AD/F406/5 - Horizontal Stabiliser Rear Attach Structure

Administered by Department of Infrastructure, Transport, Regional Development, Communications, Sport and the Arts

Legislation au F2006B09830 Not in force Legislative Instrument

Legislation content

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

 


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 CAR 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.

 

Reims Aviation F406 Series Aeroplanes

 

AD/F406/5 Horizontal Stabiliser Rear Attach Structure 8/2001

 

Applicability: Model F406 with serial numbers F406-0001 through F406-0089.

 

Requirement: Inspect in accordance with Reims Aviation Service Bulletin CAB01-5, dated 12 March 2001.

 

If cracks or elongated bolt holes are found, before further flight, repair or replace affected parts.

 

Note: DGAC AD 2001-161(A) refers.

 

Compliance: For the initial inspection:

 

Upon accumulating 2,500 hours total time in service, inspect at the next scheduled Phase 6 (600 hour) inspection. For aircraft that have accumulated more than 2,500 hours total time in service at the effective date of this directive, at the next scheduled Phase 6 inspection after 9 August 2001.

 

For repeat inspections:

 

At intervals not to exceed 2,400 hours time in service after the initial inspection. This Airworthiness Directive becomes effective on 9 August 2001.

Background:  The manufacturer received reports of fatigue cracks and elongated bolt holes found in the horizontal stabiliser rear attach structure and the vertical fin rear spar attach structure. Undetected cracking could result in structural failure of the empennage.


 

David Alan Villiers

Delegate of the Civil Aviation Safety Authority 22 June 2001

 

 

 

The above AD is notified in the Commonwealth of Australia Gazette on 11 July 2001.

 


Page 1 of 1

Interactions

Authorises

All Versions

Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.