AD 82-26-07 R1
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bell Helicopter Textron, Inc. | 214ST | Airworthiness Directives; BELL HELICOPTER TEXTRON, INC. Model 214ST Helicopters |
Unsafe Condition
Separation of the tailboom from the fuselage due to failure of the upper left tailboom attach longeron, part number 214-031-431-101, caused by cracks extending from the pin hole in the longeron.
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Required Actions
Inspect the aft portion of the upper left longeron for cracks before first flight daily and within 5 hours time in service, then every 25 hours. Install a reinforcement modification within 25 hours or before 100 hours total time, including a new support (P/N 214-031-454-101) and doubler replacement. Replace cracked parts before flight and conduct subsequent inspections every 250 hours.
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Compliance Time
Within the next 5 hours time in service after the effective date (August 17, 1984) and thereafter at intervals not to exceed 25 hours time in service for inspections. The reinforcement modification must be installed within the next 25 hours time in service after the effective date or before the accumulation of 100 hours total time in service, whichever occurs later.
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Affected Aircraft
Bell Helicopter Textron, Inc. Model 214ST helicopters with upper left tailboom attach longeron part number 214-031-431-101 installed.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Tailboom Separation
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_82-26-07_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-26-07 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BELL HELICOPTER TEXTRON, INC. Model 214ST Helicopters Subject: Tailboom Separation Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/17/1984 Make: Bell Helicopter Textron, Inc. Model: 214ST Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 82-26-07 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4884 AD NUMBER: 82-26-07 R1 SUBJECT HEADING: Airworthiness Directives; BELL HELICOPTER TEXTRON, INC. Model 214ST Helicopters ACTION: SUMMARY: DATES: Effective August 17, 1984. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-26-07 R1 BELL HELICOPTER TEXTRON, INC.: Amendment 39-4512 as amended by Amendment 39-4884. Applies to Model 214ST helicopters certificated in all categories which have upper left tailboom attach longeron part number (P/N) 214-031-431-1 01 installed. Compliance is required as indicated unless already accomplished. To prevent possible separation of the tailboom from the fuselage due to failure of the upper left tailboom attach longeron, accomplish the following: (a) Before the first flight of each day on those helicopters that have not had the longeron modification described in paragraph (d) below, inspect the aft portion of the upper left longeron, P/N 214-031-431-101, that is visible inside the oil cooler compartment and the portion visible inside the aft left electrical compartment for cracks. (b) Within the next 5 hours time in service after the effective date of this AD, unless already accomplished within the last 20 hours time in service, and thereafter at intervals not to exceed 25 hours time in service, perform the following inspection on those helicopters that have not had the longeron modification installed: (1) Remove forward fairing assembly, P/N 214-061-866-113, and LH and RH fairing assemblies, P/N's 214-061-866-115 and -117. (2) Visually inspect the aft end of the upper left longeron, P/N 214-031-431- 101, immediately adjacent to and inboard of the pin, P/N 100-048-5-4, just aft of the fairing attach bracket, P/N 214-021-700-129. Inspect for a crack that may extend from the pin hole in the longeron across the longeron and forward. (c) If the longeron is found to be cracked during the inspections of paragraphs (a) and (b) of this AD, replace it with a serviceable part and install the modification described in paragraph (d) below before further flight. (d) Within the next 25 hours time in service after the effective date of this AD or before the accumulation of 100 hours total time in service, whichever occurs later, install a reinforcement modification to the longeron, P/N 214-031-431-101, installation. This reinforcement consists of the addition of a new support, P/N 214-031-454-101, and the replacement of a doubler, P/N 214-031-702-131, with a new doubler, P/N 214-031-643-101. Remove the attaching pin, P/N 100-048-5-4, that is installed in the most aft hole in the longeron outboard flange and plug the remaining hole with adhesive. Accomplish the reinforcement in accordance with Bell Helicopter Textron (BHT) Alert Service Bulletin No. 214ST-82-3, dated 10/25/82 or other FAA approved data. (e) After installation of the longeron modification, conduct the following inspection at intervals not to exceed 250 hours time in service: (1) Remove forward fairing assembly, P/N 214-061-866-113, and LH and RH fairing assemblies, P/N's 214-061-866-115 and -117. (2) Visually inspect the aft end of the longeron, P/N 214-031-431-101, immediately adjacent to and inboard of the service deck, P/N 214-031-702-101, for cracks. Also, inspect that portion of the longeron adjacent to the newly installed support that is visible inside the aft left electrical compartment and that portion of the longeron that is visible inside the oil cooler compartment for cracks. (f) Replace any cracked parts found during the inspections of paragraph (e) with serviceable parts. (g) Any equivalent method of compliance with this AD must be approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. (h) In accordance with FAR 21.197, flight is permitted to a base where the inspection required by this AD may be accomplished. Amendment 39-4512 became effective December 23, 1982. This Amendment 39-4884 becomes effective August 17, 1984. FOOTER:
Document Text
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AD Final Rules - DRS_82-26-07_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-26-07 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BELL HELICOPTER TEXTRON, INC. Model 214ST Helicopters Subject: Tailboom Separation Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/17/1984 Make: Bell Helicopter Textron, Inc. Model: 214ST 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: 82-26-07 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4884 AD NUMBER: 82-26-07 R1 SUBJECT HEADING: Airworthiness Directives; BELL HELICOPTER TEXTRON, INC. Model 214ST Helicopters ACTION: SUMMARY: DATES: Effective August 17, 1984. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-26-07 R1 BELL HELICOPTER TEXTRON, INC.: Amendment 39-4512 as amended by Amendment 39-4884. Applies to Model 214ST helicopters certificated in all categories which have upper left tailboom attach longeron part number (P/N) 214-031-431-1 01 installed. Compliance is required as indicated unless already accomplished. To prevent possible separation of the tailboom from the fuselage due to failure of the upper left tailboom attach longeron, accomplish the following: (a) Before the first flight of each day on those helicopters that have not had the longeron modification described in paragraph (d) below, inspect the aft portion of the upper left longeron, P/N 214-031-431-101, that is visible inside the oil cooler compartment and the portion visible inside the aft left electrical compartment for cracks. (b) Within the next 5 hours time in service after the effective date of this AD, unless already accomplished within the last 20 hours time in service, and thereafter at intervals not to exceed 25 hours time in service, perform the following inspection on those helicopters that have not had the longeron modification installed: (1) Remove forward fairing assembly, P/N 214-061-866-113, and LH and RH fairing assemblies, P/N's 214-061-866-115 and -117. (2) Visually inspect the aft end of the upper left longeron, P/N 214-031-431- 101, immediately adjacent to and inboard of the pin, P/N 100-048-5-4, just aft of the fairing attach bracket, P/N 214-021-700-129. Inspect for a crack that may extend from the pin hole in the longeron across the longeron and forward. (c) If the longeron is found to be cracked during the inspections of paragraphs (a) and (b) of this AD, replace it with a serviceable part and install the modification described in paragraph (d) below before further flight. (d) Within the next 25 hours time in service after the effective date of this AD or before the accumulation of 100 hours total time in service, whichever occurs later, install a reinforcement modification to the longeron, P/N 214-031-431-101, installation. This reinforcement consists of the addition of a new support, P/N 214-031-454-101, and the replacement of a doubler, P/N 214-031-702-131, with a new doubler, P/N 214-031-643-101. Remove the attaching pin, P/N 100-048-5-4, that is installed in the most aft hole in the longeron outboard flange and plug the remaining hole with adhesive. Accomplish the reinforcement in accordance with Bell Helicopter Textron (BHT) Alert Service Bulletin No. 214ST-82-3, dated 10/25/82 or other FAA approved data. (e) After installation of the longeron modification, conduct the following inspection at intervals not to exceed 250 hours time in service: (1) Remove forward fairing assembly, P/N 214-061-866-113, and LH and RH fairing assemblies, P/N's 214-061-866-115 and -117. (2) Visually inspect the aft end of the longeron, P/N 214-031-431-101, immediately adjacent to and inboard of the service deck, P/N 214-031-702-101, for cracks. Also, inspect that portion of the longeron adjacent to the newly installed support that is visible inside the aft left electrical compartment and that portion of the longeron that is visible inside the oil cooler compartment for cracks. (f) Replace any cracked parts found during the inspections of paragraph (e) with serviceable parts. (g) Any equivalent method of compliance with this AD must be approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. (h) In accordance with FAR 21.197, flight is permitted to a base where the inspection required by this AD may be accomplished. Amendment 39-4512 became effective December 23, 1982. This Amendment 39-4884 becomes effective August 17, 1984. FOOTER:
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Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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