67-13-03 PILATUS: Amdt. 39-388, Part 39, Federal Register April 4, 1967. Applies to Model PC-6 Series Airplanes, Serial Numbers to 563.
Compliance required as indicated.
To prevent failure of rivets attaching the rudder control lever to the rudder post, accomplish the following:
(a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 50 hours' time in service and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, visually inspect the rivets attaching the rudder control lever to the rudder post for defective or failed rivets.
(b) If defective or failed rivets are found during the inspection required by (a), before further flight, replace the 3mm. diameter rivets with AN 470 AD 5-10 rivets, or FAA- approved equivalent.
(c) The repetitive inspections required by (a) of this AD may be discontinued after the rudder control lever attachment is modified in accordancewith (b) of this AD.
(Pilatus Aircraft Limited Service Bulletin No. 66 pertains to this subject.)
This directive effective May 4, 1967.