73-07-03 GENERAL DYNAMICS: Amdt. 39-1612. Applies to Model 22M Series airplanes certificated in all categories.
Compliance required as indicated.
To detect cracks and prevent further failures of the actuator fitting, accomplish the following:
(1) Within the next 150 hours' time in service after the effective date of this A.D., unless already accomplished within the last 250 hours' time in service, and thereafter at intervals not to exceed 400 hours' time in service from the last inspection, inspect the rudder boost actuator fitting P/N 30-15701-1 in accordance with General Dynamics 880M S.B. No. A27-47 dated 1 March 1973, or later FAA-approved revision.
(2) If, as a result of the inspection required by paragraph (1), cracks are found, replace the defective fittings with an identical part.
This amendment becomes effective March 29, 1973.