AD 89-19-08
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 the outboard flap vane due to skin delamination at the splice joint.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the splice joint of the outboard flap vane for skin delamination within 90 days after the effective date or within 5 calendar years after installation, whichever is later. Subsequent inspections every 18 months. Temporary repairs must be done before further flight if delamination is within limits, followed by permanent repair or replacement within 24 months. Permanent repairs or replacement are required if delamination exceeds limits.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 90 days after the effective date of this AD or within 5 calendar years after the installation of the outboard flap vanes, whichever occurs later
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 equipped with outboard flap vane part numbers ARC 1455 or 1457-1, -2, -501, -502, -503, -504, -505, or -506.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Outboard Flap Vane
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_89-19-08.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 89-19-08 Document Type: AD Final Rules Docket Number: 88-NM-125-AD Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Militar...Show more Subject: Outboard Flap Vane Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/14/1989 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: 89-19-08 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 88-NM-125-AD AMENDMENT: 39-6318 AD NUMBER: 89-19-08 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) Series Airplanes ACTION: SUMMARY: DATES: Effective October 14, 1989. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 89-19-08 MCDONNELL DOUGLAS: Amendment 39-6318. (Docket No. 88-NM-125-AD) Applicability: McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) series airplanes; equipped with outboard flap vane part numbers ARC 1455 or 1457-1, -2, -501, -502, -503, -504, -505, or -506; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the outboard flap vane, accomplish the following: A. Within 90 days after the effective date of this AD or within 5 calendar years after the installation of the outboard flap vanes, whichever occurs later, inspect the splice joint of the outboard flap vane for skin delamination, in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988. B. Within 18 months after the effective date of this AD, or within 5 calendar years after the installation of the outboard flap vane, whichever occurs later, and thereafter at intervals not to exceed 18 months, inspect the entire outboard flap vane for skin delamination, in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988. C. If the outboard flap vane skin delamination and the delamination at the splice joint are within the repairable limits specified in Figure 1, Sheet 5 of 5, of McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988, accomplish the following: 1. Prior to further flight, make temporary repairs to the outboard flap vane in accordance with McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988; and 2. Within 6 months after accomplishing the temporary repairs and thereafter at intervals not to exceed 2 months, inspect the repairs in accordance with McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988; and 3. Within 24 months after accomplishing the temporary repairs, accomplish one of the following: a. Replace the outboard flap vane in accordance with McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988; or b. Accomplish a permanent hot bond repair to the entire outboard flap vane in accordance with McDonnell Douglas Service Bulletin A57-110, Revision 2, dated December 20, 1988; or c. Accomplish a permanent repair using a repair method approved by the Manager, Los Angeles Aircraft Certification Office, Northwest Mountain Region. D. If the outboard flap vane skin delamination is greater than the limits for temporary repairs specified in Figure 1, Sheet 5 of 5, of McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988, replace the outboard flap vane before further flight, or accomplish a permanent hot bond repair to the entire outboard flap vane in accordance with McDonnell Douglas Service Bulletin A57-110, Revision 2, dated December 20, 1988. E. If the outboard flap vane skin delamination is within the unrepaired flyable limits specified in Figure 1, Sheet 3 and 4 of 5, of McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988, continue the inspections required by paragraph B., above. F. If an outboard flap vane is repaired in a manner which results in a combination of old bonding technology and new bonding technology (hot bonding) continue the inspections required by paragraph B., above. G. Installation of outboard vane assemblies ARC 1455-507, ARC 1455-508, ARC 1455-509, ARC 1455-510, ARC 1457-507, and/or ARC 1457-508 (as applicable), or the accomplishment of permanent hot bond repairs to the entire outboard flap vane in accordance with McDonnell Douglas Service Bulletin A57-110, Revision 2, dated December 20, 1988, constitutes terminating action for the repetitive inspections required by this AD. H. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Los Angeles Aircraft Certification Office. I. 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 documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-LOO (54-60). These documents may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 3229 East Spring Street, Long Beach, California. This amendment (39-6318, AD 89-19-08) becomes effective on October 14, 1989. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_89-19-08.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 89-19-08 Document Type: AD Final Rules Docket Number: 88-NM-125-AD Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Militar...Show more Subject: Outboard Flap Vane Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/14/1989 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: 89-19-08 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 88-NM-125-AD AMENDMENT: 39-6318 AD NUMBER: 89-19-08 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) Series Airplanes ACTION: SUMMARY: DATES: Effective October 14, 1989. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 89-19-08 MCDONNELL DOUGLAS: Amendment 39-6318. (Docket No. 88-NM-125-AD) Applicability: McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) series airplanes; equipped with outboard flap vane part numbers ARC 1455 or 1457-1, -2, -501, -502, -503, -504, -505, or -506; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the outboard flap vane, accomplish the following: A. Within 90 days after the effective date of this AD or within 5 calendar years after the installation of the outboard flap vanes, whichever occurs later, inspect the splice joint of the outboard flap vane for skin delamination, in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988. B. Within 18 months after the effective date of this AD, or within 5 calendar years after the installation of the outboard flap vane, whichever occurs later, and thereafter at intervals not to exceed 18 months, inspect the entire outboard flap vane for skin delamination, in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988. C. If the outboard flap vane skin delamination and the delamination at the splice joint are within the repairable limits specified in Figure 1, Sheet 5 of 5, of McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988, accomplish the following: 1. Prior to further flight, make temporary repairs to the outboard flap vane in accordance with McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988; and 2. Within 6 months after accomplishing the temporary repairs and thereafter at intervals not to exceed 2 months, inspect the repairs in accordance with McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988; and 3. Within 24 months after accomplishing the temporary repairs, accomplish one of the following: a. Replace the outboard flap vane in accordance with McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988; or b. Accomplish a permanent hot bond repair to the entire outboard flap vane in accordance with McDonnell Douglas Service Bulletin A57-110, Revision 2, dated December 20, 1988; or c. Accomplish a permanent repair using a repair method approved by the Manager, Los Angeles Aircraft Certification Office, Northwest Mountain Region. D. If the outboard flap vane skin delamination is greater than the limits for temporary repairs specified in Figure 1, Sheet 5 of 5, of McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988, replace the outboard flap vane before further flight, or accomplish a permanent hot bond repair to the entire outboard flap vane in accordance with McDonnell Douglas Service Bulletin A57-110, Revision 2, dated December 20, 1988. E. If the outboard flap vane skin delamination is within the unrepaired flyable limits specified in Figure 1, Sheet 3 and 4 of 5, of McDonnell Douglas Service Bulletin A57-110, Revision 1, dated August 10, 1988, or Revision 2, dated December 20, 1988, continue the inspections required by paragraph B., above. F. If an outboard flap vane is repaired in a manner which results in a combination of old bonding technology and new bonding technology (hot bonding) continue the inspections required by paragraph B., above. G. Installation of outboard vane assemblies ARC 1455-507, ARC 1455-508, ARC 1455-509, ARC 1455-510, ARC 1457-507, and/or ARC 1457-508 (as applicable), or the accomplishment of permanent hot bond repairs to the entire outboard flap vane in accordance with McDonnell Douglas Service Bulletin A57-110, Revision 2, dated December 20, 1988, constitutes terminating action for the repetitive inspections required by this AD. H. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Los Angeles Aircraft Certification Office. I. 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 documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-LOO (54-60). These documents may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 3229 East Spring Street, Long Beach, California. This amendment (39-6318, AD 89-19-08) becomes effective on October 14, 1989. FOOTER:
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