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AD/B747/163 Amdt 4 - Fuselage Internal Structure
Boeing 747 Series AeroplanesBoeing 747 Series Aeroplanes
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Boeing 747 Series Aeroplanes
| AD/B747/163 Amdt 4 | Fuselage Internal Structure | 11/2009 |
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| Applicability: | Model 747-100, -100B, -100B SUD, -200B, -300, 747SP, and 747SR series aircraft, identified in Boeing Alert Service Bulletin 747-53A2349 Revision 3, dated2 October 2008, or later FAA approved revision. |
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| Requirement: | Acton in accordance with the technical requirements of FAA AD 2009-18-07Amdt 39-16003. |
| Compliance: | As specified in the Requirement document, with a revised effective date of22 October 2009. |
| This Amendment becomes effective on 22 October 2009. | |
| Background: | The manufacturer conducted pressure fatigue tests that identified areas of the fuselage internal structure where fatigue cracking occurred. Such cracking, if not detected and repaired, could result in loss of structural integrity of the fuselage and rapid depressurisation of the aircraft.Amendment 1 corrected compliance, and added an inspection area in accordance with Boeing Service Letter 747-SL-53-074.Amendment 2 added new repetitive inspections for cracking of certain areas of the upper chord of the upper deck floor beams and, if necessary, repair.Amendment 3 required repetitive inspections of additional areas of the fuselage internal structure, and related actions if necessary. The new FAA AD resulted from fatigue testing of the fuselage structure of a Model 747SR series aircraft.Amendment 4 is issued in response to a new FAA AD, which results from fatigue tests and analysis by Boeing that identified areas of the fuselage where cracks can occur; and requires additional repetitive inspections for cracking of certain fuselage structure. |
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David Villiers
Delegate of the Civil Aviation Safety Authority
4 September 2009