Airworthiness Directives; Airbus SAS Airplanes, 64984-64987 [2020-22680]

Download as PDF 64984 Federal Register / Vol. 85, No. 199 / Wednesday, October 14, 2020 / Proposed Rules ApplianceStandardsQuestions@ ee.doe.gov. Signing Authority This document of the Department of Energy was signed on September 22, 2020, by Alexander N. Fitzsimmons, Deputy Assistant Secretary for Energy Efficiency, Energy Efficiency and Renewable Energy, pursuant to delegated authority from the Secretary of Energy. That document with the original signature and date is maintained by DOE. For administrative purposes only, and in compliance with requirements of the Office of the Federal Register, the undersigned DOE Federal Register Liaison Officer has been authorized to sign and submit the document in electronic format for publication, as an official document of the Department of Energy. This administrative process in no way alters the legal effect of this document upon publication in the Federal Register. Signed in Washington, DC, on September 22, 2020. Treena V. Garrett, Federal Register Liaison Officer, U.S. Department of Energy. [FR Doc. 2020–21280 Filed 10–13–20; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0914; Product Identifier 2020–NM–058–AD] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2018–16–02, which applies to all Airbus SAS Model A318–111 and –112 airplanes, Model A319–111, –112, –113, –114, and –115 airplanes, Model A320– 211, –212, –214, and –216 airplanes, and Model A321–111, –112, –211, –212, and –213 airplanes. AD 2018–16–02 requires modifying and re-identifying the aft engine mount assemblies. Since the FAA issued AD 2018–16–02, a modification has been developed for 4lug engines that the FAA has determined is necessary. This proposed AD would retain the requirement to modify and re-identify the 3-lug aft jbell on DSKJLSW7X2PROD with PRO_RULES SUMMARY: VerDate Sep<11>2014 17:18 Oct 13, 2020 Jkt 253001 engine mount assemblies and would include a new requirement to modify and re-identify the 4-lug aft engine mount assemblies, as specified in a European Union Aviation Safety Agency (EASA) AD, which will be incorporated by reference. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by November 30, 2020. 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 the material identified in this proposed AD that will be incorporated by reference (IBR), contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +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 IBR 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 on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0914. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0914; 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 NPRM, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3223; email: sanjay.ralhan@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2020–0914; Product Identifier 2020–NM–058–AD’’ at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. The FAA will consider all comments received by the closing date and may amend this NPRM based on those comments. The FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The FAA will also post a report summarizing each substantive verbal contact received about this NPRM. Discussion The FAA issued AD 2018–16–02, Amendment 39–19342 (83 FR 39326, August 9, 2018) (‘‘AD 2018–16–02’’), which applies to all Airbus SAS Model A318–111 and –112 airplanes, Model A319–111, –112, –113, –114, and –115 airplanes, Model A320–211, –212, –214, and –216 airplanes, and Model A321– 111, –112, –211, –212, and –213 airplanes. AD 2018–16–02 requires modifying and re-identifying the aft engine mount assemblies. The FAA issued AD 2018–16–02 to address nonconforming retainers of the aft engine mount. This condition could result in loss of the locking feature of the nuts of the inner and outer pins; loss of the pins will result in the aft mount engine link no longer being secured to the aft engine mount, possibly resulting in damage to the airplane. Actions Since AD 2018–16–02 Was Issued Since the FAA issued AD 2018–16– 02, a modification has been developed for 4-lug engines that the FAA has determined is necessary to address the unsafe condition. The proposed AD would retain the requirement to modify and re-identify the (3-lug) aft engine mount assemblies and would include a new requirement to modify and reidentify the (4-lug) aft engine mount assemblies The EASA, which is the Technical Agent for the Member States of the E:\FR\FM\14OCP1.SGM 14OCP1 Federal Register / Vol. 85, No. 199 / Wednesday, October 14, 2020 / Proposed Rules European Union, has issued EASA AD 2020–0085, dated April 6, 2020 (‘‘EASA AD 2020–0085’’) (also referred to as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus SAS Model A318–111 and –112 airplanes, Model A319–111, –112, –113, –114, and –115 airplanes, Model A320–211, –212, –214, –215, and –216 airplanes, and Model A321–111, –112, –211, –212, and –213 airplanes. EASA AD 2020–0085 supersedes EASA AD 2017–0251, dated December 15, 2017 (‘‘EASA AD 2017– 0251’’) (which corresponds to FAA AD 2018–16–02). 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 proposed AD was prompted by a report of a production quality deficiency on the inner retainer installed on link assemblies of the aft engine mount, which could result in failure of the retainer. The FAA is proposing this AD to address nonconforming retainers of the aft engine mount. This condition could result in loss of the locking feature of the nuts of the inner and outer pins; loss of the pins will result in the aft mount engine link no longer being secured to the aft engine mount, possibly resulting in damage to the airplane. See the MCAI for additional background information. jbell on DSKJLSW7X2PROD with PRO_RULES Explanation of Retained Requirements Although this proposed AD does not explicitly restate the requirements of AD 2018–16–02, this proposed AD would retain certain of the requirements of AD 2018–16–02. Those requirements are referenced in paragraphs (3), (4), (7), and (12) of EASA AD 2020–0085, which, in turn, is referenced in paragraph (g) of this proposed AD. Paragraph (h) of AD 2018–16–02 excluded 4-lug engines from the modification (which corresponded with the previous EASA AD). This proposed AD includes 4-lug engines in the modification as specified in paragraph (3) of EASA AD 2020–0085. EASA determined the compliance time for the modification of the 4-lug engines is the same as the compliance time for the 3lug engines. For this NPRM, the proposed compliance times for both 3lug and 4-lug engines is within 48 months after September 13, 2018 (the effective date of AD 2018–16–02). The 4-lug engines were originally excluded from AD 2018–16–02 because the installation of the engine mount retainer that was developed to address VerDate Sep<11>2014 17:18 Oct 13, 2020 Jkt 253001 the unsafe condition can lead to interference on 4-lug engines. However, since AD 2018–16–02 was issued, a new mount retainer was developed for 4-lug engines. As the unsafe condition is the same for 3-lug and 4-lug engines, it was determined that the modification for the 4-lug engines should be accomplished within the compliance time given for the 3-lug engines. EASA provided their regulated community approximately 15 months for accomplishing the modification on the 4-lug engines. The FAA expects to provide at least the same amount of time, if not longer, for affected U.S. operators to accomplish the modification on the 4-lug engines (based on the anticipated time needed to issue a final rule). The FAA has determined this compliance time is necessary to adequately address the unsafe condition for the 4-lug engines. Related IBR Material Under 1 CFR Part 51 EASA AD 2020–0085 describes procedures for procedures for modifying and re-identifying the aft engine mount retainer assembly. 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 and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with the State of Design Authority, the FAA has been notified of the unsafe condition described in the MCAI referenced above. The FAA is proposing this AD because the FAA evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in EASA AD 2020–0085 described previously, as incorporated by reference, except for any differences identified as exceptions in the regulatory text of this AD and except as discussed under ‘‘Differences Between this Proposed AD and the MCAI.’’ Differences Between This Proposed AD and the MCAI This proposed AD does not include the actions specified in paragraphs (1) PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 64985 and (2) of EASA AD 2020–0085. Those actions are required by paragraphs (l) and (m) of AD 2016–14–09, Amendment 39–18590 (81 FR 44989, July 12, 2016) (‘‘AD 2016–14–09’’). This proposed AD does not include the parts installation prohibition specified in paragraph (10) of EASA AD 2020–0085. That prohibition is included in paragraph (j) of AD 2017–04–10, Amendment 39–18805 (82 FR 11791, February 27, 2017) (‘‘AD 2017–04–10’’). This proposed AD does not supersede AD 2016–14–09 and AD 2017–04–10. However, paragraph (i) of this proposed AD provides terminating action for certain requirements of AD 2016–14–09 and a method of compliance for certain requirements of AD 2017–04–10. Explanation of Required Compliance Information In the FAA’s ongoing efforts to improve the efficiency of the AD process, the FAA initially worked with Airbus and EASA to develop a process to use certain EASA ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. The FAA has since coordinated with other manufacturers and civil aviation authorities (CAAs) to use this process. As a result, EASA AD 2020–0085 will be incorporated by reference in the FAA final rule. This proposed AD would, therefore, require compliance with EASA AD 2020–0085 in its entirety, through that incorporation, except for any differences identified as exceptions in the regulatory text of this proposed AD. Using common terms that are the same as the heading of a particular section in the EASA AD 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 the EASA AD. Service information specified in EASA AD 2020–0085 that is required for compliance with EASA AD 2020–0085 will be available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0914 after the FAA final rule is published. Costs of Compliance The FAA estimates that this proposed AD affects 119 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: E:\FR\FM\14OCP1.SGM 14OCP1 64986 Federal Register / Vol. 85, No. 199 / Wednesday, October 14, 2020 / Proposed Rules ESTIMATED COSTS FOR REQUIRED ACTIONS Action Labor cost Retained actions from AD 2018–16–02 ......... New proposed actions .................................... 20 work-hours × $85 per hour = $1,700 ........ 16 work-hours × $85 per hour = $1,360 ........ 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 The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (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. jbell on DSKJLSW7X2PROD with PRO_RULES List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: VerDate Sep<11>2014 17:18 Oct 13, 2020 Jkt 253001 Parts cost 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive (AD) 2018–16–02, Amendment 39– 19342 (83 FR 39326, August 9, 2018); and ■ b. Adding the following new AD: ■ ■ Airbus SAS: Docket No. FAA–2020–0914; Product Identifier 2020–NM–058–AD. (a) Comments Due Date The FAA must receive comments by November 30, 2020. (b) Affected ADs (1) This AD replaces AD 2018–16–02, Amendment 39–19342 (83 FR 39326, August 9, 2018) (‘‘AD 2018–16–02’’). (2) This AD affects AD 2016–14–09, Amendment 39–18590 (81 FR 44989, July 12, 2016) (‘‘AD 2016–14–09’’). (3) This AD affects AD 2017–04–10, Amendment 39–18805 (82 FR 11791, February 27, 2017) (‘‘AD 2017–04–10’’). (c) Applicability This AD applies to all the Airbus SAS airplanes identified in paragraphs (c)(1) through (4) of this AD, certificated in any category. (1) Model A318–111 and –112 airplanes. (2) Model A319–111, –112, –113, –114, and –115 airplanes. (3) Model A320–211, –212, –214, and –216 airplanes (4) Model A321–111, –112, –211, –212, and –213 airplanes. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by a report of a production quality deficiency on the inner retainer installed on link assemblies of the aft engine mount, which could result in failure of the retainer. The FAA is issuing this AD to address non-conforming retainers of the aft engine mount. This condition could result in loss of the locking feature of the nuts of the inner and outer pins; loss of the pins will result in the aft mount engine link no longer being secured to the aft engine mount, possibly resulting in damage to the airplane. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 $4,852 5,722 Cost on U.S. operators $577,388 680,918 (f) Compliance PART 39—AIRWORTHINESS DIRECTIVES § 39.13 $3,152 4,362 Cost per product 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, paragraphs (3) through (6), (8), (9), (11), and (12) of European Union Aviation Safety Agency (EASA) AD 2020– 0085, dated April 6, 2020 (‘‘EASA AD 2020– 0085’’). (h) Exceptions to EASA AD 2020–0085 (1) Where EASA AD 2020–0085 refers to its effective date, this AD requires using the effective date of this AD. (2) Where EASA AD 2020–0085 refers to August 16, 2017 (the effective date of EASA AD 2017–0138, dated August 2, 2017), this AD requires using September 13, 2018 (the effective date of AD 2018–16–02). (3) Where EASA AD 2020–0085 refers to December 15, 2017 (the issued date of EASA AD 2017–0251), this AD requires using September 13, 2018 (the effective date of AD 2018–16–02). (4) The ‘‘Remarks’’ section of EASA AD 2020–0085 does not apply to this AD. (5) Where paragraph (8) of EASA AD 2020– 0085 specifies ‘‘do not operate any airplane having installed a, and do not install on any airplane a ‘dull’ finish aft engine mount inner retainer,’’ for this AD, do not operate any airplane having installed any inner retainers affected by the production quality deficiency, and do not install on any airplane a ‘dull’ finish aft engine mount inner retainer. (6) Where paragraph (9.3) of EASA AD 2020–0085 refers to January 27, 2016 (the effective date of EASA AD 2016–0010, dated January 13, 2016), this AD requires using April 3, 2017 (the effective date of AD 2017– 04–10). (7) Where paragraph (12) of EASA AD 2020–0085 specifies a compliance time of ‘‘before next flight after December 15, 2017,’’ for this AD, that compliance time is ‘‘within 30 days after September 13, 2018’’ (the effective date of AD 2018–16–12.) (i) Terminating Action for AD 2016–14–09 and AD 2017–04–10 (1) Modification of an airplane as required by paragraph (g) of this AD (i.e., accomplishing the modification required by paragraph (3) of EASA AD 2020–0085, the replacement specified in paragraph (4) of EASA AD 2020–0085, or the modification specified in paragraph (5) of EASA AD 2020– 0085), constitutes terminating action for the repetitive detailed inspections required by paragraph (l) of AD 2016–14–09 for that airplane. E:\FR\FM\14OCP1.SGM 14OCP1 Federal Register / Vol. 85, No. 199 / Wednesday, October 14, 2020 / Proposed Rules (2) Modification of an airplane as required by paragraph (g) of this AD (i.e., accomplishing the modification required by paragraph (3) of EASA AD 2020–0085, the replacement specified in paragraph (4) of EASA AD 2020–0085, or the modification specified in paragraph (5) of EASA AD 2020– 0085), is a method of compliance with the requirements of paragraph (g) of AD 2017– 04–10 for that airplane. jbell on DSKJLSW7X2PROD with PRO_RULES (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 local Flight Standards District 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)(2) of this AD. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (ii) AMOCs approved previously for AD 2018–16–02 are approved as AMOCs for the corresponding provisions of EASA AD 2020– 0085 that are required by paragraph (g) of this AD. (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): For any service information referenced in EASA AD 2020–0085 that contains RC procedures and tests: Except as required by paragraph (j)(2) of this AD, RC 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 operator’s 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 (1) For information about EASA AD 2020– 0085, contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; phone: +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. You may view this VerDate Sep<11>2014 17:18 Oct 13, 2020 Jkt 253001 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. This material may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0914. (2) 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; phone and fax: 206–231–3223; email: sanjay.ralhan@faa.gov. Issued on October 8, 2020. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–22680 Filed 10–13–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0913; Project Identifier MCAI–2020–00971–T] RIN 2120–AA64 Airworthiness Directives; MHI RJ Aviation ULC (Type Certificate Previously Held by Bombardier, Inc.) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2015–05–03, which applies to certain MHI RJ Aviation ULC Model CL–600– 2B19 (Regional Jet Series 100 & 440) airplanes. AD 2015–05–03 requires revising the maintenance or inspection program, as applicable, to incorporate new or revised maintenance requirements and airworthiness limitations, and incorporating structural repairs and modifications to preclude widespread fatigue damage (WFD). Since the FAA issued AD 2015–05–03, the FAA has determined that new or more restrictive airworthiness limitations are necessary, as well as the corresponding structural repairs and modifications to preclude WFD. This proposed AD would require revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations and would require incorporating structural repairs and modifications to preclude WFD. The SUMMARY: PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 64987 FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by November 30, 2020. 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact MHI RJ Aviation ULC, 12655 Henri-Fabre Blvd., Mirabel, Que´bec J7N 1E1 Canada; Widebody Customer Response Center North America toll-free phone: +1–844–272– 2720 or direct-dial phone: +1–514–855– 8500; fax: +1–514–855–8501; email: thd.crj@mhirj.com; internet: https:// mhirj.com. You may view this service information 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. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0913; 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 NPRM, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 516–228–7330; fax: 516– 794–5531; email: 9-avs-nyaco-cos@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed E:\FR\FM\14OCP1.SGM 14OCP1

Agencies

[Federal Register Volume 85, Number 199 (Wednesday, October 14, 2020)]
[Proposed Rules]
[Pages 64984-64987]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-22680]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0914; Product Identifier 2020-NM-058-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2018-16-02, which applies to all Airbus SAS Model A318-111 and -112 
airplanes, Model A319-111, -112, -113, -114, and -115 airplanes, Model 
A320-211, -212, -214, and -216 airplanes, and Model A321-111, -112, -
211, -212, and -213 airplanes. AD 2018-16-02 requires modifying and re-
identifying the aft engine mount assemblies. Since the FAA issued AD 
2018-16-02, a modification has been developed for 4-lug engines that 
the FAA has determined is necessary. This proposed AD would retain the 
requirement to modify and re-identify the 3-lug aft engine mount 
assemblies and would include a new requirement to modify and re-
identify the 4-lug aft engine mount assemblies, as specified in a 
European Union Aviation Safety Agency (EASA) AD, which will be 
incorporated by reference. The FAA is proposing this AD to address the 
unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by November 
30, 2020.

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 the material identified in this proposed AD that will be 
incorporated by reference (IBR), contact the EASA, Konrad-Adenauer-Ufer 
3, 50668 Cologne, Germany; phone: +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 IBR 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 on the internet at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2020-0914.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0914; 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 NPRM, any comments received, and other information. The street 
address for Docket Operations is listed above. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
Large Aircraft Section, International Validation Branch, FAA, 2200 
South 216th St., Des Moines, WA 98198; phone and fax: 206-231-3223; 
email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2020-0914; 
Product Identifier 2020-NM-058-AD'' at the beginning of your comments. 
The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. The FAA will 
consider all comments received by the closing date and may amend this 
NPRM based on those comments.
    The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Discussion

    The FAA issued AD 2018-16-02, Amendment 39-19342 (83 FR 39326, 
August 9, 2018) (``AD 2018-16-02''), which applies to all Airbus SAS 
Model A318-111 and -112 airplanes, Model A319-111, -112, -113, -114, 
and -115 airplanes, Model A320-211, -212, -214, and -216 airplanes, and 
Model A321-111, -112, -211, -212, and -213 airplanes. AD 2018-16-02 
requires modifying and re-identifying the aft engine mount assemblies. 
The FAA issued AD 2018-16-02 to address non-conforming retainers of the 
aft engine mount. This condition could result in loss of the locking 
feature of the nuts of the inner and outer pins; loss of the pins will 
result in the aft mount engine link no longer being secured to the aft 
engine mount, possibly resulting in damage to the airplane.

Actions Since AD 2018-16-02 Was Issued

    Since the FAA issued AD 2018-16-02, a modification has been 
developed for 4-lug engines that the FAA has determined is necessary to 
address the unsafe condition. The proposed AD would retain the 
requirement to modify and re-identify the (3-lug) aft engine mount 
assemblies and would include a new requirement to modify and re-
identify the (4-lug) aft engine mount assemblies
    The EASA, which is the Technical Agent for the Member States of the

[[Page 64985]]

European Union, has issued EASA AD 2020-0085, dated April 6, 2020 
(``EASA AD 2020-0085'') (also referred to as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for all Airbus SAS Model A318-111 and -112 airplanes, Model 
A319-111, -112, -113, -114, and -115 airplanes, Model A320-211, -212, -
214, -215, and -216 airplanes, and Model A321-111, -112, -211, -212, 
and -213 airplanes. EASA AD 2020-0085 supersedes EASA AD 2017-0251, 
dated December 15, 2017 (``EASA AD 2017-0251'') (which corresponds to 
FAA AD 2018-16-02). 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 proposed AD was prompted by a report of a production quality 
deficiency on the inner retainer installed on link assemblies of the 
aft engine mount, which could result in failure of the retainer. The 
FAA is proposing this AD to address non-conforming retainers of the aft 
engine mount. This condition could result in loss of the locking 
feature of the nuts of the inner and outer pins; loss of the pins will 
result in the aft mount engine link no longer being secured to the aft 
engine mount, possibly resulting in damage to the airplane. See the 
MCAI for additional background information.

Explanation of Retained Requirements

    Although this proposed AD does not explicitly restate the 
requirements of AD 2018-16-02, this proposed AD would retain certain of 
the requirements of AD 2018-16-02. Those requirements are referenced in 
paragraphs (3), (4), (7), and (12) of EASA AD 2020-0085, which, in 
turn, is referenced in paragraph (g) of this proposed AD.
    Paragraph (h) of AD 2018-16-02 excluded 4-lug engines from the 
modification (which corresponded with the previous EASA AD). This 
proposed AD includes 4-lug engines in the modification as specified in 
paragraph (3) of EASA AD 2020-0085. EASA determined the compliance time 
for the modification of the 4-lug engines is the same as the compliance 
time for the 3-lug engines. For this NPRM, the proposed compliance 
times for both 3-lug and 4-lug engines is within 48 months after 
September 13, 2018 (the effective date of AD 2018-16-02).
    The 4-lug engines were originally excluded from AD 2018-16-02 
because the installation of the engine mount retainer that was 
developed to address the unsafe condition can lead to interference on 
4-lug engines. However, since AD 2018-16-02 was issued, a new mount 
retainer was developed for 4-lug engines. As the unsafe condition is 
the same for 3-lug and 4-lug engines, it was determined that the 
modification for the 4-lug engines should be accomplished within the 
compliance time given for the 3-lug engines.
    EASA provided their regulated community approximately 15 months for 
accomplishing the modification on the 4-lug engines. The FAA expects to 
provide at least the same amount of time, if not longer, for affected 
U.S. operators to accomplish the modification on the 4-lug engines 
(based on the anticipated time needed to issue a final rule). The FAA 
has determined this compliance time is necessary to adequately address 
the unsafe condition for the 4-lug engines.

Related IBR Material Under 1 CFR Part 51

    EASA AD 2020-0085 describes procedures for procedures for modifying 
and re-identifying the aft engine mount retainer assembly. 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 and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to the FAA's bilateral agreement with the State of Design Authority, 
the FAA has been notified of the unsafe condition described in the MCAI 
referenced above. The FAA is proposing this AD because the FAA 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2020-0085 described previously, as incorporated by 
reference, except for any differences identified as exceptions in the 
regulatory text of this AD and except as discussed under ``Differences 
Between this Proposed AD and the MCAI.''

Differences Between This Proposed AD and the MCAI

    This proposed AD does not include the actions specified in 
paragraphs (1) and (2) of EASA AD 2020-0085. Those actions are required 
by paragraphs (l) and (m) of AD 2016-14-09, Amendment 39-18590 (81 FR 
44989, July 12, 2016) (``AD 2016-14-09'').
    This proposed AD does not include the parts installation 
prohibition specified in paragraph (10) of EASA AD 2020-0085. That 
prohibition is included in paragraph (j) of AD 2017-04-10, Amendment 
39-18805 (82 FR 11791, February 27, 2017) (``AD 2017-04-10'').
    This proposed AD does not supersede AD 2016-14-09 and AD 2017-04-
10. However, paragraph (i) of this proposed AD provides terminating 
action for certain requirements of AD 2016-14-09 and a method of 
compliance for certain requirements of AD 2017-04-10.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA initially worked with Airbus and EASA to develop a 
process to use certain EASA ADs as the primary source of information 
for compliance with requirements for corresponding FAA ADs. The FAA has 
since coordinated with other manufacturers and civil aviation 
authorities (CAAs) to use this process. As a result, EASA AD 2020-0085 
will be incorporated by reference in the FAA final rule. This proposed 
AD would, therefore, require compliance with EASA AD 2020-0085 in its 
entirety, through that incorporation, except for any differences 
identified as exceptions in the regulatory text of this proposed AD. 
Using common terms that are the same as the heading of a particular 
section in the EASA AD 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 the EASA AD. Service information specified 
in EASA AD 2020-0085 that is required for compliance with EASA AD 2020-
0085 will be available on the internet at https://www.regulations.gov 
by searching for and locating Docket No. FAA-2020-0914 after the FAA 
final rule is published.

Costs of Compliance

    The FAA estimates that this proposed AD affects 119 airplanes of 
U.S. registry. The FAA estimates the following costs to comply with 
this proposed AD:

[[Page 64986]]



                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2018-16-02...  20 work-hours x $85 per           $3,152          $4,852        $577,388
                                         hour = $1,700.
New proposed actions..................  16 work-hours x $85 per            4,362           5,722         680,918
                                         hour = $1,360.
----------------------------------------------------------------------------------------------------------------

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

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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) 2018-16-02, Amendment 39-19342 
(83 FR 39326, August 9, 2018); and
0
b. Adding the following new AD:

Airbus SAS: Docket No. FAA-2020-0914; Product Identifier 2020-NM-
058-AD.

(a) Comments Due Date

    The FAA must receive comments by November 30, 2020.

(b) Affected ADs

    (1) This AD replaces AD 2018-16-02, Amendment 39-19342 (83 FR 
39326, August 9, 2018) (``AD 2018-16-02'').
    (2) This AD affects AD 2016-14-09, Amendment 39-18590 (81 FR 
44989, July 12, 2016) (``AD 2016-14-09'').
    (3) This AD affects AD 2017-04-10, Amendment 39-18805 (82 FR 
11791, February 27, 2017) (``AD 2017-04-10'').

(c) Applicability

    This AD applies to all the Airbus SAS airplanes identified in 
paragraphs (c)(1) through (4) of this AD, certificated in any 
category.
    (1) Model A318-111 and -112 airplanes.
    (2) Model A319-111, -112, -113, -114, and -115 airplanes.
    (3) Model A320-211, -212, -214, and -216 airplanes
    (4) Model A321-111, -112, -211, -212, and -213 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by a report of a production quality 
deficiency on the inner retainer installed on link assemblies of the 
aft engine mount, which could result in failure of the retainer. The 
FAA is issuing this AD to address non-conforming retainers of the 
aft engine mount. This condition could result in loss of the locking 
feature of the nuts of the inner and outer pins; loss of the pins 
will result in the aft mount engine link no longer being secured to 
the aft engine mount, possibly resulting in damage to the airplane.

(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, paragraphs (3) through (6), (8), (9), (11), and 
(12) of European Union Aviation Safety Agency (EASA) AD 2020-0085, 
dated April 6, 2020 (``EASA AD 2020-0085'').

(h) Exceptions to EASA AD 2020-0085

    (1) Where EASA AD 2020-0085 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where EASA AD 2020-0085 refers to August 16, 2017 (the 
effective date of EASA AD 2017-0138, dated August 2, 2017), this AD 
requires using September 13, 2018 (the effective date of AD 2018-16-
02).
    (3) Where EASA AD 2020-0085 refers to December 15, 2017 (the 
issued date of EASA AD 2017-0251), this AD requires using September 
13, 2018 (the effective date of AD 2018-16-02).
    (4) The ``Remarks'' section of EASA AD 2020-0085 does not apply 
to this AD.
    (5) Where paragraph (8) of EASA AD 2020-0085 specifies ``do not 
operate any airplane having installed a, and do not install on any 
airplane a `dull' finish aft engine mount inner retainer,'' for this 
AD, do not operate any airplane having installed any inner retainers 
affected by the production quality deficiency, and do not install on 
any airplane a `dull' finish aft engine mount inner retainer.
    (6) Where paragraph (9.3) of EASA AD 2020-0085 refers to January 
27, 2016 (the effective date of EASA AD 2016-0010, dated January 13, 
2016), this AD requires using April 3, 2017 (the effective date of 
AD 2017-04-10).
    (7) Where paragraph (12) of EASA AD 2020-0085 specifies a 
compliance time of ``before next flight after December 15, 2017,'' 
for this AD, that compliance time is ``within 30 days after 
September 13, 2018'' (the effective date of AD 2018-16-12.)

(i) Terminating Action for AD 2016-14-09 and AD 2017-04-10

    (1) Modification of an airplane as required by paragraph (g) of 
this AD (i.e., accomplishing the modification required by paragraph 
(3) of EASA AD 2020-0085, the replacement specified in paragraph (4) 
of EASA AD 2020-0085, or the modification specified in paragraph (5) 
of EASA AD 2020-0085), constitutes terminating action for the 
repetitive detailed inspections required by paragraph (l) of AD 
2016-14-09 for that airplane.

[[Page 64987]]

    (2) Modification of an airplane as required by paragraph (g) of 
this AD (i.e., accomplishing the modification required by paragraph 
(3) of EASA AD 2020-0085, the replacement specified in paragraph (4) 
of EASA AD 2020-0085, or the modification specified in paragraph (5) 
of EASA AD 2020-0085), is a method of compliance with the 
requirements of paragraph (g) of AD 2017-04-10 for that airplane.

(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 local Flight 
Standards District 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)(2) of this AD. Information may be emailed to: [email protected].
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (ii) AMOCs approved previously for AD 2018-16-02 are approved as 
AMOCs for the corresponding provisions of EASA AD 2020-0085 that are 
required by paragraph (g) of this AD.
    (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): For any service information 
referenced in EASA AD 2020-0085 that contains RC procedures and 
tests: Except as required by paragraph (j)(2) of this AD, RC 
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 
operator's 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

    (1) For information about EASA AD 2020-0085, contact the EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +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. 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. This material may be 
found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2020-0914.
    (2) 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; phone and 
fax: 206-231-3223; email: [email protected].

    Issued on October 8, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2020-22680 Filed 10-13-20; 8:45 am]
BILLING CODE 4910-13-P
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