Airworthiness Directive · Amendment 39-22143 · Fuselage structure
Viking Air Limited (Type Certificate Previously Held by Bombardier Inc. and de Havilland Inc.) Airplanes
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.
The FAA is superseding Airworthiness Directive (AD) 2002-14- 28, which applied to all de Havilland Inc. (type certificate currently held by Viking Air Limited) Model DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes. AD 2002-14-28 established a life limit for the front fuselage struts and required repetitively replacing the front fuselage struts every 15 years or repetitively inspecting the struts for corrosion or fatigue damage and replacing when the damage exceeded a certain level. Since the FAA issued AD 2002-14-28, Transport Canada superseded its mandatory continuing airworthiness information (MCAI) to correct this unsafe condition on these products. This AD requires either doing recurring visual inspections, borescope inspections, and non-destructive inspections (NDIs) of the struts and airframe lugs with corrective action as necessary or replacing the struts every 15 years and doing recurring NDIs of the airframe lugs with corrective action as necessary. The FAA is issuing this AD to address the unsafe condition on these products.
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.
(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.
(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.
