COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Cessna 170, 172, F172, FR172 and 175 Series Aeroplanes AD/CESSNA 170/65 Control Yoke Pivot Bolt 11/99 DM Applicability: The following serial numbers of Model 172R aircraft; that are equipped with a Cessna Modification Kit MK172-27-01 that was shipped sometime between September 21, 1998, and April 18,1999: Serial Numbers 17280003 through 17280016, 17280018 through 17280060, 17280062, 17280063, 17280065 through 17280071, 17280073 through 17280083, 17280085 through 17280088, 17280090, 17280091, and 17280093 through 17280096. Note 1: Modification Kit MK172-27-01 was issued to reduce friction in the elevator control system. Requirement: Inspect the control yoke pivot bolt to assure positive clearance between the threaded end of the pivot bolt and the aileron direct cable in accordance with the Accomplishment Instructions section of Cessna Service Bulletin SB99-27-01, dated July 12 1999. If positive clearance is not found, before further flight, accomplish the following in accordance with SB99-27-01: 1. Replace the control yoke pivot bolt; and, b. Inspect the adjacent aileron control cables for damage and replace any damaged aileron control cable. As of the effective date of this Directive, no person may incorporate on any aircraft, a Cessna Modification Kit MK172-27-01 that was shipped sometime between September 21, 1998, and April 18, 1999, unless a replacement control yoke pivot bolt is obtained from the manufacturer, and incorporated with the modification kit. Note 2: FAA AD 99-18-14 Amdt 39-11280 refers. Compliance: Within 25 hours time in service after 29 September 1999, unless already accomplished. This Airworthiness Directive becomes effective on 29 September 1999. Background: The FAA received information from the manufacturer of incorrect length control yoke pivot bolts supplied in certain Cessna Modification Kits MK172-27-01. The actions specified by this Directive are intended to prevent failure of an aileron control cable because of an incorrect length control yoke pivot bolt rubbing on one of these cables, which could result in loss of aileron control with loss of directional control of the aircraft.