AD 87-12-01
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | DC-9-81 (MD-81) | Airworthiness Directives; MCDONNELL DOUGLAS DC-9-81, -82, -83 (MD-81, -82, -83) Series Airplanes |
| aircraft | The Boeing Company | DC-9-82 (MD-82) | Airworthiness Directives; MCDONNELL DOUGLAS DC-9-81, -82, -83 (MD-81, -82, -83) Series Airplanes |
| aircraft | The Boeing Company | DC-9-83 (MD-83) | Airworthiness Directives; MCDONNELL DOUGLAS DC-9-81, -82, -83 (MD-81, -82, -83) Series Airplanes |
Unsafe Condition
Failure of the main landing gear upper torque link attach bolts (P/N 3935363) could result in loss of main landing gear structural integrity.
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Required Actions
Within 7 days after the effective date, perform a visual inspection of the bolts, washers, and nuts per SB A32-220. If missing, replace with new or serviceable parts before flight. Repeat inspections every 7 days until paragraph B/C is done. Within 90 days, perform ultrasonic inspections every 180 days until magnetic particle inspection (terminating action) is completed. Replace parts if defects found.
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Compliance Time
Within 7 days after the effective date of this AD, and within 90 days after the effective date for paragraph B.
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Affected Aircraft
McDonnell Douglas DC-9-81, -82, -83 (MD-81, -82, -83) series airplanes, Fuselage Numbers 909 through 1350.
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Federal Register Abstract
Main Landing Gear Bolts
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_87-12-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 87-12-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-9-81, -82, -83 (MD-81, -82, -83) Series Airplanes Subject: Main Landing Gear Bolts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/22/1987 Make: The Boeing Company Model: DC-9-81 (MD-81) | DC-9-82 (MD-82) | DC-9-83 (MD-83) Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 87-12-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5636 AD NUMBER: 87-12-01 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-9-81, -82, -83 (MD-81, -82, -83) Series Airplanes ACTION: SUMMARY: DATES: Effective June 22, 1987. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 87-12-01 MCDONNELL DOUGLAS: Amendment 39-5636. Applies to McDonnell Douglas Model DC-9-81, -82, -83 (MD-81, -82, -83) series airplanes, Fuselage Numbers 909 through 1350, certificated in any category. Compliance required as indicated unless previously accomplished. To ensure the integrity of the main landing gear upper torque link attach bolts, P/N 3935363, accomplish the following: A. Within 7 days after the effective date of this AD, in accordance with the Accomplishment Instructions of Douglas Aircraft Alert Service Bulletin A32-220, dated April 20, 1987, or later FAA-approved revision, perform a visual inspection to verify the installation of the left and right main landing gear upper torque arm attach bolt, washer, and nut. If a bolt is missing, prior to further flight replace with a new or serviceable bolt, washer, and nut. If the original bolt, washer, and nut are present, repeat visual inspections of the original bolt, washer, and nut at intervals not to exceed 7 days until the requirements of paragraph B. or C., below, are accomplished. B. Within 90 days after the effective date of this AD, in accordance with the Accomplishment Instructions of Douglas Aircraft Alert Service Bulletin A32-220, dated April 20, 1987, or later FAA-approved revision, perform an ultrasonic inspection of the attach bolt for defects. If no defects are found, loosen and retighten the original nut to a torque of 80 to 100 foot-pounds. Repeat the ultrasonic inspections at intervals not to exceed 180 days until the requirements of paragraph C., below, are accomplished. If a defect is found, prior to further flight replace with a new or serviceable bolt, washer, and nut. C. Accomplishment of the magnetic particle inspection of the bolt in accordance with the Accomplishment Instructions of Douglas Aircraft Alert Service Bulletin A32-220, dated April 20, 1987, or later FAA-approved revision, constitutes terminating action for the repetitive inspections required by paragraphs A. and B., above, if no defects are found as a result of the magnetic particle inspection. If a defect is found, prior to further flight replace with a new or serviceable bolt, washer, and nut. D. Installation of new or serviceable bolt, washer, and nut in accordance with the Accomplishment Instructions of Douglas Aircraft Alert Service Bulletin A32-220, dated April 20, 1987, or later FAA-approved revision, constitutes terminating action for the repetitive inspections required by this AD. E. 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. F. 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, Publications and Training, C1-750 (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 June 22, 1987. FOOTER:
Document Text
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AD Final Rules - DRS_87-12-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 87-12-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-9-81, -82, -83 (MD-81, -82, -83) Series Airplanes Subject: Main Landing Gear Bolts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/22/1987 Make: The Boeing Company Model: DC-9-81 (MD-81) | DC-9-82 (MD-82) | DC-9-83 (MD-83) 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: 87-12-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5636 AD NUMBER: 87-12-01 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-9-81, -82, -83 (MD-81, -82, -83) Series Airplanes ACTION: SUMMARY: DATES: Effective June 22, 1987. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 87-12-01 MCDONNELL DOUGLAS: Amendment 39-5636. Applies to McDonnell Douglas Model DC-9-81, -82, -83 (MD-81, -82, -83) series airplanes, Fuselage Numbers 909 through 1350, certificated in any category. Compliance required as indicated unless previously accomplished. To ensure the integrity of the main landing gear upper torque link attach bolts, P/N 3935363, accomplish the following: A. Within 7 days after the effective date of this AD, in accordance with the Accomplishment Instructions of Douglas Aircraft Alert Service Bulletin A32-220, dated April 20, 1987, or later FAA-approved revision, perform a visual inspection to verify the installation of the left and right main landing gear upper torque arm attach bolt, washer, and nut. If a bolt is missing, prior to further flight replace with a new or serviceable bolt, washer, and nut. If the original bolt, washer, and nut are present, repeat visual inspections of the original bolt, washer, and nut at intervals not to exceed 7 days until the requirements of paragraph B. or C., below, are accomplished. B. Within 90 days after the effective date of this AD, in accordance with the Accomplishment Instructions of Douglas Aircraft Alert Service Bulletin A32-220, dated April 20, 1987, or later FAA-approved revision, perform an ultrasonic inspection of the attach bolt for defects. If no defects are found, loosen and retighten the original nut to a torque of 80 to 100 foot-pounds. Repeat the ultrasonic inspections at intervals not to exceed 180 days until the requirements of paragraph C., below, are accomplished. If a defect is found, prior to further flight replace with a new or serviceable bolt, washer, and nut. C. Accomplishment of the magnetic particle inspection of the bolt in accordance with the Accomplishment Instructions of Douglas Aircraft Alert Service Bulletin A32-220, dated April 20, 1987, or later FAA-approved revision, constitutes terminating action for the repetitive inspections required by paragraphs A. and B., above, if no defects are found as a result of the magnetic particle inspection. If a defect is found, prior to further flight replace with a new or serviceable bolt, washer, and nut. D. Installation of new or serviceable bolt, washer, and nut in accordance with the Accomplishment Instructions of Douglas Aircraft Alert Service Bulletin A32-220, dated April 20, 1987, or later FAA-approved revision, constitutes terminating action for the repetitive inspections required by this AD. E. 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. F. 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, Publications and Training, C1-750 (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 June 22, 1987. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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