# AD 89-25-10: Wing Main Spar Inspection - Type: Airworthiness directive - Status: Current - Products: Textron 100, 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, A100, B100, B90, C90, C90A and 1 more - Effective: January 4, 1990 - Superseded by: Nothing supersedes this AD - Product type: Aircraft, Small airplane - Amendment: 39-6409 - Registered aircraft: 903 may be affected, by airframe or engine model (OpenAirDocs) - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/084F6FBD88079DC9862569B300529E40.0001 - DRS record last changed: January 21, 2026 - Page: https://openairdocs.org/ad/89-25-10 ## The airworthiness directive 89-25-10 BEECH: Amendment 39-6409. Applicability: Models 65-90 and 65-A90 (Serial Number (S/N) LJ-1 thru LJ-317); 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90 (all S/N); C90A (S/N LJ-1063 thru LJ-1087, except LJ-1085); E90, 100, A100 and B100 (all S/N) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To detect possible fatigue cracking of the wing main spar lower cap and associated structure, accomplish the following: (a) Within the next 200 hours time-in-service (TIS), after the effective date of this AD, or upon accumulating 3000 hours TIS, whichever occurs later, unless previously accomplished per AD 87-23-09, Amendment No. 39-5765, or AD 70-25-04, Amendment No. 39-1332, and thereafter at intervals not to exceed 1000 hours TIS (except as provided in paragraph (b) below) after the initial inspection, inspect the wing lower forward spar attach fittings, center sectionand outboard wing spar caps adjacent to the attach fittings by visual, fluorescent penetrant and eddy current methods as specified in the applicable section of Beech Structural Inspection and Repair Manual (SIRM), Part Number 98-39006, Revision A4, dated May 1, 1987. The inspection must be performed by personnel specifically trained by Beech Aircraft Corporation. NOTE 1: Beech offers a two-day training course free of charge to qualified personnel who have prior knowledge of eddy current inspection techniques. A listing of Beech Corporate maintenance facilities may be obtained from the sources contained in paragraph (g) of this AD. A listing of other facilities employing qualified inspectors is not available. (b) At each inspection required by paragraph (a) above, inspect any reinforcing strap installed per Supplemental Type Certificate (STC) SA1178CE or SA1583CE for proper tension and condition in accordance with Aviadesign Engineering Order E.O. B-8001, Issue 3, dated May30, 1985. Correct any discrepancy prior to further flight. For airplanes so equipped and inspected, the repetitive inspection interval of 1000 hours TIS in paragraph (a) above may be extended to 3000 hours TIS. (c) If any crack is found in a main spar lower cap or fitting, prior to further flight repair or replace the defective part using the instructions and limitations specified in the Beech SIRM or other FAA approved instructions provided by Beech Aircraft Corporation. (d) Within one week after completion of any inspection required by paragraph (a) or (b) of this AD, complete the reporting form included with this AD as Figure 1 and mail it to the address shown thereon (Reporting approved by the Office of Management and Budget under OMB No. 2120-0056). (e) The initial and repetitive inspections specified in this AD are no longer required when the airplane is modified by Beech Wing Modification Kit No. 90-4077-1S or 100-4007-1S. (f) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (g) An alternate method of compliance or adjustment of the initial or repetitive compliance times which provides an equivalent level of safety, may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. NOTE 2: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Beech Aircraft Corporation, Commercial Service, Department 52, Wichita, Kansas 67201-0085; or Western Aircraft Maintenance, 4444 Aeronca Street, Boise, Idaho 83705, or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. ThisAD supersedes AD 87-23-09, Amendment 39-5765, and AD 70-25-04, Amendment 39-1332. This amendment (39-6409, AD 89-25-10) becomes effective on January 4, 1990. REPORTING FORM - 89-25-10 Airplane Model No. ___________________________________________________ Airplane Serial No.____________________________________________________ Date of inspection per this AD____________________________________________ Airframe total hours time-in-service________________________________________ Were any fatigue cracks found? No Yes __ If "Yes" was checked above, complete the following: Location of crack_____________________________________________________ Was crack removable by reaming or grinding? No Yes __ Additional Comments __________________________________________________ Mailing Address: FAA, Wichita ACO Airframe Branch, Room 100 1801 Airport Road Wichita, KS 67209 FIGURE 1 - 89-25-10 ## Affected data sheets (2) (OpenAirDocs) The type certificate data sheets whose models the AD names. - [TCDS 3A20](https://openairdocs.org/tcds/3A20): Textron Aviation Inc.; names 10 of 22 models: B90, 65-A90-2, 65-A90-1, 65-A90-3, E90, 65-A90, C90A, 65-A90-4… - [TCDS A14CE](https://openairdocs.org/tcds/A14CE): Textron Aviation Inc.; names 3 of 12 models: B100, A100, 100 ## Registered aircraft it may apply to (OpenAirDocs) Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment. - Aircraft: 903 (903 by airframe model, 0 by engine model) - Makers: Beech 747, Raytheon 156 Models with the most aircraft: - [Beech C90](https://openairdocs.org/model/beech-c90): 216 aircraft (airframe model) - [Raytheon C90A](https://openairdocs.org/model/raytheon-c90a): 155 aircraft (airframe model) - [Beech E-90](https://openairdocs.org/model/beech-e-90): 145 aircraft (airframe model) - [Beech C90A](https://openairdocs.org/model/beech-c90a): 125 aircraft (airframe model) - [Beech 65-A90-1](https://openairdocs.org/model/beech-65-a90-1): 90 aircraft (airframe model) - [Beech B100](https://openairdocs.org/model/beech-b100): 58 aircraft (airframe model) - [Beech 65-A90](https://openairdocs.org/model/beech-65-a90): 34 aircraft (airframe model) - [Beech B90](https://openairdocs.org/model/beech-b90): 29 aircraft (airframe model) - [Beech A100](https://openairdocs.org/model/beech-a100): 15 aircraft (airframe model) - [Beech 100](https://openairdocs.org/model/beech-100): 14 aircraft (airframe model) - [Beech 65-A90-4](https://openairdocs.org/model/beech-65-a90-4): 13 aircraft (airframe model) - [Beech 65-90](https://openairdocs.org/model/beech-65-90): 7 aircraft (airframe model) - [Beech 65-A90-1 (U-21A)](https://openairdocs.org/model/beech-65-a90-1-u-21a): 1 aircraft (airframe model) - [Raytheon E90](https://openairdocs.org/model/raytheon-e90): 1 aircraft (airframe model) All 15 models: https://openairdocs.org/ad/89-25-10/models.md Every aircraft: https://openairdocs.org/ad/89-25-10/aircraft.md ## Related documents - [STC SA1178CE](https://openairdocs.org/stc/SA1178CE): Install wing front spar reinforcement kit.. Dynamic Aviation Group Inc., Cited in the text - [STC SA1583CE](https://openairdocs.org/stc/SA1583CE): Install wing front spar reinforcement kit.. Dynamic Aviation Group Inc., Cited in the text ## NTSB investigations that cite this AD (1) From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date, checked against the reported serial number, make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. - [NTSB WPR21FA266](https://openairdocs.org/ntsb/WPR21FA266), Jul 10, 2021: Beech C90 (N3688P), Wikieup, AZ, destroyed, 2 fatal. Probable cause: The failure and separation of the left wing’s outboard section due to a fatigue crack in the lower spar cap. Contributing to the accident was the operator’s decision to repair the wing spar instead… --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.