Document ID: chunk:federal_register_of_legislation:F2006B08097:body:0:p1
Version: federal_register_of_legislation:F2006B08097
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
    SCHEDULE OF AIRWORTHINESS DIRECTIVES

    Cessna 210 Series Aeroplanes

    AD/CESSNA 210/49 King Autopilot Roll Axis Bridle
                          Clamp - Inspection and Rectification

    11/80

               Applicability: All models 210K, 210L, 210M, 210N, T210K, T210L, T210M, T210N and P210N which have King Radio Model KFC 200 Autopilots installed in accordance with Supplemental Type Certificates (STC's) SA1202CE or SA1487CE and have the roll axis servo actuator mounted in the right outboard wing.

                 Requirement: 1. Gain access to the right wing aileron bellcrank by removing the aft cover plate on the underside of the wing between wing stations 155 and 172 in accordance with the appropriate Cessna service manual.

2.    Visually inspect the clevis bolt and nut which secures the autopilot bridle cable and the aileron cable to the aileron bellcrank to verify there is a cotter pin installed to secure the nut.

                 3.    If a cotter pin is installed, reinstall the cover plate.

4.    If no cotter pin is installed, further visually inspect the clevis bolt to determine if the bolt was cross drilled for a cotter pin.

5.    If there is a cotter pin hole and the nut is still in place, install an AN380-2-2, or equivalent, cotter pin and reinstall the cover plate.

6.    If there is no cotter pin hole, replace the clevis bolt with an AN23-15, or equivalent, bolt as defined by FAA Advisory Circular AC43.13. Reinstall the washer between the cable and fittings and install the nut and cotter pin. After securing the nut and cotter pin, re-rig the aileron system in accordance with the appropriate Cessna service manual and adjust the bridle cable to 20 + 2 pounds tension.

7.    Submit a defect report (MDR) if an incorrect clevis bolt is found to have been fitted or a cotter pin is missing.

               . Note 1: King Radio Corporation Installation Bulletin No. 170, dated October 1, 1980, has information application to this AD

               Note 2: FAA Emergency AD 80-21-03 2 October 1980 refers.

    Compliance: Within 10 hours time in service after 16 October 1980.

               Background:  It has been determined that the King Radio autopilot roll axis bridle cable may have been improperly installed on these aeroplanes. Both the bridle cable and the aileron cable were connected to the aileron bellcrank with a clevis bolt which may have no means to install a cotter pin to lock the castellated nut. This situation, if not corrected, could create a safety hazard to an operator should the nut loosen and allow the bolt to slip from the bellcrank and release both the aileron cable and servo bridle cable, resulting in the loss of roll axis flight control.
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