Commonwealth legislation

AD/F100/23 - Cargo Door Frame

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legislative instrument

Plain English Summary

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This Airworthiness Directive requires certain Fokker F100 (F28 Mk 100) aeroplanes (specified by serial number in the Fokker service bulletin) to have two reinforcement plates fitted under each hook latch of each large cargo door, following Fokker SB F100-52-050 Revision 1. It responds to tests showing possible fatigue cracks. Aircraft operators must arrange and pay for the modification and complete it before the aeroplane reaches 11,000 flight cycles or by 22 May 1999, whichever is later.

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AD/F100/23 - Cargo Door Frame

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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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.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

1 AD/F100/23 - Cargo Door Frame