Airworthiness Directives; Airbus SAS Airplanes, 31097-31100 [2021-12172]

Download as PDF Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations (5) Model A340–541 airplanes. (6) Model A340–642 airplanes. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/furnishings. (e) Reason This AD was prompted by reports that, for certain lower deck mobile crew rest (LDMCR) units, the connection of a certain halon outlet tube to the outlet of a certain fire extinguisher bottle may be incorrect. The FAA is issuing this AD to address this condition, which, in case of a fire inside the LDMCR, could lead to disconnection of the tube, possibly resulting in reduced concentration of fire suppressing agent at any location inside the LDMCR. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2020–0255. (h) Exceptions to EASA AD 2020–0255 (1) Where EASA AD 2020–0255 refers to its effective date, this AD requires using the effective date of this AD. (2) The ‘‘Remarks’’ section of EASA AD 2020–0255 does not apply to this AD. jbell on DSKJLSW7X2PROD with RULES (i) No Reporting Requirement Although the service information referenced in EASA AD 2020–0255 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9–AVS–AIR– 730–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. VerDate Sep<11>2014 17:30 Jun 10, 2021 Jkt 253001 (3) Required for Compliance (RC): Except as required by paragraph (j)(2) of this AD, if any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the 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 For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3229; email vladimir.ulyanov@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 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 2020–0255, dated November 13, 2020. (ii) [Reserved] (3) For EASA AD 2020–0255, 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. 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–2021–0140. (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 fedreg.legal@ nara.gov, or go to: https://www.archives.gov/ federal-register/cfr/ibr-locations.html. Issued on May 20, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–12175 Filed 6–10–21; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 31097 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–1113; Project Identifier MCAI–2020–00893–T; Amendment 39–21580; AD 2021–11–18] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2019–03– 10, which applied to all Airbus SAS Model A300 series airplanes; and Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4– 605R Variant F airplanes (collectively called Model A300–600 series airplanes). AD 2019–03–10 required repetitive detailed visual inspections of the main landing gear (MLG) leg components and replacement of the MLG leg if cracked components are found. This AD continues to require the actions required by AD 2019–03–10. For certain airplanes, this AD also requires modification of the MLG hinge arm by installing improved MLG hinge arm/ barrel pins; an out-of-roundness check of removed pins; repetitive inspections of any affected pins and the associated connecting rod bushes, and replacement of the MLG leg if cracked components are found; and installation of an improved spacer; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of cracks in MLG leg components and a determination that additional actions (including inspections, modifications, and checks) are needed to address the unsafe condition. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 16, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 16, 2021. ADDRESSES: For EASA material incorporated by reference (IBR) in this AD, contact EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this SUMMARY: E:\FR\FM\11JNR1.SGM 11JNR1 31098 Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations IBR material on the EASA website at https://ad.easa.europa.eu. For Safran material that will be IBR in this AD, contact Safran Landing Systems, One Carbon Way, Walton, KY 41094; telephone 859–525–8583; fax 859–485–8827; internet https:// www.safran-landing-systems.com. 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– 1113. jbell on DSKJLSW7X2PROD with RULES 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– 1113; 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 final rule, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3225; email dan.rodina@faa.gov. SUPPLEMENTARY INFORMATION: Background EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2020–0145, dated July 1, 2020 (EASA AD 2020– 0145) (also referred to as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for all Airbus SAS Model A300 series airplanes; Model A300–600 series airplanes; and Model A300F4– 608ST airplanes. EASA AD 2020–0145 supersedes EASA AD 2018–0170, dated August 6, 2018 (which corresponds to FAA AD 2019–03–10, Amendment 39– 19562 (84 FR 5595, February 22, 2019) (AD 2019–03–10)). Model A300F4– 608ST 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. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR VerDate Sep<11>2014 17:30 Jun 10, 2021 Jkt 253001 part 39 to supersede AD 2019–03–10. AD 2019–03–10 applied to all Airbus SAS Model A300 and A300–600 series airplanes. The NPRM published in the Federal Register on December 8, 2020 (85 FR 78971). The NPRM was prompted by reports of cracks in MLG leg components, and a determination that additional actions (including inspections, modifications, and out-ofroundness checks) are needed to address the unsafe condition. The NPRM proposed to continue to require the actions required by AD 2019–03–10. For certain airplanes, this AD also requires modification of the MLG hinge arm by installing improved MLG hinge arm/barrel pins; an out-of-roundness check of removed pins; repetitive inspections of any affected pins and the associated connecting rod bushes, and replacement of the MLG leg if cracked components are found; and installation of an improved spacer; as specified in an EASA AD. The FAA is issuing this AD to address cracking of certain components in the MLG leg, which could result in an MLG collapse, and consequent damage to the airplane and injury to the airplane occupants. See the MCAI for additional background information. Comments The FAA gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. Support for the NPRM The Air Line Pilots Association, International (ALPA) and an anonymous commenter indicated support for the NPRM. Request To Clarify Inspection Threshold for Certain Airplanes United Parcel Service (UPS Airlines) asked that the proposed AD be revised to add a statement to clarify that the general visual inspection (GVI) for Group 2 airplanes begins within 30 months after the effective date of the FAA AD. UPS Airlines stated that it has been accomplishing Airbus Service Bulletin A300–32–6120 at gear overhaul, which replaces the old hinge arm barrel pin with a new hinge arm barrel pin, prior to release of Airbus Service Bulletin A300–32–6121. UPS Airlines further pointed out that Airbus Service Bulletin A300–32–6121 was released after Airbus Service Bulletin A300–32–6120 (pin replacement), and added installation of a new spacer during gear overhaul. UPS Airlines added that EASA AD 2020–0145 does PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 not have clear instructions for the initial inspection start date for airplanes with modifications accomplished using Airbus Service Bulletin A300–32–6120 that have not accomplished Airbus Service Bulletin A300–32–6121. Further, UPS Airlines asserted that this request is in line with the 30-month pin replacement threshold for airplanes equipped with the older pin. Airplanes with the newer pins installed in the past three years without the spacer installation, UPS Airlines also asserted, are less prone to any safety or operational concerns than those with the older pins. The FAA does not agree with the commenter’s request. In developing an appropriate compliance time for this AD, the FAA considered the urgency associated with the subject unsafe condition as well as the recommendations of the manufacturer. The compliance time for the initial GVI for Group 2 airplanes is ‘‘Within 30 months after pin replacement,’’ as specified in EASA AD 2020–0145. Airbus Service Bulletin A300–32–6120, which provides instructions for pin replacement, was issued September 24, 2019. Therefore, the earliest possible compliance time for the inspection would be 30 months from September 24, 2019. The FAA has not changed this AD in this regard. Conclusion The FAA reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. The FAA has determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 EASA AD 2020–0145 describes procedures for repetitive detailed visual inspections of the MLG leg components and replacement of the MLG leg if cracked components are found. EASA AD 2020–0145 also describes procedures, for certain airplanes, for modification of the MLG hinge arm by installing improved pins, which would terminate the repetitive detailed inspections required by AD 2019–03– 10; an out-of-roundness check of removed pins; repetitive inspections of affected pins and the associated connecting rod bushes for cracking, and replacement of the MLG leg if cracked E:\FR\FM\11JNR1.SGM 11JNR1 Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations components are found; and installation of an improved spacer, which would terminate the repetitive pin and rod bushes inspections. EASA AD 2020– 0145 also describes procedures for reporting results of the out-of-roundness check to Safran. Safran Landing Systems has issued Safran Service Bulletin 470–32–840, dated December 3, 2019. This service information describes procedures for inspecting the hinge arm pins of the MLG barrel to detect local out-ofroundness. This material is reasonably available because the interested parties have access to it through their normal course 31099 of business or by the means identified in the ADDRESSES section. Costs of Compliance The FAA estimates that this AD affects 128 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS * Action Labor cost Parts cost Retained actions from AD 2019–03–10. New modifications ......... New inspection .............. New out-of-roundness check. 1 work-hour × $85 per hour = $85, per inspection cycle. 180 work-hours × $85 per hour = $15,300 ........ 1 work-hour × $85 per hour = $85 ..................... 4 work-hours × $85 per hour = $340 ................. $0 17,993 0 0 Cost per product Cost on U.S. operators $85, per inspection cycle. 33,293 .......................... 85 ................................. 340 ............................... $10,880, per inspection cycle. 4,261,504. 10,880. 43,520. * Table does not include estimated costs for reporting. The FAA estimates that it would take about 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 $85, or $85 per product. ESTIMATED COSTS OF ON-CONDITION ACTIONS Labor cost Parts cost Cost per product 20 work-hours × $85 per hour = $1,700 per MLG ............................................... $3,400,000 per MLG ............................. $3,401,700 per MLG. 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 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 current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177–1524. jbell on DSKJLSW7X2PROD with RULES 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 VerDate Sep<11>2014 17:30 Jun 10, 2021 Jkt 253001 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. on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. 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, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, ■ PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of 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: a. Removing Airworthiness Directive (AD) 2019–03–10, Amendment 39– 19562 (84 FR 5595, February 22, 2019); and ■ b. Adding the following new AD: ■ ■ 2021–11–18 Airbus SAS: Amendment 39– 21580; Docket No. FAA–2020–1113; Project Identifier MCAI–2020–00893–T. (a) Effective Date This airworthiness directive (AD) is effective July 16, 2021. E:\FR\FM\11JNR1.SGM 11JNR1 31100 Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations (b) Affected ADs This AD replaces AD 2019–03–10, Amendment 39–19562 (84 FR 5595, February 22, 2019) (AD 2019–03–10). (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. (c) Applicability This AD applies to all Airbus SAS airplanes, certificated in any category, identified in paragraphs (c)(1) through (5) of this AD. (1) Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. (2) Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes. (3) Model A300 B4–605R and B4–622R airplanes. (4) Model A300 F4–605R and F4–622R airplanes. (5) Model A300 C4–605R Variant F airplanes. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (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 2020–0145 that contains RC procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the 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. (4) Paperwork Reduction Act Burden Statement: 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 current 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 be 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 as required by this AD. Send comments regarding this burden estimate or any other (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by reports of cracks in main landing gear (MLG) leg components, and a determination that additional actions (including inspections, modifications, and out-of-roundness checks) are needed to address the unsafe condition. The FAA is issuing this AD to address cracking of certain components in the MLG leg, which could result in an MLG collapse, and consequent damage to the airplane and injury to the airplane occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. jbell on DSKJLSW7X2PROD with RULES (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 2020–0145, dated July 1, 2020 (EASA AD 2020–0145). (h) Exceptions to EASA AD 2020–0145 (1) Where EASA AD 2020–0145 refers to its effective date, this AD requires using the effective date of this AD. (2) Where EASA AD 2020–0145 refers to the effective date of EASA AD 2018–0170, this AD requires using March 29, 2019 (the effective date of AD 2019–03–10). (3) The ‘‘Remarks’’ section of EASA AD 2020–0145 does not apply to this AD. (4) Paragraph (3) of EASA AD 2020–0145 specifies to ‘‘send all removed pins for an out-of-roundness check.’’ For this AD, do an inspection of each pin for out-of-roundness, in accordance with Safran Service Bulletin 470–32–840, dated December 3, 2019. (5) Paragraph (3) of EASA AD 2020–0145 specifies to report inspection results to Safran within a certain compliance time. For this AD, report inspection results at the applicable time specified in paragraph (h)(5)(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. VerDate Sep<11>2014 17:30 Jun 10, 2021 Jkt 253001 PO 00000 Frm 00014 Fmt 4700 Sfmt 9990 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. (j) Related Information For more information about this AD, contact Dan Rodina, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3225; email dan.rodina@ faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 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 2020–0145, dated July 1, 2020. (ii) Safran Service Bulletin 470–32–840, dated December 3, 2019. (3) For EASA AD 2020–0145, 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) For Safran service information, contact Safran Landing Systems, One Carbon Way, Walton, KY 41094; telephone 859–525–8583; fax 859–485–8827; internet https:// www.safran-landing-systems.com. (5) 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–2020–1113. (6) 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 fedreg.legal@ nara.gov, or go to: https://www.archives.gov/ federal-register/cfr/ibr-locations.html. Issued on May 20, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–12172 Filed 6–10–21; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\11JNR1.SGM 11JNR1

Agencies

[Federal Register Volume 86, Number 111 (Friday, June 11, 2021)]
[Rules and Regulations]
[Pages 31097-31100]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-12172]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-1113; Project Identifier MCAI-2020-00893-T; 
Amendment 39-21580; AD 2021-11-18]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-03-
10, which applied to all Airbus SAS Model A300 series airplanes; and 
Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model 
A300 C4-605R Variant F airplanes (collectively called Model A300-600 
series airplanes). AD 2019-03-10 required repetitive detailed visual 
inspections of the main landing gear (MLG) leg components and 
replacement of the MLG leg if cracked components are found. This AD 
continues to require the actions required by AD 2019-03-10. For certain 
airplanes, this AD also requires modification of the MLG hinge arm by 
installing improved MLG hinge arm/barrel pins; an out-of-roundness 
check of removed pins; repetitive inspections of any affected pins and 
the associated connecting rod bushes, and replacement of the MLG leg if 
cracked components are found; and installation of an improved spacer; 
as specified in a European Union Aviation Safety Agency (EASA) AD, 
which is incorporated by reference. This AD was prompted by reports of 
cracks in MLG leg components and a determination that additional 
actions (including inspections, modifications, and checks) are needed 
to address the unsafe condition. The FAA is issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective July 16, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 16, 
2021.

ADDRESSES: For EASA 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

[[Page 31098]]

IBR material on the EASA website at https://ad.easa.europa.eu.
    For Safran material that will be IBR in this AD, contact Safran 
Landing Systems, One Carbon Way, Walton, KY 41094; telephone 859-525-
8583; fax 859-485-8827; internet https://www.safran-landing-systems.com.
    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-2020-1113.

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-
1113; 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 final rule, any comments received, and other information. The 
address for Docket Operations is U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, Large 
Aircraft Section, International Validation Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225; email 
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2020-0145, dated July 1, 2020 (EASA 
AD 2020-0145) (also referred to as the Mandatory Continuing 
Airworthiness Information, or the MCAI), to correct an unsafe condition 
for all Airbus SAS Model A300 series airplanes; Model A300-600 series 
airplanes; and Model A300F4-608ST airplanes. EASA AD 2020-0145 
supersedes EASA AD 2018-0170, dated August 6, 2018 (which corresponds 
to FAA AD 2019-03-10, Amendment 39-19562 (84 FR 5595, February 22, 
2019) (AD 2019-03-10)). Model A300F4-608ST 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.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2019-03-10. AD 2019-03-10 applied to all 
Airbus SAS Model A300 and A300-600 series airplanes. The NPRM published 
in the Federal Register on December 8, 2020 (85 FR 78971). The NPRM was 
prompted by reports of cracks in MLG leg components, and a 
determination that additional actions (including inspections, 
modifications, and out-of-roundness checks) are needed to address the 
unsafe condition. The NPRM proposed to continue to require the actions 
required by AD 2019-03-10. For certain airplanes, this AD also requires 
modification of the MLG hinge arm by installing improved MLG hinge arm/
barrel pins; an out-of-roundness check of removed pins; repetitive 
inspections of any affected pins and the associated connecting rod 
bushes, and replacement of the MLG leg if cracked components are found; 
and installation of an improved spacer; as specified in an EASA AD.
    The FAA is issuing this AD to address cracking of certain 
components in the MLG leg, which could result in an MLG collapse, and 
consequent damage to the airplane and injury to the airplane occupants. 
See the MCAI for additional background information.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The following presents the comments 
received on the NPRM and the FAA's response to each comment.

Support for the NPRM

    The Air Line Pilots Association, International (ALPA) and an 
anonymous commenter indicated support for the NPRM.

Request To Clarify Inspection Threshold for Certain Airplanes

    United Parcel Service (UPS Airlines) asked that the proposed AD be 
revised to add a statement to clarify that the general visual 
inspection (GVI) for Group 2 airplanes begins within 30 months after 
the effective date of the FAA AD. UPS Airlines stated that it has been 
accomplishing Airbus Service Bulletin A300-32-6120 at gear overhaul, 
which replaces the old hinge arm barrel pin with a new hinge arm barrel 
pin, prior to release of Airbus Service Bulletin A300-32-6121. UPS 
Airlines further pointed out that Airbus Service Bulletin A300-32-6121 
was released after Airbus Service Bulletin A300-32-6120 (pin 
replacement), and added installation of a new spacer during gear 
overhaul. UPS Airlines added that EASA AD 2020-0145 does not have clear 
instructions for the initial inspection start date for airplanes with 
modifications accomplished using Airbus Service Bulletin A300-32-6120 
that have not accomplished Airbus Service Bulletin A300-32-6121. 
Further, UPS Airlines asserted that this request is in line with the 
30-month pin replacement threshold for airplanes equipped with the 
older pin. Airplanes with the newer pins installed in the past three 
years without the spacer installation, UPS Airlines also asserted, are 
less prone to any safety or operational concerns than those with the 
older pins.
    The FAA does not agree with the commenter's request. In developing 
an appropriate compliance time for this AD, the FAA considered the 
urgency associated with the subject unsafe condition as well as the 
recommendations of the manufacturer. The compliance time for the 
initial GVI for Group 2 airplanes is ``Within 30 months after pin 
replacement,'' as specified in EASA AD 2020-0145. Airbus Service 
Bulletin A300-32-6120, which provides instructions for pin replacement, 
was issued September 24, 2019. Therefore, the earliest possible 
compliance time for the inspection would be 30 months from September 
24, 2019. The FAA has not changed this AD in this regard.

Conclusion

    The FAA reviewed the relevant data, considered the comments 
received, and determined that air safety and the public interest 
require adopting this final rule as proposed, except for minor 
editorial changes. The FAA has determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    EASA AD 2020-0145 describes procedures for repetitive detailed 
visual inspections of the MLG leg components and replacement of the MLG 
leg if cracked components are found. EASA AD 2020-0145 also describes 
procedures, for certain airplanes, for modification of the MLG hinge 
arm by installing improved pins, which would terminate the repetitive 
detailed inspections required by AD 2019-03-10; an out-of-roundness 
check of removed pins; repetitive inspections of affected pins and the 
associated connecting rod bushes for cracking, and replacement of the 
MLG leg if cracked

[[Page 31099]]

components are found; and installation of an improved spacer, which 
would terminate the repetitive pin and rod bushes inspections. EASA AD 
2020-0145 also describes procedures for reporting results of the out-
of-roundness check to Safran.
    Safran Landing Systems has issued Safran Service Bulletin 470-32-
840, dated December 3, 2019. This service information describes 
procedures for inspecting the hinge arm pins of the MLG barrel to 
detect local out-of-roundness.
    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.

Costs of Compliance

    The FAA estimates that this AD affects 128 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                     Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2019-   1 work-hour x $85 per                $0  $85, per            $10,880, per
 03-10.                           hour = $85, per                          inspection cycle.   inspection cycle.
                                  inspection cycle.
New modifications..............  180 work-hours x $85             17,993  33,293............  4,261,504.
                                  per hour = $15,300.
New inspection.................  1 work-hour x $85 per                 0  85................  10,880.
                                  hour = $85.
New out-of-roundness check.....  4 work-hours x $85 per                0  340...............  43,520.
                                  hour = $340.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.

    The FAA estimates that it would take about 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 $85, 
or $85 per product.

                                     Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
                Labor cost                          Parts cost                       Cost per product
----------------------------------------------------------------------------------------------------------------
20 work-hours x $85 per hour = $1,700 per  $3,400,000 per MLG..........  $3,401,700 per MLG.
 MLG.
----------------------------------------------------------------------------------------------------------------

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 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 current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the 
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,
    (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.

Adoption of 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:
0
a. Removing Airworthiness Directive (AD) 2019-03-10, Amendment 39-19562 
(84 FR 5595, February 22, 2019); and
0
b. Adding the following new AD:

2021-11-18 Airbus SAS: Amendment 39-21580; Docket No. FAA-2020-1113; 
Project Identifier MCAI-2020-00893-T.

(a) Effective Date

    This airworthiness directive (AD) is effective July 16, 2021.

[[Page 31100]]

(b) Affected ADs

    This AD replaces AD 2019-03-10, Amendment 39-19562 (84 FR 5595, 
February 22, 2019) (AD 2019-03-10).

(c) Applicability

    This AD applies to all Airbus SAS airplanes, certificated in any 
category, identified in paragraphs (c)(1) through (5) of this AD.
    (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
    (3) Model A300 B4-605R and B4-622R airplanes.
    (4) Model A300 F4-605R and F4-622R airplanes.
    (5) Model A300 C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by reports of cracks in main landing gear 
(MLG) leg components, and a determination that additional actions 
(including inspections, modifications, and out-of-roundness checks) 
are needed to address the unsafe condition. The FAA is issuing this 
AD to address cracking of certain components in the MLG leg, which 
could result in an MLG collapse, and consequent damage to the 
airplane and injury to the airplane occupants.

(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 
2020-0145, dated July 1, 2020 (EASA AD 2020-0145).

(h) Exceptions to EASA AD 2020-0145

    (1) Where EASA AD 2020-0145 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where EASA AD 2020-0145 refers to the effective date of EASA 
AD 2018-0170, this AD requires using March 29, 2019 (the effective 
date of AD 2019-03-10).
    (3) The ``Remarks'' section of EASA AD 2020-0145 does not apply 
to this AD.
    (4) Paragraph (3) of EASA AD 2020-0145 specifies to ``send all 
removed pins for an out-of-roundness check.'' For this AD, do an 
inspection of each pin for out-of-roundness, in accordance with 
Safran Service Bulletin 470-32-840, dated December 3, 2019.
    (5) Paragraph (3) of EASA AD 2020-0145 specifies to report 
inspection results to Safran within a certain compliance time. For 
this AD, report inspection results at the applicable time specified 
in paragraph (h)(5)(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.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Large Aircraft Section, International Validation Branch, FAA, has 
the authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or responsible Flight 
Standards Office, as appropriate. If sending information directly to 
the Large Aircraft Section, International Validation Branch, send it 
to the attention of the person identified in paragraph (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 2020-0145 that contains RC procedures or tests that are 
identified as RC, those procedures and tests must be done to comply 
with this AD; any procedures or tests that are not identified as RC 
are recommended. Those procedures and tests that are not identified 
as RC may be deviated from using accepted methods in accordance with 
the 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.
    (4) Paperwork Reduction Act Burden Statement: 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 current 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 be 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 as 
required by this AD. 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.

(j) Related Information

    For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, Large Aircraft Section, International Validation 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3225; email [email protected].

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 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 2020-0145, 
dated July 1, 2020.
    (ii) Safran Service Bulletin 470-32-840, dated December 3, 2019.
    (3) For EASA AD 2020-0145, 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) For Safran service information, contact Safran Landing 
Systems, One Carbon Way, Walton, KY 41094; telephone 859-525-8583; 
fax 859-485-8827; internet https://www.safran-landing-systems.com.
    (5) 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-2020-1113.
    (6) 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 May 20, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-12172 Filed 6-10-21; 8:45 am]
BILLING CODE 4910-13-P