- Effective
- November 20, 1964
- Published
- October 21, 1964
- Models
- 65, D50E, J50
- Registered aircraft
- 52 matched by model
- Product
- Aircraft · Small airplane
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. The FAA’s own copy is the authoritative one. DRS record last changed January 21, 2026.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
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On this page
The airworthiness directive
64-24-02 BEECH: Amdt. 823 Part 507 Federal Register October 21, 1964. Applies to Model D50E Aircraft, Serial Numbers DH-301 through DH-347, Model J50 Aircraft Serial Numbers JH-150 through JH-173, and Model 65 Aircraft, Serial Numbers LC-1 through LC-152.
Compliance required within the next 100 hours' time in service from the effective date of this AD, unless already accomplished in accordance with Beech Service Bulletins D-50E No. 37, J50 No. 9, and 65 No. 19.
It has been determined that some wing attaching bolts may have been overtorqued because of the use of lubricant during installation. The bolts must be dry and free of any dirt, lubricant, or other contaminant during installation to insure proper torquing. Accordingly, accomplish the following:
(a) Remove the wing attach bolts one at a time and check for any trace of lubricant. If the bolts have been lubricated, discard the bolt and nut.
(b) Remove any trace of lubricant by thoroughly washing all attaching parts (either new or original) and the spar fitting bearing surfaces in methyl ethyl keytone or lacquer thinner. Rinse in another bath of the clean solvent and blow dry prior to installation.
(c) Reinstall bolts and nuts found to be free of lubricant and install new bolts and nuts where the parts have been discarded in accordance with paragraph (a). Torque each bolt in accordance with paragraph (d) before advancing to the next bolt to avoid disturbing the wing adjustment. (Note: It is not necessary to replace the soft aluminum washers between the spar fittings.)
(d) Wing attach bolts, nuts, and the required torque valves are as follows:
Lower forward: NAS 495-14-29 bolt and EB 144 nut. Torque to 5000-5500 inch-pounds. Upper forward: NAS 150-38 bolt and 12B-108 nut. Torque to 2000-2300 inch- pounds. Upper and lower rear: NAS 150-33 bolts and 12B-108 nuts. Torque to 2000- 2300 inch-pounds.
(Beech Service Bulletins D50E No. 37, J50 No. 9, and 65 No. 19, as revised March 1964, cover this same subject.)
This directive effective November 20, 1964.
Affected TCDS · 2
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 52
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1924 | 1 |
|---|---|
| 1960 | 7 |
| 1961 | 7 |
| 1962 | 18 |
| 1963 | 2 |
| 1965 | 1 |
| 1966 | 1 |
| 1979 | 1 |
14 with no year recorded