COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Piper PA-31 Series Aeroplanes AD/PA-31/121 Amdt 1 Elevator Control System 5/94 DM Applicability: Model PA31, PA31P, and PA31T series aircraft. Requirement: Accomplish the following inspections and procedures: 1. Gain access to the elevator controls in the tail by removing the bottom half of the tailcone and the fuselage side panels. 2. Remove the long pushrod that connects the bellcrank and the elevator horn. 3. Secure the aft end of the bungee link to the elevator horn with safety wire for removal and installation of the bungee attach bolt. 4. Inspect, using a magnetic particle procedure, the rod end shank and threads for cracks. If found cracked, replace the rod end with a part number 49261-02 or 452- 658 rod end. 5. Visually inspect the bearing in the rod end for wear and free movement. If wear is found or the bearing will not move, replace the rod end with a part number 49261- 02 or 452-658 rod end. 6. Inspect, using a 10x magnifying glass, the forward attach holes in the pushrod for cracks, corrosion, or elongation. If cracks, corrosion, or elongation is found, replace the pushrod with a part number 40847-00, 40847-04, or 40847-07 pushrod, as applicable. 7. Visually inspect the forward and aft attach area to ensure that both a forward bolt, part number 402 311 (AN174-12A), and an aft bolt, part number 402 317 (AN174- 11A), are installed. If either one of these bolts is not installed, install the applicable bolt or replace the existing bolt with one of the applicable part number. 8. Remove the safety wire, reinstall the pushrod, check to ensure that the elevator rigging is correct, and reinstall the bottom half of the tailcone and the fuselage side panels. COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Note 1: Figure 1 of this Directive illustrates the elevator assembly and the specific areas that are to be inspected. Note 2: FAA AD 93-24-02 Rev 1 Amdt 39-8810 refers. Compliance: Within 30 hours time in service after 9 March 1994. Background: The FAA received a report of an incident where a Piper PA31T series aircraft experienced a complete loss of elevator control while in flight. An investigation disclosed that the aft control rod end bearing had separated into two pieces. Further investigation revealed a fatigue crack at the thread root, which extended through the rod end cross section. Amendment 1 is issued in response to a revision of the relevant FAA AD, which corrects the figure (contained in the AD) to reflect the correct installation, and provides an alternate rod end part number.