AD/F22/1 - Engine to Firewall Attachment

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COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety 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 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.


 

General Avia F22 Series Aeroplanes

 

AD/F22/1 Engine to Firewall Attachment 13/2004 TX

 

Applicability: Models F22A, F22B, F22C, and F22R aircraft.

 

Requirement: Perform a visual inspection for cracking of the structure surrounding the four bolts on the engine mount attachment at the firewall. Gain access from the cabin below the instrument panel, and if access is restricted, it is possible to remove the upper panels of the firewall bulkhead (the right side totally and left side partially), so that the area to be inspected can be accessed via the engine bay.

 

If cracks or failure are evident, before further flight, report details of the damage and the aircraft total hours time in service to ENAC (the Italian Airworthiness Authority) in order to determine what action is required. The contact at ENAC is Mr. C. Eminente, E-mail address c.eminente@enac.rupa.it.

 

Note: ENAC AD 2004-376 refers.

 

Compliance: Before further flight after 15 November 2004.

 

This Airworthiness Directive becomes effective on 15 November 2004.

 

Background: Several reports were received by ENAC of cracks in the engine mount to firewall attachment. Such cracking could result in detachment of the engine mounts from the firewall structure. The cause of the cracking is unknown and further action may be required.


David Villiers

Delegate of the Civil Aviation Safety Authority 12 November 2004

 

 

 

 

 

The above AD is notified in the Commonwealth of Australia Gazette on 15 November 2004.

 


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