AD 2005-07-09
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric | Company CF34-8E Series | Airworthiness Directives; General Electric Company CF34-8E Series Turbofan Engines |
Unsafe Condition
Dual-channel electrical signal faults in the master variable geometry (VG) actuator, caused by LVDT coil wire deformation and breakage due to thermal expansion of potting material, leading to an uncommanded reduction of thrust to idle and loss of ability to advance thrust above idle. This could result in multiengine loss of thrust if faults occur simultaneously on more than one engine.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Initial review within 10 days after the effective date of the AD, of the airplane computer systems for fault messages, and replacement of actuators reported faulty by the FADEC. Repetitive reviews at intervals not to exceed 10 days are also required. Actuator hardware troubleshooting may be required to identify faulty actuators. Replacement of faulty actuators is required either before further flight or within 10 days of the first fault occurrence.
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Compliance Time
Within 10 days after the effective date of the AD for initial review and repetitive reviews. Replacement of faulty actuators is required either before further flight or within 10 days of the first fault occurrence.
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Affected Aircraft
General Electric Company CF34-8E series turbofan engines with master VG actuators, part number 4120T02P02, and PMA actuators identified by P/N 1211508-002, SN 238AE, and SNs 241AE and up.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
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