Document ID: chunk:federal_register_of_legislation:F2006B11160:body:0
Version: federal_register_of_legislation:F2006B11160
Segment Type: other
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Character Range: 0–899

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

 Gates Learjet 24 & 25 Series Aeroplanes

 AD/LEARJET/8 Main Landing Gear Upper Strut - Inspection 3/75 Applicability:              Model 24 with S/Nos. 24-100 to 24-297; and model 25 with S/Nos. 25-003 to 25-182. Requirement:               To detect cracks or flaws in the MLG upper strut:-
              1. Remove strut from aeroplane, dismantle, clean and inspect using a Fluorescent Dye Penetrant Technique.

2.    If cracks or flaws are disclosed by the inspection in para. 1 evaluate the position of cracks or flaws as per Fig. 1 of Gates Learjet SB No. 23/24/25-259; reject or rework affected upper struts as specified.

            Compliance: Within 600 hours time in service after 30 April 1975 or 30 September 1976 whichever occurs first.