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Federal Register / Vol. 86, No. 242 / Tuesday, December 21, 2021 / Rules and Regulations
e Unsafe Condition This AD was prompted by the determination that fatigue cracking may occur at the left-hand and right-hand wing manhole access panel attachment holes in the bottom wing skin panels 2, between rib 13 and rib 23, on airplanes with Sharklets or its structural reinforcements installed. The FAA is issuing this AD to address this condition, which could lead to crack propagation, possibly resulting in reduced structural integrity of the wings.
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, European Union Aviation Safety Agency EASA AD 20210256, dated November 16, 2021 EASA AD 20210256.

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h Exceptions to EASA AD 20210256
1 Where EASA AD 20210256 refers to its effective date, this AD requires using the effective date of this AD.
2 Where paragraph 1 of EASA AD 2021
0256 requires a DET detailed visual inspection of the affected areas, this AD
requires a detailed visual inspection to detect discrepancies cracking of the affected areas.
3 Where paragraph 2 of EASA AD 2021
0256 specifies to contact Airbus for approved instructions and . . . accomplish the specified instructions accordingly if discrepancies are detected, for this AD if any cracking is detected, the cracking must be repaired before further flight using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SASs EASA
Design Organization Approval DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
4 Paragraph 3 of EASA AD 20210256
specifies to report inspection results to Airbus within a certain compliance time. For this AD, report inspection results at the applicable time specified in paragraph h4i 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 The Remarks section of EASA AD
20210256 does not apply to this AD.
i 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
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information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph j 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 Airbus SASs EASA Design Organization Approval DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
3 Required for Compliance RC: Except as required by paragraph i2 of this AD, if any service information referenced in EASA
AD 20210256 that contains paragraphs that are labeled as RC, the instructions in RC
paragraphs, including subparagraphs under an RC paragraph, must be done to comply with this AD; any paragraphs, including subparagraphs under those paragraphs, that are not identified as RC are recommended.
The instructions in paragraphs, including subparagraphs under those paragraphs, not identified as RC may be deviated from using accepted methods in accordance with the operators maintenance or inspection program without obtaining approval of an AMOC, provided the instructions identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to instructions identified as RC require approval of an AMOC.
j Related Information For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206
2313223; email Sanjay.Ralhan@faa.gov.
k Material Incorporated by Reference 1 The Director of the Federal Register approved the incorporation by reference of 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 AD 20210256, dated November 16, 2021.
ii Reserved 3 For EASA AD 20210256, 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.

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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 December 3, 2021.
Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202127707 Filed 121721; 11:15 am BILLING CODE 491013P

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20211064; Project Identifier MCAI202101028T; Amendment 3921856; AD 20212512
RIN 2120AA64

Airworthiness Directives; De Havilland Aircraft of Canada Limited Type Certificate Previously Held by Bombardier, Inc. Airplanes Federal Aviation Administration FAA, Department of Transportation DOT.
ACTION: Final rule; request for comments.
AGENCY:

The FAA is superseding Airworthiness Directive AD 201719
09, which applied to certain De Havilland Aircraft of Canada Limited Type Certificate Previously Held by Bombardier, Inc. Model DHC8400
series airplanes. AD 20171909
required modifying the nose landing gear NLG shock strut assembly. This new AD requires repetitive lubrications of the trailing arm of the NLG. This new AD also requires revising the existing maintenance or inspection program to include new and revised airworthiness limitations life limits for certain bolts.
This AD was prompted by reports of a certain bolt being found missing or having stress corrosion cracking. The FAA is issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective January 5, 2022.
The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD
as of January 5, 2022.
The FAA must receive comments on this AD by February 4, 2022.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
SUMMARY:

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