Document ID: chunk:federal_register_of_legislation:F2006B09624:body:0
Version: federal_register_of_legislation:F2006B09624
Segment Type: other
Provision Reference: 
Character Range: 0–1241

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

 Fokker F100 (F28 Mk 100) Series Aeroplanes

AD/F100/23 Cargo Door Frame 4/99

            Applicability: F.28 Mk.0100 aircraft, serial numbers as listed in Fokker Service Bulletin (SB) F100- 52-050, Revision 1 dated 14 September 1994.

            Requirement: Install two reinforcement plates under each hook latch fitting of each large cargo door in accordance with the Accomplishment Instructions of Fokker SB F100-52-050 Revision 1 dated 14 September 1994.

            Note: RLD BLA 94-157(A) refers.

            Compliance: Unless previously accomplished, before accumulating 11,000 flight cycles since new or 22 May 1999, whichever occurs later.

            This Airworthiness Directive becomes effective on 22 April 1999.

            Background: Stress analyses and destructive tests on the frames of F.28 Mk.0100 large cargo doors have shown that fatigue cracks may develop in the area of the hook latch fittings.
            This AD requires a modification to repair possible existing cracks and to prevent the development of new cracks in the affected large cargo door frames.