AD 70-14-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Scotts-Bell 47 Inc | 47D | Airworthiness Directives; Bell Model 47D, 47D-1, 47G, 47G-2 and 47H-1 Helicopters |
| aircraft | Scotts-Bell 47 Inc | 47D1 | Airworthiness Directives; Bell Model 47D, 47D-1, 47G, 47G-2 and 47H-1 Helicopters |
| aircraft | Scotts-Bell 47 Inc | 47G | Airworthiness Directives; Bell Model 47D, 47D-1, 47G, 47G-2 and 47H-1 Helicopters |
| aircraft | Scotts-Bell 47 Inc | 47G-2 | Airworthiness Directives; Bell Model 47D, 47D-1, 47G, 47G-2 and 47H-1 Helicopters |
| aircraft | Scotts-Bell 47 Inc | 47H-1 | Airworthiness Directives; Bell Model 47D, 47D-1, 47G, 47G-2 and 47H-1 Helicopters |
Unsafe Condition
Failure of the tail rotor hub assembly bolt due to a fatigue crack and improper installation of the hub bolt.
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Required Actions
Replace bolts with 550 hours or more total time in service within the next 50 hours time in service. Inspect bolts with less than 550 hours total time using magnetic particle or equivalent inspection, replace cracked bolts before further flight. Replace all bolts at or prior to 600 hours total time in service. Install bolts per specified maintenance manual or equivalent FAA approved procedures.
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Compliance Time
Within the next 50 hours time in service
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Affected Aircraft
Bell Model 47D, 47D-1, 47G, 47G-2, and 47H-1 helicopters equipped with tail rotor hub assembly bolt P/N 47-641-052-3.
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Federal Register Abstract
Tail Rotor Hub Assembly Bolt
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_70-14-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 70-14-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Bell Model 47D, 47D-1, 47G, 47G-2 and 47H-1 Helicopters Subject: Tail Rotor Hub Assembly Bolt Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/10/1970 Make: Scotts-Bell 47 Inc Model: 47D | 47D1 | 47G | 47G-2 | 47H-1 Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 70-14-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1023 AD NUMBER: 70-14-02 SUBJECT HEADING: Airworthiness Directives; Bell Model 47D, 47D-1, 47G, 47G-2 and 47H-1 Helicopters ACTION: SUMMARY: DATES: Effective August 10, 1970. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 70-14-02 BELL: Amendment 39-1023. Applies to all Bell Model 47D, 47D-1, 47G, 47G-2 and 47H-1 helicopters certificated in all categories, and to any other helicopters equipped with tail rotor hub assembly bolt (also called a blade grip retaining bolt or a bearing retaining bolt), P/N 47-641-052-3. Compliance required as indicated. To detect and prevent possible failure of the tail rotor hub assembly bolt due to a fatigue crack and to correct any improper installation of the hub bolt, accomplish the following: (a) Within the next 50 hours time in service, remove and replace bolts with 550 hours or more total time in service on the effective date of this AD. (b) Within the next 50 hours time in service, inspect, one time, bolts with less than 550 hours total time in service on the effective date of this AD as follows: (1) Remove and disassemble the tail rotor assembly and remove the hub assembly bolts. (2) Inspect the bolt head to shank radius for cracks using a magnetic particle or equivalent inspection method. (3) Replace cracked bolts before further flight as specified in paragraph (e). (c) Remove and replace bolts with less than 550 hours total time in service on the effective date of this AD at or prior to accumulating 600 hours total time in service. (d) Remove and replace all replacement bolts at or prior to accumulating 600 hours total time in service. (e) Install bolts in accordance with paragraph 6-16.e., Section VI, Model 47D-1, 47G and 47G-2 Maintenance and Overhaul Instruction Manual, as revised August 15, 1961, or in accordance with equivalent FAA approved procedures. This amendment becomes effective August 10, 1970. FOOTER:
Document Text
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AD Final Rules - DRS_70-14-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 70-14-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Bell Model 47D, 47D-1, 47G, 47G-2 and 47H-1 Helicopters Subject: Tail Rotor Hub Assembly Bolt Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/10/1970 Make: Scotts-Bell 47 Inc Model: 47D | 47D1 | 47G | 47G-2 | 47H-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: 70-14-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1023 AD NUMBER: 70-14-02 SUBJECT HEADING: Airworthiness Directives; Bell Model 47D, 47D-1, 47G, 47G-2 and 47H-1 Helicopters ACTION: SUMMARY: DATES: Effective August 10, 1970. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 70-14-02 BELL: Amendment 39-1023. Applies to all Bell Model 47D, 47D-1, 47G, 47G-2 and 47H-1 helicopters certificated in all categories, and to any other helicopters equipped with tail rotor hub assembly bolt (also called a blade grip retaining bolt or a bearing retaining bolt), P/N 47-641-052-3. Compliance required as indicated. To detect and prevent possible failure of the tail rotor hub assembly bolt due to a fatigue crack and to correct any improper installation of the hub bolt, accomplish the following: (a) Within the next 50 hours time in service, remove and replace bolts with 550 hours or more total time in service on the effective date of this AD. (b) Within the next 50 hours time in service, inspect, one time, bolts with less than 550 hours total time in service on the effective date of this AD as follows: (1) Remove and disassemble the tail rotor assembly and remove the hub assembly bolts. (2) Inspect the bolt head to shank radius for cracks using a magnetic particle or equivalent inspection method. (3) Replace cracked bolts before further flight as specified in paragraph (e). (c) Remove and replace bolts with less than 550 hours total time in service on the effective date of this AD at or prior to accumulating 600 hours total time in service. (d) Remove and replace all replacement bolts at or prior to accumulating 600 hours total time in service. (e) Install bolts in accordance with paragraph 6-16.e., Section VI, Model 47D-1, 47G and 47G-2 Maintenance and Overhaul Instruction Manual, as revised August 15, 1961, or in accordance with equivalent FAA approved procedures. This amendment becomes effective August 10, 1970. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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