Document ID: chunk:federal_register_of_legislation:F2006B07211:body:0
Version: federal_register_of_legislation:F2006B07211
Segment Type: other
Provision Reference: 
Character Range: 0–2278

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

 Fairchild (Swearingen) SA226 and SA227 Series Aeroplanes

AD/SWSA226/69 Wing - Upper Skin at WS 81 5/95

            Applicability: Models SA226-T, SA226-T(B), SA226-AT and SA226-TC listed in Fairchild Service Bulletin (SB) 226-57-018 Revised October 25, 1993.

            Models SA227-TT, SA227-AT, SA227-AC and SA227-BC listed in Fairchild SB 227-57-005 Revised July 1 1993. Models SA227-CC and SA227-DC listed in Fairchild SB CC7-57-002 Revised July 1, 1993.

             Requirement: 1. Visually inspect the wing upper surface skin at the top aft outboard corner of the battery box for cracking.

             Inspect in accordance with paragraph 2 ACCOMPLISHMENT INSTRUCTIONS, sub paragraph A Inspection, of the applicable Fairchild SB.

             2.    Dye penetrant inspect the edges of P/N 27-31130 straps for cracking.

             Inspect in accordance with paragraph 2 ACCOMPLISHMENT INSTRUCTIONS, sub paragraph A Inspection, of the applicable Fairchild SB.

3.    Modify the upper wing skin in accordance with paragraph 2 ACCOMPLISHMENT INSTRUCTIONS, sub paragraph B Removal, and sub para C Installation, of the applicable Fairchild SB.

            Note: FAA AD 94-07-10 refers.

             Compliance: 1. Initially inspect in accordance with Requirement 1 before 2500 hours time in service or within 100 hours time in service after 27 April 1995, which ever is the later. Re-inspect at intervals not to exceed 500 hours time in service.

2.    If cracks are found as a result of Requirement 1 inspection, inspect in accordance with Requirement 2 before further flight. Re-inspect at intervals not to exceed 50 hours time in service.

3.    Modify in accordance with Requirement 3 before further flight if cracks are found as a result of Requirement 2 inspection.

            Modification in accordance with Requirement 2 cancels the inspection requirements of this AD.

            Background: Reports have been received of cracking in the upper surface wing skin in the subject area. This AD will ensure that any problem is detected at an early stage and provides terminating repair/modification action.