AD 87-22-02 R1
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | SOCATA | TB 10 | Airworthiness Directives; Socata Model TB 10, TB 20, and TB 21 Series Airplanes |
| aircraft | SOCATA | TB 20 | Airworthiness Directives; Socata Model TB 10, TB 20, and TB 21 Series Airplanes |
| aircraft | SOCATA | TB 21 | Airworthiness Directives; Socata Model TB 10, TB 20, and TB 21 Series Airplanes |
Unsafe Condition
Structural failure of the horizontal stabilizer/elevator attachment and loss of pitch control due to cracks on fuselage frame Number 9 in the area of the hinge and attachment fittings.
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Required Actions
Visually inspect for cracks on the forward and aft surface of fuselage frame Number 9 in the area of the hinge and attachment fittings. If cracks exist, replace the cracked fuselage frame with a new serviceable part. Repetitive inspections at intervals not exceeding 100 hours TIS are required unless modified by installed Modification No. 70 (SOCATA SB No. 35/1).
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Compliance Time
Upon the accumulation of 700 hours total time-in-service (TIS) or within the next 25 hours TIS, whichever comes later, unless previously accomplished per AD 87-22-02 (unrevised). Repetitive inspections must be done at intervals not to exceed 100 hours TIS thereafter.
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Affected Aircraft
Socata Models TB 10, TB 20, and TB 21 (Serial Numbers 1 through 795 inclusive)
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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