Document ID: chunk:federal_register_of_legislation:F2006B05306:body:0
Version: federal_register_of_legislation:F2006B05306
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Character Range: 0–1882

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

 Cessna 208 Series Aeroplanes

AD/CESSNA 208/11 Flap Support 5/95

 Applicability: Cessna Caravan 1 aeroplanes

            Models 208 and 208A: S/N 20800001 to 20800206 inclusive Model 208B: S/N 208B0001 to 208B0276 inclusive
             Requirement: 1. Visually inspect the flap supports at WS 53.00 and WS 126.50 in accordance with Cessna Service Bulletin (SB) CAB92-16, Revision 2, Accomplishment Instructions.

             2. Install modifications SK208-92B1 (left flap) and SK208-92B2 (right flap) in accordance with Cessna SB CAB92-16, Revision 2, Accomplishment Instructions.

             Compliance:   1. Inspect before 2000 hours time in service or before 50 hours time in service after 27 April 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 CAB92-16, Revision 2.

             Installation of SK208-92B1 and SK208-92B2 (Requirement 2) cancels the inspection requirements of this AD.

             2.    Install the modifications:

(a)     before 500 hours time in service after initial inspection in accordance with Requirement 1 or before 100 hours time in service after 27 April 1995, whichever occurs later; or

(b)     before 100 landings after installation of SK208-92A3 or SK208-92A4, whichever occurs first.

            Note: Kits SK208-92A3 and SK208-92A4 are an interim repair for cracking of flap support ribs; Cessna SB CAB92-16, Revision 2, refers.

            Background: Service experience has shown the potential for cracks to develop in the flap support structure. Failure of this structure could mean loss of the flap and possible loss of the aeroplane.