Commonwealth legislation

AD/GAF-N22/52 - Stub Wing Upper Front Spar Cap

RepealedCTH

This Act has been repealed and is no longer in force. It is retained for historical reference.

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

2/10 complexity

What this does

This directive orders owners and operators of GAF N22 and N24 Nomad aeroplanes to inspect a specific structural part of the aircraft wing — the stub wing upper front spar cap (the reinforced beam where the wing support strut attaches) — for cracks around the bolt holes.

Who it affects

Owners and operators of all models of GAF N22 and N24 series aircraft.

What must be done

Carry out inspections and any necessary repairs exactly as described in Nomad Service Bulletin NMD-53-6.
Because removing the fasteners is technically difficult and safety-critical, operators are advised to consider hiring the manufacturer's specialist personnel and equipment.

Why this matters

Fatigue testing revealed that the bolt holes in this wing component could develop cracks over time. While aircraft inspected so far haven't shown cracks, this directive ensures potential structural failures are identified before they compromise flight safety.

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Current sections

Direct links to the current provisions in AD/GAF-N22/52 - Stub Wing Upper Front Spar Cap.

AD/GAF-N22/52 - Stub Wing Upper Front Spar Cap

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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GAF N22 and N24 Series Aeroplanes

AD/GAF-N22/52 Stub Wing Upper Front Spar Cap 1/87

Applicability: All models.

Requirement: Action in accordance with Nomad Service Bulletin NMD-53-6.

Note: Because of particular difficulties associated with fastener removal and the critical nature of the operation, it is recommended that operators consider the manufacturer’s offer of specialist personnel and equipment, as outlined in Nomad Product Support Information Letter No. IL86-07.

Compliance: As detailed in the Requirement Document.

Background: The results of full scale fatigue tests being conducted by the manufacturer have shown the need for inspection of critical fastener holes in the stub wing upper front spar cap, near the wing strut attachment. Selected lead time aircraft which have been inspected, both in Australia and overseas, have not exhibited any cracks to date.

Source text

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

1 AD/GAF-N22/52 - Stub Wing Upper Front Spar Cap