AD 99-10-10
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | 747-200B Series | Airworthiness Directives; Boeing Model 747-200, -300, and -400 Series Airplanes |
| aircraft | The Boeing Company | 747-200C Series | Airworthiness Directives; Boeing Model 747-200, -300, and -400 Series Airplanes |
| aircraft | The Boeing Company | 747-200F Series | Airworthiness Directives; Boeing Model 747-200, -300, and -400 Series Airplanes |
| aircraft | The Boeing Company | 747-300 Series | Airworthiness Directives; Boeing Model 747-200, -300, and -400 Series Airplanes |
| aircraft | The Boeing Company | 747-400 Series | Airworthiness Directives; Boeing Model 747-200, -300, and -400 Series Airplanes |
| aircraft | The Boeing Company | 747-400D Series | Airworthiness Directives; Boeing Model 747-200, -300, and -400 Series Airplanes |
| aircraft | The Boeing Company | 747-400F Series | Airworthiness Directives; Boeing Model 747-200, -300, and -400 Series Airplanes |
Unsafe Condition
Cracked fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut due to fatigue and corrosion could result in failure of the fuse pin and strut-to-wing attachment, and consequent loss of the strut and separation of the engine from the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Replace the fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut with new corrosion-resistant pins within 10 months after the effective date. Compliance must follow Boeing Service Bulletin 747-54-2155, Revision 2, and pins must be replaced in sets as specified.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 10 months after the effective date
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Boeing Model 747-200, -300, and -400 series airplanes equipped with General Electric CF6-80C2 series engines, as listed in Boeing Service Bulletin 747-54-2155, Revision 2, excluding those modified per AD 95-13-05 or AD 95-13-06.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Nacelle Strut
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_99-10-10.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 99-10-10 Document Type: AD Final Rules Docket Number: 98-NM-286-AD Subject Heading: Airworthiness Directives; Boeing Model 747-200, -300, and -400 Series Airplanes Subject: Nacelle Strut Status: Current Citation: (Federal Register: May 11, 1999 (Volume 64, Number 90)) Citation Publish Date: 05/11/1999 Effective Date: 06/15/1999 Make: The Boeing Company Model: 747-200B Series | 747-200C Series | 747-200F Series | 747-300 Series | 747-400 Series | 747-400D Ser...Show more 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 (64 FR 25197 No. 90 05/11/99) Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 99-10-10 CITATION: [Federal Register: May 11, 1999 (Volume 64, Number 90)] PAGE NUMBER: [Page 25197] DOCKET NUMBER: 98-NM-286-AD AMENDMENT: 39-11163 AD NUMBER: 99-10-10 SUBJECT HEADING: Airworthiness Directives; Boeing Model 747-200, -300, and -400 Series Airplanes ACTION: Final rule SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200, -300, and -400 series airplanes, that requires replacement of fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut with new corrosion-resistant pins. This amendment is prompted by reports of cracked fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut due to fatigue and corrosion. The actions specified by this AD are intended to prevent cracking or corrosion of the fuse pins of the nacelle strut, which could result in failure of the fuse pin and strut-to-wing attachment, and consequent loss of the strut and separation of the engine from the airplane. DATES: Effective June 15, 1999. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 15, 1999. ADDRESSES: The service information referenced in this AD may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Tamara L. Anderson, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2771; fax (425) 227-1181. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Boeing Model 747-200, -300, and -400 series airplanes was published in the Federal Register on February 18, 1999 (64 FR 8024). That action proposed to require replacement of fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut with new corrosion-resistant pins. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the two comments received. One commenter supports the proposed rule. The second commenter states that the proposed rule will have no impact on it; therefore, the commenter supports the proposed rule. Conclusion After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed. Cost Impact There are approximately 282 airplanes of the affected design in the worldwide fleet. The FAA estimates that 43 airplanes of U.S. registry will be affected by this AD, that it will take approximately 105 work hours per airplane to accomplish the required replacement, and that the average labor rate is $60 per work hour. Required parts will be provided by the manufacturer at no cost to the operators. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $270,900, or $6,300 per airplane. The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. Regulatory Impact The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: REGULATORY TEXT: 99-10-10 BOEING: Amendment 39-11163. Docket 98-NM-286-AD. Applicability: Model 747-200 and -300 series airplanes equipped with General Electric Model CF6-80C2 series engines, and Model 747-400 series airplanes; as listed in Boeing Service Bulletin 747-54-2155, Revision 2, dated June 6, 1996, certificated in any category; except those airplanes on which modifications of the strut/wing structure have been accomplished in accordance either of the following AD's: AD 95-13-05, amendment 39-9285 (60 FR 33333, June 28, 1995), or AD 95-13-06, amendment 39-9286 (60 FR 33338, June 28, 1995). NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent cracking or corrosion of the fuse pins of the nacelle strut, which could result in failure of the fuse pin and strut-to-wing attachment, and consequent loss of the strut and separation of the engine from the airplane, accomplish the following: (a) Within 10 months after the effective date of this AD, replace the fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut with new corrosion-resistant pins, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-54-2155, Revision 2, dated June 6, 1996. NOTE 2: Replacement of the fuse pins accomplished prior to the effective date of this AD in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-54-2155, dated September 23, 1993, or Revision 1, dated December 8, 1994, is considered acceptable for compliance with the applicable action specified in this amendment. NOTE 3: All fuse pins in the strut do not have to be replaced at the same time; however, the fuse pins do have to be replaced in sets, as specified in Boeing Service Bulletin 747-54-2155, Revision 2, dated June 6, 1996. (b) Accomplishment of the replacement of the fuse pins specified in paragraph (a) of this AD constitutes terminating action for the repetitive inspections of the fuse pins of the upper link, required by AD 97-14-06, amendment 39-10064; of the fuse pins of the midspar fitting, required by AD 92-24-51, amendment 39-8439; and of the fuse pins of the diagonal brace, required by AD 93-03-14, amendment 39-8518. Alternative Methods of Compliance (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. Special Flight Permits (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (e) The replacement shall be done in accordance with Boeing Service Bulletin 747-54-2155, Revision 2, dated June 6, 1996. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on June 15, 1999. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_99-10-10.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 99-10-10 Document Type: AD Final Rules Docket Number: 98-NM-286-AD Subject Heading: Airworthiness Directives; Boeing Model 747-200, -300, and -400 Series Airplanes Subject: Nacelle Strut Status: Current Citation: (Federal Register: May 11, 1999 (Volume 64, Number 90)) Citation Publish Date: 05/11/1999 Effective Date: 06/15/1999 Make: The Boeing Company Model: 747-200B Series | 747-200C Series | 747-200F Series | 747-300 Series | 747-400 Series | 747-400D Ser...Show more 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 (64 FR 25197 No. 90 05/11/99) Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 99-10-10 CITATION: [Federal Register: May 11, 1999 (Volume 64, Number 90)] PAGE NUMBER: [Page 25197] DOCKET NUMBER: 98-NM-286-AD AMENDMENT: 39-11163 AD NUMBER: 99-10-10 SUBJECT HEADING: Airworthiness Directives; Boeing Model 747-200, -300, and -400 Series Airplanes ACTION: Final rule SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200, -300, and -400 series airplanes, that requires replacement of fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut with new corrosion-resistant pins. This amendment is prompted by reports of cracked fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut due to fatigue and corrosion. The actions specified by this AD are intended to prevent cracking or corrosion of the fuse pins of the nacelle strut, which could result in failure of the fuse pin and strut-to-wing attachment, and consequent loss of the strut and separation of the engine from the airplane. DATES: Effective June 15, 1999. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 15, 1999. ADDRESSES: The service information referenced in this AD may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Tamara L. Anderson, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2771; fax (425) 227-1181. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Boeing Model 747-200, -300, and -400 series airplanes was published in the Federal Register on February 18, 1999 (64 FR 8024). That action proposed to require replacement of fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut with new corrosion-resistant pins. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the two comments received. One commenter supports the proposed rule. The second commenter states that the proposed rule will have no impact on it; therefore, the commenter supports the proposed rule. Conclusion After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed. Cost Impact There are approximately 282 airplanes of the affected design in the worldwide fleet. The FAA estimates that 43 airplanes of U.S. registry will be affected by this AD, that it will take approximately 105 work hours per airplane to accomplish the required replacement, and that the average labor rate is $60 per work hour. Required parts will be provided by the manufacturer at no cost to the operators. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $270,900, or $6,300 per airplane. The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. Regulatory Impact The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: REGULATORY TEXT: 99-10-10 BOEING: Amendment 39-11163. Docket 98-NM-286-AD. Applicability: Model 747-200 and -300 series airplanes equipped with General Electric Model CF6-80C2 series engines, and Model 747-400 series airplanes; as listed in Boeing Service Bulletin 747-54-2155, Revision 2, dated June 6, 1996, certificated in any category; except those airplanes on which modifications of the strut/wing structure have been accomplished in accordance either of the following AD's: AD 95-13-05, amendment 39-9285 (60 FR 33333, June 28, 1995), or AD 95-13-06, amendment 39-9286 (60 FR 33338, June 28, 1995). NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent cracking or corrosion of the fuse pins of the nacelle strut, which could result in failure of the fuse pin and strut-to-wing attachment, and consequent loss of the strut and separation of the engine from the airplane, accomplish the following: (a) Within 10 months after the effective date of this AD, replace the fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut with new corrosion-resistant pins, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-54-2155, Revision 2, dated June 6, 1996. NOTE 2: Replacement of the fuse pins accomplished prior to the effective date of this AD in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-54-2155, dated September 23, 1993, or Revision 1, dated December 8, 1994, is considered acceptable for compliance with the applicable action specified in this amendment. NOTE 3: All fuse pins in the strut do not have to be replaced at the same time; however, the fuse pins do have to be replaced in sets, as specified in Boeing Service Bulletin 747-54-2155, Revision 2, dated June 6, 1996. (b) Accomplishment of the replacement of the fuse pins specified in paragraph (a) of this AD constitutes terminating action for the repetitive inspections of the fuse pins of the upper link, required by AD 97-14-06, amendment 39-10064; of the fuse pins of the midspar fitting, required by AD 92-24-51, amendment 39-8439; and of the fuse pins of the diagonal brace, required by AD 93-03-14, amendment 39-8518. Alternative Methods of Compliance (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. Special Flight Permits (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (e) The replacement shall be done in accordance with Boeing Service Bulletin 747-54-2155, Revision 2, dated June 6, 1996. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on June 15, 1999. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
Related Airworthiness Directives
2025-15-07 Recurring
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: uncommanded fore and aft movement of the Captain's and First Officer's seats, which could cause a flight control obstruction or unintended flight control input, resulting in the loss of the ability...
2025-09-08
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: Outboard elevators without balance weights could result in abnormal vibration, buffeting, flutter, or oscillation that could result in loss of continued safe flight and landing. Additionally, outbo...
2025-02-05
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: improper inner diameter grinding of landing gear outer cylinders, resulting in possible heat damage to the outer cylinder of the nose landing gear (NLG), body landing gear (BLG), and wing landing g...
2024-19-01 Recurring
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: cracks at eight fastener hole locations in the fuselage skin lap splice between stations (STAs) 1450 and 1470 at stringers S-23L and S-23R
