65-28-05 MORRISEY: Amdt. 39-171 Part 39 Federal Register December 21, 1965. Applies to Models 2150 and 2150A Airplanes. \n\n\tCompliance required as indicated, unless already accomplished.\n\n\tTo detect cracking in the weldments of strut assemblies, P/N's MO-11000 and MO-11002, for both the right and left oleos of the main landing gear where the scissor assemblies are attached, accomplish the following: \n\n\t(a)\tWithin 25 hours' time in service after the effeactive date of this AD and at intervals not to exceed 25 hours' time in service from the last inspection, visually inspect for cracks the upper and lower scissors attachment fittings of the main landing gear until accomplishment of (c). \n\n\t(b)\tIf cracks are found, reinforce in accordance with (c) before further flight.\n \n\t(c)\tReinforce upper and lower scissors attachment fittings by the addition of 4130 steel plates at three locations described in Figure 1 or accomplish an equivalent repair approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis directive effective December 21, 1965.