| AD Number | 70-26-05 | Status | Active |
| Effective Date | December 29, 1970 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-1131 |
| Product Type | ["Engine"] | Product Subtype | Not specified |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Pratt & Whitney Division |
| Model(s) | JT8D-1 JT8D-11 JT8D-15 JT8D-15A JT8D-17 JT8D-17A JT8D-17AR JT8D-17R JT8D-1A JT8D-1B JT8D-209 JT8D-217 JT8D-217A JT8D-217C JT8D-219 JT8D-5 JT8D-7 JT8D-7A JT8D-7B JT8D-9 JT8D-9A |
70-26-05 PRATT & WHITNEY AIRCRAFT: Amdt. 39-1131. Applies to all model JT8D series turbofan engines.
Compliance required as indicated.
To prevent failure of the first stage compressor rotor blades as the result of improperly machined blade roots, accomplish the following:
(a) Within the next 900 hours in service after the effective date of this AD, unless already accomplished, visually inspect all P/N 487801, 511901 change letter L or earlier, 594601 and 616601 change letter B or earlier first stage compressor rotor blades, for tool marks within the radius of the Z plane platform on both sides of the blade root area. If tool marks are observed, replace the blade.
(b) Upon submission of substantiating data through an FAA Maintenance Inspector by an owner or operator to the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, compliance time may be adjusted.
(Pratt & Whitney letter PSE:HHB:0-4-6-1-33 dated April 6, 1970, pertains to this subject.)
This amendment is effective December 29, 1970.