AD 80-17-05
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bell Helicopter Textron Canada Limited | 206A | Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, and 206L Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206A-1 (OH-58A) | Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, and 206L Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206B | Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, and 206L Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206B-1 | Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, and 206L Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206L | Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, and 206L Helicopters |
Unsafe Condition
Failure of tail rotor blades, P/N 206-010-750-005 and -007, due to fatigue cracks in the blade skin surfaces between Blade Station 7.1 and 11.1.
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Required Actions
Visually check for chordwise cracks in the tail rotor blade skin surfaces between Blade Station 7.1 and 11.1 using a three-power or higher magnifying glass before the first flight of each day after the effective date. Replace blades with cracks before further flight. Blades with 450+ hours' time in service on the effective date must be removed within next 50 hours. Blades under 450 hours must be removed before attaining 500 hours' time in service.
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Compliance Time
Before the first flight of each day after the effective date of this AD
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Affected Aircraft
Bell Helicopter Textron Canada Limited Models 206A, 206B, 206A-1, 206B-1, and 206L helicopters equipped with tail rotor blades P/N 206-010-750-005 and -007.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Tail Rotor Blades
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_80-17-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 80-17-05 Document Type: AD Final Rules Docket Number: 80-ASW-18 Subject Heading: Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, and 206L Helicopters Subject: Tail Rotor Blades Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/10/1980 Make: Bell Helicopter Textron Canada Limited Model: 206A | 206A-1 (OH-58A) | 206B | 206B-1 | 206L 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: 80-17-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 80-ASW-18 AMENDMENT: 39-3875 AD NUMBER: 80-17-05 SUBJECT HEADING: Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, and 206L Helicopters ACTION: SUMMARY: DATES: Effective September 10, 1980. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 80-17-05 BELL: Amendment 39-3875. Applies to Models 206A, 206B, 206A-1, 206B-1, and 206L helicopters equipped with tail rotor blades, P/N 206-010-750-005 and -007, certificated in all categories (Airworthiness Docket No. 80-ASW-18). Compliance required as indicated. To prevent possible failure of tail rotor blades, P/N 206-010-750-005 and -007, due to fatigue cracks, accomplish the following: a. Before the first flight of each day after the effective date of this AD, visually check for chordwise cracks in the tail rotor blade skin surfaces in the area between Blade Station 7.1 and 11.1 using a three-power or higher magnifying glass. (Blade Station 0 is the center of the tail rotor yoke.) b. Replace tail rotor blades having cracks before further flight. c. Blades with 450 or more hours' time in service (as calculated in paragraph (e) below) on the effective date of this AD must be removed from service within the next 50 hours' time in service. d. Blades with less than 450 hours' time in service (as calculated in paragraph (e) below) on the effective date of this AD must be removed from service prior to or on attaining 500 hours' time in service. e. For purposes of this AD, hours' time in service is calculated by the following formula: Time on 206A/B Series + Time on 206L = Calculated Time in Service 2.4 f. The check required by paragraph (a) of this AD may be performed by the pilot, providing the pilot's logbook has been endorsed by a properly rated mechanic stating that the pilot has been trained to conduct the daily check in accordance with this AD. NOTE: For the requirements regarding the listing of compliance with this AD in the aircraft maintenance record, see FAR 91.173. (Bell Helicopter Textron Operations Safety Notice No. 206-79-5/206L-79-2, dated December 4, 1979; Alert Service Bulletin Nos. 206-80-6 dated February 22, 1980, and 206L-80- 8, Rev. A, dated June 3, 1980; and Technical Bulletin Nos. 206-78-3 dated July 18, 1978, and 206L-79-38 dated September 28, 1979, pertain to this subject.) This amendment becomes effective September 10, 1980. FOOTER:
Document Text
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AD Final Rules - DRS_80-17-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 80-17-05 Document Type: AD Final Rules Docket Number: 80-ASW-18 Subject Heading: Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, and 206L Helicopters Subject: Tail Rotor Blades Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/10/1980 Make: Bell Helicopter Textron Canada Limited Model: 206A | 206A-1 (OH-58A) | 206B | 206B-1 | 206L 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: 80-17-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 80-ASW-18 AMENDMENT: 39-3875 AD NUMBER: 80-17-05 SUBJECT HEADING: Airworthiness Directives; BELL Models 206A, 206B, 206A-1, 206B-1, and 206L Helicopters ACTION: SUMMARY: DATES: Effective September 10, 1980. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 80-17-05 BELL: Amendment 39-3875. Applies to Models 206A, 206B, 206A-1, 206B-1, and 206L helicopters equipped with tail rotor blades, P/N 206-010-750-005 and -007, certificated in all categories (Airworthiness Docket No. 80-ASW-18). Compliance required as indicated. To prevent possible failure of tail rotor blades, P/N 206-010-750-005 and -007, due to fatigue cracks, accomplish the following: a. Before the first flight of each day after the effective date of this AD, visually check for chordwise cracks in the tail rotor blade skin surfaces in the area between Blade Station 7.1 and 11.1 using a three-power or higher magnifying glass. (Blade Station 0 is the center of the tail rotor yoke.) b. Replace tail rotor blades having cracks before further flight. c. Blades with 450 or more hours' time in service (as calculated in paragraph (e) below) on the effective date of this AD must be removed from service within the next 50 hours' time in service. d. Blades with less than 450 hours' time in service (as calculated in paragraph (e) below) on the effective date of this AD must be removed from service prior to or on attaining 500 hours' time in service. e. For purposes of this AD, hours' time in service is calculated by the following formula: Time on 206A/B Series + Time on 206L = Calculated Time in Service 2.4 f. The check required by paragraph (a) of this AD may be performed by the pilot, providing the pilot's logbook has been endorsed by a properly rated mechanic stating that the pilot has been trained to conduct the daily check in accordance with this AD. NOTE: For the requirements regarding the listing of compliance with this AD in the aircraft maintenance record, see FAR 91.173. (Bell Helicopter Textron Operations Safety Notice No. 206-79-5/206L-79-2, dated December 4, 1979; Alert Service Bulletin Nos. 206-80-6 dated February 22, 1980, and 206L-80- 8, Rev. A, dated June 3, 1980; and Technical Bulletin Nos. 206-78-3 dated July 18, 1978, and 206L-79-38 dated September 28, 1979, pertain to this subject.) This amendment becomes effective September 10, 1980. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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