COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Partenavia P68 Series Aeroplanes
AD/P68/45 Wing Spar Inspection 12/98 DM
Applicability: All P68 aircraft.
Requirement: 1. Determine if the forward or rear spar or both spars of each wing were modified IAW the modifications listed in any revision of Partenavia Service Bulletin #65.
Note 1: These modifications are described as terminating action for AD/P68/22 Amdt 4.
Note 2: These modifications were included at manufacture from serial number 348 onwards.
If no modification was fitted to either spar in either wing, then no further action is necessary for this AD.
2. Inspect the areas highlighted in Partenavia Service Bulletin #65 Revision 2 for possible commencement of new fatigue cracking or further cracking of old cracks in accordance with the inspection instructions listed in Partenavia Service Bulletin #65 Revision 2.
If new cracking or further cracking is found, then the crack must be repaired in accordance with a repair approved by the Authority.
Report all findings including nil results to the following address: Manager
Structures Group
Airworthiness Branch CASA
GPO Box 2005
Canberra ACT 2601
Or by fax to:
Structures Group
Airworthiness Branch (02) 6217 1914
A proforma for this report is attached.
Compliance: Within 25 hrs or one month of receipt of this AD, whichever occurs first.
This amendment becomes effective on 7 September 1998.
Background: The modifications described in Partenavia Service Bulletin #65 address fatigue cracking of the lower spar caps. These modifications are listed in the Service Bulletin as being terminating action for repetitive inspection in the area.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
A report has been received by CASA of a P68 with a modification fitted that failed to arrest crack growth. Review of the history and operational characteristics of the subject aircraft have found no reason to suspect that some unusual circumstance has caused further crack growth. Review of the modification design suggests that further cracking is possible. Unfortunately, engineering support is no longer available from Partenavia. Therefore, a once off inspection to ensure the immediate safety of the fleet is necessary.
The results of the condition of the Australian fleet will enable an assessment of the need for any further airworthiness action.