AD 98-19-07
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus SAS | A320-111 | Airworthiness Directives; Airbus Model A320-111, -211, and -231 Series Airplanes |
| aircraft | Airbus SAS | A320-211 | Airworthiness Directives; Airbus Model A320-111, -211, and -231 Series Airplanes |
| aircraft | Airbus SAS | A320-231 | Airworthiness Directives; Airbus Model A320-111, -211, and -231 Series Airplanes |
Unsafe Condition
Fatigue cracking of certain fastener holes on the outer frames of the fuselage, which could result in reduced structural integrity of the airplane.
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Required Actions
Inspect fastener holes at fuselage frame 35 between stringers 30 and 31 using a rotating probe inspection per Airbus Service Bulletin A320-53-1137. Modify the holes and install new fasteners if no cracking is found. Repair detected cracking with an approved method.
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Compliance Time
Prior to the accumulation of 20,000 total flight cycles, or within 4,000 flight cycles after the effective date of this AD, whichever occurs later.
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Affected Aircraft
Airbus Model A320-111, -211, and -231 series airplanes where Airbus Modification 20903 has not been installed.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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