Commonwealth legislation

AD/F100/15 - Centre Section Frame Strips

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

4/10 complexity

Requires specified Fokker F100 (F28 Mk.100) aeroplanes (serials 11244–11371) to have two reinforcement plates fitted at two fuselage stations per Fokker Service Bulletin F100‑53‑072, to be done before 24,000 flight cycles; effective 22 April 1999. The directive responds to fatigue-test discoveries of cracks at those frame strips and seeks to raise the crack-initiation threshold beyond 90,000 cycles. Affected operators must arrange the structural modification, pay for parts and labour, and plan for aircraft downtime to comply.

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AD/F100/15 - Centre Section Frame Strips

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source 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.

Source text

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