AD 64-24-02
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Textron Aviation Inc. | 65 | Airworthiness Directives; Beech Model D50E, J50, and 65 Airplanes |
| aircraft | Textron Aviation Inc. | D50E | Airworthiness Directives; Beech Model D50E, J50, and 65 Airplanes |
| aircraft | Textron Aviation Inc. | J50 | Airworthiness Directives; Beech Model D50E, J50, and 65 Airplanes |
Unsafe Condition
Some wing attaching bolts may have been overtorqued due to the use of lubricant during installation, compromising proper torquing and structural integrity.
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Required Actions
Remove wing attach bolts one at a time and check for lubricant traces. Discard contaminated bolts and nuts. Clean all attaching parts with methyl ethyl ketone or lacquer thinner, rinse, and dry. Reinstall clean or new bolts and nuts, torquing each bolt per specified values (e.g., 5000-5500 inch-pounds for lower forward bolts) before proceeding to the next bolt.
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Compliance Time
within the next 100 hours' time in service from the effective date of this AD
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Affected Aircraft
Beech Model D50E (Serial Numbers DH-301 through DH-347), J50 (Serial Numbers JH-150 through JH-173), and 65 (Serial Numbers LC-1 through LC-152)
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Wing Attach Bolts
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_64-24-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-24-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Beech Model D50E, J50, and 65 Airplanes Subject: Wing Attach Bolts Status: Current Citation: Federal Register: October 21, 1964 Citation Publish Date: 10/21/1964 Effective Date: 11/20/1964 Make: Textron Aviation Inc. Model: 65 | D50E | J50 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 64-24-02 CITATION: [Federal Register: October 21, 1964] PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 64-24-02 SUBJECT HEADING: Airworthiness Directives; Beech Model D50E, J50, and 65 Airplanes ACTION: SUMMARY: DATES: Effective November 20, 1964. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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. FOOTER:
Document Text
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AD Final Rules - DRS_64-24-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-24-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Beech Model D50E, J50, and 65 Airplanes Subject: Wing Attach Bolts Status: Current Citation: Federal Register: October 21, 1964 Citation Publish Date: 10/21/1964 Effective Date: 11/20/1964 Make: Textron Aviation Inc. Model: 65 | D50E | J50 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 64-24-02 CITATION: [Federal Register: October 21, 1964] PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 64-24-02 SUBJECT HEADING: Airworthiness Directives; Beech Model D50E, J50, and 65 Airplanes ACTION: SUMMARY: DATES: Effective November 20, 1964. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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. FOOTER:
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Retrieved: Apr 8, 2026
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