Document ID: chunk:federal_register_of_legislation:F2005L01747:body:0
Version: federal_register_of_legislation:F2005L01747
Segment Type: other
Provision Reference: 
Character Range: 0–2138

AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/B747/198 and issues the following 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/B747/198 Amdt 1  Main Entry Door Stop Support Fitting  8/2005

Applicability:  Model 747-100, -100B, -100B SUD, -200B, -200C, -300, -400, and -400D series aircraft; and Model 747SR aircraft; with line numbers 1 through 1301.
Requirement:    Action in accordance with the technical requirements of FAA AD 2005-10-18 Amdt 39-14095.

                Note:  Boeing Service Bulletins 747-53-2358, 747-53-2358 Revision 1, 747-53-2485, or later FAA approved revisions, refer.
Compliance:     As specified in the Requirement document, with a revised effective date of 4 August 2005.
                This Amendment becomes effective on 4 August 2005.
Background:     The FAA received reports of stress corrosion cracking found on certain stop support fittings of the main entry doors.  Failure of the stop support fittings could result in loss of a main entry door and consequent rapid decompression of the aircraft.

                Amendment 1 is issued in response to a new FAA AD, which adds new inspections, and replacement if necessary, of the stop support fittings of main entry door 3, and adds additional aircraft to applicability.  These actions were prompted by reports of main entry door 3 having certain stop support fittings that are susceptible to stress corrosion cracking.

David Villiers
Delegate of the Civil Aviation Safety Authority

21 June 2005