AD 89-19-04 R1
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Textron Aviation Inc. | 200 | Airworthiness Directives; Beech Model 200, B200, 200C, B200C, 200CT, B200CT, 200T, B200T, and 300 Airplanes |
| aircraft | Textron Aviation Inc. | 200C | Airworthiness Directives; Beech Model 200, B200, 200C, B200C, 200CT, B200CT, 200T, B200T, and 300 Airplanes |
| aircraft | Textron Aviation Inc. | 200CT | Airworthiness Directives; Beech Model 200, B200, 200C, B200C, 200CT, B200CT, 200T, B200T, and 300 Airplanes |
| aircraft | Textron Aviation Inc. | 200T | Airworthiness Directives; Beech Model 200, B200, 200C, B200C, 200CT, B200CT, 200T, B200T, and 300 Airplanes |
| aircraft | Textron Aviation Inc. | 300 | Airworthiness Directives; Beech Model 200, B200, 200C, B200C, 200CT, B200CT, 200T, B200T, and 300 Airplanes |
| aircraft | Textron Aviation Inc. | B200 | Airworthiness Directives; Beech Model 200, B200, 200C, B200C, 200CT, B200CT, 200T, B200T, and 300 Airplanes |
| aircraft | Textron Aviation Inc. | B200C | Airworthiness Directives; Beech Model 200, B200, 200C, B200C, 200CT, B200CT, 200T, B200T, and 300 Airplanes |
| aircraft | Textron Aviation Inc. | B200CT | Airworthiness Directives; Beech Model 200, B200, 200C, B200C, 200CT, B200CT, 200T, B200T, and 300 Airplanes |
| aircraft | Textron Aviation Inc. | B200T | Airworthiness Directives; Beech Model 200, B200, 200C, B200C, 200CT, B200CT, 200T, B200T, and 300 Airplanes |
Unsafe Condition
Debonding of wing fuel bay upper skin panels made with bonded aluminum honeycomb sandwich construction could result in loss of structural integrity.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Check airplane records or inspect wing fuel bay upper skin panels to determine if bonded construction. If bonded, inspect for debonding within specified intervals (150 hours TIS or 6 months, or 600 hours TIS or 18 months) based on rivet presence. Address debonding via approved partial replacement panels, temporary repairs, or resealing per specified kits and service bulletins. Repeat inspections at intervals as required.
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Compliance Time
Within the next 30 days after the effective date of this AD, then within specified intervals (e.g., 150 hours TIS or 6 calendar months, 600 hours TIS or 18 calendar months, or subsequent intervals) depending on inspection results.
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Affected Aircraft
Beech Models 200, B200 (BB-2 to BB-1362); 200C, B200C (BL-1 to BL-135); 200CT, B200CT (BN-1 to BN-4); 200T, B200T (BT-1 to BT-33); 300 (FA-2 to FA-206 and FF-1 to FF-19) with bonded wing fuel bay upper skin panels.
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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