AD 98-25-05
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A321-111 | Airworthiness Directives; Airbus Model A321-111, -112, and -131 Series Airplanes |
| aircraft | Airbus | A321-112 | Airworthiness Directives; Airbus Model A321-111, -112, and -131 Series Airplanes |
| aircraft | Airbus | A321-131 | Airworthiness Directives; Airbus Model A321-111, -112, and -131 Series Airplanes |
Unsafe Condition
Fatigue cracking in the area surrounding certain attachment holes of the forward pintle fittings of the main landing gear (MLG) and the actuating cylinder anchorage fittings on the inner rear spar of the wings 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
Inspect using repetitive ultrasonic or eddy current inspections as specified in Airbus Service Bulletins A320-57-1101 or A320-57-1100 to detect fatigue cracking; repair if necessary, in accordance with FAA or DGAC-approved methods. Optional terminating action is provided to eliminate the need for repetitive inspections.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
No specific compliance time stated in the source; the AD applies to airplanes if imported and placed on the U.S. Register in the future.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Airbus Model A321-111, -112, and -131 series airplanes.
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
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.