AD/AE 3007/6 Amdt 1 High Pressure Turbine Stage 2 Wheels (Cth)

AIRWORTHINESS DIRECTIVE

On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/AE 3007/6 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.

Rolls Royce (Allison) Turbine Engines - AE 3007 Series

AD/AE 3007/6 Amdt 1 High Pressure Turbine Stage 2 Wheels 3/2009

Applicability:

Rolls-Royce Corporation (RRC) AE 3007A series turbofan engines with high-pressure turbine (HPT) stage 2 wheels, part numbers (P/Ns) 23065892, 23069116, 23069438, 23069592, 23074462, 23074644, 23075345, 23084520, or 23084781, installed.

Note 1:  These engines are installed on, but not limited to, Empresa Brasileira de Aeronautica S. A. (EMBRAER) EMB-135 and EMB-145 aeroplanes.

Requirement:

1.    For engines with an HPT stage 2 wheel, P/Ns 23065892, 23069116, 23069438, 23069592, 23074462, 23074644, 23075345, 23084520, or 23084781, remove the engine from service by the cycles- in-service (CIS) specified in Table 1 of this AD.

2.    Do not return to service, any HPT stage 2 wheel that was installed in any RRC AE 3007A series engine removed as a result of Requirement 1 of this AD, unless the HPT stage 2 wheel was inspected as specified in RRC Alert Service Bulletin (ASB) AE 3007A-A-72-367, dated 5 September 2008.

Later revisions of the above ASB, approved by the United States Federal Aviation Administration (FAA) as an Alternate Method of Compliance (AMOC) to FAA AD 2008-26-06 are considered acceptable for compliance with the equivalent Requirements of this AD.

Note 2:  FAA AD 2008-26-06 Amdt 39-15772 dated 12 December 2008 refers.  This AD supersedes FAA AD 2008-19-51.

Compliance:

For Requirement 1 - As detailed in Table 1.

Table 1 - Compliance Times for Engine Removal for ECI of the HPT Stage 2

If the HPT Stage 2 Wheel has Accumulated on the Effective Date of This AD:	Then Remove the Engine From Service:
16,200 cycles-since-new (CSN) or more.	Within 150 CIS.
15,800 to 16,199 CSN.	Within 300 CIS.
15,500 to 15,799 CSN.	Within 450 CIS.

For Requirement 2 - From the effective date of this AD.

This Amendment becomes effective on 12 March 2009.

Background:

This AD results from reports of cracked HPT stage 2 wheels.  We are issuing this AD to detect cracks in the HPT stage 2 wheel, which could result in a possible uncontained failure of the HPT stage 2 wheel and damage to the aeroplane.

The original issue of this AD required performing initial and repetitive eddy current inspections (ECIs) on the high-pressure turbine (HPT) stage 2 wheel for cracks.  This AD continues to require those same inspections, but revises the compliance schedule for the initial inspection and specifies the affected HPT stage 2 wheels by part number.

The original issue of this AD became effective on 12 September 2008.

James Coyne
Delegate of the Civil Aviation Safety Authority

27 January 2009