Federal Register of Legislation - Australian Government

Primary content

AD/B747/323 Amdt 2 Airworthiness Directives/Pt 105 — Aircraft as made
Nose Wheel Well Top and Side Panel Webs and Stiffeners
Administered by: Infrastructure and Regional Development
Exempt from sunsetting by the Legislation (Exemptions and Other Matters) Regulation 2015 s12 item 15
Registered 11 Jul 2007
Tabling HistoryDate
Tabled HR07-Aug-2007
Tabled Senate07-Aug-2007
Date of repeal 22 Apr 2016
Repealed by CASA ADCX 006/16 — Repeal of Airworthiness Directive

 

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/B747/323 Amdt 1 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/B747/323 Amdt 2

Nose Wheel Well Top and Side
Panel Webs and Stiffeners

8/2007

 

Applicability:

Model 747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, -400, -400D, -400F, 747SR, and 747SP series aircraft.

Requirement:

Action in accordance with the technical requirements of FAA AD 2006-22-15 Amdt 39-14812.

Note:  Boeing Alert Service Bulletins 747-53A2465 Revision 4, and 747-53A2562 Revision 1, or later FAA approved revisions, refer.

Compliance:

As specified in the Requirement document, with a revised effective date of
2 August 2007.

 

This Amendment becomes effective on 2 August 2007.

Background:

Fatigue cracks have been found in the nose wheel well side panel webs, top panel web, and side panel horizontal stiffener on seven aircraft with between 15,726 and 32,018 flight cycles.  In addition, a significant crack was found in the side panel web on Boeing’s 747-400 Fatigue Test Aircraft.

Amendment 1 expanded the area of inspection, added a new secondary inspection if certain cracking is found, and reduced the intervals for the repetitive inspections.  The AD was prompted by a report of an in-flight decompression of a 747-100 series aircraft that had accumulated 27,241 total flight cycles.

Amendment 2 is issued in response to a new FAA AD, which reduces the intervals for certain repetitive inspections and removes a certain optional inspection.  This new AD also introduces a modification which requires replacing the nose wheel well side and top panels, which terminates the repetitive inspections.


David Villiers
Delegate of the Civil Aviation Safety Authority

19 June 2007