AD 2006-07-17
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | 727-100 Series | Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727- 100C, and 727-200 Series Airplanes |
| aircraft | The Boeing Company | 727-100C Series | Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727- 100C, and 727-200 Series Airplanes |
| aircraft | The Boeing Company | 727-200 Series | Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727- 100C, and 727-200 Series Airplanes |
| aircraft | The Boeing Company | 727 Series | Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727- 100C, and 727-200 Series Airplanes |
| aircraft | The Boeing Company | 727C Series | Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727- 100C, and 727-200 Series Airplanes |
Unsafe Condition
Stress-corrosion cracking of the terminal fittings of the spars of the wings could result in failure of one of the terminal fitting connections. Such a failure, combined with a similar failure of one of the other three terminal fittings, could result in inability to carry fail-safe loads and loss of structural integrity of the wing attachment points.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Determine if terminal fittings of the wing spars are made of 7079 aluminum alloy. For positive findings, conduct repetitive inspections for cracks, corrosion, and surface defects on terminal fitting bores and flanges; apply corrosion inhibiting compound; repair or replace defective parts. Optional terminating action for repetitive inspections is provided.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
before further flight
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Affected Aircraft
Boeing Model 727, 727C, 727-100, 727-100C, and 727-200 Series airplanes
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Terminal fittings of the spars of the wings
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - 2006-07-17.pdf Copy URL Document Versions Feedback DetailsAttachments/Public Comments AD Number: 2006-07-17 Document Type: AD Final Rules Docket Number: FAA-2006-23672 Subject Heading: Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727- 100C, and 727-200 Series Airplanes Subject: Terminal fittings of the spars of the wings Status: Current Citation: (Federal Register: April 7, 2006 (Volume 71, Number 67)) Citation Publish Date: 04/07/2006 Effective Date: 05/12/2006 Make: The Boeing Company Model: 727-100 Series | 727-100C Series | 727-200 Series | 727 Series | 727C Series Product Type: Aircraft Product Subtype: Large Airplane 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: April 7, 2006 (Volume 71, Number 67)] [Rules and Regulations] [Page 17696-17698] From the Federal Register Online via GPO Access [wais.access.gpo.gov] [DOCID:fr07ap06-3] ––––––––––––––––––––––––––––––––––– DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-23672; Directorate Identifier 2005-NM-237-AD; Amendment 39-14544; AD 2006-07-17] RIN 2120-AA64 Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727-100C, and 727-200 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ––––––––––––––––––––––––––––––––––– SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing transport category airplanes. This AD requires determining if the terminal fittings of the spars of the wings are made of 7079 aluminum alloy material. For any positive finding, the AD requires doing repetitive inspections for cracks and corrosion of all exposed surfaces of the terminal fitting bores; doing repetitive inspections for cracks, corrosion, and other surface defects, of all exposed surfaces, including the flanges, of the terminal fitting; applying corrosion inhibiting compound to the terminal fittings; and repairing or replacing any cracked, corroded, or defective part with a new part. This AD also provides for an optional terminating action for the repetitive inspections. This AD results from reports of cracking of the terminal fittings of the spars of the wings. We are issuing this AD to detect and correct stress-corrosion cracking of the terminal fittings, which could result in the failure of one of the terminal fitting connections. Such a failure, combined with a similar failure of one of the other three terminal fittings, could result in the inability of the airplane structure to carry fail-safe loads, which could result in loss of structural integrity of the wing attachment points. DATES: This AD becomes effective May 12, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 12, 2006. ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207, for service information identified in this AD. 2 FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6456; fax (425) 917-6590. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647-5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Boeing transport category airplanes. That NPRM was published in the Federal Register on January 25, 2006 (71 FR 4069). That NPRM proposed to require determining if the terminal fittings of the spars of the wings are made of 7079 aluminum alloy material. For any positive finding, the NPRM proposed to require doing repetitive inspections for cracks and corrosion of all exposed surfaces of the terminal fitting bores; doing repetitive inspections for cracks, corrosion, and other surface defects, of all exposed surfaces, including the flanges, of the terminal fitting; applying corrosion inhibiting compound to the terminal fittings; and repairing or replacing any cracked, corroded, or defective part with a new part. The NPRM also proposed to provide an optional terminating action for the repetitive inspections. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. The commenter, Boeing, supports the NPRM. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed. Interim Action This AD is considered to be interim action. The inspection reports that are required by this AD will enable the manufacturer to obtain better insight into the extent of the cracking and corrosion of the terminal fittings of the front and rear spars of the wings in the fleet, and to develop additional action if necessary to address the unsafe condition. If additional action is identified, we may consider further rulemaking. Costs of Compliance There are about 302 airplanes of the affected design in the worldwide fleet. This AD will affect about 157 airplanes of U.S. registry. The determination of forging number/material identification will take about 4 work hours per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $40,820, or $260 per airplane.
Document Text
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AD Final Rules - 2006-07-17.pdf Copy URL Document Versions Feedback DetailsAttachments/Public Comments AD Number: 2006-07-17 Document Type: AD Final Rules Docket Number: FAA-2006-23672 Subject Heading: Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727- 100C, and 727-200 Series Airplanes Subject: Terminal fittings of the spars of the wings Status: Current Citation: (Federal Register: April 7, 2006 (Volume 71, Number 67)) Citation Publish Date: 04/07/2006 Effective Date: 05/12/2006 Make: The Boeing Company Model: 727-100 Series | 727-100C Series | 727-200 Series | 727 Series | 727C Series Product Type: Aircraft Product Subtype: Large Airplane 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: April 7, 2006 (Volume 71, Number 67)] [Rules and Regulations] [Page 17696-17698] From the Federal Register Online via GPO Access [wais.access.gpo.gov] [DOCID:fr07ap06-3] ––––––––––––––––––––––––––––––––––– DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2006-23672; Directorate Identifier 2005-NM-237-AD; Amendment 39-14544; AD 2006-07-17] RIN 2120-AA64 Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727-100C, and 727-200 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ––––––––––––––––––––––––––––––––––– SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing transport category airplanes. This AD requires determining if the terminal fittings of the spars of the wings are made of 7079 aluminum alloy material. For any positive finding, the AD requires doing repetitive inspections for cracks and corrosion of all exposed surfaces of the terminal fitting bores; doing repetitive inspections for cracks, corrosion, and other surface defects, of all exposed surfaces, including the flanges, of the terminal fitting; applying corrosion inhibiting compound to the terminal fittings; and repairing or replacing any cracked, corroded, or defective part with a new part. This AD also provides for an optional terminating action for the repetitive inspections. This AD results from reports of cracking of the terminal fittings of the spars of the wings. We are issuing this AD to detect and correct stress-corrosion cracking of the terminal fittings, which could result in the failure of one of the terminal fitting connections. Such a failure, combined with a similar failure of one of the other three terminal fittings, could result in the inability of the airplane structure to carry fail-safe loads, which could result in loss of structural integrity of the wing attachment points. DATES: This AD becomes effective May 12, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 12, 2006. ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207, for service information identified in this AD. 2 FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6456; fax (425) 917-6590. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647-5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Boeing transport category airplanes. That NPRM was published in the Federal Register on January 25, 2006 (71 FR 4069). That NPRM proposed to require determining if the terminal fittings of the spars of the wings are made of 7079 aluminum alloy material. For any positive finding, the NPRM proposed to require doing repetitive inspections for cracks and corrosion of all exposed surfaces of the terminal fitting bores; doing repetitive inspections for cracks, corrosion, and other surface defects, of all exposed surfaces, including the flanges, of the terminal fitting; applying corrosion inhibiting compound to the terminal fittings; and repairing or replacing any cracked, corroded, or defective part with a new part. The NPRM also proposed to provide an optional terminating action for the repetitive inspections. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. The commenter, Boeing, supports the NPRM. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed. Interim Action This AD is considered to be interim action. The inspection reports that are required by this AD will enable the manufacturer to obtain better insight into the extent of the cracking and corrosion of the terminal fittings of the front and rear spars of the wings in the fleet, and to develop additional action if necessary to address the unsafe condition. If additional action is identified, we may consider further rulemaking. Costs of Compliance There are about 302 airplanes of the affected design in the worldwide fleet. This AD will affect about 157 airplanes of U.S. registry. The determination of forging number/material identification will take about 4 work hours per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $40,820, or $260 per airplane.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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