AD 88-08-02 SUPERSEDED

88-08-02 DeHAVILLAND: Amendment 39-5889. Applies to all Model DHC-2 Mk. I (including L-20A, YL-20, U-6, and U-6A) and DHC-Mk. III (Turbo Beaver) (all serial numbers) airplanes with wing strut assemblies C2W1103, C2W1103A, C2W1104 and C2W1104A, certified in any category.

COMPLIANCE: Required as indicated after the effective date of this AD, unless already accomplished.

To detect cracks due to stress corrosion in wing lift strut assemblies, accomplish the following:

(a) Within 100 hours time-in-service (TIS), or one month, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 500 hours TIS, or 12 calendar months, whichever occurs first:

(1) Remove wing strut assemblies, 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, prior to further flight replace the complete strut assembly with a strut assembly of the same part number that has had the lower clevis fitting inspection using the dye penetrant procedure and has been found free of cracks, or strut assembly C2W1115-1 or C2W115-2, as appropriate.

(4) If no cracks or found, clean the lower clevis fitting and reinstall the wing strut assembly.

(5) If wing strut assembly C2W1115-1 or C2W1115-2 is installed, the recurring visual inspection specified in Paragraph (a) of this AD is no longer required.

(b) The airplane may be flown in accordance with FAR 21.197 to a location where the requirements of this AD may be accomplished.

(c) Upon submission of substantiating data by owner or operator through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office,FAA, New England Region, may adjust the repetitive inspection intervals specified in this AD.

(d) An equivalent means of compliance with this AD may be used if approved by the Manager, New York Aircraft Certification Office, FAA, New England Region.

All persons affected by this directive may obtain copies of the document referred to herein upon request to the DeHavilland Aircraft Company of Canada, a Division of Boeing of Canada, Ltd., Garratt Boulevard, Downsview, Ontario, Canada, M3K 1Y5; telephone: (416) 633- 7310, or these documents may be examined at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This AD supersedes AD 87-01-04, Amendment 39-5488 (51 FR 45306; December 18, 1986).
This amendment, 39-5889, becomes effective on May 11, 1988.