2022-17-05: Fuselage Structure (General)

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 2002-14-28, Amendment 39-12828 (67 FR 47684, July 22, 2002); and b. Adding the following new airworthiness directive: 2022-17-05 Viking Air Limited (type certificate previously held by Bombardier Inc. and de Havilland Inc.): Amendment 39-22143; Docket No. FAA-2022-0602; Project Identifier MCAI-2020-01211-A. (a) Effective Date This airworthiness directive (AD) is effective September 30, 2022. (b) Affected ADs This AD replaces AD 2002-14-28, Amendment 39-12828 (67 FR 47684, July 22, 2002) (AD 2002-14-28). (c) Applicability This AD applies to Viking Air Limited (type certificate previously held by Bombardier Inc. and de Havilland Inc.) Model DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes, all serial numbers, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 5300, Fuselage Structure (General). (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 identifies the unsafe condition as the development of damage to the front fuselage struts and airframe lugs over time. The FAA is issuing this AD to address this condition. The unsafe condition, if not addressed, could result in failure of the front fuselage struts, which could lead to failure of the airframe and loss of airplane control. (f) Definition of Serviceable Part For purposes of this AD, a "serviceable part" is a front fuselage strut that has a part number (P/N) other than P/N C2FS209 and C2FS210 and meets the conditions in either paragraph (f)(1) or (2) of this AD: (1) Has accumulated less than 15 years since first installation on an airplane; or (2) Has accumulated 15 or more years since first installation on an airplane and has been inspected in accordance with the requirements of this AD. (g) Compliance Comply with the initial actions in paragraph (h) of this AD at the applicable compliance time in paragraph (g)(1), (2), or (3) of this AD, unless already done. (1) For airplanes with a front fuselage strut that has been installed for less than 15 years as of the effective date of this AD: Before each front fuselage strut accumulates 15 years since first installation on an airplane. (2) For airplanes with a front fuselage strut that has been installed for more than 15 years as of the effective date of this AD or with a front fuselage strut where the date of first installation on an airplane is unknown and the ultrasonic inspection required by paragraph (d)(2) of AD 2002-14-28 has not been done within the last 5 years: Before further flight. (3) For airplanes with a front fuselage strut that has been installed for more than 15 years as of the effective date of this AD or with a front fuselage strut where the date of first installation on an airplane is unknown and the ultrasonic inspection required by paragraph (d)(2) of AD 2002-14-28 has been done within the last 5 years: Within 5 years from the date of the last ultrasonic inspection done in accordance with paragraph (d)(2) of AD 2002-14-28. (h) Initial Actions (1) Do the actions in paragraph (h)(1)(i) or (ii) of this AD: (i) Remove the front fuselage struts from service and install and seal serviceable parts in accordance with steps w. and y. through ii. of Section II.B.1. or II.B.2., as applicable to your airplane, of Viking DHC-2 Beaver Technical Bulletin No. V2/00002, Revision A, dated June 20, 2019 (Viking TB V2/00002); or (ii) Do visual and borescope inspections of the front fuselage struts and non-destructive testing (NDT) inspections of the fuselage strut fork ends for corrosion and cracks in accordance with steps m. through p. of Section II.B.1. or II.B.2., as applicable to your airplane, of Viking TB V2/00002, except you are not required to contact the manufacturer. Instead, do the actions in paragraph (h)(3) of this AD. (2) Do visual and NDT inspections of the mating airframe lug surfaces and bolt holes for corrosion and cracks and replace if necessary in accordance with steps q., r., t., and u. of Section II.B.1. or II.B.2., as applicable to your airplane, of Viking TB V2/00002, except you are not required to contact the manufacturer. (3) If, during any inspection required by paragraph (h)(1)(ii) of this AD, any crack or corrosion is found, before further flight, do one of the following: (i) Remove the part from service and install and seal a serviceable part in accordance with steps w. and y. through ii. of Section II.B.1. or II.B.2., as applicable to your airplane, of Viking TB V2/00002; or (ii) If the wall thickness of the part is 0.030 inch or more, repair in accordance with step s.(2) of Section II.B.1. or II.B.2., as applicable to your airplane, of Viking TB V2/00002; or (iii) Repair using a method approved by the Manager, New York ACO Branch, FAA; Transport Canada; or Viking Air Limited's Transport Canada Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (i) Repetitive Actions (1) After completing the actions in paragraphs (h)(1)(ii) and (2) of this AD, unless already done, do the following: (i) At intervals not to exceed 12 months, except when complying with paragraph (i)(1)(ii) or (2) of this AD, clean and visually inspect the front fuselage struts and airframe lugs for corrosion and cracking in accordance with steps n., p., and q. of Section II.B.1. or II.B.2., as applicable to your airplane, of Viking TB V2/00002. If there is a crack or any corrosion, before further flight, comply with the actions in paragraph (h)(3)(i), (ii), or (iii) of this AD. (ii) At intervals not to exceed 5 years, except when complying with paragraph (i)(2) of this AD, do visual and borescope inspections of the front fuselage struts and a visual inspection of the airframe lugs for corrosion and cracking in accordance with steps m. through q. and t. of Section II.B.1. or II.B.2., as applicable to your airplane, of Viking TB V2/00002, except you are not required to contact the manufacturer. If there is a crack or any corrosion, before further flight, comply with the actions in paragraph (h)(3)(i), (ii), or (iii) of this AD. (2) At intervals not to exceed 15 years, repeat the actions required by paragraph (h) of this AD. (j) 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 (k)(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. (k) Related Information (1) For more information about this AD, contact Aziz Ahmed, Aviation Safety Engineer, New York ACO Branch, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (516) 228-7329; email: aziz.ahmed@faa.gov. (2) Refer to Transport Canada AD CF-2020-22, dated June 5, 2020, for more information. You may examine the Transport Canada AD in the AD docket at www.regulations.gov by searching for and locating Docket No. FAA-2022-0602. (l) 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-2 Beaver Technical Bulletin No. V2/00002, Revision 'A,' dated June 20, 2019. (ii) [Reserved] (3) For Viking Air Ltd service information identified in this AD, contact Viking Air Limited Technical Support, 1959 de Havilland Way, Sidney, British Columbia, Canada, V8L 5V5; phone: (800) 663-8444; fax: (250) 656-0673; email: technical.support@vikingair.com; website: www.vikingair.com/support/service-bulletins. (4) You may view this service information at 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: www.archives.gov/federal-register/cfr/ibr-locations.html. Issued on August 4, 2022. Christina Underwood, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022-18383 Filed 8-25-22; 8:45 am]BILLING CODE 4910-13-P