AD 91-05-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | SOCATA | TB 20 | Airworthiness Directives SOCATA Models TB 20 and TB 21 airplanes |
| aircraft | SOCATA | TB 21 | Airworthiness Directives SOCATA Models TB 20 and TB 21 airplanes |
Unsafe Condition
Structural failure of the fuselage frame in the area of the landing gear attachment.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect fuselage frame No. 0 for cracks in the engine mount and landing gear mount area per Aerospatiale SB No. 42/1. Repair any cracks found prior to further flight. Repetitive inspections are not required if modified with Socata Kit 9152.
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Compliance Time
Within the next 100 hours time-in-service (TIS) after the effective date (March 25, 1991) for airplanes with >1,500 TIS hours on that date. For others, within the next 100 hours TIS or prior to 1,600 TIS hours, whichever occurs later. Thereafter, inspections every 500 TIS hours.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
SOCATA Models TB 20 and TB 21 (serial numbers 1 through 1051, except S/N 1040 and S/N 1042)
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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