AD 70-11-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | Pratt & Whitney Division | JT8D-1 | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-11 | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-15 | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-15A | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-17 | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-17A | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-17AR | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-17R | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-1A | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-1B | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-209 | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-217 | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-217A | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-217C | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-219 | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-5 | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-7 | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-7A | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-7B | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-9 | PRATT & WHITNEY Model JT8D Series Engines |
| engine | Pratt & Whitney Division | JT8D-9A | PRATT & WHITNEY Model JT8D Series Engines |
Unsafe Condition
Sixth stage compressor rotor disc failures caused by disc rim front face galling from blade retention tangs.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Replace the suspect sixth stage compressor disc with a new, used, or approved reworked disc. Compliance time depends on hours in service since a 6th stage blade failure: engines with 1200+ hours must replace within 600 hours after AD effective date; those with 1200- hours must replace before 1800 hours since the blade failure.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Compliance required as indicated in the AD's specific timeframes based on hours in service since a 6th stage blade failure.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Pratt & Whitney JT8D series engines with sixth stage compressor discs P/N 586906 (wide rim) that had prior blade failures and weren't reworked per SE:RWJ:9-6-24-1 dated 24 June 1969.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Sixth Stage Compressor Discs
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_70-11-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 70-11-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: PRATT & WHITNEY Model JT8D Series Engines Subject: Sixth Stage Compressor Discs Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/12/1970 Make: Pratt & Whitney Division Model: JT8D-1 | JT8D-11 | JT8D-15 | JT8D-15A | JT8D-17 | JT8D-17A | JT8D-17AR | JT8D-17R | JT8D-1A | JT8D-1...Show more 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: 70-11-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-993 AD NUMBER: 70-11-03 SUBJECT HEADING: PRATT & WHITNEY Model JT8D Series Engines ACTION: SUMMARY: DATES: Effective June 12, 1970. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 70-11-03 PRATT & WHITNEY: Amdt. 39-993. Pratt & Whitney Aircraft JT8D series turbofan engines. Applies to Pratt & Whitney JT8D series turbofan engines, incorporating sixth stage compressor discs P/N 586906 (wide rim) which have encountered previous sixth stage blade failures and were not subsequently reworked in accordance with P&WA Service telegram SE:RWJ: 9-6-24-1 dated 24 June 1969. Compliance required as indicated. To preclude sixth stage compressor rotor disc failures as the result of disc rim front face galling caused by blade retention tangs, accomplish the following: a. For engines incorporating any of the previously listed sixth stage compressor rotor disc: 1. With 1200 hours or more in service since a 6th stage compressor blade failure, within the next 600 hours in service after the effective date of this AD replace the suspect sixth stage compressor disc with a new, used or a disc reworked in a manner approved by Chief, Engineering and Manufacturing Branch, Eastern Region, New York. 2. With 1200 hours or less in service since a 6th stage compressor blade failure, prior to accumulation of 1800 hours time in service since 6th stage blade failure replace the suspect sixth stage compressor disc with a new, used or disc reworked in a manner approved by Chief, Engineering Branch, Eastern Region, New York. b. For the purposes of this AD a blade failure is defined as one in which any portion of the blade root is separated from the blade. c. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region, may adjust the compliance time. This amendment is effective June 12, 1970. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_70-11-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 70-11-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: PRATT & WHITNEY Model JT8D Series Engines Subject: Sixth Stage Compressor Discs Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/12/1970 Make: Pratt & Whitney Division Model: JT8D-1 | JT8D-11 | JT8D-15 | JT8D-15A | JT8D-17 | JT8D-17A | JT8D-17AR | JT8D-17R | JT8D-1A | JT8D-1...Show more 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: 70-11-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-993 AD NUMBER: 70-11-03 SUBJECT HEADING: PRATT & WHITNEY Model JT8D Series Engines ACTION: SUMMARY: DATES: Effective June 12, 1970. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 70-11-03 PRATT & WHITNEY: Amdt. 39-993. Pratt & Whitney Aircraft JT8D series turbofan engines. Applies to Pratt & Whitney JT8D series turbofan engines, incorporating sixth stage compressor discs P/N 586906 (wide rim) which have encountered previous sixth stage blade failures and were not subsequently reworked in accordance with P&WA Service telegram SE:RWJ: 9-6-24-1 dated 24 June 1969. Compliance required as indicated. To preclude sixth stage compressor rotor disc failures as the result of disc rim front face galling caused by blade retention tangs, accomplish the following: a. For engines incorporating any of the previously listed sixth stage compressor rotor disc: 1. With 1200 hours or more in service since a 6th stage compressor blade failure, within the next 600 hours in service after the effective date of this AD replace the suspect sixth stage compressor disc with a new, used or a disc reworked in a manner approved by Chief, Engineering and Manufacturing Branch, Eastern Region, New York. 2. With 1200 hours or less in service since a 6th stage compressor blade failure, prior to accumulation of 1800 hours time in service since 6th stage blade failure replace the suspect sixth stage compressor disc with a new, used or disc reworked in a manner approved by Chief, Engineering Branch, Eastern Region, New York. b. For the purposes of this AD a blade failure is defined as one in which any portion of the blade root is separated from the blade. c. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region, may adjust the compliance time. This amendment is effective June 12, 1970. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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