|GENERAL ELECTRIC CT7 9B – ATA 7230 TURBINE ENGINE COMPRESSOR SECTION – COMPRESSOR – STALLED. DR 611954248|
|During Cruise at FL210, LH engine compressor stall occurred. Flight was in icing conditions with both engine and prop de-ice on. Torque reduced, ITT was observed at 960 degrees Celsius peak and Ng fluctuating. Stall persisted for approximately 3 seconds until power lever reduced. A smoke smell occurred in the cabin. Engine operated normally for remainder of flight.|
|GARRETT TFE731 2 – ATA 7321 FUEL CONTROL/TURBINE ENGINES – TURBINE ENGINE – FLUCTUATES. DR 611954252|
|Pilots reported an oily smell after take off. Passing through 1000 ft, RH engine N1 and N2 both fluctuated approx. 5% on 4 to 5 occasions and the fuel flow was noted to fluctuate significantly. Thrust lever position was maintained, engine and fuel fluctuations stabilised. Precautionary single engine out landing carried out. Engineering investigating.|
|GENERAL ELECTRIC CF34 8E5 – ATA 7321 FUEL CONTROL/TURBINE ENGINES – TURBINE ENGINE – FAULT MESSAGE. DR 611954254|
|On push Back , EICAS Message . “Engine 2 No dispatch”. FAULT CODE :73216127E2B
|PRATT AND WHITNEY PW150 A – ATA 7261 TURBINE ENGINE OIL SYSTEM – Thermal bypass valve – HIGH TEMPERATURE. DR 611954262|
|#1 Engine oil temperature went into the red at 108 degrees Celsius on climb out through flight level 120. Engine shutdown carried out.
Ref Bombardier SL DHC8-400-SL79-006, Maint Watch provided trend data analysis indicating failure of oil cooler thermal bypass.
Actuator replaced along with engine oil and filter (main and RGB) replacement. C/O IAW AMM 05-11-00 and FIM 70-00-00. Ops check c/o IAW Actuator install procedure 79-21-06 system confirmed Serviceable.
|HONEYWELL ALF502 – ATA 7230 TURBINE ENGINE COMPRESSOR SECTION – TURBINE ENGINE – SURGED. DR 611954265|
|Unusual engine noise (surges) reported by crew. Engine bleed and fuel system checked with no defects. Aircraft awaiting #3 engine replacement.|
|IAE V2533 A5 – ATA 7230 TURBINE ENGINE COMPRESSOR SECTION – FAN CASE – DAMAGED. DR 611954277|
|During shop inspection, damage was noted that required replacement of fan case acoustic panels. On removal of the panels, fan case parent material was found to exhibit surface damage. This damage was beyond engine manual repairable limits, so the OEM was contacted to request if an extension to these limits was permissible. This request was declined, fan case will be scrapped.
The damage appears to be the result of use of a drill bit or other rotary round-nosed tool during a previous local repair of the acoustic panel. Fan case scrapped.
|ROLLS ROYCE TAY650 65015 – ATA 7321 FUEL CONTROL/TURBINE ENGINES – Fuel pump – UNSERVICEABLE. DR 611954286|
|Both engines thrust mismatched. Take off rejected.|
|PRATT AND WHITNEY PT6T 3 – ATA 7200 ENGINE (TURBINE/TURBOPROP) – TURBINE ENGINE – POWER LOSS. DR 611954298|
|On an approach to a landing site, pilot reported a sudden ‘sinking’ (or bump).
Root cause: #2 Engine high ITT, with engine rough running after landing.
#1 engine remained unaffected and operating normally.
Cause is currently being investigated. No obvious damage to the CT or PT discs, or compressor intake section was observed.
|PRATT AND WHITNEY PT6T 3B – ATA 7210 TURBINE ENGINE REDUCTION GEAR – GEARBOX – CHIP INDICATION. DR 611954306|
|During taxi for departure, ‘Cbox Chip’ caution illuminated. Pilot returned aircraft to hangar and shutdown, approx. 10m.
Root cause: Indicates internal failure of C/Box. Broken gear tooth and damaged chip detector plug.
Gearbox to be removed from A/C and dispatch to P&WC facility for strip and report.