AD 89-25-08
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Textron Aviation Inc. | 65 | Airworthiness Directives; Beech Model 65, 65-80, 65-A80, and 65-B80 Airplanes |
| aircraft | Textron Aviation Inc. | 65-80 | Airworthiness Directives; Beech Model 65, 65-80, 65-A80, and 65-B80 Airplanes |
| aircraft | Textron Aviation Inc. | 65-A80 | Airworthiness Directives; Beech Model 65, 65-80, 65-A80, and 65-B80 Airplanes |
| aircraft | Textron Aviation Inc. | 65-B80 | Airworthiness Directives; Beech Model 65, 65-80, 65-A80, and 65-B80 Airplanes |
Unsafe Condition
Fatigue cracking of the wing main spar lower cap and associated structure.
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Required Actions
Inspect the wing lower forward spar attach fittings, center section and outboard wing spar caps adjacent to the attach fittings using visual, fluorescent penetrant, and eddy current methods as specified in Beech Structural Inspection and Repair Manual P/N 98-39006, Revision A4. Inspect reinforcing straps per STC SA1583CE for proper tension and condition. Repair or replace defective parts if cracks are found.
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Compliance Time
Within the next 200 hours time-in-service after the effective date of this AD, or upon accumulating 3000 hours TIS on Models 65-80 and 65-A80 or 5000 hours TIS on Models 65 and 65-B80, whichever occurs later. Repetitive inspections at intervals not exceeding 1000 hours TIS (extendable to 3000 hours TIS for STC SA1583CE equipped airplanes).
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Affected Aircraft
Beech Models 65 (S/N L-1, L-2, L-6, LF-7 through LF-76, LC-1 through LC-180); 65-80 and 65-A80 (S/N LD-1 through LD-244); 65-A80 (S/N LD-245 through LD-269) with Modification Kit 80-4004-1/-3; and 65-B80 (all S/N).
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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