AD 81-14-10
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | AT-6D (SNJ-5) | Airworthiness Directives; North American Model AT-6D, AT-6F and T-6G Series Airplanes |
| aircraft | The Boeing Company | AT-6F (SNJ-6) | Airworthiness Directives; North American Model AT-6D, AT-6F and T-6G Series Airplanes |
| aircraft | The Boeing Company | SNJ-7 | Airworthiness Directives; North American Model AT-6D, AT-6F and T-6G Series Airplanes |
| aircraft | The Boeing Company | T-6G | Airworthiness Directives; North American Model AT-6D, AT-6F and T-6G Series Airplanes |
Unsafe Condition
Cracks in the single piece design horizontal stabilizer rear spar connector fittings (P/N 77-21021) could result in structural failure of the horizontal stabilizer.
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Required Actions
Within 20 flight hours after the effective date and every 20 flight hours thereafter until the next annual inspection, remove fairings and visually check the fittings for cracks. Replace cracked fittings before further flight. At the next annual inspection, remove fittings, perform dye penetrant inspection, replace cracked fittings, inspect fit with a feeler gauge, install shims if gaps exceed 0.010 inches, and reinstall parts.
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Compliance Time
within 20 flight hours after the effective date of this AD and every 20 flight hours thereafter until b) is accomplished
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Affected Aircraft
North American Model AT-6D (SNJ-5), AT-6F (SNJ-6), SNJ-7, and T-6G aircraft equipped with single piece design horizontal stabilizer rear spar connector fittings (P/N 77-21021, 4 fittings per spar)
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Vertical and Horizontal Stabilizers
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_81-14-10.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-14-10 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; North American Model AT-6D, AT-6F and T-6G Series Airplanes Subject: Vertical and Horizontal Stabilizers Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/13/1981 Make: The Boeing Company Model: AT-6D (SNJ-5) | AT-6F (SNJ-6) | SNJ-7 | T-6G 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 81-14-10 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4159 AD NUMBER: 81-14-10 SUBJECT HEADING: Airworthiness Directives; North American Model AT-6D, AT-6F and T-6G Series Airplanes ACTION: SUMMARY: DATES: Effective July 13, 1981. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 81-14-10 NORTH AMERICAN: Amendment 39-4159. Applies to all AT-6D 81-14-10 (SNJ-5), AT-6F (SNJ-6), SNJ-7, and T-6G aircraft equipped with single piece design horizontal stabilizer rear spar connector fittings (P/N 77-21021, 4 fittings per spar). This AD does not apply to those aircraft equipped with two piece design connector fittings (P/Ns 77-21021-3 and 77-21021-4, 8 fittings per spar). Accomplish the following: a) Within 20 flight hours after the effective date of this AD and every 20 flight hours thereafter until b) is accomplished: 1. Remove the fuselage to vertical stabilizer fairing assembly and the rear fairing assemblies at the horizontal stabilizer. 2. Visually check the spar connector fittings for cracks. If cracks are found, fitting must be replaced with an airworthy part before further flight. b) At next annual inspection: 1. Remove the fuselage to vertical stabilizer fairing assembly and the rear fairing assemblies at the horizontal stabilizer. 2. Remove the 1/4-inch bolts which attach the upper and lower spar connection fittings (P/N 77-21021) of the rear spar assembly. 3. Remove the 4 connection fittings from the spar, remove paint from the connection fittings, and check for cracks using standard dye penetrant inspection methods. Replace any cracked fittings with serviceable ones and repaint all others. (See note.) 4. Inspect for fit between the connection fittings and the spar with a feeler gage prior to installation of the bolts. If gaps greater than 0.010 inches exist, shims are necessary. 5. Fabricate aluminum shims 3-1/8 inches x 15/16 inch and of necessary thickness, and place on either side of spar flanges, maintaining a parallel overall dimension to fit inside the connection fitting with a maximum clearance of 0.010 inches. 6. Drill holes through the shims to match those in the fitting. Remove all chips and reinstall the various parts, including fairings. NOTE: One source of replacement fittings is Banaire Enterprises, 962 E. Lincoln St., Banning, California 92220 (Tel. (714) 849-8323). This amendment becomes effective July 13, 1981. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_81-14-10.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-14-10 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; North American Model AT-6D, AT-6F and T-6G Series Airplanes Subject: Vertical and Horizontal Stabilizers Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/13/1981 Make: The Boeing Company Model: AT-6D (SNJ-5) | AT-6F (SNJ-6) | SNJ-7 | T-6G 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 81-14-10 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4159 AD NUMBER: 81-14-10 SUBJECT HEADING: Airworthiness Directives; North American Model AT-6D, AT-6F and T-6G Series Airplanes ACTION: SUMMARY: DATES: Effective July 13, 1981. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 81-14-10 NORTH AMERICAN: Amendment 39-4159. Applies to all AT-6D 81-14-10 (SNJ-5), AT-6F (SNJ-6), SNJ-7, and T-6G aircraft equipped with single piece design horizontal stabilizer rear spar connector fittings (P/N 77-21021, 4 fittings per spar). This AD does not apply to those aircraft equipped with two piece design connector fittings (P/Ns 77-21021-3 and 77-21021-4, 8 fittings per spar). Accomplish the following: a) Within 20 flight hours after the effective date of this AD and every 20 flight hours thereafter until b) is accomplished: 1. Remove the fuselage to vertical stabilizer fairing assembly and the rear fairing assemblies at the horizontal stabilizer. 2. Visually check the spar connector fittings for cracks. If cracks are found, fitting must be replaced with an airworthy part before further flight. b) At next annual inspection: 1. Remove the fuselage to vertical stabilizer fairing assembly and the rear fairing assemblies at the horizontal stabilizer. 2. Remove the 1/4-inch bolts which attach the upper and lower spar connection fittings (P/N 77-21021) of the rear spar assembly. 3. Remove the 4 connection fittings from the spar, remove paint from the connection fittings, and check for cracks using standard dye penetrant inspection methods. Replace any cracked fittings with serviceable ones and repaint all others. (See note.) 4. Inspect for fit between the connection fittings and the spar with a feeler gage prior to installation of the bolts. If gaps greater than 0.010 inches exist, shims are necessary. 5. Fabricate aluminum shims 3-1/8 inches x 15/16 inch and of necessary thickness, and place on either side of spar flanges, maintaining a parallel overall dimension to fit inside the connection fitting with a maximum clearance of 0.010 inches. 6. Drill holes through the shims to match those in the fitting. Remove all chips and reinstall the various parts, including fairings. NOTE: One source of replacement fittings is Banaire Enterprises, 962 E. Lincoln St., Banning, California 92220 (Tel. (714) 849-8323). This amendment becomes effective July 13, 1981. FOOTER:
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