Rule2023-28866
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
December 29, 2023
Effective
January 3, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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.
Full Text
<html>
<head>
<title>Federal Register, Volume 88 Issue 249 (Friday, December 29, 2023)</title>
</head>
<body><pre>
[Federal Register Volume 88, Number 249 (Friday, December 29, 2023)]
[Rules and Regulations]
[Pages 90091-90094]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2023-28866]
-----------------------------------------------------------------------
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.
[[Page 90092]]
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.
<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-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:
<bullet> For material identified in this final rule, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999
000; email: <a href="/cdn-cgi/l/email-protection#3b7a7f487b5e5a485a155e4e49544b5a155e4e"><span class="__cf_email__" data-cfemail="3d7c794e7d585c4e5c1358484f524d5c135848">[email protected]</span></a>; 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, 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 <a href="http://regulations.gov">regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#1c7873697b326e697873706c745c7a7d7d327b736a"><span class="__cf_email__" data-cfemail="02666d77652c7077666d6e726a426463632c656d74">[email protected]</span></a>.
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
<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 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 <a href="http://regulations.gov">regulations.gov</a> 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
[[Page 90093]]
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
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Replacement of affected titanium 9 work-hours x $85 $220 per $985 per $110,320 per
threaded bolts. per hour = $765 replacement cycle. replacement cycle. replacement
per replacement cycle.
cycle.
Inspection of rudder mass 1 work-hour x $85 $0................ $85............... $9,520.
balance arm and other elements per hour = $85.
of the rudder trim tab
installation.
----------------------------------------------------------------------------------------------------------------
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
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[[Page 90094]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
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 already done.
(g) Required Actions
Except as specified in paragraph (h) of this AD: Comply with all
required 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 compliance time(s) specified therein, accomplish those
instructions accordingly;'' for this AD, replace that text with
``accomplish corrective action in accordance with a method approved
by the Manager, International 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 Aircraft 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, replace 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: <a href="/cdn-cgi/l/email-protection#d4edf9958287f9959d86f9e3e7e4f995999b9794b2b5b5fab3bba2"><span class="__cf_email__" data-cfemail="221b0f6374710f636b700f1511120f636f6d61624443430c454d54">[email protected]</span></a>. 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:
<a href="/cdn-cgi/l/email-protection#ed8982988ac39f988982819d85ad8b8c8cc38a829b"><span class="__cf_email__" data-cfemail="d6b2b9a3b1f8a4a3b2b9baa6be96b0b7b7f8b1b9a0">[email protected]</span></a>.
(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: <a href="/cdn-cgi/l/email-protection#48090c3b082d293b29662d3d3a273829662d3d"><span class="__cf_email__" data-cfemail="56171225163337253778332324392637783323">[email protected]</span></a>; 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 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.
(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#5f392d7136312c2f3a3c2b3630311f313e2d3e71383029"><span class="__cf_email__" data-cfemail="6107134f080f1211040215080e0f210f0013004f060e17">[email protected]</span></a>.
Issued on December 22, 2023.
Caitlin Locke,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2023-28866 Filed 12-27-23; 4:15 pm]
BILLING CODE 4910-13-P
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on December 29, 2023.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.