AD 75-06-03
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bell Helicopter Textron Canada Limited | 206A | Airworthiness Directives; Bell Model 206A, 206B, 206A-1, and 206B-1 Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206A-1 (OH-58A) | Airworthiness Directives; Bell Model 206A, 206B, 206A-1, and 206B-1 Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206B | Airworthiness Directives; Bell Model 206A, 206B, 206A-1, and 206B-1 Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206B-1 | Airworthiness Directives; Bell Model 206A, 206B, 206A-1, and 206B-1 Helicopters |
Unsafe Condition
Fatigue cracks in the main rotor pitch link assembly upper and lower clevis threaded shank could result in loss of main rotor control.
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Required Actions
Inspect each main rotor blade pitch link assembly upper and lower clevis threaded shank for fatigue cracks using fluorescent penetrant or equivalent method. Replace any clevis with a cracked shank before further flight. Ensure swashplate outer ring horn bearings (P/N 206-010-469-1) have a breakaway force not exceeding 10 pounds; replace those exceeding the limit prior to further flight.
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Compliance Time
within 10 hours' time in service after March 12, 1975, unless already accomplished
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Affected Aircraft
Bell Model 206A, 206B, 206A-1, and 206B-1 helicopters equipped with pitch link assemblies P/N 206-010-330 or 206-010-342
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Federal Register Abstract
Pitch Link Assembly
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_75-06-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 75-06-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Bell Model 206A, 206B, 206A-1, and 206B-1 Helicopters Subject: Pitch Link Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/20/1975 Make: Bell Helicopter Textron Canada Limited Model: 206A | 206A-1 (OH-58A) | 206B | 206B-1 Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 75-06-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2386 AD NUMBER: 75-06-03 SUBJECT HEADING: Airworthiness Directives; Bell Model 206A, 206B, 206A-1, and 206B-1 Helicopters ACTION: SUMMARY: DATES: Effective October 20, 1975. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 75-06-03 BELL: Amendment 39-2122 as amended by Amendment 39-2146 and 39-2350 is further amended by Amendment 39-2386. Applies to Bell Models 206A, 206B, 206A-1, and 206B-1 helicopters, certificated in all categories, equipped with pitch link assemblies, P/N 206- 010-330 or 206-010-342. Compliance required within 10 hours' time in service after March 12, 1975, unless already accomplished. To detect possible fatigue cracks in each main rotor pitch link assembly, upper and lower clevis, accomplish the following. a. Remove each main rotor blade pitch link assembly from the helicopter and measure the distance between the bolt holes. Remove the upper and lower clevis from each pitch link assembly in accordance with Bell Model 206A or 206B maintenance and overhaul instructions. b. Inspect the threaded shank of each clevis using fluorescent penetrant or an equivalent inspection method. c. Replace each clevis that has a cracked shank before further flight. d. Assemble the pitch link assemblies in accordance with the Model 206A or 206B maintenance and overhaul instructions and set the pitch link assembly to the appropriate length measured in paragraph (a) of this AD. e. Determine that each bearing, P/N 206-010-469-1, installed in the swashplate outer ring horns has a breakaway force that does not exceed 10 pounds when measured as specified in the Mailgram dated February 15, 1975, from Bell Helicopter Company to all 206A, 206B, and TH57A operators or as specified in an FAA approved equivalent procedure. f. Replace each swashplate outer ring horn bearing, P/N 206-010-469-1, that exceeds 10 pounds breakaway force measured in paragraph (e) of this AD, prior to further flight, in accordance with procedures specified in Section XIV of the Bell Model 206A or 206B maintenance and overhaul instructions dated November 1, 1972, or later revision, or as specified in an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. g. Install the pitch link assemblies in accordance with the Bell Model 206A or 206B maintenance and overhaul instructions. h. This AD does not apply to the main rotor pitch link assemblies, P/N 206-010- 355. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Company, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S. W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. Amendment 39-2122 became effective March 12, 1975. Amendment 39-2146 became effective March 19, 1975. Amendment 39-2350 became effective October 2, 1975. This amendment 39-2386 becomes effective October 20, 1975. FOOTER:
Document Text
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AD Final Rules - DRS_75-06-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 75-06-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Bell Model 206A, 206B, 206A-1, and 206B-1 Helicopters Subject: Pitch Link Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/20/1975 Make: Bell Helicopter Textron Canada Limited Model: 206A | 206A-1 (OH-58A) | 206B | 206B-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: 75-06-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2386 AD NUMBER: 75-06-03 SUBJECT HEADING: Airworthiness Directives; Bell Model 206A, 206B, 206A-1, and 206B-1 Helicopters ACTION: SUMMARY: DATES: Effective October 20, 1975. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 75-06-03 BELL: Amendment 39-2122 as amended by Amendment 39-2146 and 39-2350 is further amended by Amendment 39-2386. Applies to Bell Models 206A, 206B, 206A-1, and 206B-1 helicopters, certificated in all categories, equipped with pitch link assemblies, P/N 206- 010-330 or 206-010-342. Compliance required within 10 hours' time in service after March 12, 1975, unless already accomplished. To detect possible fatigue cracks in each main rotor pitch link assembly, upper and lower clevis, accomplish the following. a. Remove each main rotor blade pitch link assembly from the helicopter and measure the distance between the bolt holes. Remove the upper and lower clevis from each pitch link assembly in accordance with Bell Model 206A or 206B maintenance and overhaul instructions. b. Inspect the threaded shank of each clevis using fluorescent penetrant or an equivalent inspection method. c. Replace each clevis that has a cracked shank before further flight. d. Assemble the pitch link assemblies in accordance with the Model 206A or 206B maintenance and overhaul instructions and set the pitch link assembly to the appropriate length measured in paragraph (a) of this AD. e. Determine that each bearing, P/N 206-010-469-1, installed in the swashplate outer ring horns has a breakaway force that does not exceed 10 pounds when measured as specified in the Mailgram dated February 15, 1975, from Bell Helicopter Company to all 206A, 206B, and TH57A operators or as specified in an FAA approved equivalent procedure. f. Replace each swashplate outer ring horn bearing, P/N 206-010-469-1, that exceeds 10 pounds breakaway force measured in paragraph (e) of this AD, prior to further flight, in accordance with procedures specified in Section XIV of the Bell Model 206A or 206B maintenance and overhaul instructions dated November 1, 1972, or later revision, or as specified in an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. g. Install the pitch link assemblies in accordance with the Bell Model 206A or 206B maintenance and overhaul instructions. h. This AD does not apply to the main rotor pitch link assemblies, P/N 206-010- 355. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Company, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S. W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. Amendment 39-2122 became effective March 12, 1975. Amendment 39-2146 became effective March 19, 1975. Amendment 39-2350 became effective October 2, 1975. This amendment 39-2386 becomes effective October 20, 1975. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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