AD/BEECH 23/43 - Trailing Edge Flaps
1AD/BEECH 23/43 - Trailing Edge Flaps
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
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Beechcraft 19, 23 and 24 Series Aeroplanes
AD/BEECH 23/43 Trailing Edge Flaps 9/84
Applicability: All 19, 23 and 24 series.
Requirement: Inspect flap internal structure at the flap hinge arm attachment ribs for corrosion.
Note: This inspection will require leading edge skin removal or installation of inspection panels to a scheme approved by the Secretary.
Compliance: 1. Unless already accomplished, for aircraft which have achieved 5 years since date of manufacture, within 25 hours time in service after 12 September 1984 or 3 months, whichever occurs first and thereafter at intervals not exceeding 3 years.
- Unless already accomplished, for all other aircraft: before achieving 5 years since date of manufacture and thereafter at intervals not exceeding 3 years.
Background: Numerous Major Defect Reports have indicated that an advanced state of corrosion can exist without external indications. In some instances more than half of the hinge arm was corroded away.