AD 93-01-28
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | DC-10-10 | Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes |
| aircraft | The Boeing Company | DC-10-10F | Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes |
| aircraft | The Boeing Company | DC-10-15 | Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes |
| aircraft | The Boeing Company | DC-10-30 | Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes |
| aircraft | The Boeing Company | DC-10-30F (KC-10A, KDC-10) | Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes |
| aircraft | The Boeing Company | DC-10-40 | Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes |
| aircraft | The Boeing Company | DC-10-40F | Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes |
Unsafe Condition
Failure of the wing-to-fuselage titanium attach tee and subsequent reduced structural integrity of the fuselage.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform a visible dye penetrant inspection to detect cracks in the right and left wing-to-fuselage titanium attach tees within 45 days after the effective date. If no crack is found, repeat the inspection at intervals not exceeding 2,190 landings. If a crack is found, repair it prior to further flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 45 days after the effective date of this AD, unless accomplished within the last 2,190 landings prior to the effective date.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Model DC-10 series airplanes, manufacturer's fuselage numbers 1 through 83, inclusive, certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Wing-To-Fuselage Attach Tee
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_93-01-28.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 93-01-28 Document Type: AD Final Rules Docket Number: 92-NM-247-AD Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes Subject: Wing-To-Fuselage Attach Tee Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 02/17/1993 Make: The Boeing Company Model: DC-10-10 | DC-10-10F | DC-10-15 | DC-10-30 | DC-10-30F (KC-10A, KDC-10) | DC-10-40 | DC-10-40F 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: 93-01-28 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-NM-247-AD AMENDMENT: 39-8482 AD NUMBER: 93-01-28 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes ACTION: SUMMARY: DATES: Effective February 17, 1993. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 93-01-28 MCDONNELL DOUGLAS: Amendment 39-8482. Docket 92-NM-247-AD. Applicability: Model DC-10 series airplanes, manufacturer's fuselage numbers 1 through 83, inclusive, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the wing-to-fuselage titanium attach tee and subsequent reduced structural integrity of the fuselage, accomplish the following: (a) Within 45 days after the effective date of this AD, unless accomplished within the last 2,190 landings prior to the effective date of this AD, perform a visible dye penetrant inspection to detect cracks in the right and left wing-to-fuselage titanium attach tees, in accordance with McDonnell Douglas Alert Service Bulletin A53-164, dated December 16, 1992. NOTE: Inspections of Principal Structural Elements 53.10.047 and 53.10.048 performed in accordance with McDonnell Douglas Report No. L26-012, "DC-10 Supplemental Inspection Document (SID)," Volume II, Revision 1, dated May 1990; or Revision 2, dated April 1992; constitute compliance with this paragraph. (1) If no crack is found, repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 2,190 landings. (2) If any crack is found, prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. (b) 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: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspections shall be done in accordance with McDonnell Douglas Alert Service Bulletin A53-164, dated December 16, 1992. 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 McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California 90846-1771, Attention: Business Unit Manager, Technical Publications - Technical Administrative Support, C1-L5B. 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, 3229 East Spring Street, Long Beach, California 90806-2425; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on February 17, 1993. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_93-01-28.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 93-01-28 Document Type: AD Final Rules Docket Number: 92-NM-247-AD Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes Subject: Wing-To-Fuselage Attach Tee Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 02/17/1993 Make: The Boeing Company Model: DC-10-10 | DC-10-10F | DC-10-15 | DC-10-30 | DC-10-30F (KC-10A, KDC-10) | DC-10-40 | DC-10-40F 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: 93-01-28 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-NM-247-AD AMENDMENT: 39-8482 AD NUMBER: 93-01-28 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes ACTION: SUMMARY: DATES: Effective February 17, 1993. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 93-01-28 MCDONNELL DOUGLAS: Amendment 39-8482. Docket 92-NM-247-AD. Applicability: Model DC-10 series airplanes, manufacturer's fuselage numbers 1 through 83, inclusive, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the wing-to-fuselage titanium attach tee and subsequent reduced structural integrity of the fuselage, accomplish the following: (a) Within 45 days after the effective date of this AD, unless accomplished within the last 2,190 landings prior to the effective date of this AD, perform a visible dye penetrant inspection to detect cracks in the right and left wing-to-fuselage titanium attach tees, in accordance with McDonnell Douglas Alert Service Bulletin A53-164, dated December 16, 1992. NOTE: Inspections of Principal Structural Elements 53.10.047 and 53.10.048 performed in accordance with McDonnell Douglas Report No. L26-012, "DC-10 Supplemental Inspection Document (SID)," Volume II, Revision 1, dated May 1990; or Revision 2, dated April 1992; constitute compliance with this paragraph. (1) If no crack is found, repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 2,190 landings. (2) If any crack is found, prior to further flight, repair it in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. (b) 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: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspections shall be done in accordance with McDonnell Douglas Alert Service Bulletin A53-164, dated December 16, 1992. 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 McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California 90846-1771, Attention: Business Unit Manager, Technical Publications - Technical Administrative Support, C1-L5B. 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, 3229 East Spring Street, Long Beach, California 90806-2425; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on February 17, 1993. 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
2025-23-53
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: The engine-pylon structure of the Model MD-11 and MD-11F airplanes is similar in design to that of the Model MD-10-10F, MD-10-30F, DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC...
2023-12-15
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: 5G C-Band interference can cause radio altimeters to not perform their intended function, resulting in increased flightcrew workload while on approach with the flight director, autothrottle, or aut...
2023-10-02
final ruleAirworthiness Directives; Transport and Commuter Category Airplanes
Unsafe Condition: Radio altimeter anomalies that are undetected by the automation or pilot, particularly close to the ground (e.g., landing flare), could lead to loss of continued safe flight and landing. Additional...
2021-08-10 Recurring
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: possible cracking of the wing pylon at the aft bulkhead bracket, which could result in the inability of the pylon to sustain limit load and adversely affect the structural integrity of the airplane.
