AD 63-18-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Corporation | 188A | LOCKHEED Models 188A and 188C Aircraft |
| aircraft | Lockheed Martin Corporation | 188C | LOCKHEED Models 188A and 188C Aircraft |
Unsafe Condition
Cracks have been found in fuselage stringers at the forward rivet through the 'tee' clips attaching them to the forward side of the pressure bulkhead at fuselage Station 1117.0.
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Required Actions
Inspect fuselage stringers below the floor and at or above the floor for cracks using visual, X-ray, or FAA-approved methods. Repair cracked stringers before further flight by replacing a section with thicker material per Lockheed's repair manual and reinforce stringers per Lockheed drawing or approved method. Inspections must be repeated at specified intervals unless repairs and reinforcements are done.
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Compliance Time
For aircraft with more than 4,000 hours' time in service: inspect stringers below the floor within the next 460 hours' time in service after the effective date (unless done within 540 hours before), and stringers above/longerons within 920 hours after. For aircraft with less than 4,000 hours: inspect below floor before 4,460 hours and above/longerons before 4,920 hours. Repetitive inspections at intervals not exceeding 1,000 hours (below floor) or 4,000 hours (above floor/longerons).
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Affected Aircraft
Lockheed Models 188A and 188C Aircraft.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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