ATTACHMENT "A"
FAA AIRWORTHINESS DIRECTIVE
59-22-3
MOONEY(Applies to all Mooney M-18 series aircraft)
COMPLIANCE REQUIRED WITHIN THE NEXT 10 FLIGHT-HOURS BUT NOT LATER THAN DECEMBER 1 1959
The following inspections, repairs, and replacements shall be accomplished
(a)Empennage
(1)Remove and disassemble empennage. Remove control surface and hinge brackets from fin and horizontal stabilizer. Remove bolts through stabilizer main spar attach blocks. Disassemble stabilizer and fin from empennage truss and each other.
(2)Inspect all bolted joints for the following items.
(i)Wear on bolt
(ii)Wear on bolt holes in fittings and lugs
(iii)Wear on bushing
(iv)Wear on bushing on fittings, lugs and wood.
(Replace parts as necessary)
(3)Remove all fabric from stabilizer and fin. Inspect all wood and glue joints including attachment of leading edge skin to main spar for deterioration.
(4)At center section of stabilizer spar inspect glue joint between attach blocks and spar for deterioration and inspect spar and blocks for cracks. Inspect fin spar for cracks at attach bolts.
(5)Any defective wood parts shall be replaced or repaired in accordance with CAM 18 and/or manufacturer's recommendations. When the fin and stabilizer are satisfactory, reinforcement of the stabilizer main spar center section and the fin and stabilizer center hinge rib-rear spar attachment shall be accomplished in accordance with Mooney M-18 Service Letter No. 16. (Kits of reinforcement parts are available from Mooney Aircraft, Inc.)
(6)Clean all empennage drain holes, and see that they are located as specified in Mooney M-18 Service Letter 16.
(7)Inspect welds at rudder and elevator hinges and control horns ans at all joints on the tail truss for inadequate welds (i.e. weld which does not fill fillet cross section area) and for cracks using either method (i) or (ii) below.
(i) Magnetic particle or X-ray inspection.
(ii) Remove paint and primer and visually inspect welds with a 10-power glass.
