AD/B747/340 Fuselage Main Frame (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/B747/340 Fuselage Main Frame 5/2006

Applicability:

Model 747-200F, -200C, -400, -400D, -400F series aircraft.

Requirement:

Action in accordance with the technical requirements of FAA AD 2006-05-02
Amdt 39-14499.

Note:  Boeing Alert Service Bulletin 747-53A2500, or later FAA approved revision, refers.

Compliance:

As specified in the Requirement document, with a revised effective date of
11 May 2006.

This Airworthiness Directive becomes effective on 11 May 2006.

Background:

The FAA requires repetitive inspections for cracking of certain fuselage internal structure, which results from fatigue tests and analysis that identified areas of the fuselage where cracks can occur.

David Villiers
Delegate of the Civil Aviation Safety Authority

31 March 2006