COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Instruments and Automatic Pilots AD/INST/42 KSA 470 Autopilot Servo Actuator 7/98 Applicability: Allied Signal Bendix/King Model KSA-470 autopilot servo actuators, part numbers 065-0076-10 through 065-0076-15, serial numbers 0001 through 3081 inclusive. Note: The actuators are known to be fitted to, but not limited to the aircraft listed below: Aircraft Flight Part Number Location Director/Auto pilot System Raytheon (Beech) 400 Series KFC 400 065-0076-11 Yaw Axis 065-0076-15 Roll Axis Raytheon (Beech) 200 Series KFC 400 065-0076-11 Yaw Axis Raytheon (Beech) 300 Series KFC 400 065-0076-15 Yaw Axis Dassault Falcon 20 KFC 400 065-0076-15 Pitch Axis 065-0076-15 Roll Axis Fairchild C26A/C26B KFC 400 065-0076-11 Yaw Axis Fairchild SA227- AC/AT/BC/CC/DC KFC 400 065-0076-15 Roll Axis Learjet 31A KFC 3100 065-0076-12 Pitch Axis 065-0076-14 Yaw Axis 065-0076-15 Roll Axis Lockheed (Grumman) S-2 Tracker KFC 325 065-0076-10 Special Piper 400LS and PA-42-1000 KFC 400 065-0076-15 Yaw Axis Requirement: 1. Replace the autopilot servo actuator with an actuator that incorporates Mod 3, in accordance with procedures in the applicable maintenance manual. 2. An actuator, listed in the Applicability Statement, that has not had Mod 3 incorporated may not be installed on any aeroplane. Note: FAA AD 98-08-20 Amdt 39-10469 refers. Compliance: 1. Within the next 100 hours time in service after the effective date of this directive. 2. As of the effective date of this directive. COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 107 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES This airworthiness directive becomes effective on 18 June 1998. Background: This directive requires the replacement of the autopilot servo actuator with a modified servo actuator. This is a result of the FAA receiving two reports of the affected actuators containing loose roll pins within the servo housing. Loose pins could fall out and become lodged in the output shaft, preventing this mechanism from disengaging. The actions mandated by this directive are intended to prevent such an occurrence, which could result in an increased effort by the pilot to control the aircraft and possible loss of control of the affected flight control axis.