AD 2010-01-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Boeing | Company Model 747-200F | Airworthiness Directives; The Boeing Company Model 747-200F, 747-200C, 747-400, 747-400D, and 747-400F Series Airplanes |
Unsafe Condition
Fatigue cracks can occur in certain fuselage structure, including Section 41 fuselage frames where they connect to upper deck floor beams, and Section 41 fuselage frames between stringers (S-8 and S-12).
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Required Actions
Conduct additional repetitive inspections for cracking of certain fuselage structure (Section 41 fuselage frames where they connect to upper deck floor beams, and Section 41 fuselage frames between stringers S-8 and S-12). Perform investigative/corrective actions if necessary. Reduce inspection threshold and repetitive inspection intervals for certain airplanes.
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Compliance Time
Within 12 months of the effective date (February 16, 2010).
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Affected Aircraft
The Boeing Company Model 747-200F, 747-200C, 747-400, 747-400D, and 747-400F series airplanes, certificated in any category.
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Source: Official FAA Source ↗
Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
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