AD 98-25-15
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | MD-11 | Airworthiness Directives; McDonnell Douglas Model MD-11 Series Airplanes |
| aircraft | The Boeing Company | MD-11F | Airworthiness Directives; McDonnell Douglas Model MD-11 Series Airplanes |
Unsafe Condition
Failure of the attachment bolts on the forward and aft flanges of the No. 4 banjo fitting and the pylon carry-through cap due to fatigue cracking, leading to reduced controllability during flight and ground operation.
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Required Actions
Within 1,500 landings after the effective date, perform an external visual inspection for attachment failures. Repeat inspections every 1,500 landings until terminating actions are done. If failed attachments are found, perform eddy current inspections and replace attachments. Within 5 years, perform eddy current inspections to detect cracking; replace attachments if no cracking found, repair and replace if cracking detected.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 1,500 landings after the effective date of this AD, and within 5 years after the effective date of this AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
McDonnell Douglas Model MD-11 series airplanes listed in Service Bulletin MD11-55-013, Revision 03, dated May 15, 1998, certificated in any category.
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Federal Register Abstract
Attachment Bolts On Forward And Aft Flanges
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_98-25-15.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 98-25-15 Document Type: AD Final Rules Docket Number: 96-NM-227-AD Subject Heading: Airworthiness Directives; McDonnell Douglas Model MD-11 Series Airplanes Subject: Attachment Bolts On Forward And Aft Flanges Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/19/1999 Make: The Boeing Company Model: MD-11 | MD-11F Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 98-25-15 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 96-NM-227-AD AMENDMENT: 39-10941 AD NUMBER: 98-25-15 SUBJECT HEADING: Airworthiness Directives; McDonnell Douglas Model MD-11 Series Airplanes ACTION: SUMMARY: DATES: Effective January 19, 1999. ADDRESSES: FOR FURTHER INFORMATION CONTACT: John L. Cecil, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone (562) 627-5229; fax (562) 627-5210. SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 98-25-15 MCDONNELL DOUGLAS: Amendment 39-10941. Docket 96-NM-227-AD. Applicability: Model MD-11 series airplanes; as listed in McDonnell Douglas Service Bulletin MD11-55-013, Revision 03, dated May 15, 1998; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been 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 (e) 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 failure of the attachment bolts on the forward and aft flanges of the No. 4 banjo fitting and the pylon carry-through cap due to fatigue cracking, and consequent reduced controllability of the airplane during flight and ground operation, accomplish the following: (a) Within 1,500 landings after the effective date of this AD, perform an external visual inspection for attachment failures of the 12 attachments located on the No. 4 banjo fitting/pylon carry-through cap, in accordance with McDonnell Douglas Service Bulletin MD11-55-013, Revision 02, dated October 28, 1996; or Revision 03, dated May 15, 1998. (1) If no failed attachment is found, repeat the external visual inspection thereafter at intervals not to exceed 1,500 landings until the terminating action specified in paragraph (b) of this AD is accomplished. (2) If any failed attachment is found, prior to further flight, accomplish the actions specified in paragraph (b) of this AD. (b) Except as provided by paragraph (c) of this AD: Within 5 years after the effective date of this AD, perform an eddy inspection to detect cracking of the forward and aft flanges and bolt holes of the No. 4 banjo fitting, in accordance with McDonnell Douglas MD-11 Service Bulletin 55-13, Revision 1, dated December 17, 1993; or McDonnell Douglas Service Bulletin MD11-55-013, Revision 02, dated October 28, 1996; or McDonnell Douglas Service Bulletin MD11-55-013, Revision 03, dated May 15, 1998. (1) If no cracking is found, within 5 years after the effective date of this AD, replace the 12 attachments located on the No. 4 banjo fitting/pylon carry-through cap with new or serviceable attachments in accordance with Revision 03 of the service bulletin. Such replacement constitutes terminating action for the repetitive inspections required by paragraph (a)(1) of this AD. (2) If any cracking is found, prior to further flight, repair the fitting, and replace the 12 attachments located on the No. 4 banjo fitting/pylon carry-through cap with new or serviceable attachments in accordance with Revision 03 of the service bulletin. Such replacement constitutes terminating for the repetitive inspections required by paragraph (a)(1) of this AD. (c) For airplanes on which McDonnell Douglas MD-11 Service Bulletin 55-13, dated December 22, 1992, has been accomplished, and on which no failed attachment was found during the inspection required by paragraph (a) of this AD: The eddy current bolt hole inspection specified in paragraph (b) of this AD is not required provided that all 12 attachments have been replaced in accordance with the original issue of the service bulletin. (d) If the service bulletin specifies that the manufacturer may be contacted for disposition of enlargement of holes beyond the specifications of the service bulletin, or for an evaluation for deferment of repairs: Those conditions shall be addressed in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. (e) 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, Los Angeles ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (f) 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. (g) Except as provided by paragraph (d) of this AD, the actions shall be done in accordance with McDonnell Douglas MD-11 Service Bulletin 55-13, Revision 1, dated December 17, 1993; McDonnell Douglas Service Bulletin MD11-55-013, Revision 02, dated October 28, 1996; or McDonnell Douglas Service Bulletin MD11-55-013, Revision 03, dated May 15, 1998; as applicable. 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 The Boeing Company, Douglas Products Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Technical Publications Business Administration, Dept. C1-L51 (2-60). Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on January 19, 1999. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_98-25-15.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 98-25-15 Document Type: AD Final Rules Docket Number: 96-NM-227-AD Subject Heading: Airworthiness Directives; McDonnell Douglas Model MD-11 Series Airplanes Subject: Attachment Bolts On Forward And Aft Flanges Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/19/1999 Make: The Boeing Company Model: MD-11 | MD-11F 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: AIRWORTHINESS DIRECTIVES FINAL RULES: 98-25-15 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 96-NM-227-AD AMENDMENT: 39-10941 AD NUMBER: 98-25-15 SUBJECT HEADING: Airworthiness Directives; McDonnell Douglas Model MD-11 Series Airplanes ACTION: SUMMARY: DATES: Effective January 19, 1999. ADDRESSES: FOR FURTHER INFORMATION CONTACT: John L. Cecil, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone (562) 627-5229; fax (562) 627-5210. SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 98-25-15 MCDONNELL DOUGLAS: Amendment 39-10941. Docket 96-NM-227-AD. Applicability: Model MD-11 series airplanes; as listed in McDonnell Douglas Service Bulletin MD11-55-013, Revision 03, dated May 15, 1998; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been 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 (e) 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 failure of the attachment bolts on the forward and aft flanges of the No. 4 banjo fitting and the pylon carry-through cap due to fatigue cracking, and consequent reduced controllability of the airplane during flight and ground operation, accomplish the following: (a) Within 1,500 landings after the effective date of this AD, perform an external visual inspection for attachment failures of the 12 attachments located on the No. 4 banjo fitting/pylon carry-through cap, in accordance with McDonnell Douglas Service Bulletin MD11-55-013, Revision 02, dated October 28, 1996; or Revision 03, dated May 15, 1998. (1) If no failed attachment is found, repeat the external visual inspection thereafter at intervals not to exceed 1,500 landings until the terminating action specified in paragraph (b) of this AD is accomplished. (2) If any failed attachment is found, prior to further flight, accomplish the actions specified in paragraph (b) of this AD. (b) Except as provided by paragraph (c) of this AD: Within 5 years after the effective date of this AD, perform an eddy inspection to detect cracking of the forward and aft flanges and bolt holes of the No. 4 banjo fitting, in accordance with McDonnell Douglas MD-11 Service Bulletin 55-13, Revision 1, dated December 17, 1993; or McDonnell Douglas Service Bulletin MD11-55-013, Revision 02, dated October 28, 1996; or McDonnell Douglas Service Bulletin MD11-55-013, Revision 03, dated May 15, 1998. (1) If no cracking is found, within 5 years after the effective date of this AD, replace the 12 attachments located on the No. 4 banjo fitting/pylon carry-through cap with new or serviceable attachments in accordance with Revision 03 of the service bulletin. Such replacement constitutes terminating action for the repetitive inspections required by paragraph (a)(1) of this AD. (2) If any cracking is found, prior to further flight, repair the fitting, and replace the 12 attachments located on the No. 4 banjo fitting/pylon carry-through cap with new or serviceable attachments in accordance with Revision 03 of the service bulletin. Such replacement constitutes terminating for the repetitive inspections required by paragraph (a)(1) of this AD. (c) For airplanes on which McDonnell Douglas MD-11 Service Bulletin 55-13, dated December 22, 1992, has been accomplished, and on which no failed attachment was found during the inspection required by paragraph (a) of this AD: The eddy current bolt hole inspection specified in paragraph (b) of this AD is not required provided that all 12 attachments have been replaced in accordance with the original issue of the service bulletin. (d) If the service bulletin specifies that the manufacturer may be contacted for disposition of enlargement of holes beyond the specifications of the service bulletin, or for an evaluation for deferment of repairs: Those conditions shall be addressed in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. (e) 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, Los Angeles ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (f) 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. (g) Except as provided by paragraph (d) of this AD, the actions shall be done in accordance with McDonnell Douglas MD-11 Service Bulletin 55-13, Revision 1, dated December 17, 1993; McDonnell Douglas Service Bulletin MD11-55-013, Revision 02, dated October 28, 1996; or McDonnell Douglas Service Bulletin MD11-55-013, Revision 03, dated May 15, 1998; as applicable. 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 The Boeing Company, Douglas Products Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Technical Publications Business Administration, Dept. C1-L51 (2-60). Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on January 19, 1999. FOOTER:
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Retrieved: Apr 8, 2026
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