AD 2024-03-06

17719 Federal Register / Vol. 89, No. 49 / Tuesday, March 12, 2024 / Rules and Regulations locations on Model A350 airplanes. The unsafe condition, if not addressed, could lead to lavatory module detachment, with consequent injury to cabin crew and passengers, and possibly result in reduced evacuation capacity from the airplane in case of an emergency. (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 2023–0102, dated May 17, 2023 (EASA AD 2023–0102). (h) Exceptions to EASA AD 2023–0102 (1) Where EASA AD 2023–0102 refers to its effective date, this AD requires using the effective date of this AD. (2) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2023–0102. (3) Paragraph (4) of EASA AD 2023–0102 specifies to report inspection results to Airbus within a certain compliance time. For this AD, report inspection results at the applicable time specified in paragraph (h)(3)(i) or (ii) of this AD. (i) For each inspection done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (ii) For any inspection done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (4) Where paragraph (2) of EASA AD 2023– 0102 specifies ‘‘any discrepancy, as defined in the SB, is detected,’’ this AD requires replacing those words with ‘‘any corrosion and other damage is detected.’’ (i) No Requirement for Return of Parts Although the service information referenced in EASA AD 2023–0102 specifies to return parts to the manufacturer, this AD does not include that requirement. (j) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, 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 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, 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 (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) Additional Information For more information about this AD, contact Dat Le, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228– 7317; email dat.v.le@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 2023–0102, dated May 17, 2023. (ii) [Reserved] (3) For EASA AD 2023–0102, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; website easa.europa.eu. You may find this EASA AD on the EASA website at ad.easa.europa.eu. (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ ibr-locationsoremailfr.inspection@nara.gov. Issued on February 6, 2024. Victor Wicklund, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024–05190 Filed 3–11–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–2001; Project Identifier MCAI–2023–00666–T; Amendment 39–22676; AD 2024–03–06] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is superseding Airworthiness Directive (AD) 2021–20– 13, which applied to certain Bombardier, Inc., Model CL–600–2B16 (604 Variant) airplanes. AD 2021–20–13 required repetitive lubrication and repetitive detailed visual inspections (DVI) and non-destructive test (NDT) inspections of the main landing gear (MLG) shock strut lower pins, and replacement if necessary. This AD continues to require the lubrication and inspections specified in AD 2021–20–13 until the MLG shock strut assembly is modified by replacing the trailing arm bushing and installing new dynamic joint components. This AD was prompted by a new design solution for this potential failure of the shock strut lower pin. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective April 16, 2024. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 16, 2024. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of November 18, 2021 (86 FR 57033, October 14, 2021). ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2023–2001; 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, the mandatory continuing airworthiness information (MCAI), 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. Material Incorporated by Reference: • For service information identified in this final rule, contact Bombardier, VerDate Sep<11>2014 16:07 Mar 11, 2024 Jkt 262001 PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 E:\FR\FM\12MRR1.SGM 12MRR1 khammond on DSKJM1Z7X2PROD with RULES

17720 Federal Register / Vol. 89, No. 49 / Tuesday, March 12, 2024 / Rules and Regulations Inc., 200 Co ˆ te-Vertu Road West, Dorval, Que ´bec H4S 2A3, Canada; North America toll-free telephone 1–866–538– 1247 or direct-dial telephone 1–514– 855–2999; email ac.yul@ aero.bombardier.com; website bombardier.com. • You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th Street, Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available at regulations.gov under Docket No. FAA– 2023–2001. FOR FURTHER INFORMATION CONTACT : Gabriel Kim, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7300; email 9-avs-nyaco-cos@ faa.gov. SUPPLEMENTARY INFORMATION : Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2021–20–13, Amendment 39–21751 (86 FR 57033, October 14, 2021) (AD 2021–20–13). AD 2021–20–13 applied to certain Bombardier, Inc., Model CL–600–2B16 (604 Variant) airplanes. AD 2021–20–13 required repetitive lubrication and repetitive DVI and NDT inspections of the MLG shock strut lower pins, and replacement if necessary. The FAA issued AD 2021–20–13 to correct an unsafe condition identified as cracking of the MLG shock strut lower pin part number 19146–3. The NPRM published in the Federal Register on October 25, 2023 (88 FR 73265). The NPRM was prompted by AD CF–2023–32, dated May 9, 2023, issued by Transport Canada, which is the aviation authority for Canada (Transport Canada AD CF–2023–32) (also referred to as the MCAI). The MCAI states there is a new design solution for this potential failure of the shock strut lower pin, which involves replacing the training arm bushings at the attachment and reassembly of the MLG shock strut assembly to training arm assembly joint with new dynamic joint components. As a result, the MCAI requires this new design as terminating action for the requirements of Transport Canada AD CF–2020–54R1. In the NPRM, the FAA proposed to continue to require the lubrication and inspections specified in AD 2021–20–13 until the MLG shock strut assembly is modified by replacing the trailing arm bushing and installing new dynamic joint components. The FAA is issuing this AD to address cracking of the MLG shock strut lower pin. The unsafe condition, if not addressed, could result in structural failure of one or both MLG. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2023–2001. Discussion of Final Airworthiness Directive Comments The FAA received comments from three commenters, including Executive Jet Management, Inc., NetJets, and Boeing. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Update the Service Information to the Latest Revision and Provide Credit Executive Jet Management, Inc. NetJets, and Boeing requested the FAA revise the proposed AD to allow using Bombardier Service Bulletin 604–32– 031 Revision 01, dated March 17, 2023; Bombardier Service Bulletin 605–32– 008 Revision 01, dated March 17, 2023; and Bombardier Service Bulletin 650– 32–005 Revision 01, dated March 17, 2023. NetJets also requested that the proposed AD be revised to add credit for using the original issues of the service information. The FAA agrees to update this final rule to reference Bombardier Service Bulletin 604–32–031 Revision 01, dated March 17, 2023; Bombardier Service Bulletin 605–32–008 Revision 01, dated March 17, 2023; and Bombardier Service Bulletin 650–32–005 Revision 01, dated March 17, 2023, which include minor changes that do not affect the substantive requirements proposed in the NPRM. The FAA has revised this AD to reflect the updated service bulletins. The FAA has also added paragraph (n) of this AD to provide credit for the original issues of the applicable service bulletins, and redesignated subsequent paragraphs accordingly. Conclusion 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 this State of Design Authority, it has notified the FAA of the unsafe condition described in the MCAI referenced above. The FAA reviewed the relevant data, considered the comments received, and determined that air safety requires adopting this AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on this product. Except for minor editorial changes, and any other changes described previously, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. Related Service Information Under 1 CFR Part 51 The FAA reviewed the following Bombardier service information: • Service Bulletin 604–32–031, Revision 01, dated March 17, 2023. • Service Bulletin 605–32–008, Revision 01, dated March 17, 2023. • Service Bulletin 650–32–005, Revision 01, dated March 17, 2023. This service information contains procedures for disassembling the left- and right-hand MLG shock strut and trailing arm joint, replacing the trailing arm bushings at the attachment, and re- assembling the joint with new dynamic joint components. These documents are distinct since they apply to different airplane configurations. This AD also requires the following Bombardier service information, which the Director of the Federal Register approved for incorporation by reference as of November 18, 2021 (86 FR 57033, October 14, 2021): • Service Bulletin 604–32–030, dated June 30, 2020. • Service Bulletin 605–32–007, dated June 30, 2020. • Service Bulletin 650–32–004, dated June 30, 2020. This service information 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 433 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: VerDate Sep<11>2014 16:07 Mar 11, 2024 Jkt 262001 PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 E:\FR\FM\12MRR1.SGM 12MRR1 khammond on DSKJM1Z7X2PROD with RULES

17721 Federal Register / Vol. 89, No. 49 / Tuesday, March 12, 2024 / Rules and Regulations E STIMATED C OSTS FOR R EQUIRED A CTIONS Action Labor cost Parts cost Cost per product Cost on U.S. operators Lubrication and inspections (retained actions from AD 2021–20–13). 7 work-hours × $85 per hour = $595 $0 $595 per cycle ........... $257,635 per cycle. Modification and testing (new actions) 9 work-hours × $85 per hour = $765 2,435 $3,200 ........................ $1,385,600. The FAA estimates the following costs to do any necessary on-condition replacement that would be required based on the results of the repetitive inspections. The FAA has no way of determining the number of aircraft that might need this on-condition action: E STIMATED C OSTS OF O N -C ONDITION R EPLACEMENT Labor cost Parts cost Cost per product 6 work-hours × $85 per hour = $510 ...................................................................................................................... $2,435 $2,945 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 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. 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 2021–20–13, Amendment 39–21751 (86 FR 57033, October 14, 2021); and ■ b. Adding the following new Airworthiness Directive: 2024–03–06 Bombardier, Inc: Amendment 39–22676; Docket No. FAA–2023–2001; Project Identifier MCAI–2023–00666–T. (a) Effective Date This airworthiness directive (AD) is effective April 16, 2024. (b) Affected ADs This AD replaces AD 2021–20–13, Amendment 39–21751 (86 FR 57033, October 14, 2021) (AD 2021–20–13). (c) Applicability This AD applies to Bombardier, Inc., Model CL–600–2B16 (604 Variant) airplanes, serial numbers (S/N) 5301 through 5665 inclusive, 5701 through 5988 inclusive, and 6050 through 6188 inclusive, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code: 32, Landing gear. (e) Reason This AD was prompted by reports of cracking of the main landing gear (MLG) shock strut lower pin. The FAA is issuing this AD to address cracking of the MLG shock strut lower pin. The unsafe condition, if not addressed, could result in structural failure of one or both MLG. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Repetitive Lubrication, With Revised Applicability This paragraph restates the requirements of paragraph (g) of AD 2021–20–13, with revised applicability. Within 200 flight hours (FH) or 12 months after November 18, 2021 (the effective date of AD 2021–20–13), whichever occurs first, lubricate the left-hand (LH) and right-hand (RH) MLG shock strut lower pins having part number (P/N) 19146– 3, in accordance with paragraph 2.B., ‘‘Part A,’’ of the Accomplishment Instructions of the applicable service bulletin, as specified in paragraphs (g)(1) through (3) of this AD. Repeat thereafter at intervals not to exceed 200 FH or 12 months, whichever occurs first. (1) For airplanes having S/N 5301 through 5665 inclusive: Bombardier Service Bulletin 604–32–030, dated June 30, 2020. (2) For airplanes having S/N 5701 through 5988 inclusive: Bombardier Service Bulletin 605–32–007, dated June 30, 2020. (3) For airplanes having S/N 6050 through 6188 inclusive: Bombardier Service Bulletin 650–32–004, dated June 30, 2020. (h) Retained Detailed Visual Inspections (DVI), With No Changes This paragraph restates the requirements of paragraph (h) of AD 2021–20–13, with no changes. At the applicable compliance time specified in paragraphs (h)(1) through (3) of this AD, perform the DVI for cracking and damage of the LH and RH MLG shock strut lower pins having part number (P/N) 19146– 3, in accordance with paragraph 2.C., ‘‘Part B,’’ of the Accomplishment Instructions of the applicable service bulletin, as specified in paragraphs (g)(1) through (3) of this AD. VerDate Sep<11>2014 16:07 Mar 11, 2024 Jkt 262001 PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 E:\FR\FM\12MRR1.SGM 12MRR1 khammond on DSKJM1Z7X2PROD with RULES

17722 Federal Register / Vol. 89, No. 49 / Tuesday, March 12, 2024 / Rules and Regulations Repeat thereafter at intervals not to exceed 400 FH or 24 months, whichever occurs first. If the DVI coincides with a non-destructive testing (NDT) inspection required by paragraph (i) of this AD, the NDT inspection supersedes the DVI for that interval only. If the accumulated flight cycles (FC) of the MLG shock strut lower pin are not known, use the related MLG assembly accumulated FC to determine when to accomplish the actions required by this paragraph. (1) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before November 18, 2021 (the effective date of AD 2021–20–13) and on which an MLG shock strut lower pin has accumulated fewer than 600 total FC on the pin as of November 18, 2021: Before the accumulation of 750 total FC on the pin. (2) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before November 18, 2021 (the effective date of AD 2021–20–13) and on which an MLG shock strut lower pin has accumulated 600 total FC or more on the pin as of November 18, 2021: Within 150 FC after November 18, 2021. (3) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued after November 18, 2021 (the effective date of AD 2021–20–13): Before the accumulation of 750 total FC. (i) Retained NDT Inspection, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2021–20–13, with no changes. At the applicable compliance time specified in paragraphs (i)(1) through (4) of this AD: Perform the NDT inspection for cracking and damage of the LH and RH MLG shock strut lower pins having P/N 19146–3, in accordance with paragraph 2.D., ‘‘Part C,’’ of the Accomplishment Instructions of the applicable service bulletin, as specified in paragraphs (g)(1) through (3) of this AD. Repeat thereafter at intervals not to exceed 900 FC. If the accumulated FC of the MLG shock strut lower pin is not known, use the related MLG assembly accumulated FC to determine when to accomplish the actions required by this paragraph. (1) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before November 18, 2021 (the effective date of AD 2021–20–13) and on which an MLG shock strut lower pin has accumulated fewer than 1,200 total FC on the pin as of November 18, 2021: Before the accumulation of 1,500 total FC on the pin. (2) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before November 18, 2021 (the effective date of AD 2021–20–13) and on which an MLG shock strut lower pin has accumulated 1,200 total FC or more but fewer than 2,000 total FC on the pin as of November 18, 2021: Within 300 FC after November 18, 2021, or before the accumulation of 2,200 total FC on the pin, whichever occurs first. (3) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before November 18, 2021 (the effective date of AD 2021–20–13) and on which an MLG shock strut lower pin has accumulated 2,000 total FC or more on the pin as of November 18, 2021: Within 200 FC after November 18, 2021. (4) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued after November 18, 2021 (the effective date of AD 2021–20–13): Before the accumulation of 1,500 total FC. (j) Retained Replacement, With No Changes This paragraph restates the requirements of paragraph (j) of AD 2021–20–13, with no changes. If, during any inspection required by this AD, any crack or damage of the MLG shock strut lower pin is detected, before further flight, replace the affected MLG shock strut lower pin with a new part in accordance with paragraph 2.E., ‘‘Part D,’’ of the Accomplishment Instructions of the applicable service bulletin, as specified in paragraphs (g)(1) through (3) of this AD. (k) New Requirement of This AD: Modification Within 60 months from the effective date of this AD, modify the LH and RH MLG assembly in accordance with paragraph 2.B. of the Accomplishment Instructions of the applicable service bulletin, as specified in paragraphs (k)(1) through (3) of this AD. (1) For airplanes having S/N 5301 through 5665 inclusive: Bombardier Service Bulletin 604–32–031, Revision 01, dated March 17, 2023. (2) For airplanes having S/N 5701 through 5988 inclusive: Bombardier Service Bulletin 605–32–008, Revision 01, dated March 17, 2023. (3) For airplanes having S/N 6050 through 6188 inclusive: Bombardier Service Bulletin 650–32–005, Revision 01, dated March 17, 2023. (l) New Requirement of the AD: Testing Before further flight after completing the actions required by paragraph (k) of this AD, perform the testing of the MLG shock strut assembly to trailing arm assembly joint in accordance with paragraph 2.C. of the Accomplishment Instructions of the applicable service bulletin, as specified in paragraphs (k)(1) through (3) of this AD. (m) Terminating Action Modifying and testing an airplane as required by paragraphs (k) and (l) of this AD terminates the initial and repetitive lubrication and inspections required by paragraphs (g), (h), and (i) of this AD for that airplane. (n) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (k) and (l) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 604–32–031, dated December 29, 2022; Bombardier Service Bulletin 605–32–008, dated December 29, 2022; or Bombardier Service Bulletin 650– 32–005, dated December 29, 2022. (o) Additional AD Provisions (1) Alternative Methods of Compliance (AMOCs): The Manager, 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 manager of the International Validation Branch, mail it to the address identified in paragraph (p)(2) of this AD or email to: 9- AVS-AIR-730-AMOC@faa.gov. If mailing information, also submit information by email. 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, International Validation Branch, FAA; or Transport Canada; or Bombardier, Inc.’s Transport Canada Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (p) Additional Information (1) Refer to Transport Canada AD CF– 2023–32, dated May 9, 2023, for related information. This Transport Canada AD may be found in the AD docket at regulations.gov under Docket No. FAA–2023–2001. (2) For more information about this AD, contact Gabriel Kim, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7300; email 9-avs-nyaco-cos@faa.gov. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(5) and (6) of this AD. (q) 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. (3) The following service information was approved for IBR on April 16, 2024. (i) Bombardier Service Bulletin 604–32– 031, Revision 01, dated March 17, 2023. (ii) Bombardier Service Bulletin 605–32– 008, Revision 01, dated March 17, 2023. (iii) Bombardier Service Bulletin 650–32– 005, Revision 01, dated March 17, 2023. (4) The following service information was approved for IBR on November 18, 2021 (86 FR 57033, October 14, 2021). (i) Bombardier Service Bulletin 604–32– 030, dated June 30, 2020. (ii) Bombardier Service Bulletin 605–32– 007, dated June 30, 2020. (iii) Bombardier Service Bulletin 650–32– 004, dated June 30, 2020. (5) For service information identified in this AD, contact Bombardier, Inc., 200 Co ˆ te- Vertu Road West, Dorval, Que ´bec H4S 2A3, Canada; North America toll-free telephone 1– VerDate Sep<11>2014 16:07 Mar 11, 2024 Jkt 262001 PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 E:\FR\FM\12MRR1.SGM 12MRR1 khammond on DSKJM1Z7X2PROD with RULES

17723 Federal Register / Vol. 89, No. 49 / Tuesday, March 12, 2024 / Rules and Regulations 866–538–1247 or direct-dial telephone 1– 514–855–2999; email ac.yul@ aero.bombardier.com; website bombardier.com. (6) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th Street, Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (7) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ ibr-locationsoremailfr.inspection@nara.gov. Issued on February 7, 2024. Victor Wicklund, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024–05191 Filed 3–11–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–2230; Project Identifier MCAI–2023–00861–T; Amendment 39–22677; AD 2024–03–07] RIN 2120–AA64 Airworthiness Directives; Deutsche Aircraft GmbH (Type Certificate Previously Held by 328 Support Services GmbH; AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftahrt GmbH) Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for all Deutsche Aircraft GmbH Model 328–100 and 328–300 airplanes. This AD was prompted by operator reports of worn and ruptured bonding straps inside the feeder wing tanks and in both outer and inner wing tanks. This AD requires a one-time detailed inspection of each affected part, and applicable corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective April 16, 2024. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 16, 2024. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2023–2230; 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, the mandatory continuing airworthiness information (MCAI), 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. Material Incorporated by Reference: • For EASA material incorporated by reference in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; website easa.europa.eu. You may find this material on the EASA website at ad.easa.europa.eu. • You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available in the AD docket at regulations.gov under Docket No. FAA– 2023–2230. FOR FURTHER INFORMATION CONTACT : Todd Thompson, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206–231–3228; email Todd.Thompson@faa.gov. SUPPLEMENTARY INFORMATION : Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Deutsche Aircraft GmbH (Type Certificate previously held by 328 Support Services GmbH; AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328–100 and 328–300 airplanes. The NPRM published in the Federal Register on December 6, 2023 (88 FR 84764). The NPRM was prompted by AD 2023–0137, dated July 12, 2023 (EASA AD 2023–0137) (also referred to as the MCAI), issued by EASA, which is the Technical Agent for the Member States of the European Union. The MCAI states that operators reported findings of damaged affected parts. The extent of the detected damage of the affected parts did not ensure that appropriately low electrical impedance is obtained and maintained through the affected bonding path. The unsafe condition, if not detected and corrected, could lead to the loss of bonding function and, in combination with a lightning strike, create a source of ignition in a fuel tank, possibly resulting in a fire or explosion. In the NPRM, the FAA proposed to require a one-time detailed inspection of each affected part, and applicable corrective actions, as specified in EASA AD 2023–0137. The FAA is issuing this AD to address the unsafe condition on these products. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2023–2230. Discussion of Final Airworthiness Directive Comments The FAA received no comments on the NPRM or on the determination of the cost to the public. Conclusion 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 this State of Design Authority, it has notified the FAA of the unsafe condition described in the MCAI referenced above. The FAA reviewed the relevant data and determined that air safety requires adopting this AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on this product. Except for minor editorial changes, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. Related Service Information Under 1 CFR Part 51 EASA AD 2023–0137 specifies procedures for a one-time detailed inspection of each affected part for worn and ruptured bonding straps, and applicable corrective actions (replacing the affected parts). 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. Interim Action The FAA considers that this AD is an interim action. If final action is later identified, the FAA might consider further rulemaking then. Costs of Compliance The FAA estimates that this AD affects 35 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: VerDate Sep<11>2014 16:07 Mar 11, 2024 Jkt 262001 PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 E:\FR\FM\12MRR1.SGM 12MRR1 khammond on DSKJM1Z7X2PROD with RULES