73-19-09 BELL: Amdt. 39-1718. Applies to Model 206A, 206B, 206A-1 and 206B-1 helicopters equipped with main rotor blade pitch link assemblies, P/N 206-010-330 and 206-010- 342, as applicable, certificated in all categories.
Compliance required within 25 hours time in service after the effective date of this A.D., unless previously accomplished and thereafter at intervals not to exceed 50 hours time in service from the last inspection.
To detect and prevent possible corrosion and cracks in the main rotor blade pitch link tubes, P/N 206-010-330, all dash numbers, accomplish the following:
(a) Inspect the ends and outside diameter surface of each tube for corrosion and cracking, using a 3 power or higher magnifying glass.
(b) Replace corroded or cracked tubes prior to next flight except a helicopter with corroded tubes may be flown in accordance with FAR 21.197 to a base where replacement may be accomplished.
(c) If tubes are replaced or adjusted, track themain rotor blades in accordance with the appropriate model maintenance and overhaul information manual.
(d) Apply corrosion preventive compound, MIL-C-16173, Grade 2, or equivalent, to the exposed threads of the upper and lower clevises, the ends of each tube, the mating faces of the locks and nuts and the top surfaces of the nuts after the nuts are properly torqued on each pitch link assembly.
(e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, may adjust the repetitive inspection interval specified in this A.D. to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.
(Bell Helicopter Company Service Bulletin No. 206-04-2-73-1 dated May 7, 1973 pertains to this subject.)
This amendment becomes effective September 17, 1973.