Airworthiness Directives; ATR-GIE Avions de Transport Régional Airplanes

[Federal Register Volume 91, Number 156 (Friday, August 14, 2026)]
[Rules and Regulations]
[Pages 52484-52487]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-16657]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2026-3878; Project Identifier MCAI-2025-00913-T; 
Amendment 39-23437; AD 2026-16-07]
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 superseding Airworthiness Directive (AD) 2023-21-
10, which applied to certain ATR-GIE Avions de Transport 
R[eacute]gional Model ATR42-500 and ATR72-212A airplanes. AD 2023-21-10 
required an inspection of the horizontal stabilizer (HS) left- and 
right-hand leading edge lateral ribs, the box in between, the center 
box upper panel, and HS forward back-up fitting for discrepancies and 
applicable corrective action. Since the FAA issued AD 2023-21-10, it 
was determined that additional airplanes are affected and additional 
areas must be inspected. This AD continues to require the actions in AD 
2023-21-10 and requires expanding the applicability and inspecting the 
HS front spar web and center box internal area for discrepancies and 
accomplishing applicable corrective actions. The FAA is issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective September 18, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 18, 
2026.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2026-3878; 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; telephone +49 221 8999 000; email [email protected]. 
You may find this material on the EASA website at ad.easa.europa.eu.
    <bullet> For ATR-GIE Avions de Transport R[eacute]gional material 
identified in this AD, contact ATR--GIE Avions de Transport 
R[eacute]gional, 1 All[eacute]e Pierre Nadot, 31712 Blagnac Cedex, 
France; telephone +33 (0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 
email continued.airworthiness@atr aircraft.com; website atr-
aircraft.com.
    <bullet> 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-2026-3878.

FOR FURTHER INFORMATION CONTACT: Christopher Spencer, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
phone: 516-228-7332; email: [email protected].

[[Page 52485]]


SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2023-21-10, Amendment 39-22582 (88 FR 
83820, December 1, 2023) (AD 2023-21-10). AD 2023-21-10 applied to 
certain ATR-GIE Avions de Transport R[eacute]gional Model ATR42-500 and 
ATR72-212A airplanes. AD 2023-21-10 required an inspection of the HS 
affected areas (HS left-hand and right-hand leading edge lateral ribs, 
the box in between, the center box upper panel, and HS forward back-up 
fitting) for discrepancies and applicable corrective action. The FAA 
issued AD 2023-21-10 to address loose, missing, or incorrectly 
installed fasteners, composite delamination, and cracks in the HS. The 
unsafe condition, if not addressed, could result in reduced structural 
integrity of the airplane.
    The NPRM was published in the Federal Register on May 4, 2026 (91 
FR 23919). The NPRM was prompted by EASA AD 2025-0110, dated May 14, 
2025 (EASA AD 2025-0110) (also referred to as the MCAI), issued by 
EASA, which is the Technical Agent for the Member States of the 
European Union. The MCAI states that it has been determined that 
additional airplane serial numbers are affected and that the HS front 
spar web and center box internal area also needs to be inspected to 
address loose, missing, or incorrectly installed fasteners, composite 
delamination, and cracks in the HS.
    In the NPRM, the FAA proposed to continue to require the actions in 
AD 2023-21-10 and require expanding the applicability and inspecting 
the HS front spar web and center box internal area for discrepancies 
and accomplishing applicable corrective actions, as specified in EASA 
AD 2025-0110. 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-2026-3878.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from the Air Line Pilots Association, 
International (ALPA) who supported the NPRM without change.

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, 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 2025-0110 specifies procedures for a one-time detailed 
inspection of the HS left-hand and right-hand leading edge lateral 
ribs, the box in between the center box upper panel, HS forward back-up 
fitting, and the HS front spar web and center box internal area for 
discrepancies (i.e., any loose, missing, or incorrectly installed 
fasteners, any composite delamination, and any cracked fittings); and 
applicable corrective actions. Corrective actions include contacting 
the manufacturer for repair instructions if any discrepancy is detected 
during any inspection.
    The FAA also reviewed ATR Service Bulletin ATR42-55-0020, Revision 
03, dated January 31, 2025; ATR Service Bulletin ATR72-55-1013, 
Revision 03, dated January 31, 2025; ATR Service Bulletin ATR42-55-
0025, dated February 3, 2025; and ATR Service Bulletin ATR72-55-1018, 
dated February 3, 2025. This material identifies the affected airplane 
serial numbers.
    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 16 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2023-21-10...  8 work-hours x $85 per                $0            $680         $10,880
                                         hour = $680.
New actions...........................  14 work-hours x $85 per                0           1,190          19,040
                                         hour = $1,190.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition repairs specified in this AD.

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.

[[Page 52486]]

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:
0
a. Removing Airworthiness Directive (AD) 2023-21-10, Amendment 39-22582 
(88 FR 83820, December 1, 2023); and
0
b. Adding the following new AD:

2026-16-07 ATR-GIE Avions de Transport R[eacute]gional: Amendment 
39-23437; Docket No. FAA-2026-3878; Project Identifier MCAI-2025-
00913-T.

(a) Effective Date

    This airworthiness directive (AD) is effective September 18, 
2026.

(b) Affected ADs

    This AD replaces AD 2023-21-10, Amendment 39-22582 (88 FR 83820, 
December 1, 2023) (AD 2023-21-10).

(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 ATR Service Bulletin ATR42-55-0020, 
Revision 03, dated January 31, 2025; ATR Service Bulletin ATR72-55-
1013, Revision 03, dated January 31, 2025; ATR Service Bulletin 
ATR42-55-0025, dated February 3, 2025; or ATR Service Bulletin 
ATR72-55-1018, dated February 3, 2025; as applicable.

(d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by reports of loose fasteners and cracks in 
the horizontal stabilizer (HS) left- and right-hand leading edge 
lateral ribs, the box in between, the center box upper panel, and HS 
forward back-up fitting. This AD was also prompted by a 
determination that additional airplanes are affected by the unsafe 
condition, and that the HS front spar web and center box internal 
area also need to be inspected. The FAA is issuing this AD to 
address loose, missing, or incorrectly installed fasteners, 
composite delamination, and cracks in the HS. 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 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 
2025-0110, dated May 14, 2025 (EASA AD 2025-0110).

(h) Exceptions to EASA AD 2025-0110

    (1) Where the Groups definition for Group 3 airplanes in EASA AD 
2025-0110 refers to ``the SB2'', this AD requires replacing this 
text with ``ATR Service Bulletin ATR42-55-0025, dated February 3, 
2025; or ATR Service Bulletin ATR72-55-1018, dated February 3, 2025; 
as applicable''.
    (2) Where EASA AD 2025-0110 refers to ``06 July 2023 [the 
effective date of EASA AD 2023-0125],'' this AD requires using 
January 5, 2024 (the effective date of AD 2023-21-10).
    (3) Where EASA AD 2025-0110 refers to its effective date, this 
AD requires using the effective date of this AD.
    (4) Where paragraph (2) of EASA AD 2025-0110 specifies if ``any 
discrepancy as defined in the SB1 or the SB2, as applicable, is 
detected, before next flight, contact ATR for approved repair 
instructions and, within the compliance time identified therein, 
accomplish those instructions accordingly. If no compliance time for 
the repair is identified in those instructions, accomplish those 
instructions before next flight.'', this AD requires replacing that 
text with ``any discrepancy other than cracking is detected, before 
next flight, contact ATR for approved repair instructions and, 
within the compliance time identified therein, accomplish those 
instructions accordingly, except if no compliance time for the 
repair is identified in those instructions, accomplish those 
instructions before next flight; and if any crack is detected, the 
crack must be repaired before further flight 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.''
    (5) This AD does not adopt the ``Remarks'' section of EASA AD 
2025-0110.

(i) No Reporting Requirement

    Although the material referenced in EASA AD 2025-0110 specifies 
to submit certain information to the manufacturer, this AD does not 
include that requirement.

(j) Additional AD Provisions

    The following provisions also apply to this AD:
    (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 (k) 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 DOA. If approved by the DOA, the approval 
must include the DOA-authorized signature.

(k) Additional Information

    For more information about this AD, contact Christopher Spencer, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: 516-228-7332; 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 this AD specifies otherwise.
    (i) ATR Service Bulletin ATR42-55-0020, Revision 03, dated 
January 31, 2025.
    (ii) ATR Service Bulletin ATR42-55-0025, dated February 3, 2025.
    (iii) ATR Service Bulletin ATR72-55-1013, Revision 03, dated 
January 31, 2025.
    (iv) ATR Service Bulletin ATR72-55-1018, dated February 3, 2025.
    (v) European Union Aviation Safety Agency (EASA) AD 2025-0110, 
dated May 14, 2025.
    (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]. You may find this material on 
the EASA website at ad.easa.europa.eu.
    (4) For ATR-GIE Avions de Transport R[eacute]gional material 
identified in this AD, contact ATR-GIE Avions de Transport 
R[eacute]gional, 1 All[eacute]e Pierre Nadot, 31712 Blagnac Cedex, 
France; telephone +33 (0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 
email continued.airworthiness@atr aircraft.com; website atr-
aircraft.com.
    (5) 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.
    (6) 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].


[[Page 52487]]


    Issued on July 30, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2026-16657 Filed 8-13-26; 8:45 am]
BILLING CODE 4910-13-P

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