AD/CF34/16 FADEC Software Version 8Ev5.40 (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.
General Electric Turbine Engines - CF34 Series
| AD/CF34/16 | FADEC Software Version 8Ev5.40 | 13/2008 |
Applicability: | CF34-8E series turbofan engines with full authority digital electronic controls (FADEC), part numbers (P/N) 4120T00P47, 4120T00P48, 111E9320G48 or 111E9320G49, installed. |
| Note 1: These engines are known to be installed on, but not limited to, Empresa Brasileira de Aeronáutica S.A. (EMBRAER) ERJ 170 series aeroplanes. | |
Requirement: | 1. Unless already accomplished, remove FADEC software version 8Ev5.40 by accomplishing either of the following: |
| a. Replace the FADEC P/N 4120T00P47, 4120T00P48, 111E9320G48 or 111E9320G49, with a FADEC P/N not listed in the applicability statement of this Directive, or | |
| b. Reprogram the FADEC software to a version approved by the United States Federal Aviation Administration (FAA). | |
| General Electric Alert Service Bulletin CF34-8E-AL S/B 73-A0019, dated | |
| Note 2: Removal of FADEC software version 8Ev5.40 may have already been accomplished in accordance with AD/ERJ-170/16 Amdt 1 (Brazilian Agência Nacional de Aviação Civil (ANAC) AD 2008-03-01R1). | |
| 2. FADEC P/N 4120T00P47, 4120T00P48, 111E9320G48 or 111E9320G49 may not be installed onto any CF34-8E engine. | |
| Note 3: FAA AD 2008-16-01 Amdt 39-15619 refers. | |
Compliance: | For Requirement 1 - Within 660 hours time in service after the effective date of this Directive. |
| For Requirement 2 - After 18 December 2008 (the effective date of this Directive). | |
| This Airworthiness Directive becomes effective on 18 December 2008. |
Background: | This Directive results from six loss of thrust control events from the same software fault scenario. The Directive is issued to prevent loss of thrust control and controllability of the aeroplane. |
James Coyne
Delegate of the Civil Aviation Safety Authority
6 November 2008
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