-17639 Filed 8-27-26; 8:45 am]
BILLING CODE 4910-13-P

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