2021-24-09: Main Rotor Head

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: 2021-24-09 Bell Textron Canada Limited: Amendment 39-21830; Docket No. FAA-2021-1011; Project Identifier MCAI-2021-00867-R. (a) Effective Date This airworthiness directive (AD) is effective December 7, 2021. (b) Affected ADs None. (c) Applicability This AD applies to Bell Textron Canada Limited Model 430 helicopters, having serial number 49001 through 49129, inclusive, certificated in any category. (d) Subject Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor Head. (e) Unsafe Condition This AD was prompted by an in-flight failure of the main rotor (M/R) pitch link clevis (clevis) due to fatigue damage and excessive wear. The FAA is issuing this AD to detect and address any wear and damage of the M/R clevis neck or threaded area. The unsafe condition, if not addressed, could result in crack initiation at the M/R clevis neck and failure of the M/R pitch link, resulting in loss of control of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Within 25 hours time-in-service (TIS) or 30 days, whichever occurs first, after the effective date of this AD: (i) Remove and disassemble each M/R pitch link assembly part number (P/N) 430-010-411-105, or P/N 430-010-411-107, but do not remove the inserts from the tube. Visually inspect the M/R clevis P/N 430-010-432-101 and rod end for wear, corrosion, and damage, which for the purposes of this inspection may be indicated by distortion, bending, a crack, or damaged M/R clevis threads. If there is any wear, corrosion or damage, before further flight, remove the affected M/R clevis or the affected rod end from service. (ii) Visually inspect each universal bearing P/N 212-010-412-001 for binding, stiffness, wear, looseness, excess axial and radial play, and damage, which for the purposes of this inspection may be indicated by distortion, bending, or a crack. (A) If there is any wear, looseness, excess axial and radial play, or damage and the M/R pitch link assembly is P/N 430-010-411-105 or P/N 430-010-411-107 and has accumulated 5,000 or less total hours TIS, before further flight, remove the universal bearing P/N 212-010-412-001 from service and replace with an airworthy part. (B) If there is any binding or stiffness and the M/R pitch link assembly is P/N 430-010-411-105 or P/N 430-010-411-107 and has accumulated more than 5,000 total hours TIS, before further flight, remove the universal bearing P/N 212-010-412-001 and M/R clevis from service and replace with airworthy parts. (C) If there is any wear, looseness, excess axial and radial play, or damage and the M/R pitch link assembly is P/N 430-010-411-105 or P/N 430-010-411-107 and has accumulated more than 5,000 total hours TIS, before further flight, remove the universal bearing P/N 212-010-412-001 from service and replace with an airworthy part. (iii) Purge grease the bearings of each universal bearing. (iv) Perform a magnetic particle inspection for any crack on each M/R clevis by following the Accomplishment Instructions, Part I, paragraphs 8. through 8.d., of Bell Alert Service Bulletin 430-21-60, dated July 13, 2021 (ASB 430-21-60). If there is any crack, before further flight, remove each affected M/R clevis from service. If there is no crack, before further flight, perform a selective brush cadmium plating to replace any missing cadmium plating and apply a chromate conversion coating. (2) Within 50 hours TIS after completion of paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 50 hours TIS: (i) Using a 10X magnifying glass, visually inspect the neck and threaded area of each M/R clevis for wear, corrosion, and damage, which for the purposes of this inspection may be indicated by distortion, bending, a crack, or damaged M/R clevis threads. Refer to Figure 3 of ASB 430-21-60 for a depiction of the area to inspect on each M/R clevis. If there is any wear, corrosion, or damage, before further flight, remove the affected M/R clevis from service and replace with an airworthy part. (ii) Perform the actions required in paragraph (g)(1)(iv) of this AD for each M/R clevis. (3) Within 150 hours TIS after the completion of paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 150 hours TIS, visually inspect and purge grease each universal bearing, by performing the actions as required in paragraphs (g)(1)(ii) and (iii) of this AD. (h) Special Flight Permits A special flight permit may be permitted provided that there are no passengers onboard. (i) Alternative Methods of Compliance (AMOCs) (1) 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 local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (j) Related Information (1) For more information about this AD, contact Hal Jensen, Aerospace Engineer, Operational Safety Branch, Compliance & Airworthiness Division, FAA, 950 L'Enfant Plaza N SW, Washington, DC 20024; telephone (202) 267-9167; email hal.jensen@faa.gov. (2) The subject of this AD is addressed in Transport Canada CF-2021-26 AD, dated July 26, 2021. You may view the Transport Canada AD at https://www.regulations.gov in Docket No. FAA-2021-1011. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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 the AD specifies otherwise. (i) Bell Alert Service Bulletin 430-21-60, dated July 13, 2021. (ii) [Reserved] (3) For service information identified in this AD, contact Bell Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J 1R4, Canada; telephone 1-450-437-2862 or 1-800-363-8023; fax 1-450-433-0272; email productsupport@bellflight.com; or at https://www.bellflight.com/support/contact-support. (4) You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222-5110. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fr.inspection@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued on November 16, 2021. Ross Landes, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021-25489 Filed 11-18-21; 11:15 am]BILLING CODE 4910-13-P