AD 99-26-15
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A300 B2-1A | Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes |
| aircraft | Airbus | A300 B2-1C | Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes |
| aircraft | Airbus | A300 B2-203 | Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes |
| aircraft | Airbus | A300 B2K-3C | Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes |
| aircraft | Airbus | A300 B4-103 | Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes |
| aircraft | Airbus | A300 B4-203 | Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes |
| aircraft | Airbus | A300 B4-2C | Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes |
Unsafe Condition
Stress corrosion cracking of the inner skin panel of the longitudinal lap joint between frames 65 and 72 at stringer 57, which could result in rapid depressurization of the airplane.
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Required Actions
Perform an external eddy current inspection within 400 flight cycles after the effective date. Thereafter, perform internal or external eddy current inspections at intervals not exceeding 1,250 flight cycles or 7 months, whichever comes first. If cracking is detected, repair or modify the panel per specified service bulletins before further flight.
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Compliance Time
Within 400 flight cycles after January 25, 2000
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Affected Aircraft
Airbus Model A300 B2 and B4 series airplanes, manufacturer serial numbers 003 through 156 inclusive.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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