AD 74-19-06
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | 747-100 Series | BOEING Model 747 Airplanes |
| aircraft | The Boeing Company | 747-100B Series | BOEING Model 747 Airplanes |
| aircraft | The Boeing Company | 747-100B SUD Series | BOEING Model 747 Airplanes |
| aircraft | The Boeing Company | 747-200B Series | BOEING Model 747 Airplanes |
| aircraft | The Boeing Company | 747-200C Series | BOEING Model 747 Airplanes |
| aircraft | The Boeing Company | 747-200F Series | BOEING Model 747 Airplanes |
| aircraft | The Boeing Company | 747-300 Series | BOEING Model 747 Airplanes |
| aircraft | The Boeing Company | 747-400 Series | BOEING Model 747 Airplanes |
| aircraft | The Boeing Company | 747-400D Series | BOEING Model 747 Airplanes |
| aircraft | The Boeing Company | 747-400F Series | BOEING Model 747 Airplanes |
| aircraft | The Boeing Company | 747SP Series | BOEING Model 747 Airplanes |
| aircraft | The Boeing Company | 747SR Series | BOEING Model 747 Airplanes |
Unsafe Condition
Cracks in torque tube cranks, Part Numbers 65B05025-1 and -2, 69B02875-1 and -2, and 65B09704-1 on passenger doors Nos. 2, 4, and 5 right- and left-hand sides.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect torque tube cranks for cracks. If no cracks found, apply LPS-3 and retorque cross bolts per Boeing Service Bulletin 747-52-2090. If cracks found, repair or replace per the service bulletin or approved method.
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Compliance Time
Within the next 1200 hours time in-service after the effective date of this AD, unless already accomplished in the last 800 hours time in-service, and at intervals thereafter not to exceed 2,000 hours time in-service
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Boeing Model 747 airplanes, certificated in all categories, affected by Boeing Service Bulletin 747-52-2090
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Torque Tube Cranks
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_74-19-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 74-19-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: BOEING Model 747 Airplanes Subject: Torque Tube Cranks Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: The Boeing Company Model: 747-100 Series | 747-100B Series | 747-100B SUD Series | 747-200B Series | 747-200C Series | 747-200...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: 74-19-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1960 AD NUMBER: 74-19-06 SUBJECT HEADING: BOEING Model 747 Airplanes ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 74-19-06 BOEING: Amendment 39-1960. Applies to Boeing Model 747 airplanes, certificated in all categories, which are affected by Boeing Service Bulletin 747-52-2090. Compliance required as indicated: (A) Within the next 1200 hours time in-service after the effective date of this AD, unless already accomplished in the last 800 hours time in-service, and at intervals thereafter not to exceed 2,000 hours time in-service, visually inspect the torque tube cranks, Part Numbers 65B05025-1 and -2, 69B02875-1 and -2, and 65B09704-1 on passenger doors Nos. 2, 4, and 5 right- and left-hand sides for cracks. If cracks are not found, apply LPS-3 and retorque cross bolts in accordance with Paragraph III, Part I of FAA-approved Boeing Service Bulletin 747-52- 2090, dated May 17, 1974, or FAA approved revisions. If cracks are found, repair or replace in accordance with Paragraph (B) below. (B) Cracked parts may be repaired by installation of a saddle clamp in accordance with Paragraph III, Part II of FAA-approved Boeing Service Bulletin 747-52-2090, or FAA-approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, and shall be reinspected in accordance with FAA-approved Boeing Service Bulletin 747-52-2090 at intervals thereafter not to exceed 3,200 hours time in-service. As terminating action, cracked parts may be replaced with new parts in accordance with Paragraph III, Part III of FAA-approved Boeing Service Bulletin 747-52-2090, or FAA-approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. (C) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection interval of the operator, if the request contains substantiating data to justify the adjustment. This amendment becomes effective thirty days after September 20, 1974. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_74-19-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 74-19-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: BOEING Model 747 Airplanes Subject: Torque Tube Cranks Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: The Boeing Company Model: 747-100 Series | 747-100B Series | 747-100B SUD Series | 747-200B Series | 747-200C Series | 747-200...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: 74-19-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1960 AD NUMBER: 74-19-06 SUBJECT HEADING: BOEING Model 747 Airplanes ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 74-19-06 BOEING: Amendment 39-1960. Applies to Boeing Model 747 airplanes, certificated in all categories, which are affected by Boeing Service Bulletin 747-52-2090. Compliance required as indicated: (A) Within the next 1200 hours time in-service after the effective date of this AD, unless already accomplished in the last 800 hours time in-service, and at intervals thereafter not to exceed 2,000 hours time in-service, visually inspect the torque tube cranks, Part Numbers 65B05025-1 and -2, 69B02875-1 and -2, and 65B09704-1 on passenger doors Nos. 2, 4, and 5 right- and left-hand sides for cracks. If cracks are not found, apply LPS-3 and retorque cross bolts in accordance with Paragraph III, Part I of FAA-approved Boeing Service Bulletin 747-52- 2090, dated May 17, 1974, or FAA approved revisions. If cracks are found, repair or replace in accordance with Paragraph (B) below. (B) Cracked parts may be repaired by installation of a saddle clamp in accordance with Paragraph III, Part II of FAA-approved Boeing Service Bulletin 747-52-2090, or FAA-approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, and shall be reinspected in accordance with FAA-approved Boeing Service Bulletin 747-52-2090 at intervals thereafter not to exceed 3,200 hours time in-service. As terminating action, cracked parts may be replaced with new parts in accordance with Paragraph III, Part III of FAA-approved Boeing Service Bulletin 747-52-2090, or FAA-approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. (C) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection interval of the operator, if the request contains substantiating data to justify the adjustment. This amendment becomes effective thirty days after September 20, 1974. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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