AD 66-04-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric Company | CJ805-23 | GENERAL ELECTRIC Models CJ805-3, -3A, -3B, -23, -23B, and -23C Engines |
| engine | General Electric Company | CJ805-23B | GENERAL ELECTRIC Models CJ805-3, -3A, -3B, -23, -23B, and -23C Engines |
| engine | General Electric Company | CJ805-23C | GENERAL ELECTRIC Models CJ805-3, -3A, -3B, -23, -23B, and -23C Engines |
| engine | General Electric Company | CJ805-3 | GENERAL ELECTRIC Models CJ805-3, -3A, -3B, -23, -23B, and -23C Engines |
| engine | General Electric Company | CJ805-3A | GENERAL ELECTRIC Models CJ805-3, -3A, -3B, -23, -23B, and -23C Engines |
| engine | General Electric Company | CJ805-3B | GENERAL ELECTRIC Models CJ805-3, -3A, -3B, -23, -23B, and -23C Engines |
Unsafe Condition
Failure of the thrust reverser due to second stage turbine discs with insufficient cycle life remaining.
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Required Actions
Remove from service second stage turbine discs with less than 7,000 cycles on the effective date before accumulating 7,200 cycles. Remove from service discs with 7,000 or more cycles within the next 200 cycles. Disc life may be extended to 10,000 cycles if meeting criteria in GE Service Bulletin 880-72-263 or 990-72-272.
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Compliance Time
Effective February 7, 1968.
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Affected Aircraft
General Electric Models CJ805-3, -3A, -3B, -23, -23B, and -23C Turbojet Engines.
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Federal Register Abstract
Thrust Reverser
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_66-04-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 66-04-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: GENERAL ELECTRIC Models CJ805-3, -3A, -3B, -23, -23B, and -23C Engines Subject: Thrust Reverser Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 02/07/1968 Make: General Electric Company Model: CJ805-23 | CJ805-23B | CJ805-23C | CJ805-3 | CJ805-3A | CJ805-3B Product Type: Engine Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 66-04-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-548 AD NUMBER: 66-04-01 SUBJECT HEADING: GENERAL ELECTRIC Models CJ805-3, -3A, -3B, -23, -23B, and -23C Engines ACTION: SUMMARY: DATES: Effective February 7, 1968. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 66-04-01 GENERAL ELECTRIC: Amdt. 39-548 Part 39 Federal Register February 5, 1966. Applies to Models CJ805-3, -3A, -3B, -23, -23B, and -23C Turbojet Engines. Compliance required as indicated. To prevent the failure of thrust reverser, accomplish the following: (a) Remove from service second stage turbine discs with less than 7,000 cycles on the effective date of this AD before the accumulation of 7,200 cycles. (b) Remove from service second stage turbine discs with 7,000 or more cycles on the effective date of this AD within the next 200 cycles. (c) For the purpose of this AD, the number of cycles equals the number of flights that involve an engine operating sequence consisting of engine starting, takeoff operation, landing, and engine shutdown. The number of cycles may be determined by actual count or, subject to acceptance by the assigned FAA maintenance inspector, may be calculated by dividing each second stage turbine disc's hours time in service by the operator's fleet average time per flight (involving an engine operating sequency consisting of engine starting, takeoff operation, landing, and engine shutdown) for airplanes equipped with General Electric CJ805 engines. (d) The disc life specified in this AD may be extended to 10,000 cycles provided the discs meet the criteria outlined in paragraphs 1.k and 2 of General Electric Service Bulletin (880) 72-263 or (990) 72-272. This amendment is effective February 7, 1968. (General Electric telegram to CJ805 operators dated December 1, 1965, pertains to this subject.) This directive effective February 3, 1966. FOOTER:
Document Text
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AD Final Rules - DRS_66-04-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 66-04-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: GENERAL ELECTRIC Models CJ805-3, -3A, -3B, -23, -23B, and -23C Engines Subject: Thrust Reverser Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 02/07/1968 Make: General Electric Company Model: CJ805-23 | CJ805-23B | CJ805-23C | CJ805-3 | CJ805-3A | CJ805-3B 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: 66-04-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-548 AD NUMBER: 66-04-01 SUBJECT HEADING: GENERAL ELECTRIC Models CJ805-3, -3A, -3B, -23, -23B, and -23C Engines ACTION: SUMMARY: DATES: Effective February 7, 1968. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 66-04-01 GENERAL ELECTRIC: Amdt. 39-548 Part 39 Federal Register February 5, 1966. Applies to Models CJ805-3, -3A, -3B, -23, -23B, and -23C Turbojet Engines. Compliance required as indicated. To prevent the failure of thrust reverser, accomplish the following: (a) Remove from service second stage turbine discs with less than 7,000 cycles on the effective date of this AD before the accumulation of 7,200 cycles. (b) Remove from service second stage turbine discs with 7,000 or more cycles on the effective date of this AD within the next 200 cycles. (c) For the purpose of this AD, the number of cycles equals the number of flights that involve an engine operating sequence consisting of engine starting, takeoff operation, landing, and engine shutdown. The number of cycles may be determined by actual count or, subject to acceptance by the assigned FAA maintenance inspector, may be calculated by dividing each second stage turbine disc's hours time in service by the operator's fleet average time per flight (involving an engine operating sequency consisting of engine starting, takeoff operation, landing, and engine shutdown) for airplanes equipped with General Electric CJ805 engines. (d) The disc life specified in this AD may be extended to 10,000 cycles provided the discs meet the criteria outlined in paragraphs 1.k and 2 of General Electric Service Bulletin (880) 72-263 or (990) 72-272. This amendment is effective February 7, 1968. (General Electric telegram to CJ805 operators dated December 1, 1965, pertains to this subject.) This directive effective February 3, 1966. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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