AD/Beech 76/19 Trailing Edge Flaps (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Beechcraft 76 (Duchess) Series Aeroplanes

AD/BEECH 76/19 Trailing Edge Flaps 2/2005

Applicability:

All Beechcraft 76 series.

Requirement:

Inspect flap internal structure at the flap hinge bracket attachment ribs for corrosion.

This inspection will require leading edge skin removal or installation of inspection panels to a scheme approved by the Authority or a suitably authorised CAR 35 person.

Compliance:

Unless already accomplished, within 25 hours time in service after 17 February 2005 or 3 months, whichever occurs first and thereafter at intervals not exceeding 3 years.

This Airworthiness Directive becomes effective on 17 February 2005.

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 bracket was corroded away.

Neville Probert
Delegate of the Civil Aviation Safety Authority

21 December 2004

The above AD is notified in the Commonwealth of Australia Gazette on 26 January 2005.