AD 89-25-10
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Textron Aviation Inc. | 100 | Airworthiness Directives; Beech Model 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, 100, A100 and B100 Aircraft |
| aircraft | Textron Aviation Inc. | 65-90 | Airworthiness Directives; Beech Model 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, 100, A100 and B100 Aircraft |
| aircraft | Textron Aviation Inc. | 65-A90 | Airworthiness Directives; Beech Model 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, 100, A100 and B100 Aircraft |
| aircraft | Textron Aviation Inc. | 65-A90-1 | Airworthiness Directives; Beech Model 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, 100, A100 and B100 Aircraft |
| aircraft | Textron Aviation Inc. | 65-A90-2 | Airworthiness Directives; Beech Model 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, 100, A100 and B100 Aircraft |
| aircraft | Textron Aviation Inc. | 65-A90-3 | Airworthiness Directives; Beech Model 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, 100, A100 and B100 Aircraft |
| aircraft | Textron Aviation Inc. | 65-A90-4 | Airworthiness Directives; Beech Model 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, 100, A100 and B100 Aircraft |
| aircraft | Textron Aviation Inc. | A100 | Airworthiness Directives; Beech Model 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, 100, A100 and B100 Aircraft |
| aircraft | Textron Aviation Inc. | B100 | Airworthiness Directives; Beech Model 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, 100, A100 and B100 Aircraft |
| aircraft | Textron Aviation Inc. | B90 | Airworthiness Directives; Beech Model 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, 100, A100 and B100 Aircraft |
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 per Beech SIRM Part No. 98-39006 Rev A4. Inspect reinforcing straps per Aviadesign E.O. B-8001 Issue 3 for tension and condition. Repair or replace cracked parts per Beech SIRM instructions. Submit inspection reports to FAA within one week.
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Compliance Time
Within the next 200 hours time-in-service (TIS) after the effective date or upon accumulating 3000 hours TIS, whichever occurs later, then every 1000 hours TIS (extendable to 3000 hours TIS if STC straps are installed and inspected).
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Affected Aircraft
Beech Models 65-90, 65-A90 (S/N LJ-1 to LJ-317); 65-A90-1 to 65-A90-4, B90, C90 (all S/N); C90A (S/N LJ-1063 to LJ-1087 except LJ-1085); E90, 100, A100, B100 (all S/N) airplanes.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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