Airworthiness Directives; Airbus SAS Airplanes, 72171-72174 [2021-27707]

Download as PDF Federal Register / Vol. 86, No. 242 / Tuesday, December 21, 2021 / Rules and Regulations (1) The substituted intermediary is eligible to receive the assistance approved for the original intermediary; (2) The substituted intermediary bears a close and genuine relationship to the original intermediary; and (3) The need for and scope of the project and the purposes for which Agency IRP loan funds will be used remain substantially unchanged. jspears on DSK121TN23PROD with RULES1 § 4274.352 Loan documentation for ultimate recipients. (a) Agency IRP loans. Prior Agency concurrence is required when an intermediary makes loans to an ultimate recipient from its Agency IRP loan funds (this applies to each Agency IRP loan received). A request for Agency concurrence in approval of a proposed loan to an ultimate recipient, whether made directly or through a loan participation purchase, must contain or comply with, as appropriate, the items identified in paragraph (b)(1) through (5) of this section and must include information listed in the IRP Revolving Loan Fund File Checklist, on the Agency website at the USDA Rural Development Intermediary Relending Program website: (1) Certification by the intermediary that: (i) The ultimate recipient is eligible for the loan; (ii) The loan is for an eligible purpose; (iii) Agency IRP loan funds are not more than 75 percent of the total project costs; (iv) The loan complies with all applicable statutes and regulations; (v) The ultimate recipient is unable to finance the proposed project through commercial credit or other Federal, State, or local programs at reasonable rates and terms; and (vi) The intermediary and its principal officers (including immediate family) hold no legal or financial interest or influence in the ultimate recipient, and the ultimate recipient and its principal officers (including immediate family) hold no legal or financial interest or influence in the intermediary. The interest and influence of a cooperative member when the intermediary is a cooperative is an allowable exception to this paragraph. (2) A completed and executed request for environmental information on a form provided by the Agency for projects that meet the criteria for a NEPA review categorical exclusion, NEPA environmental assessment or NEPA environmental impact statement in accordance with § 4274.305(b)(2). (3) All comments obtained in accordance with § 4274.305(a) regarding intergovernmental consultation (if required). VerDate Sep<11>2014 17:14 Dec 20, 2021 Jkt 256001 (4) Copies of sufficient material from the ultimate recipient’s application and the intermediary’s related files to allow the Agency to determine the: (i) Name, address, DUNS number, Federal ID number, and North American Classification System (NAICS) Code of the ultimate recipient; (ii) Loan purpose; (iii) Interest rate and term; (iv) Location, nature, and scope of the project being financed; (v) Uses and sources of funds; and (vi) Nature and lien priority of the collateral. (5) Such other information as the Agency may request. (b) Revolved IRP loan funds. An intermediary may use revolved funds to make loans to ultimate recipients in accordance with § 4274.320(b) without obtaining prior Agency concurrence as required in § 4274.352(a) and are also exempted from completion of items required by paragraphs (a)(2) and (3) of this section. 72171 Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. cracking of the area, and corrective action if necessary, 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 becomes effective January 5, 2022. The Director of the Federal Register approved the incorporation by reference of a certain publication 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: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For material incorporated by reference (IBR) in this AD, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this IBR material on the EASA website at https://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 in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–1065. The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. This AD was prompted by the determination that fatigue cracking may occur at the wing manhole access panel attachment holes at certain wing skin panels on airplanes with Sharklets or its structural reinforcements installed. This AD requires repetitive inspections for Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–1065; 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 AD, the mandatory continuing airworthiness information (MCAI), any comments received, and other information. The street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, § 4274.353–§ 4274.359 [Reserved] Karama Neal, Administrator, Rural Business-Cooperative Service. [FR Doc. 2021–27522 Filed 12–20–21; 8:45 am] BILLING CODE 3410–XY–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–1065; Project Identifier MCAI–2021–01264–T; Amendment 39–21858; AD 2021–25–14] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY: SUMMARY: PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 E:\FR\FM\21DER1.SGM 21DER1 72172 Federal Register / Vol. 86, No. 242 / Tuesday, December 21, 2021 / Rules and Regulations Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223; email Sanjay.Ralhan@faa.gov. SUPPLEMENTARY INFORMATION: jspears on DSK121TN23PROD with RULES1 Comments Invited The FAA invites you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2021–1065; Project Identifier MCAI–2021–01264–T’’ at the beginning of your comments. The most helpful comments reference a specific portion of the final rule, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this final rule because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this final rule. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this AD contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this AD, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this AD. Submissions containing CBI should be sent to Sanjay Ralhan, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223; email Sanjay.Ralhan@ faa.gov. Any commentary that the FAA receives that is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background EASA, which is the Technical Agent for the Member States of the European VerDate Sep<11>2014 17:14 Dec 20, 2021 Jkt 256001 Union, has issued EASA AD 2021–0256, dated November 16, 2021 (EASA AD 2021–0256) (also referred to as the MCAI), to correct an unsafe condition for all Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –215, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. Model A320–215 airplanes are not certificated by the FAA and are not included on the U.S. type certificate data sheet; this AD therefore does not include those airplanes in the applicability. 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. See the MCAI for additional background information. Related Service Information Under 1 CFR Part 51 EASA AD 2021–0256 specifies procedures for repetitive detailed visual inspections to detect discrepancies (cracking) of the left-hand and righthand wing manhole access panel attachment holes in the bottom wing skin panels 2, between rib 13 and rib 23. 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. FAA’s Determination These products have been approved by the 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, it has notified the FAA of the unsafe condition described in the MCAI described above. The FAA is issuing this AD after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type designs. Requirements of This AD This AD requires accomplishing the actions specified in EASA AD 2021– 0256 described previously, except for any differences identified as exceptions in the regulatory text of this AD. PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 Explanation of Required Compliance Information In the FAA’s ongoing efforts to improve the efficiency of the AD process, the FAA developed a process to use some civil aviation authority (CAA) ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. The FAA has been coordinating this process with manufacturers and CAAs. As a result, EASA AD 2021–0256 is incorporated by reference in this AD. This AD requires compliance with EASA AD 2021–0256 in its entirety through that incorporation, except for any differences identified as exceptions in the regulatory text of this AD. Using common terms that are the same as the heading of a particular section in EASA AD 2021–0256 does not mean that operators need comply only with that section. For example, where the AD requirement refers to ‘‘all required actions and compliance times,’’ compliance with this AD requirement is not limited to the section titled ‘‘Required Action(s) and Compliance Time(s)’’ in EASA AD 2021–0256. Service information required by EASA AD 2021–0256 for compliance will be available at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–1065 after this AD is published. Interim Action The FAA considers this AD interim action. If final action is later identified, the FAA might consider further rulemaking then. FAA’s Justification and Determination of the Effective Date Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 U.S.C. 551 et seq.) authorizes agencies to dispense with notice and comment procedures for rules when the agency, for ‘‘good cause,’’ finds that those procedures are ‘‘impracticable, unnecessary, or contrary to the public interest.’’ Under this section, an agency, upon finding good cause, may issue a final rule without providing notice and seeking comment prior to issuance. Further, section 553(d) of the APA authorizes agencies to make rules effective in less than thirty days, upon a finding of good cause. An unsafe condition exists that requires the immediate adoption of this AD without providing an opportunity for public comments prior to adoption. The FAA has found that the risk to the flying public justifies forgoing notice and comment prior to adoption of this rule because fatigue cracking at the wing E:\FR\FM\21DER1.SGM 21DER1 Federal Register / Vol. 86, No. 242 / Tuesday, December 21, 2021 / Rules and Regulations 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 are installed, could lead to crack propagation, possibly resulting in reduced structural integrity of the wings. In addition, the compliance time for the required action is shorter than the time necessary for the public to comment and for publication of the final rule. Accordingly, notice and opportunity for prior public comment are impracticable and contrary to the public interest pursuant to 5 U.S.C. 553(b)(3)(B). In addition, the FAA finds that good cause exists pursuant to 5 U.S.C. 553(d) for making this amendment effective in less than 30 days, for the same reasons the FAA found good cause to forgo notice and comment. Regulatory Flexibility Act (RFA) The requirements of the RFA do not apply when an agency finds good cause 72173 pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and comment. Because the FAA has determined that it has good cause to adopt this rule without notice and comment, RFA analysis is not required. Costs of Compliance The FAA estimates that this AD affects 1,463 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS * Labor cost Cost per product Parts cost 14 work-hours × $85 per hour = $1,190 ...................... $0 $1,190 Cost on U.S. operators $1,740,970 per inspection cycle. * Table does not include estimated costs for reporting inspection results. The FAA estimates that it takes 1 work-hour per product to comply with the reporting requirement in this AD. The average labor rate is $85 per hour. Based on these figures, the FAA estimates the cost of reporting the inspection results on U.S. operators to be $124,355, or $85 per product, per inspection cycle. The FAA has received no definitive data on which to base the cost estimates for the on-condition actions specified in this AD. jspears on DSK121TN23PROD with RULES1 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. VerDate Sep<11>2014 17:14 Dec 20, 2021 Jkt 256001 Authority for This Rulemaking List of Subjects in 14 CFR Part 39 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. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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, and (2) Will not affect intrastate aviation in Alaska. PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2021–25–14 Airbus SAS: Amendment 39– 21858; Docket No. FAA–2021–1065; Project Identifier MCAI–2021–01264–T. (a) Effective Date This airworthiness directive (AD) is effective January 5, 2022. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus SAS airplanes identified in paragraphs (c)(1) through (3) of this AD and certificated in any category. (1) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (2) Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes. (3) Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. E:\FR\FM\21DER1.SGM 21DER1 72174 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 2021–0256, dated November 16, 2021 (EASA AD 2021–0256). jspears on DSK121TN23PROD with RULES1 (h) Exceptions to EASA AD 2021–0256 (1) Where EASA AD 2021–0256 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 SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (4) Paragraph (3) of EASA AD 2021–0256 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 (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) The ‘‘Remarks’’ section of EASA AD 2021–0256 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 VerDate Sep<11>2014 17:14 Dec 20, 2021 Jkt 256001 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 SAS’s 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 (i)(2) of this AD, if any service information referenced in EASA AD 2021–0256 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 operator’s 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– 231–3223; 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. 552(a) 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 2021–0256, dated November 16, 2021. (ii) [Reserved] (3) For EASA AD 2021–0256, 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 206–231–3195. PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 (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. 2021–27707 Filed 12–17–21; 11:15 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–1064; Project Identifier MCAI–2021–01028–T; Amendment 39–21856; AD 2021–25–12] RIN 2120–AA64 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) 2017–19– 09, which applied to certain De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Model DHC–8–400 series airplanes. AD 2017–19–09 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: E:\FR\FM\21DER1.SGM 21DER1

Agencies

[Federal Register Volume 86, Number 242 (Tuesday, December 21, 2021)]
[Rules and Regulations]
[Pages 72171-72174]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-27707]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-1065; Project Identifier MCAI-2021-01264-T; 
Amendment 39-21858; AD 2021-25-14]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and 
-232 airplanes. This AD was prompted by the determination that fatigue 
cracking may occur at the wing manhole access panel attachment holes at 
certain wing skin panels on airplanes with Sharklets or its structural 
reinforcements installed. This AD requires repetitive inspections for 
cracking of the area, and corrective action if necessary, 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 becomes effective January 5, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication 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:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For material incorporated by reference (IBR) in this AD, contact 
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
8999 000; email [email protected]; internet www.easa.europa.eu. You 
may find this IBR material on the EASA website at https://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 in the AD docket at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2021-1065.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-1065; 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 AD, the mandatory 
continuing airworthiness information (MCAI), any comments received, and 
other information. The street address for Docket Operations is listed 
above.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,

[[Page 72172]]

Large Aircraft Section, FAA, International Validation Branch, 2200 
South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223; 
email [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
ADDRESSES. Include ``Docket No. FAA-2021-1065; Project Identifier MCAI-
2021-01264-T'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the final rule, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this final rule because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this final rule.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this AD contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this AD, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this AD. Submissions containing CBI should be sent to Sanjay 
Ralhan, Aerospace Engineer, Large Aircraft Section, FAA, International 
Validation Branch, 2200 South 216th St., Des Moines, WA 98198; 
telephone and fax 206-231-3223; email [email protected]. Any 
commentary that the FAA receives that is not specifically designated as 
CBI will be placed in the public docket for this rulemaking.

Background

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2021-0256, dated November 16, 2021 
(EASA AD 2021-0256) (also referred to as the MCAI), to correct an 
unsafe condition for all Model A319-111, -112, -113, -114, -115, -131, 
-132, and -133 airplanes; Model A320-211, -212, -214, -215, -216, -231, 
-232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes. Model A320-215 airplanes are not 
certificated by the FAA and are not included on the U.S. type 
certificate data sheet; this AD therefore does not include those 
airplanes in the applicability.
    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. See the MCAI for additional 
background information.

Related Service Information Under 1 CFR Part 51

    EASA AD 2021-0256 specifies procedures for repetitive detailed 
visual inspections to detect discrepancies (cracking) of 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. 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.

FAA's Determination

    These products have been approved by the 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, it has notified the FAA of the unsafe condition described in 
the MCAI described above. The FAA is issuing this AD after determining 
that the unsafe condition described previously is likely to exist or 
develop on other products of the same type designs.

Requirements of This AD

    This AD requires accomplishing the actions specified in EASA AD 
2021-0256 described previously, except for any differences identified 
as exceptions in the regulatory text of this AD.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA developed a process to use some civil aviation 
authority (CAA) ADs as the primary source of information for compliance 
with requirements for corresponding FAA ADs. The FAA has been 
coordinating this process with manufacturers and CAAs. As a result, 
EASA AD 2021-0256 is incorporated by reference in this AD. This AD 
requires compliance with EASA AD 2021-0256 in its entirety through that 
incorporation, except for any differences identified as exceptions in 
the regulatory text of this AD. Using common terms that are the same as 
the heading of a particular section in EASA AD 2021-0256 does not mean 
that operators need comply only with that section. For example, where 
the AD requirement refers to ``all required actions and compliance 
times,'' compliance with this AD requirement is not limited to the 
section titled ``Required Action(s) and Compliance Time(s)'' in EASA AD 
2021-0256. Service information required by EASA AD 2021-0256 for 
compliance will be available at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-1065 after this AD is 
published.

Interim Action

    The FAA considers this AD interim action. If final action is later 
identified, the FAA might consider further rulemaking then.

FAA's Justification and Determination of the Effective Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and 
comment procedures for rules when the agency, for ``good cause,'' finds 
that those procedures are ``impracticable, unnecessary, or contrary to 
the public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than thirty days, 
upon a finding of good cause.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies forgoing notice and comment prior to adoption of this rule 
because fatigue cracking at the wing

[[Page 72173]]

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 are installed, could lead to crack 
propagation, possibly resulting in reduced structural integrity of the 
wings. In addition, the compliance time for the required action is 
shorter than the time necessary for the public to comment and for 
publication of the final rule. Accordingly, notice and opportunity for 
prior public comment are impracticable and contrary to the public 
interest pursuant to 5 U.S.C. 553(b)(3)(B).
    In addition, the FAA finds that good cause exists pursuant to 5 
U.S.C. 553(d) for making this amendment effective in less than 30 days, 
for the same reasons the FAA found good cause to forgo notice and 
comment.

Regulatory Flexibility Act (RFA)

    The requirements of the RFA do not apply when an agency finds good 
cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and 
comment. Because the FAA has determined that it has good cause to adopt 
this rule without notice and comment, RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 1,463 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                     Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
                                                                   Cost per
                  Labor cost                      Parts cost        product          Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
14 work-hours x $85 per hour = $1,190.........              $0          $1,190  $1,740,970 per inspection cycle.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting inspection results.

    The FAA estimates that it takes 1 work-hour per product to comply 
with the reporting requirement in this AD. The average labor rate is 
$85 per hour. Based on these figures, the FAA estimates the cost of 
reporting the inspection results on U.S. operators to be $124,355, or 
$85 per product, per inspection cycle.
    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition actions specified in this AD.

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, and
    (2) Will not affect intrastate aviation in Alaska.

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:

2021-25-14 Airbus SAS: Amendment 39-21858; Docket No. FAA-2021-1065; 
Project Identifier MCAI-2021-01264-T.

(a) Effective Date

    This airworthiness directive (AD) is effective January 5, 2022.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus SAS airplanes identified in 
paragraphs (c)(1) through (3) of this AD and certificated in any 
category.
    (1) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (2) Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes.
    (3) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

[[Page 72174]]

(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 
2021-0256, dated November 16, 2021 (EASA AD 2021-0256).

(h) Exceptions to EASA AD 2021-0256

    (1) Where EASA AD 2021-0256 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 SAS's EASA Design Organization Approval 
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.
    (4) Paragraph (3) of EASA AD 2021-0256 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 (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) The ``Remarks'' section of EASA AD 2021-0256 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 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: [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, Large Aircraft 
Section, International Validation Branch, FAA; or EASA; or Airbus 
SAS's 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 (i)(2) of this AD, if any service information referenced 
in EASA AD 2021-0256 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 operator's 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 206-231-3223; email [email protected].

(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. 552(a) 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 2021-0256, 
dated November 16, 2021.
    (ii) [Reserved]
    (3) For EASA AD 2021-0256, contact EASA, Konrad-Adenauer-Ufer 3, 
50668 Cologne, Germany; telephone +49 221 8999 000; email 
[email protected]; 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 206-231-3195.
    (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 
[email protected], or go to https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on December 3, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-27707 Filed 12-17-21; 11:15 am]
BILLING CODE 4910-13-P
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