CTHIn ForceLegislation
AD/CFE 738/4 - Stage 2 High Pressure Turbine Aft Cooling Plate
CFE Company Turbine Engines - CFE 738 SeCFE Company Turbine Engines - CFE 738 Series
Start here
Get a plain-English read of CFE Company Turbine Engines - CFE 738 Se
Turn the raw legal text into a practical explanation grounded in AD/CFE 738/4 - Stage 2 High Pressure Turbine Aft Cooling Plate.
CFE Company Turbine Engines - CFE 738 Series
| AD/CFE 738/4 | Stage 2 High Pressure TurbineAft Cooling Plate | 3/2006 |
|---|
| Applicability: | CFE Model CFE738-1-1B turbofan engines, part number (P/N) 3050000-5, with gas generator modules P/N 6091T09G01, serial numbers (SN's) 800421, 800422, 800423, 800424, 800425, 800426, 800427, 800428, 800429, and 800430 installed.Note 1: These engines are installed on, but not limited to Dassault-Breguet Falcon 2000 series aeroplanes. |
|---|---|
| Requirement: | 1. Inspect the stage 2 HPT aft cooling plate for nicks, dents, and scratches on surface D in accordance with the requirements of CFE Alert Service Bulletin (ASB) No. CFE738-A72-8031, Revision 4, dated 27 March 2002, paragraph 2.B.(1).2. Repair those stage 2 HPT aft cooling plates with indentation 0.003 inch deep or less in accordance with ASB No. CFE738-A72-8031, Revision 4 paragraph 2.B.(1).3. Remove from service before further flight those stage 2 HPT aft cooling plates that have nicks, dents, and/or scratches that exceed the acceptance limits in accordance with ASB No. CFE738-A72-8031, paragraph 2.B.(1), and replace with serviceable parts.4. Inspect the stage 2 HPT rotor disk post aft mating surface for raised metal, and remove raised metal if present in accordance with ASB No. CFE738-A72-8031, Revision 4, paragraph 2.B.(2).Note 2: FAA AD 99-27-16R1 Amdt 39-12791 refers. |
| Compliance: | Unless previously accomplished, carry out at the next shop visit where the HPT assembly is sufficiently disassembled to afford access to the stage 2 HPT aft cooling plate but not later than 4,500 part cycles-since-new. |
| This Airworthiness Directive becomes effective on 16 March 2006. |
| Background: | The actions detailed in this AD are intended to prevent stage 2 high pressure turbine (HPT) aft cooling plate failure, which could result in an uncontained engine failure and damage to the aeroplane. |
|---|
Image unavailable in extracted text
James Coyne
Delegate of the Civil Aviation Safety Authority
1 February 2006