AD 2020-17-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | SAS | Airworthiness Directives; Airbus SAS Airplanes |
| aircraft | Aviat | Various | Airworthiness Directives; Airbus SAS Airplanes |
Unsafe Condition
Fatigue cracks on continuity fittings at the lower framing of the front windshield on airplanes on which Airbus Production Modification 22058 has been embodied, which could lead to failure of the continuity fittings at the lower node of the windshield central frame, possibly resulting in decompression of the airplane and injury to occupants.
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Required Actions
Repetitive high frequency eddy current (HFEC) inspections of the central node windshield area for cracking, and applicable corrective actions if cracking is found, as specified in EASA AD 2020-0005.
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Compliance Time
Before further flight
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Affected Aircraft
Airbus SAS Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
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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