48-49-01 LUSCOMBE: Applies to All Model 8 Series Aircraft.
Compliance required by January 15, 1949.
If the present vertical stabilizer rear spar fuselage attachment fitting No. 18419 is fabricated of 0.049 thickness steel or has been replaced by a new 0.049 thickness steel fitting from the Luscombe Airplane Corp., this airworthiness directive does not apply.
Inspect the vertical stabilizer rear spar fuselage attachment fitting No. 18419 for evidence of cracks in the flange of the fitting adjacent to the 3/8-inch tube welded across the web between the flanges. If the present fitting has been fabricated of 0.035 thickness steel and the 3/8-inch tube has been welded to the flanges with a satisfactory 360 degrees weld and/or a partial weld (180 degrees) provided the flange of the fitting has been locally widened to a minimum of 3/16-inch edge distance at the 3/8-inch cross tube and there is no evidence of cracks in the flange, the fitting is considered satisfactory. However, if the fitting is cracked or does not have a satisfactory weld around the entire circumference of the bushing, the fitting must be reworked by making a complete 360 degrees weld around the 3/8-inch tube attaching it to the flange in addition to welding any existing cracks. As an alternate repair or reinforcement, weld one-half of an AN 960-616 washer or equivalent to each flange of the 18419 fitting so that the flat cut edge is parallel to the web of the fitting. In any event the fitting should be removed for reworking. If more than one crack is found in each flange, or if any crack has occurred between the bushing and the fitting web, the fitting must be replaced.
The Luscombe Airplane Corp. will furnish without charge a new fitting fabricated of 0.049 thickness steel for each old fitting fabricated of 0.035 thickness steel found to be defective.
(Luscombe Service Bulletin 3-47, dated November 26, 1947, covers this same subject.)
This supersedes AD 48-08-04