2022-10-07: Flight 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 89-24-06 R1, Amendment 39-6670 (Docket No. 89-CE-29-AD; 55 FR 29347, July 19, 1990); and b. Adding the following new airworthiness directive: 2022-10-07 Viking Air Limited (Type Certificate Previously Held by Bombardier, Inc. and de Havilland, Inc.): Amendment 39-22045; Docket No. FAA-2022-0099; Project Identifier 2019-CE-019-AD. (a) Effective Date This airworthiness directive (AD) is effective June 23, 2022. (b) Affected ADs This AD replaces AD 89-24-06 R1, Amendment 39-6670 (Docket No. 89-CE-29-AD; 55 FR 29347, July 19, 1990) (AD 89-24-06 R1). (c) Applicability This AD applies to Viking Air Limited (Type Certificate previously held by Bombardier, Inc. and de Havilland, Inc.) Model DHC-6-1, DHC-6-100, DHC-6-200, DHC-6-300, and DHC-6-400 airplanes, all serial numbers, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 2700, Flight Control System. (e) Unsafe Condition This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as damage to the flight control system. The FAA is issuing this AD to prevent failure of the flight control system. The unsafe condition, if not addressed, could result in loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Elevator Quadrant and Support Brackets: Inspections, Replacements, and Modifications (1) Visually inspect the elevator quadrant for indications of distortion (warping, buckling, or score marks) by following paragraphs III.A.2.(a) and III.A.2.(b) of the Accomplishment Instructions in Viking DHC-6 (Twin Otter) Service Bulletin 6-511, Revision A, dated June 22, 1990 (DHC-6 SB 6-511, Revision A) at the following applicable compliance times: (i) For Model DHC-6-1, DHC-6-100, DHC-6-200, and DHC-6-300 airplanes, before further flight after the effective date of this AD or within 400 hours time-in-service (TIS) after the last inspection required by AD 89-24-06 R1, whichever occurs later, and thereafter at intervals not to exceed 400 hours TIS; or (ii) For Model DHC-6-400 airplanes, before further flight after the effective date of this AD and thereafter at intervals not to exceed 400 hours TIS. Note 1 to paragraph (g)(1): The elevator quadrant may be identified as part number (P/N) C6CFM1138-27 (Pre Mod 6/1394), P/N C6CFM1450-27 (Post Mod 6/1394 or production cut-in (PCI) serial number (S/N) 331, Pre Mod 6/1678), or P/N C6CFM1450-29 (Post Mod 6/1678 or PCI S/N 602), and is referred to as assembly P/N C6CF1137-1, -3, -5, or -7. (2) If any indication of distortion is found on the elevator quadrant during any inspection required by paragraph (g)(1) of this AD, before further flight, replace the elevator quadrant with a serviceable part and inspect the elevator quadrant support bracket assembly for cracks by following paragraphs III.B.1. through III.B.4.(b) of the Accomplishment Instructions in DHC-6 SB 6-511, Revision A. This AD requires that you do a fluorescent penetrant inspection as the type of required dye penetrant inspection. If a crack is found in the elevator quadrant support bracket, before further flight, replace with a serviceable part by following paragraphs III.B.5 through III.B.12 of the Accomplishment Instructions in DHC-6 SB 6-511, Revision A. (3) For Model DHC-6-1, DHC-6-100, DHC-6-200, and DHC-6-300 airplanes: Within 400 hours TIS after the effective date of this AD, unless already done within the preceding 12 months before the effective date of this AD, inspect the elevator quadrant support bracket assembly for cracks by following paragraphs III.B.1. through III.B.4.(b) of the Accomplishment Instructions in DHC-6 SB 6-511, Revision A. This AD requires that you do a fluorescent penetrant inspection as the type of required dye penetrant inspection. If a crack is found in the elevator quadrant support bracket, before further flight, replace with a serviceable part by following paragraphs III.B.5 through III.B.12 of the Accomplishment Instructions in DHC-6 SB 6-511, Revision A. (h) Credit for Previous Actions (1) For Model DHC-6-1, DHC-6-100, DHC-6-200, and DHC-6-300 airplanes: This paragraph provides credit for the inspection required by paragraph (g)(1) of this AD if you performed the inspection before the effective date of this AD using paragraph (a)(1) of AD 89-24-06 R1. (2) For Model DHC-6-1, DHC-6-100, DHC-6-200, and DHC-6-300 airplanes: This paragraph provides credit for the fluorescent penetrant inspection and subsequent replacement of the elevator quadrant support bracket due to a crack found from the fluorescent penetrant inspection required by paragraph (g)(2) of this AD if performed before the effective date of this AD using paragraphs (a)(3) and (4) of AD 89-24-06 R1. (i) Alternative Methods of Compliance (AMOCs) (1) 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 local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (j)(1) of this AD. (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 Darren Gassetto, Aviation Safety Engineer, New York ACO Branch, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (516) 228-7323; email: 9-avs-nyaco-cos@faa.gov. (2) Refer to Transport Canada AD CF-1972-06R5, dated June 22, 2018, for more information. You may examine the Transport Canada AD at https://www.regulations.gov by searching for and locating Docket No. FAA-2022-0099. (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) Viking DHC-6 (Twin Otter) Service Bulletin 6-511, Revision A, dated June 22, 1990. (ii) [Reserved] (3) For service information identified in this AD, contact Viking Air Ltd., 1959 de Havilland Way, Sidney British Columbia, Canada V8L 5V5; phone: (800) 663-8444; email: continuing.airworthiness@vikingair.com; website: https://www.vikingair.com. (4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. 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 May 5, 2022. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022-10758 Filed 5-18-22; 8:45 am]BILLING CODE 4910-13-P