AD 98-20-26
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A320-111 | Airworthiness Directives; Airbus Model A320-111, -211, and -231 Series Airplanes |
| aircraft | Airbus | A320-211 | Airworthiness Directives; Airbus Model A320-111, -211, and -231 Series Airplanes |
| aircraft | Airbus | A320-231 | Airworthiness Directives; Airbus Model A320-111, -211, and -231 Series Airplanes |
Unsafe Condition
Fatigue cracking in the bolts and fittings of the frame-to-pressure-floor connection at frames 43 and 44, which could result in reduced structural integrity of the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform a detailed visual inspection to detect cracked or missing bolts and fittings prior to 20,000 total flight cycles or within 60 days after the AD's effective date, whichever is later. Repeat inspections at intervals not exceeding 5,100 flight cycles. Replace any cracked or missing bolts with new ones before further flight. Optional terminating action includes reinforcing fittings per specified service bulletins.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to the accumulation of 20,000 total flight cycles, or within 60 days 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 listed in Airbus Service Bulletin A320-53-1083, Revision 2, dated August 28, 1997.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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