AD 2005-04-51
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Boeing | 747-100B SUD | Airworthiness Directives; Boeing Model 747-100B SUD, -200B, -200C, -200F, and -300 Series Airplanes |
Unsafe Condition
Fatigue cracks in fuselage frames and body skin at body stations (BS) 420, 440, and 460 between stringers S-8 and S-12 inclusive, which could lead to severed frames, rapid decompression, and loss of structural integrity.
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Required Actions
Conduct repetitive external detailed inspections for cracked skin or loose/missing fasteners of the body skin between BS 420 and 460 inclusive and between stringers S-8 and S-12 inclusive on the left and right sides of the airplane. If cracks or loose/missing fasteners are detected, perform a high frequency eddy current (HFEC) inspection for cracks in the frames at BS 420, 440, and 460 between stringers S-8 and S-12. Repair any cracked frame or skin and replace any loose or missing fastener with a new fastener.
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Compliance Time
Before further flight
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Affected Aircraft
Boeing Model 747-100B SUD, -200B, -200C, -200F, and -300 series airplanes; and Boeing Model 747-200B series airplanes retrofitted with a stretched upper deck (SUD).
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
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