AD 90-19-12
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
Inadvertent opening of a cargo door in flight could result in loss of pressurization and control of the aircraft due to failure of cargo door latch bolts.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Remove sealant and perform a torque test on the cargo door latch spool fitting attach bolts. If a bolt breaks, replace it with a new bolt and seal. If the bolt passes the test, retorque and seal it. Inconel bolts with specified part numbers are exempt from testing.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within 30 calendar days after the effective date of this AD, unless previously accomplished within the last 60 days
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
McDonnell Douglas Model DC-10 series airplanes, manufacturer's fuselage numbers 1 through 379
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Cargo Door Latch Bolts
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_90-19-12.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-19-12 Document Type: AD Final Rules Docket Number: 90-NM-170-AD Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes Subject: Cargo Door Latch Bolts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/01/1990 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: 90-19-12 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 90-NM-170-AD AMENDMENT: 39-6735 AD NUMBER: 90-19-12 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes ACTION: SUMMARY: DATES: Effective October 1, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-19-12 MCDONNELL DOUGLAS: Amendment 39-6735. Docket No. 90-NM-170-AD. Applicability: McDonnell Douglas Model DC-10 series airplanes, manufacturer's fuselage numbers 1 through 379, certificated in any category. Compliance: Required as indicated. To prevent inadvertent opening of a cargo door in flight, a condition which could result in loss of pressurization and control of the aircraft, accomplish the following: A. Except as provided in paragraph B. of this AD, within 30 calendar days after the effective date of this AD, unless previously accomplished within the last 60 days, remove sealant in accordance with Figure 1, Step 2, and perform the torque test on the cargo door latch spool fitting attach bolts, in accordance with the Accomplishment Instructions for Group 1, Phase 1, of McDonnell Douglas DC-10 Service Bulletin 52-183, Revision 2, dated April 15, 1981 (hereafter referred to as the Service Bulletin). NOTE: The requirements of this AD are applicable to Model DC-10 series airplanes, manufacturers's fuselage numbers 1 through 379, regardless of the effectivity as specified in the McDonnell Douglas Service Bulletin. 1. If a bolt breaks, prior to further flight, replace it with a new bolt and seal in accordance with Figure 1 of the Service Bulletin. 2. If a bolt passes the torque test, prior to further flight, retorque the bolt and seal in accordance with the Accomplishment Instructions for Group 1, Phase 1, of the Service Bulletin. B. The test required by paragraph A. of this AD is not required for Inconel bolts, part numbers RA21026-7, 77711-7, and 3D0031-7 (grip lengths as applicable per location as specified in Figure 1, sheets 3 and 4, of the Service Bulletin). C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes unpressurized to a base for the accomplishment of the requirements of this AD. D. 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 (ACO), FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Los Angeles ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Los Angeles ACO. 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, P. O. Box 1771, Long Beach, California 90846-0001, Attention: Business Unit Manager, Technical Publications, C1-HDR (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. This amendment (39-6735, AD 90-19-12) becomes effective on October 1, 1990. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_90-19-12.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-19-12 Document Type: AD Final Rules Docket Number: 90-NM-170-AD Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes Subject: Cargo Door Latch Bolts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/01/1990 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: 90-19-12 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 90-NM-170-AD AMENDMENT: 39-6735 AD NUMBER: 90-19-12 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-10 Series Airplanes ACTION: SUMMARY: DATES: Effective October 1, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-19-12 MCDONNELL DOUGLAS: Amendment 39-6735. Docket No. 90-NM-170-AD. Applicability: McDonnell Douglas Model DC-10 series airplanes, manufacturer's fuselage numbers 1 through 379, certificated in any category. Compliance: Required as indicated. To prevent inadvertent opening of a cargo door in flight, a condition which could result in loss of pressurization and control of the aircraft, accomplish the following: A. Except as provided in paragraph B. of this AD, within 30 calendar days after the effective date of this AD, unless previously accomplished within the last 60 days, remove sealant in accordance with Figure 1, Step 2, and perform the torque test on the cargo door latch spool fitting attach bolts, in accordance with the Accomplishment Instructions for Group 1, Phase 1, of McDonnell Douglas DC-10 Service Bulletin 52-183, Revision 2, dated April 15, 1981 (hereafter referred to as the Service Bulletin). NOTE: The requirements of this AD are applicable to Model DC-10 series airplanes, manufacturers's fuselage numbers 1 through 379, regardless of the effectivity as specified in the McDonnell Douglas Service Bulletin. 1. If a bolt breaks, prior to further flight, replace it with a new bolt and seal in accordance with Figure 1 of the Service Bulletin. 2. If a bolt passes the torque test, prior to further flight, retorque the bolt and seal in accordance with the Accomplishment Instructions for Group 1, Phase 1, of the Service Bulletin. B. The test required by paragraph A. of this AD is not required for Inconel bolts, part numbers RA21026-7, 77711-7, and 3D0031-7 (grip lengths as applicable per location as specified in Figure 1, sheets 3 and 4, of the Service Bulletin). C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes unpressurized to a base for the accomplishment of the requirements of this AD. D. 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 (ACO), FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Los Angeles ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Los Angeles ACO. 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, P. O. Box 1771, Long Beach, California 90846-0001, Attention: Business Unit Manager, Technical Publications, C1-HDR (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. This amendment (39-6735, AD 90-19-12) becomes effective on October 1, 1990. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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