Document ID: chunk:federal_register_of_legislation:F2006B03915:body:0
Version: federal_register_of_legislation:F2006B03915
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Character Range: 0–976

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

 Beechcraft 400 Series Aeroplanes

AD/BEECH 400/13 Spoiler Control Push Rod 3/96

Applicability: Model 400A aircraft, with serial numbers RK-1 through RK-96.

            Requirement: Perform a detailed visual inspection to verify if the securing rivet is installed on the control push rods of the spoiler flight control system, and an inspection to verify if the jam nut is secure on the opposite rod end, in accordance with Beechcraft Safety Communique 400A-113.

Note. FAA AD 95-25-05 Amdt 39-9450 refers.

 Compliance: Within 50 hours time in service after 29 February 1996.

            Background:  The FAA received a report of a loss of roll control on the co-pilot's control wheel shortly after take-off. An investigation revealed that this loss of control was due to a rivet missing from the spoiler control push rod.