AD 2005-25-05 Airworthiness Directives; Pratt & Whitney JT8D Series Turbofan Engines

This AD applies to Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series turbofan engines. These engines are installed on, but not limited to Boeing 727 and 737 series, and McDonnell Douglas DC-9 series airplanes.

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 481672, as appropriate for PW JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series turbofan engines, and (2) for air carriers, revise the approved mandatory inspections section of the continuous airworthiness maintenance program, by adding the following: “Critical Life Limited Part Inspection A. Inspection Requirements: (1) This section has 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 was not damaged or related to the cause for its removal from the engine. (3) The inspections specified in this paragraph do not replace or make not necessary other recommended inspections for these parts or other parts. B. Parts Requiring Inspection: Note: Piece part is defined as any of the listed parts with all the blades removed.   Description Section Inspection Number Hub (Disk), 1st Stage Compressor: Hub Detail—All P/Ns 72-33-31 -02, -03, -04, -05 Hub Assembly—All P/Ns 72-33-31 -02, -03, -04, -05 2nd Stage Compressor: Disk—All P/Ns 72-33-33 -02, -03 Disk Assembly—All P/Ns 72-33-33 -02, -03 Disk, 13th Stage Compressor—All P/Ns 72-36-47 -02 HP Turbine Disk, First Stage w/integral Shaft—All P/Ns 72-52-04 -03 HP Turbine, First Stage, w/separable Shaft: 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 (Separable), 4th Stage Turbine—All P/Ns 72-53-15 -02 Disk (Integral Disk/Hub), 4th Stage Turbine—All P/Ns 72-53-18 -02” Alternative Methods of

This AD results from the need to require enhanced inspection of selected critical life-limited parts of PW JT8D series turbofan engines. 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.