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Federal Register / Vol. 86, No. 166 / Tuesday, August 31, 2021 / Rules and Regulations a. Removing Airworthiness Directive AD 20171213, Amendment 39
18928 82 FR 27983, June 20, 2017; and b. Adding the following new AD:

20171703 Airbus SAS: Amendment 39
21686; Docket No. FAA20210334;
Project Identifier MCAI202001662T.
a Effective Date This airworthiness directive AD is effective October 5, 2021.
b Affected ADs This AD replaces AD 20171213, Amendment 3918928 82 FR 27983, June 20, 2017.
c Applicability This AD applies to Airbus SAS airplanes specified in paragraphs c1 through 3 of this AD, certificated in any category, as identified in European Union Aviation Safety Agency EASA AD 20200280, dated December 14, 2020 EASA AD 20200280.
1 Model A318111, 112 and 122
airplanes.
2 Model A319111, 112, 113, 114, 115, 131, 132, and 133 airplanes.
3 Model A320211, 212, 214, 231, 232, and 233 airplanes.
d Subject Air Transport Association ATA of America Code 53, Fuselage.

i No Reporting Requirement
e Reason This AD was prompted by a report of a crack found during an inspection of the pocket radius of the fuselage frame, and a determination that similar cracks may develop in nearby areas of the fuselage frame and that additional airplanes are subject to the unsafe condition. The FAA is issuing this AD to address cracking of the pocket radius, which could lead to in-flight decompression of the airplane and possible injury to the passengers.
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 20200280.

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h Exceptions to EASA AD 20200280
1 Where EASA AD 20200280 refers to its effective date, this AD requires using the effective date of this AD.
2 Where paragraph 9 of EASA AD 2020
0280 specifies if any crack is found during any inspection to contact Airbus for approved repair instructions and accomplish those instructions accordingly, this AD
requires if any cracking is found, 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
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EASA Design Organization Approval DOA.
If approved by the DOA, the approval must include the DOA-authorized signature.
3 Where paragraph 10 of EASA AD
20200280 specifies credit for actions in accordance with the instructions of an Airbus Repair Design Approval Sheet RDAS, and to accomplish the next inspection of each repaired area in accordance with the instructions of, and within the compliance time as specified in, the applicable RDAS, this AD requires using in accordance with repair instructions approved, and within the compliance time specified in the repair approval, using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SASs EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
4 Where paragraph 11 of EASA AD
20200280 specifies terminating actions apply only if specified in the Airbus RDAS
instructions for a repaired aeroplane, this AD requires using in repair instructions approved using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SASs EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
5 The Remarks section of EASA AD
20200280 does not apply to this AD.
Although the service information referenced in EASA AD 20200280 specifies to submit certain information to the manufacturer, this AD does not include that requirement.
j Other FAA 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 Airbus SASs EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
3 Required for Compliance RC: Except as required by paragraph j2 of this AD, if
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any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are 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 procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC.
k Related Information For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 2062313223; email Sanjay.Ralhan@
faa.gov.
l 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. 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 20200280, dated December 14, 2020.
ii Reserved 3 For EASA AD 20200280, 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. This material may be found in the AD docket on the internet at https
www.regulations.gov by searching for and locating Docket No. FAA20210334.
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 August 4, 2021.
Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202118702 Filed 83021; 8:45 am BILLING CODE 491013P

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