AD 63-17-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Corporation | 188A | LOCKHEED Models 188A and 188C Series Aircraft |
| aircraft | Lockheed Martin Corporation | 188C | LOCKHEED Models 188A and 188C Series Aircraft |
Unsafe Condition
Fatigue cracking in the horizontal stabilizer spar web at fuselage Station 1167.7, stabilizer Station 29, in the 0.62-inch radius near the lower cap.
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Required Actions
Within 210 hours' time in service after the effective date, inspect the horizontal stabilizer spar web using dye-penetrant method or FAA approved equivalent, repair cracks as necessary. Stop drill cracks of 3/4 inch or less before further flight; repair larger cracks per Lockheed SB 88/SB-579 or equivalent. Repetitive inspections required at intervals based on crack size: uncracked every 1,200 hours, stop-drilled cracks ≤3/16 inch every 840 hours, 3/16-1/2 inch every 420 hours, >1/2-3/4 inch every 210 hours. Adjustments to intervals may be requested with substantiating data.
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Compliance Time
Within the next 210 hours' time in service after the effective date of this AD
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Affected Aircraft
Lockheed Models 188A and 188C Series Aircraft except those repaired per Lockheed SB 88/SB-579 or equivalent approved by FAA Western Region.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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