Document ID: chunk:federal_register_of_legislation:F2006B09615:body:0
Version: federal_register_of_legislation:F2006B09615
Segment Type: other
Provision Reference: 
Character Range: 0–969

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/F100/15 Centre Section Frame Strips 4/99

 Applicability: F.28 Mk.0100 aircraft, serial numbers 11244 through 11371.

            Requirement: Install two reinforcement plates each at fuselage STA.14911 and STA.17011 in accordance with Fokker Service Bulletin (SB) F100-53-072 dated 12 March 1993.

            Note: RLD BLA 93-037(A) refers.

 Compliance: Unless previously accomplished, before accumulating 24,000 flight cycles since new.

            This Airworthiness Directive becomes effective on 22 April 1999.

            Background:   During fatigue tests on the F.28 Mk.0100, cracks were discovered in the frame strips at fuselage STA.14911 and STA.17011. This AD requires a modification to increase the crack initiation threshold beyond 90,000 flight cycles.