Document ID: chunk:federal_register_of_legislation:F2006L03881:body:0:p2
Version: federal_register_of_legislation:F2006L03881
Segment Type: other
Provision Reference: 
Character Range: 2882–4443

date of this directive when the module is disassembled for refurbishment or overhaul, but not later than 1 January 2015.

               - if both engines on the same aircraft are affected, on at least one engine before 1 January 2011.

             For Tay 651 -54 Engines:

               - on all engines at the next shop visit after the effective date of this directive when the module is disassembled for refurbishment or overhaul, but no later than 8,200 flight hours after the effective date of this directive.
             This Airworthiness Directive becomes effective on 18 January 2007.
Background:  Some engines have experienced heavy High Pressure (HP) compressor stator vane tip rubs with partial loss of the corresponding HP compressor rotor spacer material on the HP compressor stages 4 to 9.  This damage can occur because the minimum vane tip clearance between the HP compressor stator vane tips and the corresponding HP compressor rotor spacers can be potentially too small in adverse operating conditions leading to heavy HP compressor stator vane tip rubs potentially leading to an in-flight shut down (IFSD).

             This AD introduces a revised HP compressor vane setting procedure to prevent a multiple-engine IFSD.

   The AD/F100/75 was applicable to Tay engines installed on Fokker model F100 aircraft only.  This AD replaces AD/F100/75 and mandates the requirements on Tay engines irrespective of the aircraft installation.

James Coyne
Delegate of the Civil Aviation Safety Authority

23 November 2006