AD 72-07-09
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Cessna Aircraft Company | 182 | Airworthiness Directives; CESSNA Models 205, 206, P206, TP206, 182, U206, TU206, 207, T207, 210, T210 Series Airplanes |
| aircraft | Cessna Aircraft Company | 182A | Airworthiness Directives; CESSNA Models 205, 206, P206, TP206, 182, U206, TU206, 207, T207, 210, T210 Series Airplanes |
| aircraft | Cessna Aircraft Company | 182B | Airworthiness Directives; CESSNA Models 205, 206, P206, TP206, 182, U206, TU206, 207, T207, 210, T210 Series Airplanes |
| aircraft | Cessna Aircraft Company | 182C | Airworthiness Directives; CESSNA Models 205, 206, P206, TP206, 182, U206, TU206, 207, T207, 210, T210 Series Airplanes |
| aircraft | Cessna Aircraft Company | 182D | Airworthiness Directives; CESSNA Models 205, 206, P206, TP206, 182, U206, TU206, 207, T207, 210, T210 Series Airplanes |
| aircraft | Cessna Aircraft Company | 182E | Airworthiness Directives; CESSNA Models 205, 206, P206, TP206, 182, U206, TU206, 207, T207, 210, T210 Series Airplanes |
| aircraft | Cessna Aircraft Company | 182F | Airworthiness Directives; CESSNA Models 205, 206, P206, TP206, 182, U206, TU206, 207, T207, 210, T210 Series Airplanes |
| aircraft | Cessna Aircraft Company | 182G | Airworthiness Directives; CESSNA Models 205, 206, P206, TP206, 182, U206, TU206, 207, T207, 210, T210 Series Airplanes |
| aircraft | Cessna Aircraft Company | 182H | Airworthiness Directives; CESSNA Models 205, 206, P206, TP206, 182, U206, TU206, 207, T207, 210, T210 Series Airplanes |
| aircraft | Cessna Aircraft Company | 182J | Airworthiness Directives; CESSNA Models 205, 206, P206, TP206, 182, U206, TU206, 207, T207, 210, T210 Series Airplanes |
Unsafe Condition
Cracks and loose bolts in the fin and rudder could lead to inflight separation of the fin and rudder.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect aft fin spar attachment bolts for looseness and visually inspect forward/aft vertical fin attachment structure for cracks. Dye penetrant inspect specified areas for cracks. If cracks/looseness found, remove/reinstall bolts with dye penetrant inspection of holes, check for excessive elongation, torque bolts to specified values, replace damaged parts, and install inspection putty. Report discrepancies via FAA Form 8330.2.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 50 hours' time in service after the effective date of this AD on all airplanes with 1000 or more hours' time in service, and thereafter at intervals not to exceed 1000 hours'. 206 series with floatplane vertical stabilizer: initial at 500 hours and 500 hour intervals thereafter.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Cessna Models 205, 206, P206, TP206 series; 182 series (Serial Numbers 18253599 through 18261528); U206 and TU206 series (Serial Numbers U206-0276 through U20601905); 207 and T207 series (Serial Numbers 20700001 through 20700216); 210 series (Serial Numbers 21057841 through 21059739); and T210 series (Serial Numbers T210-0001 through T210-0454 and 21059200 through 21059739).
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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