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Federal Register / Vol. 86, No. 222 / Monday, November 22, 2021 / Rules and Regulations
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.

f Compliance Comply with this AD within the compliance times specified, unless already done.

List of Subjects in 14 CFR Part 39

h Exceptions to EASA AD 20210237E
1 Where EASA AD 20210237E refers to its effective date, this AD requires using the effective date of this AD.
2 The Remarks section of EASA AD
20210237E does not apply to this AD.
3 For this AD, the safety seal installation only may be deferred up to 750 flight hours or 6 months, whichever occurs first, after the effective date of this AD, if the safety seal is not available at the time of the snap wire installation.

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 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

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

20212407 ATRGIE Avions de Transport Regional: Amendment 39
21828; Docket No. FAA20211008;
Project Identifier MCAI202101210T.
a Effective Date This airworthiness directive AD is effective November 22, 2021.
b Affected ADs None.
c Applicability This AD applies to the ATRGIE Avions de Transport Regional airplanes specified in paragraphs c1 and 2 of this AD, certificated in any category, as identified in European Union Aviation Safety Agency EASA Emergency AD 20210237E, dated November 4, 2021 EASA AD 20210237E.
1 Model ATR42200, 300, 320, and 500 airplanes.
2 Model ATR72101, 102, 201, 202, 211, 212, and 212A airplanes.

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d Subject Air Transport Association ATA of America Code 26, Fire protection.
e Unsafe Condition This AD was prompted by a report of a certain procedure in the aircraft maintenance manual AMM that incorrectly described a visual inspection of the fire handle. The FAA
is issuing this AD to address snap wires made of incorrect material, which, if not detected and corrected, and combined with an engine fire, could lead to a failure of the engine fire handle to operate, possibly resulting in an uncontrolled engine fire and reduced control of the airplane.

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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 20210237E.

i No Reporting Requirement Although the service information referenced in EASA AD 20210237E
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, Large Aircraft Section, 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 Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph k of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. 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, Large Aircraft Section, International Validation Branch, FAA; or EASA; or ATRGIE Avions de Transport Regionals EASA Design Organization Approval DOA. If approved by the DOA, the approval must include the DOAauthorized signature.
k Related Information For more information about this AD, contact Shahram Daneshmandi, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 2062313220; email Shahram.Daneshmandi@faa.gov.
l Material Incorporated by Reference 1 The Director of the Federal Register approved the incorporation by reference of
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the service information listed in this paragraph under 5 U.S.C. 552a and 1 CFR
part 51.
2 You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise.
i European Union Aviation Safety Agency EASA Emergency AD 20210237E, dated November 4, 2021.
ii Reserved 3 For EASA AD 20210237E, contact EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https
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 2062313195.
5 You may view this material that is incorporated by reference at the National Archives and Records Administration NARA. For information on the availability of this material at NARA, email fr.inspection@nara.gov, or go to: https
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on November 12, 2021.
Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202125494 Filed 111821; 11:15 am BILLING CODE 491013P

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20211011; Project Identifier MCAI202100867R; Amendment 3921830; AD 20212409
RIN 2120AA64

Airworthiness Directives; Bell Textron Canada Limited Helicopters Federal Aviation Administration FAA, DOT.
ACTION: Final rule; request for comments.
AGENCY:

The FAA is adopting a new airworthiness directive AD for certain Bell Textron Canada Limited Model 430
helicopters. This AD was prompted by an in-flight failure of the main rotor M/
R pitch link clevis clevis due to fatigue damage and excessive wear. This AD requires a visual inspection of the M/R clevis, rod end, and a certain partnumbered universal bearing, performing a purge grease, and performing a magnetic particle inspection of each M/
R clevis. Depending on the visual
SUMMARY:

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