AD/B767/96 Amdt 2 - Trailing Edge Flaps - Hinge Fitting Assembly Bolts (Cth)

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.