Airworthiness directives › 2004-04-04
AD 2004-04-04 Airworthiness Directives; General Electric Company CF34-8E Series Turbofan Engines
Applicability*9
This AD applies to General Electric Company (GE) CF34-8E series turbofan engines, with master variable geometry (VG) actuators, part number (P/N) 4120T02P02, serial number (SN) APM238AE, and SNs APM242AE and up. These engines are installed on, but not limited to, Embraer 170 series airplanes.
Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. (f) Before installation of a replacement VG actuator, P/N 4120T02P02 with SNs APM238AE, APM242AE and up, confirm that the actuator is new, or if used, confirm that records show that the linear variable differential transformer (LVDT), installed on the master VG actuator, has been replaced since last actuator use. Initial Review (g) Within 10 days after the effective date of this AD, initially review the airplane computer systems for fault messages, and replace actuators with faults reported by the FADEC. Follow the review and replacement requirements of paragraph 3 of the Accomplishment Instructions of GE Alert Service Bulletin (ASB) No. CF34-8E-AL S/B 75-A0001, Revision 1, dated February 10, 2004. The specific review instructions are dependent on the version of FADEC software installed at the time of the review, as detailed in the ASB. Repetitive Review (h) At intervals not to exceed 10 days, repetitively review the computer systems for fault messages, and replace actuators with faults reported by the FADEC. Follow the review and replacement requirements of paragraph 3 of the Accomplishment Instructions of GE ASB No. CF34-8E-AL S/B 75-A0001, Revision 1, dated February 10, 2004. The specific review instructions are dependent on the version of FADEC software installed at the time of the review, as detailed in the ASB. Alternative Methods of
Unsafe condition
This AD results from nine reports of CF34-8C master VG actuator electrical signal faults, one report of which was a dual-channel fault, resulting in the Full Authority Digital Engine Control (FADEC) commanding the engine power to idle. We are issuing this AD to prevent VG master actuator dual-channel electrical signal faults: (1) Which will cause an uncommanded reduction of thrust to idle with a subsequent loss of the ability to advance thrust above idle; and (2) Which could result in a multi-engine loss of thrust if dual-channel faults occur on more than one engine simultaneously.
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