59-22-03 MOONEY: Applies to All M-18 Series Aircraft.
Compliance required within the next 10 flight-hours but not later than December 15, 1959.
The following inspections, repairs, and replacements shall be accomplished:
(a) Empennage
(1) Remove and disassemble empennage. Remove control surfaces 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 bolts
(ii) Wear on bolt holes in fittings and lugs
(iii) Wear on bushing
(iv) Wear of 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 and 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. Parts with defective welds are to be replaced or repaired. A joint may be rewelded providing the old weld is removed and the surfaces thoroughly cleaned.
(8) Remove upper tail truss attach fittings from aft fuselage bulkhead and inspect as described in item (2). Inspect bulkhead front and back for cracks in area of these fittings. Inspect glue joint between bulkhead and aft fuselage skin and longerons for deterioration or separation. Repair in accordance with Mooney M-18 Service Letter No. 17. Examine trim linkage attached to lower part of aft bulkhead for worn bolts. Replace bolts as necessary.
(9) Reassemble and install empennage making sure all bolts are tight. Block airplane solidly at tail skid and inspect for empennage play as follows:
(i) Stabilizer - Move up and down at one tip and measure at opposite tip. Total allowable play 1/2-inch up and down.
(ii) Stabilizer - Move fore and aft at one tip and measure at opposite tip. Total allowable play 3/4-inch fore and aft.
(iii) Fin - Move fore and aft at top leading edge and measure at bottom rudder trailing edge. Total allowable play 1/2-inch up and down.
(b) Aft Fuselage
(1) Inspect wood around forward fuselage tubular structure attach fittings for deterioration. Clean all drain holes. Inspect all glue joints for deterioration. See that drain holes are located as specified in Mooney M-18 Service Letter 16.
(c) Wing
(1) Remove-seat, auxiliary fuel tank and belly access panel. Inspect ribs, skin and both spars at lower center section and around fuselage fittings for wood and glue joint deterioration.
(2) Inspect all wood and glue joints in wheel well area for deterioration. Inspect both spars for cracks in area of the gear attachments.
(3) Inspect interior of wing in areas having access openings.
(4) Remove aileron and inspect hinges and control horn in accordance with part (a), item (7).
(5) Remove wing fabric locally in area of aileron hinges and at inboard corner of aileron cutout and check condition of wood and glue joints. If evidence of deterioration is found remove fabric further as necessary for complete examination of forward area of wing trailing edge. Check security of attachment of wing trailing edge in aileron area.
(6) Clean all drain holes in wing, and see that they are located as specified in Mooney M-18 Service Letter 16.
(d) Control Systems
(1) Inspect all control systems (aileron, trim, rudder, and elevator).
(i) Visually inspect all welds for cracks and inadequate welds (i.e. weld which does not completely fill fillet cross section area).
(ii) Check security of all bolted hinge and fitting attach points.
(Mooney M-18 Service Letters Nos. 16 and 17 pertains to this same subject.)