AD 89-09-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | 737-100 Series | Airworthiness Directives; BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-200 Series | Airworthiness Directives; BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-200C Series | Airworthiness Directives; BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-300 Series | Airworthiness Directives; BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-400 Series | Airworthiness Directives; BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-500 Series | Airworthiness Directives; BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-600 Series | Airworthiness Directives; BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-700 Series | Airworthiness Directives; BOEING Model 737 Series Airplanes |
| aircraft | The Boeing Company | 737-800 Series | Airworthiness Directives; BOEING Model 737 Series Airplanes |
Unsafe Condition
Decompression of the airplane due to potential failure of lap joints between BS 259 and BS 1016 and disbonding of tearstraps, which could result from corrosion and delamination in the fuselage structure.
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Required Actions
Accomplish terminating repair at lap joints between BS 259 and BS 1016 by replacing upper row fasteners with standard protruding head solid fasteners and ensuring functional tearstraps using mechanical fasteners where disbonding occurs. Perform preventative modification along S-17 using standard fasteners and ensure tearstraps are functional. Conduct external visual inspections for corrosion and delamination, followed by low and high frequency eddy current inspections if corrosion exceeds 10% skin thickness or cracks are found. Repair corrosion, delamination, and cracks as required.
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Compliance Time
Modify within the next 6, 12, 18, 24, or 36 months based on landings on the effective date for fuselage structure between BS 360 and BS 1016. For structure between BS 259 and BS 360, modifications must be done prior to 80,000 flight cycles or 4 years after the effective date, whichever comes first, or one year after the effective date, whichever is later. Inspections under paragraph C must be conducted within 15 months after accomplishment or 6 months after the effective date, whichever is later, and continue at intervals not exceeding 15 months. Corrosion over 10% requires reinspection every 2,250 cycles or 6 months until repair.
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Affected Aircraft
Boeing Model 737 airplanes, line numbers 001 through 291, certificated in any category.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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