2024-03-06: Landing gear

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. 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. 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: [email protected]. 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 [email protected]. (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 Côte-Vertu Road West, Dorval, Québec H4S 2A3, Canada; North America toll-free telephone 1- 866-538-1247 or direct-dial telephone 1-514-855-2999; email [email protected]; 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/[email protected]. 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