[Federal Register Volume 90, Number 59 (Friday, March 28, 2025)]
[Rules and Regulations]
[Pages 14019-14022]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-05297]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-2416; Project Identifier MCAI-2024-00491-T;
Amendment 39-22999; AD 2025-06-11]
RIN 2120-AA64
Airworthiness Directives; ATR--GIE Avions de Transport
R[eacute]gional 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 ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500
and ATR72-212A airplanes. This AD was prompted by a report of the
possible use of improper material during the manufacturing of vertical
stabilizer to horizontal stabilizer junction fittings. This AD requires
inspections of affected parts, applicable repairs, and eventual
replacement of certain affected parts, as specified in a European Union
Aviation Safety Agency (EASA) 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 May 2, 2025.
[[Page 14020]]
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 2, 2025.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2024-2416; 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:
For EASA material identified in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +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.
You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the availability of this material at the
FAA, call 206-231-3195. It is also available at regulations.gov under
Docket No. FAA-2024-2416
FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone 206-231-3220; 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 ATR--GIE Avions
de Transport R[eacute]gional Model ATR42-500 and ATR72-212A airplanes.
The NPRM published in the Federal Register on November 1, 2024 (89 FR
87311). The NPRM was prompted by AD 2024-0171, dated August 27, 2024,
issued by EASA, which is the Technical Agent for the Member States of
the European Union (EASA AD 2024-0171) (also referred to as the MCAI).
The MCAI states that a report was received of the possible use of
improper material during the manufacturing of vertical stabilizer to
horizontal stabilizer junction fittings. Subsequent review identified
the population of affected parts and the airplanes equipped with those
affected parts. Vertical stabilizer to horizontal stabilizer junction
fittings manufactured with improper material, if not addressed, could
reduce the structural integrity of the airplane.
In the NPRM, the FAA proposed to require inspections of affected
parts, applicable repairs, and eventual replacement of certain affected
parts, as specified in EASA AD 2024-0171. 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-2024-2416.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
This product has been approved by the aviation authority of another
country and is 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
referenced above. The FAA reviewed the relevant data and determined
that air safety requires adopting this AD as proposed. Accordingly, the
FAA is issuing this AD to address the unsafe condition on this product.
Except for minor editorial changes, this AD is adopted as proposed in
the NPRM. None of the changes will increase the economic burden on any
operator.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2024-0171 specifies procedures for a special detailed
inspection (SDI) (conductivity measurement, hardness test, and X-ray
fluorescence (XRF) inspection) to determine the material tolerance of
affected vertical to horizontal stabilizer junction fittings installed
on group 1 or 2 airplanes; repair of parts not within the tolerances of
material AL7075-T73 (except those within the tolerances of material
AL7050-T7452); repetitive detailed visual inspections for any damage
(including corrosion and dents) of each affected part that is within
the tolerances of material AL7050-T7452 or is installed on a group 3
airplane; repair of damaged parts; and eventual replacement of any
affected part that is within the tolerances of material AL7050-T7452 or
installed on a group 3 airplane. EASA AD 2024-0171 also specifies
reporting the inspection results of the SDI to ATR. 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 36 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
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Labor cost Parts cost Cost per product Cost on U.S. operators
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Up to 26 work-hours x $85 per hour $0 Up to $2,210.......... Up to $79,560.
= $2,210.
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The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any
required actions. The FAA has no way of determining the number of
aircraft that might need these on-condition actions:
Estimated Costs of On-Condition Actions
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Labor cost Parts cost Cost per product
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Up to 523 work-hours x $85 per hour = $6,340 $50,795
$44,455.............................
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[[Page 14021]]
The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs specified in this AD.
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some or all of the costs of
this AD may be covered under warranty, thereby reducing the cost impact
on affected operators.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to take
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, and completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Send comments regarding this burden estimate
or any other aspect of this collection of information, including
suggestions for reducing this burden, to: Information Collection
Clearance Officer, Federal Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177-1524.
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:
2025-06-11 ATR--GIE Avions de Transport R[eacute]gional: Amendment
39-22999; Docket No. FAA-2024-2416; Project Identifier MCAI-2024-
00491-T.
(a) Effective Date
This airworthiness directive (AD) is effective May 2, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to ATR--GIE Avions de Transport R[eacute]gional
Model ATR42-500 and ATR72-212A airplanes, certificated in any
category, as identified in European Union Aviation Safety Agency
(EASA) AD 2024-0171, dated August 27, 2024 (EASA AD 2024-0171).
(d) Subject
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by a report of the possible use of improper
material during the manufacturing of vertical stabilizer to
horizontal stabilizer junction fittings. The FAA is issuing this AD
to address the potential usage of improper material during the
manufacturing of vertical stabilizer to horizontal stabilizer
junction fittings. The unsafe condition, if not addressed, could
result in reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2024-0171.
(h) Exceptions to EASA AD 2024-0171
(1) Where EASA AD 2024-0171 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where paragraph (2) of EASA AD 2024-0171 specifies to
``accomplish a detailed visual inspection (DVI) of each affected
part in accordance with the instructions of ATR Maintenance
Procedure (MP) A-55-36-XX-02ZZZ-281Z-A'' for this AD replace that
text with ``accomplish a detailed visual inspection (DVI) for damage
of each affected part in accordance with the instructions of ATR
Maintenance Procedure (MP) A-55-36-XX-02ZZZ-281Z-A, and before
further flight repair any damage using a method approved by the
Manager, International Validation Branch, FAA; or EASA; or ATR--GIE
Avions de Transport R[eacute]gional's EASA Design Organization
Approval (DOA). If approved by the DOA, the approval must include
the DOA-authorized signature.''
(3) Where paragraph (4) of EASA AD 2024-0171 specifies to
``accomplish a DVI of the affected part in accordance with the
instructions of ATR MP A-55-36-XX-02ZZZ-281Z-A'' for this AD replace
that text with ``accomplish a DVI for damage of the affected part in
accordance with the instructions of ATR MP A-55-36-XX-02ZZZ-281Z-A,
and before further flight repair any damage using a method approved
by the Manager, International Validation Branch, FAA; or EASA; or
ATR--GIE Avions de Transport R[eacute]gional's EASA DOA. If approved
by the DOA, the approval must include the DOA-authorized
signature.''
(4) Paragraph (5) of EASA AD 2024-0171 specifies to report
inspection results to ATR within a certain compliance time. For this
AD, report inspection results at the applicable time specified in
paragraph (h)(4)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
(5) This AD does not adopt the ``Remarks'' section of EASA AD
2024-0171.
(i) Additional AD Provisions
The following provisions also apply to this AD:
[[Page 14022]]
(1) 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 responsible Flight Standards 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:
[email protected]. Before using any approved AMOC, notify your
appropriate principal inspector, or lacking a principal inspector,
the manager of the responsible Flight Standards Office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, International
Validation Branch, FAA; or EASA; or ATR--GIE Avions de Transport
R[eacute]gional's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.
(j) Additional Information
For more information about this AD, contact Shahram Daneshmandi,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: 206-231-3220; email:
[email protected].
(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 this AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2024-0171,
dated August 27, 2024.
(ii) [Reserved]
(3) For EASA material identified in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +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.
(4) You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th St.,
Des Moines, WA. For information on the availability of this material
at the FAA, call 206-231-3195.
(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 March 21, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2025-05297 Filed 3-27-25; 8:45 am]
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