AD 88-09-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Corporation | 382 | LOCKHEED-GEORGIA Model 382 Series Airplanes |
| aircraft | Lockheed Martin Corporation | 382B | LOCKHEED-GEORGIA Model 382 Series Airplanes |
| aircraft | Lockheed Martin Corporation | 382E | LOCKHEED-GEORGIA Model 382 Series Airplanes |
| aircraft | Lockheed Martin Corporation | 382F | LOCKHEED-GEORGIA Model 382 Series Airplanes |
| aircraft | Lockheed Martin Corporation | 382G | LOCKHEED-GEORGIA Model 382 Series Airplanes |
Unsafe Condition
Failure of the control column and loss of control of the airplane due to fatigue cracking initiating at the sharp edge formed by thickness transition approximately midway up from the bottom of the 1.25-inch diameter hole on the forward side of the control column base, propagating aft around the perimeter of the base along the thickness transition.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Within 250 hours time-in-service after the effective date, perform an eddy current inspection of the left and right control column bases. If suspected defects are found, confirm with fluorescent penetrant inspection. Replace the control column base with a serviceable unit if defects are confirmed. Restore finishes, reinstall components, and rig the control system as required.
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Compliance Time
within 250 hours time-in-service after the effective date of this AD
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Affected Aircraft
Lockheed-Georgia Model 382 series airplanes, including models 382, 382B, 382E, 382F, 382G, 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 8, 2026
Rights: U.S. Government Public Domain
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