AD 88-03-08
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | DC-10-10 | Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-10-10F | Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-10-15 | Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-10-30 | Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-10-30F (KC-10A, KDC-10) | Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-10-40 | Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) Series Airplanes |
Unsafe Condition
Failure of a horizontal stabilizer skin panel or a spar cap bolt due to stress corrosion.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Within 6 months after the effective date, inspect horizontal stabilizer skin panels and apply LPS-3 corrosion-inhibiting compound. Inspect spar cap bolts made from H-11 material every year. Replace broken bolts or cracked panels prior to further flight. Reinspect cracked panels every 3 months if within acceptable limits.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 6 months after the effective date of this AD, unless already accomplished since May 8, 1987, and thereafter at intervals not to exceed specified periods (2 years for skin panels, 1 year for bolts, 3 months for reinspection).
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) series airplanes, certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Horizontal Stabilizer
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_88-03-08.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 88-03-08 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Militar...Show more Subject: Horizontal Stabilizer Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/11/1988 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 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 88-03-08 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5838 AD NUMBER: 88-03-08 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) Series Airplanes ACTION: SUMMARY: DATES: Effective March 11, 1988. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 88-03-08 MCDONNELL DOUGLAS: Amendment 39-5838. Applies to McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent failure of a horizontal stabilizer skin panel or a spar cap bolt due to stress corrosion, accomplish the following: A. Within the next 6 months after the effective date of this AD, unless already accomplished since May 8, 1987, and thereafter at intervals not to exceed 2 years, inspect the horizontal stabilizer constant and outer section upper and lower skin panels and apply LPS-3 (or equivalent) corrosion-inhibiting compound in accordance with McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision. B. Within the next 6 months after the effective date of this AD, unless already accomplished since May 8, 1987, and thereafter at intervals not to exceed one year, inspect the horizontal stabilizer spar cap bolts made from H-11 material in accordance with McDonnell Douglas Alert Service Bulletin A55-17, dated May 8, 1987, or later FAA-approved revision. C. If a broken bolt is found, prior to further flight, replace the broken bolt with a new bolt in accordance with McDonnell Douglas Alert Service Bulletin A55-17, dated May 8, 1987, or later FAA-approved revision. D. If a crack is found in a skin panel: 1. Prior to further flight, repair or replace in accordance with McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision; or 2. If the crack is within limits defined in McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision, accomplish the following: a. Prior to further flight, apply LPS-3 (or equivalent corrosion inhibiting compound in accordance with McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision; and b. Prior to further flight, inspect the horizontal stabilizer spar cap bolts nearest to the cracked panel(s) and, if necessary, replace broken attachment bolts in accordance with McDonnell Douglas Alert Service Bulletin A55-17, dated May 8, 1987, or later FAA-approved revision; and c. At intervals not to exceed 3 months from the last inspection, reinspect the cracked skin panel(s) and the adjacent panels (forward and aft and inboard or outboard) and horizontal stabilizer spar cap bolts nearest to the cracked panel(s) in accordance with paragraphs A. and B., above. E. If, at any inspection, a crack is found in the skin panel which is outside acceptable limits defined in paragraph D.2., above, prior to further flight, repair or replace in accordance with McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision. F. Installation of a new inconel or multiphase bolt, as applicable, to replace an H-11 material bolt constitutes terminating action for the repetitive inspections required by this AD for that bolt. G. 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. H. 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 Publications, C1-L00 (54-60). These documents 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 March 11, 1988. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_88-03-08.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 88-03-08 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Militar...Show more Subject: Horizontal Stabilizer Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/11/1988 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 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 88-03-08 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5838 AD NUMBER: 88-03-08 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) Series Airplanes ACTION: SUMMARY: DATES: Effective March 11, 1988. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 88-03-08 MCDONNELL DOUGLAS: Amendment 39-5838. Applies to McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent failure of a horizontal stabilizer skin panel or a spar cap bolt due to stress corrosion, accomplish the following: A. Within the next 6 months after the effective date of this AD, unless already accomplished since May 8, 1987, and thereafter at intervals not to exceed 2 years, inspect the horizontal stabilizer constant and outer section upper and lower skin panels and apply LPS-3 (or equivalent) corrosion-inhibiting compound in accordance with McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision. B. Within the next 6 months after the effective date of this AD, unless already accomplished since May 8, 1987, and thereafter at intervals not to exceed one year, inspect the horizontal stabilizer spar cap bolts made from H-11 material in accordance with McDonnell Douglas Alert Service Bulletin A55-17, dated May 8, 1987, or later FAA-approved revision. C. If a broken bolt is found, prior to further flight, replace the broken bolt with a new bolt in accordance with McDonnell Douglas Alert Service Bulletin A55-17, dated May 8, 1987, or later FAA-approved revision. D. If a crack is found in a skin panel: 1. Prior to further flight, repair or replace in accordance with McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision; or 2. If the crack is within limits defined in McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision, accomplish the following: a. Prior to further flight, apply LPS-3 (or equivalent corrosion inhibiting compound in accordance with McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision; and b. Prior to further flight, inspect the horizontal stabilizer spar cap bolts nearest to the cracked panel(s) and, if necessary, replace broken attachment bolts in accordance with McDonnell Douglas Alert Service Bulletin A55-17, dated May 8, 1987, or later FAA-approved revision; and c. At intervals not to exceed 3 months from the last inspection, reinspect the cracked skin panel(s) and the adjacent panels (forward and aft and inboard or outboard) and horizontal stabilizer spar cap bolts nearest to the cracked panel(s) in accordance with paragraphs A. and B., above. E. If, at any inspection, a crack is found in the skin panel which is outside acceptable limits defined in paragraph D.2., above, prior to further flight, repair or replace in accordance with McDonnell Douglas Alert Service Bulletin A55-16, dated May 8, 1987, or later FAA-approved revision. F. Installation of a new inconel or multiphase bolt, as applicable, to replace an H-11 material bolt constitutes terminating action for the repetitive inspections required by this AD for that bolt. G. 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. H. 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 Publications, C1-L00 (54-60). These documents 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 March 11, 1988. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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