Airworthiness Directive · Amendment 39-15091 · Wings
Viking Air Limited (Type Certificate No. A-806 Previously Held by deHavilland Inc.) Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III Airplanes
This AD applies to Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes, all serial numbers, that:
(1) Are certificated in any category; and
(2) Are equipped with wing lift strut assemblies, part numbers (P/Ns) C2W1103, C2W1103A, C2W1104, or C2W1104A.
We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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:
For all Models DHC-2 Mk. I and DHC-2 Mk. III airplanes certificated in any category that are equipped with wing lift strut assemblies, P/Ns C2W1103, C2W1103A, C2W1104, or C2W1104A: Within the next 100 hours time-in-service (TIS) after May 11, 1988 (the effective date of AD 88-08-02) or one month after May 11, 1988 (the effective date of AD 88-08-02), whichever occurs first, and thereafter at intervals not to exceed 500 hours TIS or 12 calendar months, whichever occurs first, do the following:
(1) Remove the wing lift strut assemblies, P/Ns C2W1103 or C2W1103A and C2W1104 or C2W1104A from the airplane and prepare the assemblies for inspection as described in the “ACCOMPLISHMENT INSTRUCTIONS” section of DeHavilland Service Bulletin (S/B) No. 2/41, Revision A, dated August 14, 1987.
(2) Conduct a dye penetrant inspection with a 10-power glass for cracks in the lugs of the lower attachment clevis fitting.
(3) If cracks are found, before further flight, replace the complete wing lift strut assembly with a:
(i) Wing lift strut assembly of the same part number that has had the lower clevis fitting inspected using the dye penetrant procedure and has been found free of cracks; or
(ii) Wing lift strut assembly, P/N C2W1115-1 or P/N C2W1115-2, as appropriate.
(4) If no cracks are found, before further flight, clean the lower clevis fitting and reinstall the wing lift strut assembly.
(5) If wing strut assembly P/N C2W1115-1 or P/N C2W1115-2 is installed, the recurring inspection specified in paragraph (f) of this AD is no longer required.
Unless already done, do either (1) or (2) of the following actions:
(1) Inspection using fluorescent penetrant method: Perform the Accomplishment Instructions of Viking Air Ltd. Service Bulletin No. 2/41, Revision C, dated June 23, 2006.
(i) For airplanes previously affected by AD 88-08-02: Inspect the wing lift strut assemblies within the next 12 calendar months after the last inspection required by AD 88-08-02 or within the next 30 days after July 16, 2007 (the effective date of this AD), whichever occurs later, and thereafter at intervals not to exceed 12 calendar months.
(ii) For airplanes not previously affected by AD 88-08-02: Inspect the wing lift strut assemblies within the next 100 hours time-in-service (TIS) after July 16, 2007 (the effective date of this AD) or within the next 12 calendar months after July 16, 2007 (the effective date of this AD), whichever occurs first, and thereafter at intervals not to exceed 12 calendar months.
(2) Inspection using eddy current method: Perform the Accomplishment Instructions of Viking Air Ltd. SB No. 2/55, dated June 23, 2006.
(i) For airplanes previously affected by AD 88-08-02: Inspect the wing lift strut assemblies within the next 12 calendar months after the last inspection required by AD 88-08-02 or within the next 30 days after July 16, 2007 (the effective date of this AD), whichever occurs later, and thereafter at intervals not to exceed 24 calendar months.
(ii) For airplanes not previously affected by AD 88-08-02: Inspect the wing lift strut assemblies within the next 100 hours TIS after July 16, 2007 (the effective date of this AD) or within the next 12 calendar months after July 16, 2007 (the effective date of this AD), whichever occurs first, and thereafter at intervals not to exceed 24 calendar months.
(3) If cracks are found during any inspection required by either paragraph (g)(1) or (g)(2) of this AD, before further flight:
(i) Replace the complete wing lift strut assembly with a wing lift strut assembly of the same part number that has had the lower clevis fitting inspected using either the fluorescent penetrant method specified in paragraph (g)(1) of this AD or the eddy current method specified in paragraph (g)(2) of this AD and is found free of cracks. After replacement, continue with the repetitive inspections specified in paragraphs (g)(1) and (g)(2) of this AD; or
(ii) Replace the complete wing lift strut assembly with strut assembly C2W1115-1 or C2W1115-2, as appropriate. Installing wing strut assembly C2W1115-1 or C2W1115-2 as replacement parts terminates the repetitive inspections required in paragraphs (g)(1) and (g)(2) of this AD.
(4) If no cracks are found during any inspection required in paragraphs (g)(1) or (g)(2) of this AD, before further flight, clean the lower clevis fitting and reinstall the wing strut assembly. After reinstallation, continue with the repetitive inspections specified in paragraphs (g)(1) and (g)(2) of this AD.
Note: This AD differs from the MCAI and/or service information as follows: No differences.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
