AD/JT8D/27 Amdt 2 - First Stage Compressor Hub (Cth)

AIRWORTHINESS DIRECTIVE For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/JT8D/27 Amdt 1 and issues the following AD under subregulation 39.001(1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Pratt and Whitney Turbine Engines - JT8D Series AD/JT8D/27 Amdt 2 First Stage Compressor Hub 7/2005

Applicability: Pratt & Whitney (PW) Model JT8D-9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines containing front compressor fan hub Part Number (P/N) 817401 with the following serial numbers: J78892 through J80538, K32019 through K34018, L32197 through L34133, or M05722 through M07296; and all serial numbers of fan hubs P/N 594301, 640601, 743301, 749801, 750101, 791801, 806001. Requirement: Inspect and / or shotpeen and / or remove from service front compressor fan hub as per Requirements of FAA Airworthiness Directive (AD) 95-10-10.

Note: FAA AD 95-10-10 Amendment 39-9227refers. Compliance: Unless previously accomplished, as per compliance schedule of the FAA AD 95-10-10 Amendment 39-9227. This Amendment becomes effective on 7 July 2005. Background: Fracture of the front compressor fan hub can result in an uncontained engine failure and damage to the aircraft. The requirements of this AD are aimed at prevention of the hub fracture and resultant uncontained engine failure.