Document ID: chunk:federal_register_of_legislation:F2006B04518:body:0
Version: federal_register_of_legislation:F2006B04518
Segment Type: other
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Character Range: 0–1374

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 Bell Helicopter Textron Canada (BHTC) 206 and Agusta Bell 206 Series Helicopters

 AD/BELL 206/65
 Amdt 2

 Main Rotor Pitch Link Clevises - Inspection 7/78

 Applicability: All models 206A, 206B and AB206 series.

             Requirement: 1. Inspect with the aid of an approved dye penetrant method the entire threaded portion of the upper and lower clevises in pitch link assemblies P/Nos. 206-010- 330 (all dash numbers) and 206-010-342 (all dash numbers).

            Note: It is desirable to use a fluorescent dye penetrant for this inspection but if unavailable a colour contrast penetrant may be used. Particular attention is drawn to ANO 108.10, Appendix 1, Para. 2.5.

             2. Prior to reinstallation of pitch links, check the force required to move bearing P/N 206-010-469-1 in swashplate outer ring horns by installing NAS 1305-27D bolt through bearing and installing cotter pin in bolt. Bottom bolt head against bearing and hook spring balance through head of cotter pin. If force to move bearing exceeds ten pounds, replace bearing.

            Compliance: Within 100 hours time in service after 5 May 1975, and thereafter prior to each installation on an aircraft.

 Background: AD/Agusta 206/56A.