AD/Tay/19 LP Compressor Rotor Blade Cracking (Cth)
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (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.
Rolls Royce Turbine Engines - Tay Series
| AD/TAY/19 | LP Compressor Rotor Blade Cracking | 7/2007 |
Applicability: | Rolls-Royce Deutschland (RRD) Ltd. Co. KG. Tay 650-15, Tay 650-15/10 and Tay 651-54 engines. Note 1: These engines are known to be fitted to but not limited to Fokker 100 and Boeing 727 aircraft. |
Requirement: | 1. Carry out an inspection as detailed in paragraph D, PART 1 of RRD Service Bulletin (SB) Tay-72-1442 Revision 4. 2. Carry out an inspection as detailed in paragraph D, PART 2 of RRD SB 3. For Tay 650-15 engines with serial numbers: 17201, 17202, 17226, 17253, 17341, 17356, 17428, 17450, 17457, 17458, 17497, 17530, 17622, 17643, 17655, 17678, 17709, 17751, 17755, 17805 and 17806, perform an ultrasonic inspection on the LP compressor rotor blades in accordance with RRD SB TAY-72-1591 Revision 1. Note 2: EASA AD 2007-0113 dated 26 April 2007 refers. |
Compliance: | 1. Whenever LP compressor blades are removed and installed in a different engine, after the effective date of this AD. 2. At every shop visit, after the effective date of this AD. 3. As detailed in RRD SB Tay-72-1591 Revision 1, unless previously accomplished. |
| This Airworthiness Directive becomes effective on 5 July 2007. |
Background: | The manufacturer introduced SB TAY-72-1442 in 1997 to carry out an ultrasonic inspection of the LP rotor compressor blades. Revision 2 extended the applicability of that SB. Revision 3 of that document changed the affectivity of the SB once again and introduced an alternative procedure for removing fan blades. The latest amendment to SB TAY-72-1442, revision 4, and that mandated by this AD reduces the applicability of the engines. Previously these inspections were requirements detailed in AD/TAY/2 and AD/TAY/9. This AD supersedes AD/TAY/2 and AD/TAY/9 which have been cancelled. |
Charles Lenarcic
Delegate of the Civil Aviation Safety Authority
25 May 2007
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