AD/B747/353 - Fuselage Skin Cracks aft of Left Main Door (Cth)

AIRWORTHINESS DIRECTIVE For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(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 747 Series Aeroplanes AD/B747/353 Fuselage Skin Cracks aft of Left Main Door 2/2007

Applicability: Model 747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, -400, -400D, -400F, 747SR, and 747SP series aircraft; as identified in Boeing Alert Service Bulletin 747-53A2675, original issue, or later FAA approved revision. Requirement: Action in accordance with the technical requirements of FAA AD 2006-24-05 Amdt 39-14834. Compliance: As specified in the Requirement document, with a revised effective date of 15 February 2007. This Airworthiness Directive becomes effective on 15 February 2007. Background: The FAA received a report of fatigue cracks detected in the skin in section 41 of the fuselage, on an in-service Model 747 aircraft. Such cracking, unless detected and corrected, could join together and cause a loss of structural integrity and rapid decompression of the aircraft.

David Villiers Delegate of the Civil Aviation Safety Authority

19 December 2006