2022-09-07: Tail Rotor Control System

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 (AD) 2019-11-05, Amendment 39-19651 (84 FR 26546, June 7, 2019); and b. Adding the following new AD: 2022-09-07 Bell Textron Canada Limited (Type Certificate Previously Held by Bell Helicopter Textron Canada Limited): Amendment 39-22027; Docket No. FAA-2022-0145; Project Identifier MCAI-2021-00522-R. (a) Effective Date This airworthiness directive (AD) is effective May 31, 2022. (b) Affected ADs (1) This AD replaces AD 2019-11-05, Amendment 39-19651 (84 FR 26546, June 7, 2019) (AD 2019-11-05). (2) This AD affects AD 2020-17-10, Amendment 39-21215 (85 FR 49941, August 17, 2020) (AD 2020-17-10). (c) Applicability This AD applies to Bell Textron Canada Limited (type certificate previously held by Bell Helicopter Textron Canada Limited) Model 429 helicopters, certificated in any category, serial numbers 57001 through 57401 inclusive. (d) Subject Joint Aircraft Service Component (JASC) Code: 6720, Tail Rotor Control System. (e) Unsafe Condition This AD was prompted by a report of a worn pitch link. The FAA is issuing this AD to address a worn pitch link, which if not corrected, could result in pitch link failure and subsequent loss of control of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Requirements (1) For pitch link assembly part number(P/N) 429-012-112-101, 429-012-112-103, 429-012-112-101FM, and 429-012-112-103FM: Within 50 hours time-in-service (TIS) after July 12, 2019 (the effective date of AD 2019-11-05) and thereafter at intervals not to exceed 50 hours TIS: (i) Perform a dimensional inspection of each inboard and outboard pitch link assembly for axial and radial bearing play. With a 10X or higher power magnifying glass, inspect the bearing liner for a crack, deterioration of the liner, and extrusion of the liner from the plane. If there is axial or radial play that exceeds allowable limits, or if there is a crack, deterioration of the liner, or extrusion of the liner, before further flight, replace the bearing. (ii) Inspect the pitch link assembly sealant for pin holes and voids and to determine if the sealant thickness is 0.025 inch (0.64 mm) or less, extends over the roll staked lip by 0.030 inch (0.76 mm) or more, and is clear of the bearing ball. If there is a pin hole or void, or if the sealant exceeds 0.026 inch (0.66 mm), does not extend over the roll staked lip by 0.030 inch (0.76 mm) or more, or is not clear of the bearing ball, before further flight, replace the bearing. (2) For pitch link assembly P/N 429-012-112-101, 429-012-112-103, 429-012-112-101FM, and 429-012-112-103FM, within 200 hours TIS following the initial inspection required by paragraph (g)(1) of this AD, or if the hours TIS of a pitch link assembly exceed 250 hours TIS or are unknown, at the next 50-hour-TIS inspection required by paragraph (g)(1) of this AD: (i) Replace each bearing P/N 429-312-107-103 with a date of manufacture before January 13, 2015, with a bearing P/N 429-312-107-103 that was manufactured on or after January 13, 2015. (ii) Using a white permanent fine point marker or equivalent, re-identify the pitch link assembly: (A) Re-identify P/N 429-012-112-101 and 429-012-112-101FM as 429-012-112-111FM. (B) Re-identify P/N 429-012-112-103 and 429-012-112-103FM as 429-012-112-113FM. (iii) Apply a coating of DEVCON 2-TON (C-298) or equivalent over the new P/N. (h) New Requirements For pitch link assemblies other than P/N 429-012-112-101, 429-012-112-103, 429-012-112-101FM, and 429-012-112-103FM: Within 50 hours TIS after the effective date of this AD and thereafter at intervals not to exceed 50 hours TIS: (1) Perform a dimensional inspection of each inboard and outboard pitch link assembly for axial and radial bearing play. With a 10× or higher power magnifying glass, inspect the bearing liner for a crack, deterioration of the liner, and extrusion of the liner from the plane. If there is axial or radial play that exceeds allowable limits, or if there is a crack, deterioration of the liner, or extrusion of the liner, before further flight, replace the bearing. (2) Inspect the pitch link assembly sealant for pin holes and voids and to determine if the sealant thickness is 0.025 inch (0.64 mm) or less, extends over the roll staked lip by 0.030 inch (0.76 mm) or more, and is clear of the bearing ball. If there is a pin hole or void, or if the sealant exceeds 0.026 inch (0.66 mm), does not extend over the roll staked lip by 0.030 inch (0.76 mm) or more, or is not clear of the bearing ball, before further flight, replace the bearing. (i) Terminating Action for Certain Actions in AD 2020-17-10 Accomplishing the initial inspection required by paragraph (g)(1) or (h) of this AD constitutes terminating action for the inspections required by paragraph (f)(2) of AD 2020-17-10 for that pitch link assembly only. (j) Optional Terminating Action The repetitive inspections required by paragraph (h) of this AD are no longer required for helicopters that incorporate pitch link assemblies, P/N 429-012-212-105 or 429-012-212-107, in accordance with Part III of the Accomplishment Instructions of Bell Alert Service Bulletin No. 429-15-16, Revision C, dated October 16, 2020. (k) 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 (l)(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. (l) 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; phone: (202) 267-9167; email: hal.jensen@faa.gov. (2) The subject of this AD is addressed in Transport Canada Civil Aviation AD CF-2015-16R3, dated April 30, 2021. You may view the Transport Canada AD at https://www.regulations.gov in Docket No. FAA-2022-0145. (m) 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 No. 429-15-16, Revision C, dated October 16, 2020. (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; phone: 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 April 15, 2022. Ross Landes, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022-08797 Filed 4-25-22; 8:45 am]BILLING CODE 4910-13-P