AD 2013-19-05
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bell Helicopter Textron, Inc. | 214B | Airworthiness Directives; Bell Helicopter Textron, Inc., Helicopters |
| aircraft | Bell Helicopter Textron, Inc. | 214B-1 | Airworthiness Directives; Bell Helicopter Textron, Inc., Helicopters |
| aircraft | Bell Helicopter Textron, Inc. | 214ST | Airworthiness Directives; Bell Helicopter Textron, Inc., Helicopters |
Unsafe Condition
Failure of the pylon support spindle assembly due to cracks, corrosion, or damage leading to loss of control of the helicopter.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Create a component history card or equivalent record for each spindle, establish retirement life limits based on model, and replace any spindle that has reached its retirement life.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Before further flight
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Bell Helicopter Textron, Inc. Model 214B, 214B-1, and 214ST helicopters with affected pylon support spindle assemblies.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
JASC Code: 6330, Transmission Mount
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - 2013-19-05.pdf Copy URL Document Versions Feedback DetailsAttachments/Public Comments AD Number: 2013-19-05 Document Type: AD Final Rules Docket Number: FAA-2008-0288 Subject Heading: Airworthiness Directives; Bell Helicopter Textron, Inc., Helicopters Subject: JASC Code: 6330, Transmission Mount Status: Current Citation: Federal Register Volume 78, Number 190 (Tuesday, October 1, 2013) Citation Publish Date: 10/01/2013 Effective Date: 11/05/2013 Make: Bell Helicopter Textron, Inc. Model: 214B | 214B-1 | 214ST Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Automatic Zoom Actual Size Page Fit Page Width 50% 75% 100% 125% 150% 200% 300% 400% 125% of 6 1 [Federal Register Volume 78, Number 190 (Tuesday, October 1, 2013)] [Rules and Regulations] [Pages 60182-60185] From the Federal Register Online via the Government Printing Office [www.gpo.gov] [FR Doc No: 2013-23099] –––––––––––––––––––––––––––––––––– DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2008-0288; Directorate Identifier 2006-SW-25-AD; Amendment 39-17587; AD 2013-19-05] RIN 2120-AA64 Airworthiness Directives; Bell Helicopter Textron, Inc., Helicopters AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. –––––––––––––––––––––––––––––––––– SUMMARY: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (Bell), Model 214B, 214B-1, and 214ST helicopters. This AD requires creating a component history card or equivalent record for certain pylon support spindle assemblies (spindles), establishes a new retirement life for spindles installed on Model 214B and 214B-1 helicopters, reduces the retirement life for spindles installed on Model 214ST helicopters, and requires replacing any spindle that has reached its airworthiness retirement life. This AD was prompted by three in-flight failures of the spindle that resulted in forced landings. The actions of this AD are intended to prevent failure of a spindle and subsequent loss of control of the helicopter. DATES: This AD is effective November 5, 2013. ADDRESSES: For service information identified in this AD, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101; telephone (817) 280-3391; fax (817) 280-6466; or at http://www.bellcustomer.com/files/. You may review a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800-647-5527) is U.S. Department of Transportation, Docket Operations Office, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. 2 FOR FURTHER INFORMATION CONTACT: Martin Crane, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5056; email 7-AVS-ASW-170@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On March 13, 2008, at 73 FR 13513, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Bell Model 214B and 214B-1 helicopters with a certain spindle installed. The NPRM proposed to require creating a component history card or equivalent record for each spindle, inspecting the spindles for any corrosion, or a nick, scratch, dent, or crack, and repairing or replacing any unairworthy spindle before further flight. The actions proposed in the NPRM were intended to be interim actions until a retirement life for the affected spindles could be developed and new replacement spindles became available. The NPRM was prompted by three in-flight failures of spindles which resulted in forced landings and one serious injury. On May 28, 2013, at 78 FR 31860, the Federal Register published our supplemental notice of proposed rulemaking (SNPRM), which revised some of the actions of the NPRM. The SNPRM added Bell Model 214ST to the proposed applicability, revised the proposed recording requirements, removed the proposed inspection requirements, established a new proposed retirement life for spindle part number (P/N) 214-030-606-005, reduced the proposed retirement life for spindle P/N 214-030- 606-103, and added a proposed requirement to replace any spindle that has exceeded its retirement life. The Model 214ST was added after a crack was reported in a Model 214ST spindle, P/N 214-030- 606-103. Bell determined it necessary to establish a retirement life for the spindles because the speed at which a crack can propagate is such that a more frequent inspection interval would not be practical. In addition, the cost of compliance information was updated in the SNPRM by correcting the estimated number of work-hours to replace both spindles, by updating the estimated labor cost per work-hour from $80 to $85, and by updating the cost of required parts to current replacement parts cost. The proposed actions in the SNPRM were intended to prevent failure of a spindle and subsequent loss of control of the helicopter. Comments We gave the public the opportunity to comment on the NPRM (73 FR 13513, March 13, 2008) and the SNPRM (78 FR 31860, May 28, 2013). We received comments to the NPRM which we addressed in the SNPRM. The following presents those comments and the FAA's response to each comment. Request Bell stated that results from analysis and review of the pylon spindle assembly, P/N 214-030- 606-005, identified the requirement to assign an airworthiness retirement life to that assembly. They also stated that alert service bulletins would detail the retirement life of the spindle. We agreed and revised the SNPRM (78 FR 31860, May 28, 2013) accordingly. Bell commented that the NPRM (73 FR 13513, March 13, 2008) did not address conversion of torque events to retirement index number (RIN). We agreed and revised the SNPRM accordingly. Bell also stated that the NPRM mis-identified the visual inspection requirements of using a magnifying glass on each outer radius of the spindle; that this visual inspection requirement is for the main rotor hub spindle, not the transmission spindle. They also stated that once cracks start, they progress very rapidly and visual inspection at a frequency designed to discover cracking would not be
Document Text
Show stored source text (verify against official source)
AD Final Rules - 2013-19-05.pdf Copy URL Document Versions Feedback DetailsAttachments/Public Comments AD Number: 2013-19-05 Document Type: AD Final Rules Docket Number: FAA-2008-0288 Subject Heading: Airworthiness Directives; Bell Helicopter Textron, Inc., Helicopters Subject: JASC Code: 6330, Transmission Mount Status: Current Citation: Federal Register Volume 78, Number 190 (Tuesday, October 1, 2013) Citation Publish Date: 10/01/2013 Effective Date: 11/05/2013 Make: Bell Helicopter Textron, Inc. Model: 214B | 214B-1 | 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: Automatic Zoom Actual Size Page Fit Page Width 50% 75% 100% 125% 150% 200% 300% 400% 125% of 6 1 [Federal Register Volume 78, Number 190 (Tuesday, October 1, 2013)] [Rules and Regulations] [Pages 60182-60185] From the Federal Register Online via the Government Printing Office [www.gpo.gov] [FR Doc No: 2013-23099] –––––––––––––––––––––––––––––––––– DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2008-0288; Directorate Identifier 2006-SW-25-AD; Amendment 39-17587; AD 2013-19-05] RIN 2120-AA64 Airworthiness Directives; Bell Helicopter Textron, Inc., Helicopters AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. –––––––––––––––––––––––––––––––––– SUMMARY: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (Bell), Model 214B, 214B-1, and 214ST helicopters. This AD requires creating a component history card or equivalent record for certain pylon support spindle assemblies (spindles), establishes a new retirement life for spindles installed on Model 214B and 214B-1 helicopters, reduces the retirement life for spindles installed on Model 214ST helicopters, and requires replacing any spindle that has reached its airworthiness retirement life. This AD was prompted by three in-flight failures of the spindle that resulted in forced landings. The actions of this AD are intended to prevent failure of a spindle and subsequent loss of control of the helicopter. DATES: This AD is effective November 5, 2013. ADDRESSES: For service information identified in this AD, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101; telephone (817) 280-3391; fax (817) 280-6466; or at http://www.bellcustomer.com/files/. You may review a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800-647-5527) is U.S. Department of Transportation, Docket Operations Office, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. 2 FOR FURTHER INFORMATION CONTACT: Martin Crane, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5056; email 7-AVS-ASW-170@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On March 13, 2008, at 73 FR 13513, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Bell Model 214B and 214B-1 helicopters with a certain spindle installed. The NPRM proposed to require creating a component history card or equivalent record for each spindle, inspecting the spindles for any corrosion, or a nick, scratch, dent, or crack, and repairing or replacing any unairworthy spindle before further flight. The actions proposed in the NPRM were intended to be interim actions until a retirement life for the affected spindles could be developed and new replacement spindles became available. The NPRM was prompted by three in-flight failures of spindles which resulted in forced landings and one serious injury. On May 28, 2013, at 78 FR 31860, the Federal Register published our supplemental notice of proposed rulemaking (SNPRM), which revised some of the actions of the NPRM. The SNPRM added Bell Model 214ST to the proposed applicability, revised the proposed recording requirements, removed the proposed inspection requirements, established a new proposed retirement life for spindle part number (P/N) 214-030-606-005, reduced the proposed retirement life for spindle P/N 214-030- 606-103, and added a proposed requirement to replace any spindle that has exceeded its retirement life. The Model 214ST was added after a crack was reported in a Model 214ST spindle, P/N 214-030- 606-103. Bell determined it necessary to establish a retirement life for the spindles because the speed at which a crack can propagate is such that a more frequent inspection interval would not be practical. In addition, the cost of compliance information was updated in the SNPRM by correcting the estimated number of work-hours to replace both spindles, by updating the estimated labor cost per work-hour from $80 to $85, and by updating the cost of required parts to current replacement parts cost. The proposed actions in the SNPRM were intended to prevent failure of a spindle and subsequent loss of control of the helicopter. Comments We gave the public the opportunity to comment on the NPRM (73 FR 13513, March 13, 2008) and the SNPRM (78 FR 31860, May 28, 2013). We received comments to the NPRM which we addressed in the SNPRM. The following presents those comments and the FAA's response to each comment. Request Bell stated that results from analysis and review of the pylon spindle assembly, P/N 214-030- 606-005, identified the requirement to assign an airworthiness retirement life to that assembly. They also stated that alert service bulletins would detail the retirement life of the spindle. We agreed and revised the SNPRM (78 FR 31860, May 28, 2013) accordingly. Bell commented that the NPRM (73 FR 13513, March 13, 2008) did not address conversion of torque events to retirement index number (RIN). We agreed and revised the SNPRM accordingly. Bell also stated that the NPRM mis-identified the visual inspection requirements of using a magnifying glass on each outer radius of the spindle; that this visual inspection requirement is for the main rotor hub spindle, not the transmission spindle. They also stated that once cracks start, they progress very rapidly and visual inspection at a frequency designed to discover cracking would not be
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Retrieved: Apr 8, 2026
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