Document ID: chunk:federal_register_of_legislation:F2005L01305:body:0
Version: federal_register_of_legislation:F2005L01305
Segment Type: other
Provision Reference: 
Character Range: 0–2301

AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/JT8D/21 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/21 Amdt 1  High Pressure Compressor Spacers  7/2005

Applicability:  Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17,
                -17A, -17R, and -17AR turbofan engines.
Requirement:    To prevent crack propagation and subsequent high pressure compressor (HPC) removable sleeve spacer rupture, perform a one time, eddy current inspection of HPC removable sleeve spacers stages 7-8, 8-9, and 9-10 for cracks, and replace all stages of HPC removable sleeve spacers with the respective HPC integral sleeve spacers, in accordance with the requirements of FAA Airworthiness Directive 86-08-04 R1.

                Note:  FAA AD 86-08-04 R1 Amendment 39-5424 refers.
Compliance:     Unless previously accomplished, as per compliance schedule of the FAA AD
                86-08-04 R1.
                This Amendment becomes effective on 7 July 2005.
Background:     There have been reports of crack initiation, crack propagation and subsequent high pressure compressor (HPC) removable sleeve spacer rupture, resulting in engine failure.  The inspection requirements of this AD are aimed at detection of cracks and prevention of resultant 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.

                Original issue of this Directive became effective on 21 April 1986.

James Coyne
Delegate of the Civil Aviation Safety Authority

25 May 2005