AD 2001-23-04
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Socata | Various | Airworthiness Directives; SOCATA-Groupe Aerospatiale Models TB 9, TB 10, TB 20, TB 21, and TB 200 Airplanes |
| aircraft | Aviat | Various | Airworthiness Directives; SOCATA-Groupe Aerospatiale Models TB 9, TB 10, TB 20, TB 21, and TB 200 Airplanes |
Unsafe Condition
Fatigue cracks in the lower rudder hinge fitting could cause the lower rudder to detach from the control linkage, resulting in loss of control of the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect the lower rudder hinge fitting for cracks upon accumulating 2,000 hours time-in-service (TIS) or within 100 hours TIS after January 4, 2002, and thereafter at intervals not exceeding 12 calendar months. If any crack is found, obtain a repair scheme from the manufacturer through the FAA and incorporate the repair scheme prior to further flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 100 hours time-in-service after January 4, 2002, or upon accumulating 2,000 hours TIS, whichever occurs later.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
SOCATA-Groupe Aerospatiale Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes, all serial numbers, certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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