Commonwealth legislation

AD/F28/71 - Wing to Fuselage Skin Connection

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legislative instrument

Plain English Summary

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This AD requires operators of specified Fokker F28 serial numbers to install a reinforcement on the centre‑wing-to‑fuselage connecting angles per RLD AD 91‑055, to address in‑service fatigue cracking. The work must be done before 30,000 flights or by 1 June 1997, whichever is later.

Operators fund and schedule the one‑off modification; once fitted the repeated inspection in the Structural Integrity Program is no longer required, trading a recurring inspection burden for an upfront modification cost.

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AD/F28/71 - Wing to Fuselage Skin Connection

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Fokker F28 Series Aeroplanes

AD/F28/71 Wing to Fuselage Skin Connection 13/92

Applicability: Serial Numbers 11003 to 11161 inclusive, 11991 and 11992.

Requirement: Reinforce the connecting angles in accordance with RLD AD 91-055, dated 14 June 1991.

Note: Fokker SB F28/53-101 refers.

Compliance: Before 30,000 flights, or 1 June 1997, whichever is the later.

Note: This reinforcement eliminates the need for further inspection in accordance with the F28 Structural Integrity Program, Part 1, item 53-10-14 (AD F28/45).

Background: Fatigue cracks have been reported in earlier F28 connection angles, which form part of the centre wing to fuselage skin connection. Service experience has shown that these cracks can grow to a large size between inspections. The RLD has therefore determined that modifying these angles should be a mandatory requirement.

Source text

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

1 AD/F28/71 - Wing to Fuselage Skin Connection