AD 76-21-04
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric Company | CF6-6D | GENERAL ELECTRIC Models CF6-6D and CF6-6D1 Engines |
| engine | General Electric Company | CF6-6D1 | GENERAL ELECTRIC Models CF6-6D and CF6-6D1 Engines |
Unsafe Condition
Excessive overpressure in the high pressure compressor
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Required Actions
Remove the abradable material from the inside diameter of the Fan Stator Shroud Mid Ring (Booster Stage) in accordance with General Electric Service Bulletin (CF6-6) 72-647 or subsequent FAA Approved Revision thereto.
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Compliance Time
Compliance required by June 30, 1978, unless previously accomplished.
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Affected Aircraft
General Electric Models CF6-6D and CF6-6D1 Turbofan Engines
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Federal Register Abstract
High Pressure Compressor
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_76-21-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 76-21-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: GENERAL ELECTRIC Models CF6-6D and CF6-6D1 Engines Subject: High Pressure Compressor Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/30/1977 Make: General Electric Company Model: CF6-6D | CF6-6D1 Product Type: Engine Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 76-21-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3085 AD NUMBER: 76-21-04 SUBJECT HEADING: GENERAL ELECTRIC Models CF6-6D and CF6-6D1 Engines ACTION: SUMMARY: DATES: Effective November 30, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 76-21-04 GENERAL ELECTRIC: Amendment 39-2747 as amended by Amendment 39-3085. Applies to Models CF6-6D and CF6-6D1 Turbofan Engines. Compliance required by June 30, 1978, unless previously accomplished. To prevent excessive overpressure in the high pressure compressor, remove the abradable material from the inside diameter of the Fan Stator Shroud Mid Ring (Booster Stage) in accordance with General Electric Service Bulletin (CF6-6) 72-647 or subsequent FAA Approved Revision thereto. The manufacturer's service bulletins identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to General Electric Company, Cincinnati, Ohio 45215. These documents may also be examined at the FAA Great Lakes Region, 2300 E. Devon Avenue, Des Plaines, Illinois 60018 and at FAA headquarters, 800 Independence Avenue, S.W., Washington, D.C A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Great Lakes Region. Amendment 39-2747 became effective October 20, 1976. This amendment 39-3085 becomes effective November 30, 1977. FOOTER:
Document Text
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AD Final Rules - DRS_76-21-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 76-21-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: GENERAL ELECTRIC Models CF6-6D and CF6-6D1 Engines Subject: High Pressure Compressor Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/30/1977 Make: General Electric Company Model: CF6-6D | CF6-6D1 Product Type: Engine Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 76-21-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3085 AD NUMBER: 76-21-04 SUBJECT HEADING: GENERAL ELECTRIC Models CF6-6D and CF6-6D1 Engines ACTION: SUMMARY: DATES: Effective November 30, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 76-21-04 GENERAL ELECTRIC: Amendment 39-2747 as amended by Amendment 39-3085. Applies to Models CF6-6D and CF6-6D1 Turbofan Engines. Compliance required by June 30, 1978, unless previously accomplished. To prevent excessive overpressure in the high pressure compressor, remove the abradable material from the inside diameter of the Fan Stator Shroud Mid Ring (Booster Stage) in accordance with General Electric Service Bulletin (CF6-6) 72-647 or subsequent FAA Approved Revision thereto. The manufacturer's service bulletins identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to General Electric Company, Cincinnati, Ohio 45215. These documents may also be examined at the FAA Great Lakes Region, 2300 E. Devon Avenue, Des Plaines, Illinois 60018 and at FAA headquarters, 800 Independence Avenue, S.W., Washington, D.C A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Great Lakes Region. Amendment 39-2747 became effective October 20, 1976. This amendment 39-3085 becomes effective November 30, 1977. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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