Airworthiness Directive · Amendment 39-14242 · Pratt & Whitney JT8D-209, -217, -217A, -217C, and -219 Turbofan Engines
Pratt & Whitney JT8D-209, -217, -217A, -217C, and -219 Turbofan Engines
Superseded. A later AD replaced this one: AD 2011-04-04. Comply with the one in force.
This AD applies to Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 turbofan engines. These engines are installed on, but not limited to Boeing 727 and McDonnell Douglas MD-80 series airplanes.
The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 turbofan engines. That AD currently requires revisions to the engine manufacturer's time limits section (TLS) to include enhanced inspection of selected critical life-limited parts at each piece-part opportunity. This AD requires modifying the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. An FAA study of in-service events involving uncontained failures of critical rotating engine parts has indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. We are issuing this AD to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
(f) Within the next 30 days after the effective date of this AD, (1) revise the Time Limits section (TLS) of the manufacturer's Engine Manual, Part Number 773128, as appropriate for PW JT8D-209, -217, -217A, -217C, and -219 turbofan engines, and (2) for air carriers, revise the approved mandatory inspections section of the continuous airworthiness maintenance program, by adding the following:
A. Inspection Requirements:
(1) This section contains the definitions for individual engine piece-parts and the inspection procedures, which are necessary, when these parts are removed from the engine.
(2) It is necessary to do the inspection procedures of the piece-parts in Paragraph B when:
(a) The part is removed from the engine and disassembled to the level specified in paragraph B and
(b) The part has accumulated more than 100 cycles since the last piece part inspection, provided that the part is not damaged or related to the cause of its removal from the engine.
(3) The inspections specified in this section do not replace or make unnecessary other recommended inspections for these parts or other parts.
Note: Piece part is defined as any of the listed parts with all the blades removed.
| Description | Section | Inspection No. |
|---|---|---|
| Hub (Disk), 1st Stage Compressor: | ||
| Hub Detail—All P/Ns | 72-33-31 | -02, -03, -04 |
| Hub Assembly—All P/Ns | 72-33-31 | -02, -03, -04 |
| Disk, 13th Stage Compressor—All P/Ns | 72-36-47 | -02 |
| HP Turbine, First Stage: | ||
| Rotor Assembly—All P/Ns | 72-52-02 | -04 |
| Disk—All P/Ns | 72-52-02 | -03 |
| Disk, 2nd Stage Turbine—All P/Ns | 72-53-16 | -02 |
| Disk, 3rd Stage Turbine—All P/Ns | 72-53-17 | -02 |
| Disk, 4th Stage Turbine—All P/Ns | 72-53-18 | -02 |
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
