AD 80-18-04 R1
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bell Helicopter Textron Canada Limited | 206A | Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206A-1 (OH-58A) | Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206B | Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206B-1 | Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206L | Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206L-1 | Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 Helicopters |
Unsafe Condition
Failure of the main rotor trunnion due to fatigue cracks in parts numbered 206-010-104-3, 206-011-113-001, or 206-011-120-001.
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Required Actions
Accomplish magnetic particle inspections per Bell Helicopter Textron Alert Service Bulletins 206-80-7/206L-80-9 or FAA-approved equivalent. Inspections must be done within specified intervals based on trunnion time in service: trunnions with <1,100 hours must inspect before 1,200 and 2,400 hours, then every 600 hours. Trunnions with 1,100-1,700 hours or unknown time must inspect within next 100 hours, then every 600 hours. Replace trunnion if cracks found before further flight. Report cracks to FAA as specified.
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Compliance Time
Compliance required as indicated in the AD, with specific inspection timelines based on trunnion time in service as of the effective date (November 24, 1980).
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Affected Aircraft
Bell Helicopter Textron Canada Limited Models 206A, 206B, 206A-1, 206B-1, 206L, 206L-1 helicopters equipped with main rotor trunnions P/N 206-010-104-3, 206-011-113-001, or 206-011-120-001.
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Federal Register Abstract
Main Rotor Trunnion
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_80-18-04_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 80-18-04 R1 Document Type: AD Final Rules Docket Number: 80-ASW-28 Subject Heading: Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 Helicopters Subject: Main Rotor Trunnion Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/24/1980 Make: Bell Helicopter Textron Canada Limited Model: 206A | 206A-1 (OH-58A) | 206B | 206B-1 | 206L | 206L-1 Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 80-18-04 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 80-ASW-28 AMENDMENT: 39-3954 AD NUMBER: 80-18-04 R1 SUBJECT HEADING: Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 Helicopters ACTION: SUMMARY: DATES: Effective November 24, 1980. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 80-18-04 R1 BELL: Amendment 39-3884 as amended by Amendment 39-3954. Applies to Models 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 helicopters equipped with main rotor trunnions, P/N 206-010-104-3, 206-011-113-001, or 206-011-120-001 certificated in all categories (Airworthiness Docket No. 80-ASW-28). Compliance required as indicated. To prevent possible failure of the main rotor trunnion, P/N 206-010-104-3, 206-011-113- 001, and 206-011-120-001 due to fatigue cracks, accomplish the following, unless already accomplished, in accordance with Bell Helicopter Textron Alert Service Bulletin 206-80-7, Revision A, dated February 26, 1980 (206A, 206B, 206A-1, 206B-1) or 206L-80-9, Revision A, dated February 26, 1980 (206L, 206L-1) or FAA approved equivalent. a. For trunnions with less than 1,100 hours' total time in service, on the effective date of this AD, accomplish a magnetic particle inspection prior to attaining 1,200 hours and again prior to attaining 2,400 hours, and thereafter at intervals not to exceed 600 hours. b. For trunnions with more than 1,100 hours and less than 1,700 hours' total time in service, on the effective date of this AD, accomplish a magnetic particle inspection within the next 100 hours' time in service and again prior to attaining 2,400 hours, and thereafter at intervals not to exceed 600 hours. c. For trunnions with 1,700 hours or more total time in service, on the effective date of this AD, accomplish a magnetic particle inspection within the next 100 hours' time in service, and thereafter at intervals not to exceed 600 hours. d. For trunnions with time unknown, on the effective date of this AD, accomplish a magnetic particle inspection within the next 100 hours' time in service, and thereafter at intervals not to exceed 600 hours. e. If a crack is found, remove and replace the trunnion before further flight. f. If no cracks are found, reassemble and install the main rotor hub on the helicopter in accordance with the pertinent Model 206 Maintenance and Overhaul Manual and continue the repetitive inspections specified above. g. Report in writing any cracks found during the inspections required herein to Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southwest Region, P.O. Box 1689, Fort Worth, Texas 76101. Each report must include the location of the cracks and the trunnion total time in service. Reporting approved by the Office of Management and Budget under OMB No. 04-R0174. h. If trunnion P/N 206-011-113-103 (206A, 206B, 206A-1, 206B-1) or P/N 206- 011-120-103 (206L, 206L-1) is installed, the inspections specified in this AD are not required. i. The helicopter may be flown in accordance with FAR 21.197 to a base where inspections can be performed. j. Upon submission of substantiating data through an FAA Aviation Safety Inspector, the Chief, Engineering and Manufacturing Branch, Southwest Region, may adjust the inspection intervals. Amendment 39-3884 became effective September 15, 1980. This amendment 39-3954 becomes effective November 24, 1980. FOOTER:
Document Text
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AD Final Rules - DRS_80-18-04_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 80-18-04 R1 Document Type: AD Final Rules Docket Number: 80-ASW-28 Subject Heading: Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 Helicopters Subject: Main Rotor Trunnion Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/24/1980 Make: Bell Helicopter Textron Canada Limited Model: 206A | 206A-1 (OH-58A) | 206B | 206B-1 | 206L | 206L-1 Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 80-18-04 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 80-ASW-28 AMENDMENT: 39-3954 AD NUMBER: 80-18-04 R1 SUBJECT HEADING: Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 Helicopters ACTION: SUMMARY: DATES: Effective November 24, 1980. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 80-18-04 R1 BELL: Amendment 39-3884 as amended by Amendment 39-3954. Applies to Models 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 helicopters equipped with main rotor trunnions, P/N 206-010-104-3, 206-011-113-001, or 206-011-120-001 certificated in all categories (Airworthiness Docket No. 80-ASW-28). Compliance required as indicated. To prevent possible failure of the main rotor trunnion, P/N 206-010-104-3, 206-011-113- 001, and 206-011-120-001 due to fatigue cracks, accomplish the following, unless already accomplished, in accordance with Bell Helicopter Textron Alert Service Bulletin 206-80-7, Revision A, dated February 26, 1980 (206A, 206B, 206A-1, 206B-1) or 206L-80-9, Revision A, dated February 26, 1980 (206L, 206L-1) or FAA approved equivalent. a. For trunnions with less than 1,100 hours' total time in service, on the effective date of this AD, accomplish a magnetic particle inspection prior to attaining 1,200 hours and again prior to attaining 2,400 hours, and thereafter at intervals not to exceed 600 hours. b. For trunnions with more than 1,100 hours and less than 1,700 hours' total time in service, on the effective date of this AD, accomplish a magnetic particle inspection within the next 100 hours' time in service and again prior to attaining 2,400 hours, and thereafter at intervals not to exceed 600 hours. c. For trunnions with 1,700 hours or more total time in service, on the effective date of this AD, accomplish a magnetic particle inspection within the next 100 hours' time in service, and thereafter at intervals not to exceed 600 hours. d. For trunnions with time unknown, on the effective date of this AD, accomplish a magnetic particle inspection within the next 100 hours' time in service, and thereafter at intervals not to exceed 600 hours. e. If a crack is found, remove and replace the trunnion before further flight. f. If no cracks are found, reassemble and install the main rotor hub on the helicopter in accordance with the pertinent Model 206 Maintenance and Overhaul Manual and continue the repetitive inspections specified above. g. Report in writing any cracks found during the inspections required herein to Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southwest Region, P.O. Box 1689, Fort Worth, Texas 76101. Each report must include the location of the cracks and the trunnion total time in service. Reporting approved by the Office of Management and Budget under OMB No. 04-R0174. h. If trunnion P/N 206-011-113-103 (206A, 206B, 206A-1, 206B-1) or P/N 206- 011-120-103 (206L, 206L-1) is installed, the inspections specified in this AD are not required. i. The helicopter may be flown in accordance with FAR 21.197 to a base where inspections can be performed. j. Upon submission of substantiating data through an FAA Aviation Safety Inspector, the Chief, Engineering and Manufacturing Branch, Southwest Region, may adjust the inspection intervals. Amendment 39-3884 became effective September 15, 1980. This amendment 39-3954 becomes effective November 24, 1980. FOOTER:
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Retrieved: Apr 8, 2026
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