Document ID: chunk:federal_register_of_legislation:F2006B07293:body:0
Version: federal_register_of_legislation:F2006B07293
Segment Type: other
Provision Reference: 
Character Range: 0–2160

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

 Aerospatiale (Socata) TB9 and TB10 (Tobago) Series Aeroplanes

 AD/TB10/25
 Amdt 2

 Wing Rear Attachment Fittings 10/96

 Applicability: Models TB10 and TB200 S/N 804, 807,808, 816 to 819, 823 to 1701, 1707 to 1733,
            1737 to 1761.

             Requirement: 1. Remove the cowling under hull Nr.218 to gain access to the wing rear attachment fitting. Visually inspect the bend radii of the wing to fuselage rear attachment fitting for cracks.

             2. Remove and prepare the wing to rear fuselage rear attachment fittings in accordance with Socata SB 10-82-57 Amdt.1 and inspect using a fluorescent dye penetrant per CAO 108.10.

            Note: DGAC AD 94-249(A)R1 refers in part.

             Compliance: 1. Initially inspect within 100 hours time in service after 22 June 1995, thereafter at intervals not exceeding 200 hours time in service.

             2. Unless already accomplished in accordance with the initial issue of Requirement 2 Socata document; before the accumulation of 3 000 flights, or 2 000 hours time in service, whichever occurs first; thereafter at intervals not exceeding 3000 flights or 2000 hours time in service, whichever occurs first.

            Installation of kit OPT10 920300 terminates this Directive on the side to which the kit is fitted.

            The compliance remains unchanged from the previous issue. This Amendment becomes effective on 12 September 1996.
            Background: Inspection of the wing to fuselage attachment is necessary to ensure the continued integrity of the structure.

            Amendment 1 added an in-situ visual inspection of the fittings due to reports to the Authority of cracks developing within times significantly less than that required by the DGAC AD and the manufacturer.

            Amendment 2 provides terminating action.

            The original issue of this Airworthiness Directive became effective on 2 March 1995. Amendment 1 of this Airworthiness Directive became effective on 22 June 1995.