AD 77-10-12
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | DC-8-11 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-12 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-21 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-31 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-32 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-33 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-41 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-42 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-43 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-51 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-52 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-53 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-55 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-61 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-61F | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-62 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-62F | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-63 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-63F | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-71 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-71F | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-72 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-72F | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-73 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8-73F | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8F-54 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
| aircraft | The Boeing Company | DC-8F-55 | Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes |
Unsafe Condition
Cracks and failure or jamming of the elevator geared tab crank arm and gust lock assemblies could occur, leading to reduced elevator control effectiveness.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect both left and right side inboard and outboard elevator geared tab crank arm assemblies (P/N 4710541 and 4710542) and gust lock assembly (P/N 5644178) for cracks and failure. Replace failed or cracked parts with serviceable ones before further flight. Verify clearance between crank assemblies and box section throughout elevator travel.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within the next 300 hours time in service or 30 days after the effective date of this AD, whichever comes first, unless already accomplished within the past 30 days
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
McDonnell Douglas DC-8 Series airplanes, including models DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, DC-8-43, DC-8-51, and others as listed, certificated in all categories.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Crank Arm Assembly
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_77-10-12.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 77-10-12 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes Subject: Crank Arm Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/26/1977 Make: The Boeing Company Model: DC-8-11 | DC-8-12 | DC-8-21 | DC-8-31 | DC-8-32 | DC-8-33 | DC-8-41 | DC-8-42 | DC-8-43 | DC-8-51 | ...Show more 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: 77-10-12 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2906 AD NUMBER: 77-10-12 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes ACTION: SUMMARY: DATES: Effective May 26, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 77-10-12 MCDONNELL DOUGLAS: Amendment 39-2906. Applies to Model DC-8 Series airplanes, certificated in all categories. Compliance required within the next 300 hours time in service or 30 days after the effective date of this AD, whichever comes first, unless already accomplished within the past 30 days. To detect cracks and prevent failure or jamming of the elevator geared tab crank arm and gust lock assemblies, comply with the following: (a) Visually inspect both the left and right side inboard and outboard elevator geared tab crank arm assemblies, P/N's 4710541 and 4710542 for failure and/or cracks. (b) Visually inspect the P/N 5644178 gust lock assembly, and specifically, the torque tube section of the P/N 4644181 crank assembly, for failure and/or cracks. (c) Failed or cracked parts must be replaced with like serviceable parts before further flight. (d) Verify that clearance exists between the crank assemblies, P/N 4710541 and 4710542, and the box section for all positions along elevator travel. Note: McDonnell Douglas DC-8 Alert Service Bulletin A27-262, dated April 28, 1977, covers the same subject. (e) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to authorize operation of an airplane to a base to perform the inspections required by this AD. This amendment becomes effective May 26, 1977. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_77-10-12.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 77-10-12 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes Subject: Crank Arm Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/26/1977 Make: The Boeing Company Model: DC-8-11 | DC-8-12 | DC-8-21 | DC-8-31 | DC-8-32 | DC-8-33 | DC-8-41 | DC-8-42 | DC-8-43 | DC-8-51 | ...Show more 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: 77-10-12 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2906 AD NUMBER: 77-10-12 SUBJECT HEADING: Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes ACTION: SUMMARY: DATES: Effective May 26, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 77-10-12 MCDONNELL DOUGLAS: Amendment 39-2906. Applies to Model DC-8 Series airplanes, certificated in all categories. Compliance required within the next 300 hours time in service or 30 days after the effective date of this AD, whichever comes first, unless already accomplished within the past 30 days. To detect cracks and prevent failure or jamming of the elevator geared tab crank arm and gust lock assemblies, comply with the following: (a) Visually inspect both the left and right side inboard and outboard elevator geared tab crank arm assemblies, P/N's 4710541 and 4710542 for failure and/or cracks. (b) Visually inspect the P/N 5644178 gust lock assembly, and specifically, the torque tube section of the P/N 4644181 crank assembly, for failure and/or cracks. (c) Failed or cracked parts must be replaced with like serviceable parts before further flight. (d) Verify that clearance exists between the crank assemblies, P/N 4710541 and 4710542, and the box section for all positions along elevator travel. Note: McDonnell Douglas DC-8 Alert Service Bulletin A27-262, dated April 28, 1977, covers the same subject. (e) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to authorize operation of an airplane to a base to perform the inspections required by this AD. This amendment becomes effective May 26, 1977. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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