Document ID: chunk:federal_register_of_legislation:F2006B03449:body:0
Version: federal_register_of_legislation:F2006B03449
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Character Range: 0–2436

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

                    AIRWORTHINESS DIRECTIVE

 For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/B767/96 Amdt 1 and issues the following AD under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

 Boeing 767 Series Aeroplanes

 AD/B767/96
 Amdt 2

                 Trailing Edge Flaps - Hinge Fitting Assembly Bolts

 9/2003

 Applicability: Model 767-200, -300, and -300F series aircraft, line numbers 1 through 710. Requirement:              Action in accordance with the technical requirements of FAA AD 2003-09-08 Amdt
            39-13137.

            Note: Boeing Alert Service Bulletin 767-27A0151 Revision 4 and Service Bulletin 767-27A0155 Revision 2 refer.

            Compliance: As specified in the Requirement document, with a revised effective date of 7 August 2003.

            This Amendment becomes effective on 4 September 2003.

            Background: The manufacturer received a report of the separation of a 20-foot section of trailing edge flap, with associated damage to spoilers 9 and 12. Investigation revealed that four bolts attaching the inboard hinge fitting had failed; one bolt had previously fractured due to fatigue, two bolts partially fractured due to fatigue with subsequent overload, and one bolt failed fully in overload.

            Amendment 1 introduced revision 2 of the Requirement document, which clarified and alleviated certain requirements.

            Amendment 2 is issued in response to a new FAA AD, which reduces the applicability of the existing FAA AD, adds inspections, and mandates terminating action.

 David Villiers
 Delegate of the Civil Aviation Safety Authority 22 July 2003

 The above AD is notified in the Commonwealth of Australia Gazette on 13 August 2003.

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