preamble attached >>>
ADs updated daily at www.Tdata.com
2023-26-05 PILATUS AIRCRAFT LTD.: Amendment 39-22648; Docket No. FAA-2023-2404; Project Identifier MCAI-2023-01268-A.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective January 3, 2024.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD  applies to Pilatus Aircraft Ltd.  Model  PC-24 Airplanes,  as
    identified in European Union Aviation Safety Agency  (EASA)  Emergency
    AD 2023-0219-E,  dated December 19, 2023 (EASA Emergency AD 2023-0219-
    E), certificated in any category.

(d) SUBJECT

    Joint Aircraft System Component  (JASC) Code 2721,  Rudder Tab Control
    System.

(e) UNSAFE CONDITION

    This AD  was prompted  by a  determination that  the titanium threaded
    bolts  installed  at  the forward  end of  the short  rudder trim  tab
    actuating rods could be subject to unexpectedly high oscillating loads
    due to aerodynamic forces  acting on the rudder  trim tab. The FAA  is
    issuing this AD to address the unsafe condition. The unsafe condition,
    if not addressed, could result  in failure of titanium threaded  bolts
    with consequent damage to the rudder and rudder trim tab, which  could
    result in in loss of rudder control and reduced or loss of control  of
    the airplane.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) REQUIRED ACTIONS

    Except as specified in paragraph (h)  of this AD:  Comply with all re-
    quired actions and compliance times specified in,  and  in  accordance
    with, EASA Emergency AD 2023-0219-E.

(h) EXCEPTIONS TO EASA EMERGENCY AD 2023-0219-E

(1) Where EASA Emergency AD 2023-0219-E refers to its effective date, this
    AD requires using the effective date of this AD.

(2) Where EASA Emergency AD 2023-0219-E  requires  compliance  in terms of
    flight hours, this AD requires using hours time-in-service.

(3) Where paragraph (4)  of  EASA  Emergency AD 2023-0190-E  specifies  to
    "contact Pilatus to obtain approved instructions,  and within the com-
    pliance  time(s)  specified  therein,  accomplish  those  instructions
    accordingly;" for this AD,  replace that text with "accomplish correc-
    tive action in accordance with a method approved by the Manager, Inter
    -national Validation Branch,  FAA;  or  EASA;  or  Pilatus EASA Design
    Organization Approval (DOA). If approved by the DOA, the approval must
    include the DOA-authorized signature."

(4) Where the service information  referenced  in  EASA Emergency AD 2023-
    0190-E specifies to "Return bellcrank bolts with damage to Pilatus Air
    -craft Ltd." and "Return the two threaded bolts (3) (that you removed)
    to Pilatus Aircraft Ltd.", this AD does not require those actions.

(5) Where the service information  referenced  in  EASA Emergency AD 2023-
    0190-E specifies "Discard the two lock washers (2)",  for this AD, re-
    place that text with "Remove the two lock washers (2) from service."

(6) This AD does not adopt the Remarks paragraph of EASA Emergency AD 2023
    -0190-E.

(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 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, mail it to the address identified  in
    paragraph (j) of this  AD or email to:  9-AVS-AIR-730-AMOC@faa.gov. If
    mailing information,  also submit  information by  email. 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: doug.rudolph@faa.gov.

(k) MATERIAL INCORPORATED BY REFERENCE

(1) The Director of the Federal Register  approved  the  incorporation  by
    reference  (IBR)  of the service information  listed in this paragraph
    under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable  to do the actions
    required by this AD, unless the AD specifies otherwise.

(i) European Union Aviation Safety Agency (EASA) Emergency AD 2023-0219-E,
    dated December 19, 2023.

(ii) [Reserved]

(3) For EASA Emergency AD 2023-0219-E,  contact EASA, Konrad-Adenauer-Ufer
    3, 50668 Cologne, Germany;  phone: +49 221 8999 000;  email: ADs@easa.
    europa.eu;  website: easa.europa.eu.  You may find this EASA Emergency
    AD on the EASA website at ad.easa.europa.eu.

(4) You may view this service information at the FAA,  Airworthiness Prod-
    ucts Section,  Operational Safety Branch,  901 Locust, Kansas City, MO
    64106. 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 Admin-
    istration (NARA). For information on the availability of this material
    at NARA,  visit www.archives.gov/federal-register/cfr/ibr-locations or
    email fr.inspection@nara.gov.

Issued on December 22, 2023.  Caitlin Locke,  Director,  Compliance & Air-
worthiness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT:  Doug Rudolph,  Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (816) 329-
4059; email: doug.rudolph@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-2404; Project Identifier MCAI-2023-01268-A;
Amendment 39-22648; AD 2023-26-05]
RIN 2120-AA64

Airworthiness Directives
; Pilatus Aircraft Ltd. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Pilatus Aircraft Ltd. (Pilatus) Model PC-24 airplanes. This AD
was prompted by a determination that the titanium threaded bolts at the
forward end of the short rudder trim tab actuating rods could be
subject to unexpectedly high oscillating loads due to aerodynamic
forces acting on the rudder trim tab. This AD requires periodic
replacement of affected titanium threaded bolts, a one-time inspection
of the rudder mass balance arm and other elements of the rudder trim
tab installation for correct attachment, damage (gouges), cracks,
deformation, surface finish, and corrosion on any surrounding parts
and, depending on findings, accomplishment of applicable corrective
actions, as specified in a European Union Aviation Safety Agency (EASA)
emergency AD, which is incorporated by reference. The FAA is issuing
this AD to address the unsafe condition on these products.

DATES: This AD is effective January 3, 2024.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 3,
2024.
The FAA must receive comments on this AD by February 12, 2024.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.
Fax: (202) 493-2251.
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.
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 regulations.gov under
Docket No. FAA-2023-2404; 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
street address for Docket Operations is listed above.
Material Incorporated by Reference:
For material identified in this final rule, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999
000; email: ADs@easa.europa.eu; website: easa.europa.eu. You may find
this material on the EASA website at ad.easa.europa.eu.
You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 901 Locust, Kansas City,
MO 64106. 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-2023-2404.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (816) 329-4059; email: doug.rudolph@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to send any written data, views, or arguments
about this final rule. Send your comments to an address listed under
ADDRESSES. Include ``Docket No. FAA-2023-2404; Project Identifier MCAI-
2023-01268-A'' at the beginning of your comments. The most helpful
comments reference a specific portion of the final rule, 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 final rule 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
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this final rule.

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 AD 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 AD, 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 AD. 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

EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA Emergency AD 2023-0219-E, dated
December 19, 2023 (EASA Emergency AD 2023-0219-E) (also referred to as
the MCAI), to correct an unsafe condition on certain Pilatus Model PC-
24 airplanes. The MCAI states it was determined that the titanium
threaded bolts at the forward end of the short rudder trim tab
actuating rods could be subject to unexpectedly high oscillating loads
due to aerodynamic forces acting on the rudder trim tab. If not
corrected, this condition could lead to failure of the bolt with
consequent damage to the rudder and rudder trim tab, which could result
in loss of rudder control and reduced or loss of control of the
airplane. The MCAI identifies the affected parts as titanium threaded
bolts, part number (P/N) 527.20.24.489, installed on the rudder trim
tab short control rods. The MCAI identifies the serviceable part as any
threaded titanium bolt, having P/N 527.20.24.489 that is new and not
previously installed. To address the unsafe condition, Pilatus, pending
the development of a new design installation, issued Pilatus PC-24
Service Bulletin 27-009, dated December 18, 2023, which specifies
instructions to replace the affected part and a one-time inspection of
the rudder mass balance arm and other elements of the rudder trim tab
installation for correct attachment, damage, cracks, deformation,
surface finish, and corrosion on any surrounding parts. The MCAI
requires periodic replacement of affected parts, a one-time inspection
of the rudder mass balance arm and other elements of the rudder trim
tab installation and, depending on findings, accomplishment of
applicable corrective actions.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2023-2404.

Related Service Information Under 1 CFR Part 51

EASA Emergency AD 2023-0219-E specifies procedures for periodic
replacement of affected parts, a one-time inspection of the rudder mass
balance arm and other elements of the rudder trim tab installation and,
depending on findings, accomplishment of applicable corrective actions.
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 ADDRESSES.

FAA's Determination

These products have been approved by the 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, it has notified the FAA of the unsafe condition described in
the MCAI described above. The FAA is issuing this AD after determining
that the unsafe condition described previously is likely to exist or
develop on other products of the same type design.

AD Requirements


This AD requires accomplishing the actions specified in EASA
Emergency AD 2023-0219-E, described previously, as incorporated by
reference, except for any differences identified as exceptions in the
regulatory text of this AD and except as discussed under ``Differences
Between this AD and EASA Emergency AD 2023-0219-E.''

Differences Between This AD and EASA Emergency AD 2023-0219-E

Paragraph (4) of EASA Emergency AD 2023-0219-E requires contacting
Pilatus for corrective actions if damage is found on the rudder mass balance
arm during the one-time inspection, but this AD requires approval for
corrective actions in accordance with a method approved by the Manager,
International Validation Branch, FAA; EASA; or Pilatus' EASA Design
Organization Approval (DOA). If approved by the DOA, the approval must
include the DOA-authorized signature.

Interim Action

The FAA considers that this AD is an interim action. If final
action is later identified, the FAA might consider further rulemaking.

Justification for Immediate Adoption and Determination of the Effective
Date


Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and
comment procedures for rules when the agency, for ``good cause,'' finds
that those procedures are ``impracticable, unnecessary, or contrary to
the public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without providing notice and seeking
comment prior to issuance. Further, section 553(d) of the APA
authorizes agencies to make rules effective in less than thirty days,
upon a finding of good cause.
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies forgoing notice and comment prior to adoption of this rule
because failure of titanium threaded bolts installed at the forward end
of the short rudder trim tab actuating rods, if not addressed, could
lead to damage to the rudder and rudder trim tab, which could result in
loss of rudder control and reduced or loss of control of the airplane.
Analysis shows that these bolts could fail without notice once the
airplane accumulates 300 hours time-in-service (TIS) and of the 112
airplanes affected by this AD, 75 have already accumulated more than
300 hours TIS and need these bolts replaced within 10 hours TIS after
the effective date of this AD. Accordingly, notice and opportunity for
prior public comment are impracticable and contrary to the public
interest pursuant to 5 U.S.C. 553(b)(3)(B).
In addition, the FAA finds that good cause exists pursuant to 5
U.S.C. 553(d) for making this amendment effective in less than 30 days,
for the same reasons the FAA found good cause to forgo notice and
comment.

Regulatory Flexibility Act

The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because the FAA has determined
that it has good cause to adopt this rule without prior notice and
comment, RFA analysis is not required.

Costs of Compliance

The FAA estimates that this AD affects 112 airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:

Estimated Costs

Action Labor cost Parts cost Cost per product Cost on U.S. operators
Replacement of affected titanium threaded bolts 9 work-hours x $85 per hour = $765 per replacement cycle $220 per replacement cycle $985 per replacement cycle $110,320 per replacement cycle
Inspection of rudder mass balance arm and other elements of the rudder trim tab installation 1 work-hour x $85 per hour = $85 $0 $85 $9,520

The corrective actions that may be required as a result of the
inspection could vary significantly from airplane to airplane. The FAA
has no data to determine the costs to accomplish the corrective actions
or the number of airplanes that may require corrective actions.
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, and
(2) Will not affect intrastate aviation in Alaska.

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

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]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive: