Document ID: chunk:federal_register_of_legislation:F2006L00722:body:0:p2
Version: federal_register_of_legislation:F2006L00722
Segment Type: other
Provision Reference: 
Character Range: 3039–5338

four upper fittings are required to be x-ray inspected as they are the most highly loaded in tension and therefore most susceptible to fatigue cracking.  If cracks are found, replace with a new part before further flight.

                6. Replace the first three steel rivets outboard of the butt rib through the two forward upper horizontal stabiliser attachment fittings in accordance with the Accomplishment Instructions of Service Bulletin 640 (340D) 55-4.

             Note:  FAA AD 82-19-02 Amdt 39-4458 refers.
Compliance:     1. Within 250 hours time in service after 13 April 2006, unless previously accomplished within 450 hours before 13 April 2006; thereafter at intervals not to exceed 700 hours time in service.

                2. Within 250 hours time in service after 13 April 2006, unless previously accomplished within 1150 hours time in service before 13 April 2006; thereafter at intervals not to exceed 1400 hours time in service.

                3. Unless already accomplished, within 10,000 hours time in service after 16 September 1982 (the effective date of FAA AD 82-19-02).  Continue to inspect after bushing replacement in accordance with Requirement 1 and 2.

                4. Within 250 hours time in service after 13 April 2006, unless previously accomplished within 450 hours time in service before 13 April 2006; thereafter at intervals not to exceed 700 hours time in service.

                5. Within 250 hours time in service after 13 April 2006, unless previously accomplished within 1150 hours time in service before 13 April 2006; thereafter at intervals not to exceed 1400 hours time in service.

                6. Unless already accomplished, within 10,000 hours time in service after 16 September 1982 (the effective date of FAA AD 82-19-02).  Continue to inspect after rivet replacement in accordance with Requirement 4 and 5.
             This Airworthiness Directive becomes effective on 13 April 2006.

Background:  The FAA requires certain inspections to prevent the possible loss of the horizontal stabiliser due to failure of the stabiliser attachment fittings (part numbers
             340-8510150 and 340-8510151), caused by fatigue cracks.

David Punshon
Delegate of the Civil Aviation Safety Authority

1 March 2006