Commonwealth legislation

AD/A109/24 - Main Rotor Blade - Trailing Edge

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This Act has been repealed and is no longer in force. It is retained for historical reference.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

3/10 complexity

This rule requires owners and operators of Agusta A109A and A109A II helicopters fitted with main rotor blades P/N 109-0103-01 to perform regular inspections to prevent catastrophic blade failure from manufacturing-related cracking.

Operators must do daily visual checks of the trailing edge and regular detailed inspections (including 3× magnification and dye‑penetrant confirmation) on the schedule set by the rule, and inspect immediately after any unexplained vibration. Undetected cracks have led to dangerous failures.

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Current sections

Direct links to the current provisions in AD/A109/24 - Main Rotor Blade - Trailing Edge.

AD/A109/24 - Main Rotor Blade - Trailing Edge

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Agusta A109 Series Helicopters

AD/A109/24 Main Rotor Blade - Trailing Edge 5/95

Applicability: All Agusta A109A and A109A II series helicopters with main rotor blades P/N 109- 0103-01.

Requirement: 1. Visually inspect the trailing edge of the main rotor blades for dents, cracks or other damage in accordance with Agusta Bolletino Technico 109-50 Part I.

Perform a close visual inspection using a 3X magnifying glass of the upper and lower surfaces of the trailing edge of the main rotor blades for cracks. Confirm all indications with dye penetrant. Inspect in accordance with Agusta Bolletino Technico 109-50 Part II.

Note: RAI AD 92-190 refers.

Compliance: 1. Inspect in accordance with Requirement 1 before the first flight of the day.

2. Initially inspect in accordance with Requirement 2 before 500 hours’ time in service, or within 25 hours’ time in service after 27 April 1995, whichever occurs later. Re-inspect at intervals not to exceed 25 hours’ time in service.

3. Inspect in accordance with Requirement 2 before further flight after any unexplained vibration is experienced.

Background: Several cases of cracking have been reported in the trailing edge of the main rotor blades. The cracking is caused by anomalies in production.

Source text

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

1 AD/A109/24 - Main Rotor Blade - Trailing Edge