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 |
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 |
| 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. The current amendment deletes reference to the manufacturer’s document and refers to the FAA AD as part of the harmonisation with the engine certificating Authority requirements. Amendment 1 of this Directive became effective on 9 December 1993. |
James Coyne
Delegate of the Civil Aviation Safety Authority
25 May 2005
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