Document ID: chunk:federal_register_of_legislation:F2006B07209:body:0
Version: federal_register_of_legislation:F2006B07209
Segment Type: other
Provision Reference: 
Character Range: 0–1717

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/SWSA226/67 Horizontal Stabiliser Rear Spar 9/93 DM

            Applicability: Models SA226-T, SA226-T(B), SA226-AT and SA226-TC listed in Fairchild Aircraft Service Bulletin (SB) 226-55-005 (Revised 7 January 1991) and models SA227-TT, SA227-AT and SA227-AC listed in Fairchild Aircraft SB 227-55-002 (Revised 13 October 1988).

             Requirement: 1. Inspect the horizontal stabiliser rear spar near the outboard elevator hinge for cracks in accordance with Fairchild Aircraft SB 226-55-005 or Fairchild Aircraft SB 227-55-002, whichever is applicable. Use a fluorescent dye penetrant in accordance with CAO 108.10.

             2. Modify the horizontal stabiliser rear spar outboard hinges in accordance with Fairchild Aircraft SB 226-55-005 or Fairchild Aircraft SB 227-55-002, whichever is applicable.

            Note: FAA AD 93-07-12 refers.

             Compliance: 1. Inspect before 2500 flight hours or, unless previously inspected within the last 450 flight hours, inspect within 50 flight hours from 12 July 1993, whichever occurs later. Reinspect at intervals not to exceed 500 flight hours until modified as per Requirement 2.

            2. Modify before 2200 flight hours from 12 July 1993.

            Background: Elevator hinge loads have been causing cracks in the horizontal stabiliser rear spar. Failure of the spar could cause loss of the aircraft. This AD introduces a repetitive inspection to maintain safety in the short term until the hinge attachment is strengthened.