Document ID: chunk:federal_register_of_legislation:F2005L01306:body:0
Version: federal_register_of_legislation:F2005L01306
Segment Type: other
Provision Reference: 
Character Range: 0–2406

AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/JT8D/22 Amdt 4 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/22 Amdt 5  Combustion Chamber Outer Case  7/2005

Applicability:  Pratt & Whitney (PW) Models JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15,
                -15A, -17, -17A, -17R, and -17AR turbofan engines, with combustion chamber outer case (CCOC) part numbers (P/Ns) 490547, 542155, 616315, 728829, 728829-001, 730413, 730413-001, 730414, 730414-001, 767197, 767279, 767279-001 installed.
Requirement:    To prevent CCOC flange cracks that could result in uncontained engine failure, in-flight engine shutdown, engine cowl release, and airframe damage, comply with the Requirements of FAA Airworthiness Directive (AD) 96-23-14 Amendment 39-9820.

                Note:  FAA AD 96-23-14 Amendment 39-9820 refers.
Compliance:     Unless previously accomplished, as per compliance schedule of the FAA AD
                96-23-14 Amendment 39-9820.
                This Amendment becomes effective on 7 July 2005.
Background:     There have been reports of crack origins in the forward face of the rear flange of the CCOC.  These cracks, if undetected, may cause CCOC failure leading to uncontained engine failure, in-flight engine shutdown, engine cowl release, and airframe damage.  The actions specified by this AD are intended to address the unsafe condition identified above.

                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 25 April 1996.

James Coyne
Delegate of the Civil Aviation Safety Authority

25 May 2005