AD 87-21-04
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | DC-10-10 | Airworthiness Directives; McDONNELL DOUGLAS DC-10 and KC-10A Series Airplanes |
| aircraft | The Boeing Company | DC-10-10F | Airworthiness Directives; McDONNELL DOUGLAS DC-10 and KC-10A Series Airplanes |
| aircraft | The Boeing Company | DC-10-15 | Airworthiness Directives; McDONNELL DOUGLAS DC-10 and KC-10A Series Airplanes |
| aircraft | The Boeing Company | DC-10-30 | Airworthiness Directives; McDONNELL DOUGLAS DC-10 and KC-10A Series Airplanes |
| aircraft | The Boeing Company | DC-10-30F (KC-10A, KDC-10) | Airworthiness Directives; McDONNELL DOUGLAS DC-10 and KC-10A Series Airplanes |
| aircraft | The Boeing Company | DC-10-40 | Airworthiness Directives; McDONNELL DOUGLAS DC-10 and KC-10A Series Airplanes |
| aircraft | The Boeing Company | DC-10-40F | Airworthiness Directives; McDONNELL DOUGLAS DC-10 and KC-10A Series Airplanes |
Unsafe Condition
Failure of the inboard slat drive arm due to fatigue.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the inboard slat drive arm using magnetic particle, ultrasonic, or eddy current inspection procedures per Service Bulletin A27-203. Replace or rework the arm if cracks exceed or are within reworkable limits as defined in the Service Bulletin.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to the accumulation of 10,000 landings, or within 15 days after the effective date of this AD (October 30, 1987), whichever occurs later, and thereafter at intervals not to exceed 2,000 landings.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
McDonnell Douglas Model DC-10 and KC-10A series airplanes, certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Inboard Slat Drive Arm
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_87-21-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 87-21-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; McDONNELL DOUGLAS DC-10 and KC-10A Series Airplanes Subject: Inboard Slat Drive Arm Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/30/1987 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: 87-21-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5737 AD NUMBER: 87-21-04 SUBJECT HEADING: Airworthiness Directives; McDONNELL DOUGLAS DC-10 and KC-10A Series Airplanes ACTION: SUMMARY: DATES: Effective October 30, 1987. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 87-21-04 McDONNELL DOUGLAS: Amendment 39-5737. Applies to McDonnell Douglas Model DC-10 and KC-10A series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent failure of the inboard slat drive arm due to fatigue, accomplish the following: A. Prior to the accumulation of 10,000 landings, or within 15 days after the effective date of this AD, whichever occurs later, unless previously accomplished within the last 90 days, and thereafter at intervals not to exceed 2,000 landings, inspect the inboard slat drive arm in accordance with the expanded magnetic particle, ultrasonic, or eddy current inspection (Option 2) procedures in the Accomplishment Instructions in McDonnell Douglas Service Bulletin A27-203, Revision 1, dated July 9, 1987, or later FAA-approved revision. 1. If crack(s) are found that are beyond the reworkable limits defined by McDonnell Douglas Service Bulletin A27-203, Revision 1, dated July 9, 1987, or later FAA-approved revision, before further flight, replace the cracked arm in accordance with that Service Bulletin. 2. If crack(s) are found that are within the reworkable limits defined by McDonnell Douglas Service Bulletin A27-203, Revision 1, dated July 9, 1987, or later FAA-approved revision, before further flight, rework or replace the arm in accordance with the Accomplishment Instructions in that Service Bulletin. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publication, C1-L00 (54-60). This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This Amendment becomes effective October 30, 1987. FOOTER:
Document Text
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AD Final Rules - DRS_87-21-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 87-21-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; McDONNELL DOUGLAS DC-10 and KC-10A Series Airplanes Subject: Inboard Slat Drive Arm Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/30/1987 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: 87-21-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5737 AD NUMBER: 87-21-04 SUBJECT HEADING: Airworthiness Directives; McDONNELL DOUGLAS DC-10 and KC-10A Series Airplanes ACTION: SUMMARY: DATES: Effective October 30, 1987. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 87-21-04 McDONNELL DOUGLAS: Amendment 39-5737. Applies to McDonnell Douglas Model DC-10 and KC-10A series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent failure of the inboard slat drive arm due to fatigue, accomplish the following: A. Prior to the accumulation of 10,000 landings, or within 15 days after the effective date of this AD, whichever occurs later, unless previously accomplished within the last 90 days, and thereafter at intervals not to exceed 2,000 landings, inspect the inboard slat drive arm in accordance with the expanded magnetic particle, ultrasonic, or eddy current inspection (Option 2) procedures in the Accomplishment Instructions in McDonnell Douglas Service Bulletin A27-203, Revision 1, dated July 9, 1987, or later FAA-approved revision. 1. If crack(s) are found that are beyond the reworkable limits defined by McDonnell Douglas Service Bulletin A27-203, Revision 1, dated July 9, 1987, or later FAA-approved revision, before further flight, replace the cracked arm in accordance with that Service Bulletin. 2. If crack(s) are found that are within the reworkable limits defined by McDonnell Douglas Service Bulletin A27-203, Revision 1, dated July 9, 1987, or later FAA-approved revision, before further flight, rework or replace the arm in accordance with the Accomplishment Instructions in that Service Bulletin. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publication, C1-L00 (54-60). This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This Amendment becomes effective October 30, 1987. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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