Document ID: chunk:federal_register_of_legislation:F2006B05307:body:0
Version: federal_register_of_legislation:F2006B05307
Segment Type: other
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Character Range: 0–1626

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

 Cessna 208 Series Aeroplanes

AD/CESSNA 208/12 Flap Outboard Support 6/95

 Applicability: Cessna 208 (Caravan 1) series aeroplanes:

            Models 208 and 208A: S/N 20800001 to 20800227 inclusive Model 208B: S/N 208B0001 to 208B0336 inclusive.
             Requirement: 1. Visually inspect the outboard flap support rib flanges at WS 214.30 in accordance with Cessna Service Bulletin (SB) CAB93-11, Accomplishment Instructions.

             2. Install modifications SK208-109-1 (left flap) and SK208-109-2 (right flap) in accordance with Cessna SB CAB93-11, Accomplishment Instructions.

             Compliance: 1. Inspect before 2000 hours time in service or before 50 hours time in service after 25 May 1995, whichever occurs later. Re-inspect at intervals not to exceed 100 hours time in service.

             If cracks are found, comply with the numbered "Compliance" paragraphs of Cessna SB CAB93-11.

             Installation of SK208-109-1 and SK208-109-2 (Requirement 2) cancels the inspection requirements of this AD.

             2. Install the modifications before 500 hours time in service after initial inspection in accordance with Requirement 1 or before 100 hours time in service after 25 May 1995, whichever occurs later.

            Background: Fatigue testing has shown the potential for cracks to develop in the outboard flap support rib structure. Failure of this structure could result in loss of the flap and possible loss of the aeroplane.