AD 80-04-06
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Thrush Aircraft, Inc. | 600 S-2D | Airworthiness Directives; Ayres Model S-2D, S-2R, S2R-T11, S2R-T15, S2R-T34 and S2R-R3S Airplanes |
| aircraft | Thrush Aircraft, Inc. | S-2R | Airworthiness Directives; Ayres Model S-2D, S-2R, S2R-T11, S2R-T15, S2R-T34 and S2R-R3S Airplanes |
| aircraft | Thrush Aircraft, Inc. | S2R-R3S | Airworthiness Directives; Ayres Model S-2D, S-2R, S2R-T11, S2R-T15, S2R-T34 and S2R-R3S Airplanes |
| aircraft | Thrush Aircraft, Inc. | S2R-T11 | Airworthiness Directives; Ayres Model S-2D, S-2R, S2R-T11, S2R-T15, S2R-T34 and S2R-R3S Airplanes |
| aircraft | Thrush Aircraft, Inc. | S2R-T15 | Airworthiness Directives; Ayres Model S-2D, S-2R, S2R-T11, S2R-T15, S2R-T34 and S2R-R3S Airplanes |
| aircraft | Thrush Aircraft, Inc. | S2R-T34 | Airworthiness Directives; Ayres Model S-2D, S-2R, S2R-T11, S2R-T15, S2R-T34 and S2R-R3S Airplanes |
Unsafe Condition
Cracks in the tubular front spar of the horizontal stabilizer in the area of the left and right fuselage attach bushings could lead to structural failure.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the horizontal stabilizer front spar tube (P/N 40221-19) within 25 hours time in service after the effective date and every 500 hours thereafter. If cracked, replace with P/N 40221-70 or a serviceable P/N 40221-61 and continue inspections every 500 hours. Adjust flying wires per Maintenance Manual.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within 25 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 500 hours time in service from the last inspection
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Ayres Models S-2D (all serial numbers), S-2R (S/N 1416R-2560R, 5000R-5100R), S2R-T11 (T11-001-002), S2R-T15 (T15-001-005), S2R-T34 (6000-6049, T34-001-019), S2R-R3S (R3S-001-008)
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Cracks in Tubular Front Spar
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_80-04-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 80-04-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Ayres Model S-2D, S-2R, S2R-T11, S2R-T15, S2R-T34 and S2R-R3S Airplanes Subject: Cracks in Tubular Front Spar Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 02/20/1980 Make: Thrush Aircraft, Inc. Model: 600 S-2D | S-2R | S2R-R3S | S2R-T11 | S2R-T15 | S2R-T34 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: 80-04-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3688 AD NUMBER: 80-04-06 SUBJECT HEADING: Airworthiness Directives; Ayres Model S-2D, S-2R, S2R-T11, S2R-T15, S2R-T34 and S2R-R3S Airplanes ACTION: SUMMARY: DATES: Effective February 20, 1980. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 80-04-06 AYRES CORPORATION (formerly Rockwell International and Snow Aeronautical Company): Amendment 39-3688. Applies to the following Ayres Models and serial numbers with 2000 or more hours time in service after the effective date of this AD, certificated in all categories: Model S-2D: All S/N's Model S-2R: S/N's 1416R through 2560R; S/N's 5000R through 5100R Model S2R-T11: S/N's T11-001 and T11-002 Model S2R-T15: S/N's T15-001 through T15-005 Model S2R-T34: S/N's 6000 through 6049; S/N's T34-001 through T34- 019 Model S2R-R3S: S/N's R3S-001 through R3S-008 Compliance required as indicated unless already accomplished. To prevent the possible structural failure of the horizontal stabilizer due to a crack or cracks in the tubular front spar, accomplish the following within 25 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 500 hours time in service from the last inspection. 1. Inspection Procedures a. Remove fuselage side skins to provide access to the inspection hole in the bottom of the horizontal stabilizer. b. Disconnect the flying wires, left and right sides, from both upper and lower surfaces of the horizontal stabilizer to permit the exercising of the stabilizer. c. Inspect the horizontal stabilizer front spar tube (P/N 40221-19) in the area of both the left and right fuselage attach bushings as shown in Figure 1 using a flashlight and an inspection mirror. IMPORTANT - the stabilizer must be exercised with both an up and down force at the tip during the inspection to ensure detection of a crack. d. If the spar is cracked, comply with Paragraph 2. If the spar is not cracked, comply with Paragraph 3. 2. Action Required If Spar Is Cracked If the spar is cracked in the area of the front spar-to-fuselage attach bushing, accomplish either Paragraph a. or b. listed below: a. Before further flight, replace the cracked horizontal stabilizer assembly P/N 40221-61 with a new horizontal stabilizer assembly P/N 40221-70. When P/N 40221-70 is installed, the repetitive inspections required by Paragraph 1 may be discontinued. b. Before further flight, replace the cracked horizontal stabilizer assembly P/N 40221-61 with a serviceable assembly of the same part number. Continue the Paragraph 1 inspection at intervals not to exceed 500 hours time in service from the last inspection. Reinstall the horizontal stabilizer assembly and adjust the flying wires in accordance with the Rigging Procedures in Section VII of the Maintenance Manual. Finally, adjust the tension in each flying wire until the midpoint has a deflection of 0.30 + 0.05 inch with an applied side load of 20 pounds. 3. Action Required If The Spar Is Not Cracked Reattach the flying wires to the horizontal stabilizer and adjust the flying wires in accordance with the Rigging Procedures in Section VII of the Maintenance Manual. Finally, adjust the tension in each wire until the midpoint has a deflection of 0.30 + 0.05 inch with an applied side load of 20 pounds. Continue the Paragraph 1 inspection at intervals not to exceed 500 hours time in service from the last inspection. When horizontal stabilizer assembly P/N 40221-70 is installed, the repetitive inspections may be discontinued. Compliance with the provisions of this AD may be accomplished in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. This amendment is effective February 20, 1980. FOOTER:
Document Text
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AD Final Rules - DRS_80-04-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 80-04-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Ayres Model S-2D, S-2R, S2R-T11, S2R-T15, S2R-T34 and S2R-R3S Airplanes Subject: Cracks in Tubular Front Spar Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 02/20/1980 Make: Thrush Aircraft, Inc. Model: 600 S-2D | S-2R | S2R-R3S | S2R-T11 | S2R-T15 | S2R-T34 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: 80-04-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3688 AD NUMBER: 80-04-06 SUBJECT HEADING: Airworthiness Directives; Ayres Model S-2D, S-2R, S2R-T11, S2R-T15, S2R-T34 and S2R-R3S Airplanes ACTION: SUMMARY: DATES: Effective February 20, 1980. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 80-04-06 AYRES CORPORATION (formerly Rockwell International and Snow Aeronautical Company): Amendment 39-3688. Applies to the following Ayres Models and serial numbers with 2000 or more hours time in service after the effective date of this AD, certificated in all categories: Model S-2D: All S/N's Model S-2R: S/N's 1416R through 2560R; S/N's 5000R through 5100R Model S2R-T11: S/N's T11-001 and T11-002 Model S2R-T15: S/N's T15-001 through T15-005 Model S2R-T34: S/N's 6000 through 6049; S/N's T34-001 through T34- 019 Model S2R-R3S: S/N's R3S-001 through R3S-008 Compliance required as indicated unless already accomplished. To prevent the possible structural failure of the horizontal stabilizer due to a crack or cracks in the tubular front spar, accomplish the following within 25 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 500 hours time in service from the last inspection. 1. Inspection Procedures a. Remove fuselage side skins to provide access to the inspection hole in the bottom of the horizontal stabilizer. b. Disconnect the flying wires, left and right sides, from both upper and lower surfaces of the horizontal stabilizer to permit the exercising of the stabilizer. c. Inspect the horizontal stabilizer front spar tube (P/N 40221-19) in the area of both the left and right fuselage attach bushings as shown in Figure 1 using a flashlight and an inspection mirror. IMPORTANT - the stabilizer must be exercised with both an up and down force at the tip during the inspection to ensure detection of a crack. d. If the spar is cracked, comply with Paragraph 2. If the spar is not cracked, comply with Paragraph 3. 2. Action Required If Spar Is Cracked If the spar is cracked in the area of the front spar-to-fuselage attach bushing, accomplish either Paragraph a. or b. listed below: a. Before further flight, replace the cracked horizontal stabilizer assembly P/N 40221-61 with a new horizontal stabilizer assembly P/N 40221-70. When P/N 40221-70 is installed, the repetitive inspections required by Paragraph 1 may be discontinued. b. Before further flight, replace the cracked horizontal stabilizer assembly P/N 40221-61 with a serviceable assembly of the same part number. Continue the Paragraph 1 inspection at intervals not to exceed 500 hours time in service from the last inspection. Reinstall the horizontal stabilizer assembly and adjust the flying wires in accordance with the Rigging Procedures in Section VII of the Maintenance Manual. Finally, adjust the tension in each flying wire until the midpoint has a deflection of 0.30 + 0.05 inch with an applied side load of 20 pounds. 3. Action Required If The Spar Is Not Cracked Reattach the flying wires to the horizontal stabilizer and adjust the flying wires in accordance with the Rigging Procedures in Section VII of the Maintenance Manual. Finally, adjust the tension in each wire until the midpoint has a deflection of 0.30 + 0.05 inch with an applied side load of 20 pounds. Continue the Paragraph 1 inspection at intervals not to exceed 500 hours time in service from the last inspection. When horizontal stabilizer assembly P/N 40221-70 is installed, the repetitive inspections may be discontinued. Compliance with the provisions of this AD may be accomplished in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. This amendment is effective February 20, 1980. FOOTER:
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Retrieved: Apr 8, 2026
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