FAA Proposed Airworthiness Directive for Certain Airbus A320 and A321 Cargo Door Structures
AI-generated summary for informational purposes only. Not legal advice. See the original source for the authoritative text.
The proposal would require U.S. operators of certain Airbus A320 and A321 aircraft to inspect the upper corners of the bulk cargo door for cracks. The issue was found during fatigue testing, where cracks appeared around fastener holes near the forward and aft upper corners of the door. If left unchecked, the cracks could weaken the aircraft structure. Affected operators would need to carry out a rototest inspection using the EASA directive and Airbus service bulletin referenced by the FAA. If cracks are found, the aircraft would need an approved repair before it flies again. If no cracks are found, operators may need to strengthen the area by cold working the fastener holes. Comments are due by June 18, 2026. The FAA estimates 1,069 U.S.-registered aircraft are affected, with basic inspection costs of about $340 per aircraft, not including possible repair costs.
AI-generated summary. May contain errors. Refer to official sources for legal decisions.
Key Changes
- Requires rototest inspections for cracks at the forward and aft upper corners of the bulk cargo door on specified Airbus A320 and A321 models
- Requires approved repairs before further flight if cracks are found
- Requires operators to follow EASA AD 2025-0193 and Airbus Service Bulletin A320-53-1303, with FAA-specific exceptions
Obligations
What this law requires
U.S. operators of affected Airbus A320-211, -212, -214, -216, -231, -232, and -233 airplanes and A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes must perform a rototest inspection for cracks around the fastener holes at the forward and aft upper corners of the bulk cargo door at sections 16 and 17, on both left-hand and right-hand sides, using EASA AD 2025-0193 and the referenced Airbus service information.
If any crack is detected during the required inspection, the operator must contact the manufacturer for repair instructions and complete an approved repair before the aircraft flies again.
If no crack is detected during the required inspection, the operator must modify the affected area by cold working the fastener holes where required by EASA AD 2025-0193.
Anyone submitting comments on the proposed AD must ensure the FAA receives the comments by June 18, 2026.
Anyone submitting comments must include “Docket No. FAA-2026-3879; Project Identifier MCAI-2025-01452-T” at the beginning of the comments.