AD 98-20-36
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
Fatigue-related cracking of the fuselage, wing, and vertical stabilizer structures could result in reduced structural integrity.
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Required Actions
Perform inspections for cracks in specified areas of the upper fuselage skin, circumferential fuselage splice plates, and stringer couplings as per service bulletins. Repairs must be done prior to further flight if cracks are found. Installation of specific modifications (e.g., Airbus Modification 2147 or 2526/1693) may terminate repetitive inspection requirements.
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Compliance Time
Required as indicated, unless accomplished previously. Initial inspections must be done by the later of 18,000 total landings or 18,000 total flight hours, whichever occurs earlier, or within one year after September 26, 1986. Subsequent inspections every 3,000 flight hours if no cracks detected.
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Affected Aircraft
Airbus Model A300 B2 and B4 series airplanes (excluding Model A300-600 series), all serial numbers listed in specified service bulletins.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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