AD 2009-18-07
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Boeing | 747-100 | Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD, -200B, and -300 Series Airplanes; and Model 747SP and 747SR Series Airplanes |
Unsafe Condition
Fatigue cracks can occur in certain areas of the fuselage internal structure, potentially leading to loss of structural integrity and rapid depressurization of the airplane.
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Required Actions
Perform repetitive internal detailed inspections to detect cracks in specified fuselage areas, including sections 42 and 46 upper and lower lobe frames, main entry door cutouts, and bulkheads at body stations 260, 340, and 400. Investigate and take corrective actions if necessary.
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Compliance Time
Within 1,000 flight cycles after June 11, 1993, or prior to the accumulation of 22,000 total flight cycles, and thereafter at intervals not exceeding 3,000 flight cycles.
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Affected Aircraft
Boeing Model 747-100, -100B, -100B SUD, -200B, -300 Series, and Model 747SP and 747SR Series airplanes, certificated in any category, identified in Boeing Service Bulletin 747-53A2349, Revision 3, dated October 2, 2008.
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Source: Official FAA Source ↗
Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
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