2021-23-03: 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 adding the following new airworthiness directive: 2021-23-03 De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.): Amendment 39-21801; Docket No. FAA-2021-0613; Project Identifier MCAI-2020-01431-T. (a) Effective Date This airworthiness directive (AD) is effective December 6, 2021. (b) Affected ADs None. (c) Applicability This AD applies to De Havilland Aircraft of Canada Limited Model DHC-8-400, -401, and -402 airplanes, certificated in any category, serial numbers 4001, 4003, and subsequent. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Unsafe Condition This AD was prompted by a report of cracking found on a main landing gear (MLG) drag strut assembly. The FAA is issuing this AD to address cracking of the MLG drag strut assembly and possible failure under compression loads during landing or ground operations, which could result in asymmetric MLG configuration and potential runway excursion. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Records Review, Repetitive Inspections, and On-Condition Actions Within 30 days after the effective date of this AD: Review the applicable airplane maintenance records to determine if any affected MLG drag strut assembly identified in figure 1 to the introductory text of paragraph (g) of this AD is installed. If any affected MLG drag strut assembly is installed, do the actions specified in paragraphs (g)(1) and (2) of this AD. Figure 1 to the Introductory Text of Paragraph ( g )-Affected MLG Drag Strut Assembly Part No. Serial No. 46301-13 MBM0056 MBM0073 MBM0076 MBM0130 MBM0136 MBM0145 MBM0179 MBM0204 MBM0208 MBM0302 MBM0303 MBM0324 MBM0405 MBM0408 MBM0412 MBM0417 MBM0423 (1) Within 80 flight hours after accomplishing the records review required by paragraph (g) of this AD, do a detailed inspection for cracking of the affected MLG drag strut assembly, and do all applicable on-condition actions before further flight, in accordance with a method approved by the Manager, New York ACO Branch, FAA. Repeat the inspection thereafter at intervals not to exceed 80 flight hours until the magnetic particle inspection required by paragraph (g)(2) of this AD is done. Note 1 to paragraph (g)(1): Guidance on the inspections and on-condition actions required by this AD can be found in Transport Canada Civil Aviation (TCCA) AD CF-2020-43, dated October 21, 2020. (2) Within 1,600 flight hours or 12 months after the effective date of this AD, whichever occurs first, perform a magnetic particle inspection for cracks of the entire tubular section of the affected MLG drag strut assembly, and do all on-condition actions before further flight, in accordance with a method approved by the Manager, New York ACO Branch, FAA. Performing the magnetic particle inspection required by this paragraph terminates the repetitive detailed inspections required by paragraph (g)(1) of this AD. (h) Parts Installation Prohibition As of the effective date of this AD, no person may install an affected MLG drag strut assembly identified in figure 1 to the introductory text of paragraph (g) of this AD on any airplane unless the inspections and applicable on-conditions specified in paragraphs (g)(1) and (2) of this AD are done before further flight. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO 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 certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531. 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, New York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or De Havilland Aircraft of Canada Limited's TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) TCCA AD CF-2020-43, dated October 21, 2020, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-0613. (2) For more information about this AD, contact Aziz Ahmed, Aerospace Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; fax 516-794-5531; email [email protected]. (3) For information about TCCA AD CF-2020-43, dated October 21, 2020, contact TCCA, Transport Canada National Aircraft Certification, 159 Cleopatra Drive, Nepean, Ontario K1A 0N5, Canada; telephone 888-663-3639; email [email protected]; internet https://tc.canada.ca/en/aviation. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. (k) Material Incorporated by Reference None. Issued on October 26, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021-23656 Filed 10-29-21; 8:45 am]BILLING CODE 4910-13-P