CTHIn ForceLegislation
AD/JT8D/41 - Compressor Hubs and Disks
Pratt and Whitney Turbine Engines - JT8DPratt and Whitney Turbine Engines - JT8D Series
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Pratt and Whitney Turbine Engines - JT8D Series
| AD/JT8D/41 | Compressor Hubs and Disks | 12/2005 |
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| Applicability: | Pratt & Whitney (PW) JT8D-1, -1A, -1B, - 7, -7A, -7B, -9, -9A, -11, -15, -15A, -17,-17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 turbofan engines.Note 1: These engines are installed on, but not limited to, Boeing 727 and 737 series, and McDonnell Douglas DC-9 series and MD-80 series aeroplanes. |
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| Requirement: | 1. Remove all coating from the disks and hubs identified in Tables 1 and 2 of FAA Airworthiness Directive (AD) 2005-17-16 and visually, dimensionally and non-destructively inspect the parts using the inspection criteria listed in the Accomplishment Instructions portion of Pratt & Whitney Alert Service Bulletin (ASB) No. JT8D A6442 dated 4 April 2003 or later FAA approved revisions.2. Do not install any disk or hub listed in Table 1 of FAA AD 2005-17-16 that has zero cycles-in-service since 14 May 2001.3. Do not return to service any engine that has a disk or hub listed in Table 1 of FAA AD 2005-17-16 that has zero cycles-in-service since 14 May 2001.Note 2: FAA AD 2005-17-16 Amdt 39-14327 refers. |
| Compliance: | 1. At the next shop visit after the effective date of this AD, but no later than 31 March 2008 for all parts listed in Table 1 of FAA AD 2005-17-16 and at next part accessibility for all parts listed in Table 2 of FAA AD 2005-17-16.A shop visit is defined as an engine and/or module removal where engine maintenance entails separation of pairs of major engine flanges or the removal of a disk, hub or spool at a maintenance facility, regardless of the scheduled maintenance action or the reason for engine removal.For the purposes of this AD, accessibility of the HPC rear hub is removing the hub from the engine.2. After the effective date of this AD.3. After the effective date of this AD. |
| This Airworthiness Directive becomes effective on 24 November 2005. |
| Background: | This AD results from reports that certain JT8D critical life-limited rotating parts have been returned to service with cracks, corrosion pitting, or dimensions outside of manual limits. This AD is intended to prevent failure of critical life-limited rotating engine parts, which could result in an uncontained engine failure and damage to the aeroplane. |
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