GE CF34-3A1

Service difficulty reports · 1,372

Newest first. General aviation reporting is voluntary.

Query with SQL
duckdb -csv -c "SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy
  FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet'
  WHERE engine_model_key = 'CF343A1'
  ORDER BY difficulty_date DESC"

Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.

SDR CA120126003Indication Sys · malfunctioned(CAN) THE OPERATOR IS REPORTING ABOUT FLAME FROM THE ENGINE ON THE GROUND DURING START. IAW INITIAL INFORMATION CREW WAS PERFORMING THE ENGINE START PROCEDURE WITH PAX ON BOARD. THE ITT WAS EXCEEDING 900 C AND THE ENGINE WAS STOPPED. IAW FDR THE TEMP WAS 1080 Jan 25, 2012 · Cndair CL6002B19 · Engine EGT/TIT Indicating SystemSDR CA120118010Drain · broken(CAN) AIRSPEED INDICATOR SHOWS +450 KTS WHILE MAIN SHOWING 250 , INCREASES EXPTENTIALLY AS AIRSPEED INCREASES 2. FOUND STBY PITIOT DRAIN CRACKED AND BROKEN. 3 .REPLACED STBY PITOT DRAIN (P/N 50034-001) THE NR 3 STATIC - PRESSURE SYSTEM HAS BEEN INSPECTED Jan 16, 2012 · Cndair CL6002B19 · Pitot/Static SystemSDR CA120118007Engine · vibration(CAN) IFSD AND AIR TURNBACK. ACFT WAS AT 11,000 FT WHEN RT ENGINE VIBRATION LEVEL INCREASED THEN ITT WENT TO 1100.Jan 11, 2012 · Cndair CL6002B19 · Engine (Turbine/Turboprop)SDR CA120109010Servo · frozen(CAN) THE FLIGHT CREW REPORTED THAT THE ELEVATOR CONTROL WAS VERY STIFF DURING THE LANDING FLARE, ALMOST LIKE HE WAS FIGHTING THE AUTOPILOT. THE CREW CONFIRMED THE AP WAS DISENGAGED. AFTER LANDING, AT THE GATE THE ELEVATOR CONTROL STILL SEEMED VERY STIFF. THJan 7, 2012 · Cndair CL6002B19 · Elevator Tab Control SystemSDR CA120103008Fairing · dislodged(CAN) UPON REACHING CRUISE ALTITUDE OF FL 240 EXPERIENCED PRONOUNCED BUFFETING OF AIRFRAME AT APPROXIMATELY 300 KTS. BUFFETING SUBSIDED BY 250 KTS. TRIED DIFFERENT ALTITUDES, BUT EXPERIENCED SAME EFFECT TIME AFTER TIME. NO WARNING OR CAUTION MESSAGES. ENGINE Dec 26, 2011 · Cndair CL6002B19 · Aerodynamic FairingsSDR CA111222002Wire · burned(CAN) NR 1 IRS FAILED AFTER TAKEOFF, RESULTING IN A BLANK SCREEN AND HEADING FLAGS. ACFT DIVERTED. TROUBLESHOOTING CARRIED OUT AND FOUND WIRE 1FP9F22BLU SHORTED TO GROUND BETWEEN JB-10 AND MFD 1. DAMAGED WIRE LOCATED BEHIND MFD 1, REPAIRED IAW ESPM 20-11-00.Dec 22, 2011 · Cndair CL6002B19 · Instrument System WiringSDR CA111220002Bulkhead Web · cracked(CAN) WHILE PERFORMING TASK RJ2-53-280-607, MRM TASK 53-61-153, IAW REQUIREMENTS OF ADCF-2011-30, PART B, 2 CRACKS WHERE FOUND ON THE FORWARD FACE OF REAR BULKHEAD WEB AT BS 621. CRACK A WAS FOUND TO BE .400" LONG ABOUT 0.400" FROM RIVET LINE ON REL 27.5 AND Dec 19, 2011 · Cndair CL6002B19 · Fuselage Main, BulkheadSDR CA111214008Skin · cracked(CAN) DURING A ROUTINE INSPECTION, A CRACK WAS FOUND AT APPROX WS 61.0 ON THE UNDERSIDE OF THE WING. THE CRACK IS 0.75 INCHES LONG. THE CRACK STARTS AT THE EDGE OF A SMALL RIVETED PANEL & PROCEEDS INTO THE THICKER SKIN. WING PLANK 601R10046.Dec 9, 2011 · Cndair CL6002B19 · Wing, Plate/SkinSDR CA111209006Tube · cracked(CAN) CENTER FUEL TANK WAS FUELED TO MAX CAPACITY, 5005 POUNDS. ACFT WAS PARKED IN HANGAR & FUEL WAS NOTED TO BE DRIPPING FROM LT AFT FACE OF MLG WW FWD BULKHEAD JUST TO LT OF ACFT CTR LINE. FURTHER INVESTIGATION REVEALED THE LEAK WAS COMING THROUGH THE BACKDec 6, 2011 · Cndair CL6002B19 · Aircraft Fuel Distribution SystemSDR CA111205010Bpsu · failed(CAN) ON APPROACH WHEN THE FLAPS WERE SELECTED FROM 8 TO 20 DEGREES THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE. THE FLAPS STOPPED AT 10 DEGREES. THE FLAP SKEW DETECTION SYSTEM WAS RESET AND THE ACFT DISPATCHED UNDER MEL 27-02 IAW ADCF-2007-10R1. UPON RETDec 2, 2011 · Cndair CL6002B19 · Trailing Edge Flap Control SystemSDR CA111202001Selector Valve · failed(CAN) DURING THE APPROACH, THE NLG FAILED TO EXTEND UPON GEAR DOWN SELECTION AND THE CREW RECEIVED A GEAR DISAGREE WARNING MESSAGE. THE GEAR SELECTOR WAS CYCLED SEVERAL TIMES WITHOUT SUCCESS. THE LANDING GEAR MANUAL RELEASE HANDLE WAS PULLED AND ALL 3 GEARS Dec 1, 2011 · Cndair CL6002B19 · Landing Gear Retraction/Extension SystemSDR CA111124004Windshield · failed(CAN) THE RT SIDE WINDSHIELD OUTER PLY CRACKED IN CRUISE FLIGHT AT FL360. FLIGHT CREW ACTIONED THE QRH AND RETURNED TO BASE. MAINTENANCE R & R THE RT SIDE WINDSHIELD IAW AMM CHAP 56-11-01.Nov 23, 2011 · Cndair CL6002B19 · Flight Compartment WindowsSDR CA111125002Mount · cracked(CAN) DURING ROUTINE INSPECTION, THE ENGINEER FOUND CRACKS ON BOTH LOWER LUGS OF THE NLG DOOR ACTUATOR MECHANISM BASE. THE BASE IS MOUNTED ON THE RT WALL IN THE FWD SECTION OF THE NOSE WW. THE BASE WAS REPLACED. DURING REMOVAL OF THE ACTUATOR, ONE OF THE LUNov 23, 2011 · Cndair CL6002B19 · Landing Gear Retraction/Extension SystemSDR CA111116010Angle · cracked(CAN) CRACKS FOUND ON THE OTBD SIDE OF LT SUPPORT ANGLE IN THE LT SIDE COLLECTOR TANK BY AN AME WHEN HE WAS IN THE FUEL TANKS CARRYING OUT TASK: RJ2-28-900-750 FOR FUNCTIONAL CHECK OF COLLECTOR TANK CHECK VALVES. THE CRACKS ARE APPROXIMATELY 2.300" EMINATING Nov 15, 2011 · Cndair CL6002B19 · Wing Miscellaneous StructureSDR CA111117009Angle · cracked(CAN) WHILE CARRYING OUT TASK: RJ2-28-900-750 FOR FUNCTIONAL CHECK OF COLLECTOR TANK CHECK VALVES, CRACKS WERE FOUND ON THE OTBD SIDE OF ANGLE, PN 601R10011-14A IN THE RT SIDE COLLECTOR TANK. THE CRACKS ARE 1.495" AND 1.200" IN LENGTH AND WERE OBSERVED TO BE Nov 15, 2011 · Cndair CL6002B19 · Wing Miscellaneous StructureSDR CA111114005Selector Valve · failed(CAN) DURING THE APPROACH, THE NLG DIDN`T COME DOWN ON SELECTION. THE CREW MANAGED TO LOWERED THE GEAR AND THE ACFT LANDED WITHOUT FURTHER INCIDENT. THE LANDING GEAR RETRACTION SYS WAS DEFERRED IAW MEL 32-30-01 AND THE ACFT FLEW TO A MX BASE. THE NLG EXTENSINov 9, 2011 · Cndair CL6002B19 · Landing Gear Retraction/Extension SystemSDR CA111111001Valve · failed(CAN) ACFT HAD A LT PACK DEFERRED. PILOT REPORTED THE RT PACK OVER PRESSURIZED ON TAKEOFF. 10TH STAGE VLV CLOSED & CREW WAS NOT ABLE TO RE-OPEN THE VLV. THE RT PACK SHUTOFF & THE AIRPLANE DEPRESSURIZED, PAX O2 MASKS WERE DROPPED & USED. THE ACFT DIVERTED, Nov 9, 2011 · Cndair CL6002B19 · Cabin Pressure Control SystemSDR CA111109001Windshield · failed(CAN) ON DESCENT INTO DESTINATION, CAPTAIN`S WINDSHIELD SHATTERED. FLIGHT CONTINUED ON INTO DESTINATION AND LANDED SAFELY. ACFT REMOVED FROM SERVICE. MX REPLACED LT WINDSHIELD IAW AMM 56-11-01 AND OPS TEST CARRIED OUT SERVICEABLE. THERE APPEARS TO BE EROSIONNov 2, 2011 · Cndair CL6002B19 · Flight Compartment WindowsSDR CA111026001Switch · intermittent(CAN) SHORTLY AFTER TAKEOFF THE NOSE GEAR DIDN`T RETRACT UPON GEAR UP SELECTION. THE FLIGHT CREW FOLLOWED THE QUICK REF HANDBOOK PROCEDURE, CONDUCTED AN ALTERNATE GEAR EXTENSION AND LANDED BACK WITHOUT FURTHER INCIDENT. HISTORICAL REVIEW INDICATED THAT 2 SIMIOct 21, 2011 · Cndair CL6002B19 · Landing Gear Retraction/Extension SystemSDR CA111021003Bearing · seized(CAN) IN CRUISE, WITH THE AUTOPILOT (AP) ENGAGED, THE ACFT STARTED TO ROLL. THE AP WAS DISENGAGED AND THE CREW FELT SEVERE STIFFNESS ON THE AILERON SYS. FOLLOWING THE QUICK REF HANDBOOK PROCEDURE, THE CREW DISCONNECT THE AILERON SYS. THE CAPTAIN SIDE REMAINEDOct 20, 2011 · Cndair CL6002B19 · Aileron Control SystemSDR CA111005009Skin · cracked(CAN) DURING A SCHEDULED IN-HOUSE TASK FOR SCRATCH AND DENT SURVEY OF THE EXTERNAL FUSELAGE, THE AME NOTICED A CRACK EMITING FROM BOTH THE FWD AND AFT LATCH CUT-OUT FOR THE LT SIDE ELECTRONICS BAY DOOR IN THE NOSE OF THE ACFT. THE DAMAGE LOCATED AT STA FS 177Oct 4, 2011 · Cndair CL6002B19 · Fuselage Main, Plate/SkinSDR CA110930001Windshield · failed(CAN) DURING THE APPROACH, THE LT WINDSHIELD SHATTERED, THE CREW CONTINUED THE APPROACH AND LANDED WITHOUT FURTHER INCIDENT. THE WINDSHIELD WAS REPLACED AND THE ACFT RELEASED FOR SERVICE.Sep 28, 2011 · Cndair CL6002B19 · Flight Compartment WindowsSDR COMA2011092750072Engine · vibrationON CLIMBOUT FROM DTW CONSTANT LEFT ENGINE N1 VIB INDICATION, AT NORMAL CRUISE POWER IN EXCESS OF 3.2. NORMAL INDICATION AT REDUCED LESS THAN 60 PERCENT POWER SETTINGS. EMERGENCY DECLARED, A/C RETURNED TO DTW LANDED SAFELY. PERFORMED INSPECTION OF LEFT ENGINSep 26, 2011 · N868CA · Cndair CL6002B19 · Engine (Turbine/Turboprop)SDR CA110927006Engine · overtemp(CAN) DURING CLIMB THE CREW HEARD BANG SOUND FOLLOWED BY ACFT VIBRATION. LT ENGINE ITT INDICATING OVERTEMP WITH DECREASING N1 & N2, THE CREW SHUTDOWN THE LT ENGINE, DECLARED EMERGENCY THEN BACK TO THE ORIGIN. MX CONFIRMED ITT 1149 DEGREE CELSIUS MAXIMUM. Sep 25, 2011 · Cndair CL6002B19 · Engine (Turbine/Turboprop)SDR CA110920002Sensor · failed(CAN) "FLAPS FAIL" ON ED1 AFTER FLAPS RETRACTION. FLAPS STOPPED AT 6 DEGREES. ACFT RETURNED TO AIRPORT. MX FOUND AN INOPERATIVE SKEW SENSOR ON LT WING.Sep 19, 2011 · Cndair CL6002B19 · Trailing Flap Position Indicating SystemSDR CA110921002Stud · broken(CAN) ON TAXI OUT ACFT LOST APU CAME BACK TO GATE, FOUND APU STUD MISSING THAT HOLDS OIL LINE IN PLACE CAUSED AUTO SHUTDOWN. APU BAY WAS COMPLETLY COVERED IN OIL. CLEANED UP ALL VISIBLE OIL , CHECKED DUCTS NO OIL FOUND. APU PUT ON MEL AND NEXT TAKEOFF ABORTESep 19, 2011 · Cndair CL6002B19 · APU Oil SystemSDR CA110921006Turbine · failed(CAN) IN THE CLIMB, CREW HEARD A LOUD BANG FROM THE NR1 ENGINE, FOLLOWED BY VERY HIGH ITT INTO RED ABOVE 900 AND VIBRATION INDICATION WENT TO DASH LINES. ENGINE THROTTLED BACK AND ITT WAS IN RED, VIBRATION REMAINED LOUD AND CONTINUOUS STRONG VIBRATION. CREW SSep 18, 2011 · Cndair CL6002B19 · Turbine SectionSDR CA110916003Actuator · seized(CAN) FLAP FAIL ON APPROACH. FLAPS AT ZERO, SELECTED TO 8 AND RECEIVED FLAP FAIL MESSAGE. THERE WAS NO MOVEMENT OF THE FLAPS AT 3000 FT WITH AN OAT OF 8 DEGREES SPEED 195 KNOTS. CRUISE ALT FOR FLIGHT WAS FL 350 AND THEY WERE THERE FOR APPROX 1.5 HRS AND OAT ASep 15, 2011 · Cndair CL6002B19 · Trailing Edge Flap ActuatorSDR CA110916006Bushing · unserviceable(CAN) BRAKE FOUND LEAKING ON LANDING AND SPRAYED BRAKE FLUID ONTO HOT BRAKES WHICH CAUSED SMOKE TO BE NOTICED FROM AIRPORT TOWER. EMERGENCY RESPONSE SUMMONED TO INVESTIGATE, ACFT TOWED TO GATE, BRAKE CHANGED AND RETURNED TO SERVICE. INVESTIGATION OF CONTINUASep 14, 2011 · Cndair CL6002B19 · Landing Gear Brake SystemSDR CA110914008Rvdt · inoperative(CAN) "STEERING INOP" CAUTION MSG ON ED1. RVDT REPLACED IAW 32-51-20.Sep 13, 2011 · Cndair CL6002B19 · Landing Gear Steering SystemSDR CA110831001Window · cracked(CAN) DURING A FLIGHT THE ACFT EXPERIENCED ARCING FOLLOWED BY CRACKING IN THE PILOT`S LT SIDE WINDOW. NO PRESSURIZATION ISSUES FELT AND FLIGHT CONTINUED. ACFT GROUNDED AND ULTIMATELY FERRIED IAW SL RJ-SL-56-004 WHERE SIDE WINDOW WAS REPLACED.Aug 30, 2011 · Cndair CL6002B19 · Flight Compartment WindowsSDR CA110826002Wire · damaged(CAN) DURING TESTING OF THE FLAP ELECTRICAL SYS FOR AN UNRELATED REASON, MX FOUND AN OPEN CIRCUIT BETWEEN THE NR 1 FLAP POWER DRIVE UNIT (PDU) THERMISTOR AND THE FLAP ELECTRONIC CONTROL UNIT (FECU). FURTHER INVESTIGATION REVEALED THAT ELECTRICAL WIRE, 1CE46A2Aug 26, 2011 · Cndair CL6002B19 · Flight Control System WiringSDR CA110824001Angle · cracked(CAN) WHILE CARRYING OUT AN INSPECTION OF THE WING FUEL TANKS FOR TASK RJ2-57-510-502 AND RJ2-57-610-502, THE AME NOTICED CRACKS ON THE LOWER CAP ANGLES FWD OF RIB AT APPROX WS29.42 IN THE CENTER AND RT FUEL TANKS. CAP ANGLES PN 601R-10011-13A AND 601R10011-14Aug 23, 2011 · Cndair CL6002B19 · Wing Miscellaneous StructureSDR CA110824004Windshield · broken(CAN) WHILE CRUISING AT F320, F/O NOTICED HIS WINDSCREEN BEGIN TO ARC, IMMEDIATELY AFTERWARD THE OUTER WINDSCREEN PANE SHATTERED. CREW FOLLOWED THEIR QUICK REF HANDBOOK AND CONTINUED TO DESTINATION. NO EMERGENCY WAS DECLARED. MX REPLACED WINDSHIELD ASSY.Aug 23, 2011 · Cndair CL6002B19 · Flight Compartment WindowsSDR CA110818004Door · damaged(CAN) THE FLIGHT CREW REPORTED A POSSIBLE BIRD STRIKE ON ROTATION IN THE AREA OF THE NOSE GEAR. SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE LT LOWER CORNER OF THE NLG AFT DOOR (GEAR DOWN CONFIGURATION). THE NLG AFT DOOR WAS REPLACED AND THE ACFT RETURNED TOAug 15, 2011 · Cndair CL6002B19 · Landing Gear DoorsSDR CA110825004Shutoff Valve · failed(CAN) DURING INITIAL CLIMB, THE LT PACK OFF(S) CAME ON EICAS. THE CREW DECIDE TO KEEP THE APU ON AFTER 5000 FT. THE CREW COULD NOT FIND A QRH FOR THE LOSS OF 1 PACK, BUT THEY TRIED TO RESET THE LT PACK WITHOUT SUCCESS. REACHING FL130 THEY DECIDED TO TRANSFEAug 15, 2011 · Cndair CL6002B19 · Cabin Pressure Control SystemSDR CA110811003Bearing · wornON DEPARTURE THE CREW REJECTED THE TAKEOFF AT V1 DUE TO A CONFIG SPOILER WARNING MESSAGE. THIS RESULTED IN A HIGH ENERGY STOP. THE CAUSE OF THE CONFIG SPOILER MESSAGE WAS DETERMINED TO BE A LARGE AMOUNT OF PLAY (ABOUT .040) IN THE LT FLIGHT SPOILER OTBD BEARAug 7, 2011 · Cndair CL6002B19 · SpoilersSDR CA110808004Wire Harness · failedDURING CLIMB THE FLAPS WERE RETRACTED TO ZERO, SHORTLY AFTER THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE. THE FLIGHT CONTINUED AND THE CREW PERFORMED A FLAPLESS LANDING WITHOUT FURTHER INCIDENT. LOCAL MX FOUND THE FLAPS CONT CH1 AND FLAPS CONT CH2 CIRCUIT BRAug 5, 2011 · Cndair CL6002B19 · Flight Control System WiringSDR CA110803019Windshield · crackedDURING CRUISE FLIGHT A 12" LONG CRACK DEVELOPED IN THE LT WINDSHIELD. THERE WERE NO REPORTED PRESSURIZATION PROBLEMS. THE ACFT DIVERTED AND THE WINDSHIELD WAS REPLACED. WINDSHIELD PN NP139321-13, SN 05111H6795, WINDOW TSN 13718, CSN 11263.Jul 31, 2011 · Cndair CL6002B19 · Flight Compartment WindowsSDR CA110812001Angle · crackedDURING HEAVY MX VISIT, AN AME NOTICED A CRACK TO AN ANGLE AT FS409+128, STR 21R. THERE WERE NO SPECIFIC INSPECTIONS CALLED UP FOR THAT AREA AT THIS TIME. MFG WAS NOTIFIED OF FINDING. THE DAMAGED PORTION OF THE ANGLE WAS CUT OUT AND A TEMPORARY REPAIR HAS BEENJul 30, 2011 · Cndair CL6002B19 · Fuselage Miscellaneous StructureSDR CA110708011Fitting · corrodedWHILE COMPLETING A DETAILED INSP OF THE HORIZ STABILIZER PIVOT FITTINGS IAW TASK RJ2-55-320-502, IRON OXIDE COLORED CORROSION WAS OBSERVED COMING THROUGH THE FITTING HALVES ON BOTH THE LT AND RT FITTINGS. UPON FURTHER INSP, THE BUSHING IN THE LT HORIZONTAL SJul 5, 2011 · Cndair CL6002B19 · Horizontal Stabilizer StructureSDR CA110704004Compressor Blade · damagedSHORTLY AFTER TAKEOFF, THE CREW HEARD A LOUD BANG AND FELT A SEVERE VIBRATION, THE ENGINE INDICATION AND CREW ALERTING SYS (EICAS) DISPLAYED THE NR 2 ENGINE INTER TURBINE TEMP (ITT) AT 960C AND THE N2 CORE VIBRATION AMBER MESSAGE. THE CREW SHUTDOWN THE NR 2 EJul 1, 2011 · Cndair CL6002B19 · Turbine Engine Compressor SectionSDR LEJM2011FA0000422O-Ring · failedON APPROACH, THE CREW RECIEVED A "IDG 2" CAS MESSAGE. THE CREW LANDED WITHOUT INCIDENT. I NSP OF THE GENERATOR FOUND THAT THE FILTER DELTA P INDICATOR O-RING HAD FAILED RESULTING IN TOTAL FLUID LOSS. OPS WERE CONTINUED IAW MEL.Jun 27, 2011 · N591ML · Cndair CL6002B19 · AC Generator-AlternatorSDR CA110526004Line · chafedDURING CRUISE FLIGHT INBD TO A MX BASE, THE NR 1 HYD QUANTITY WENT TO ZERO FOLLOWED BY THE PRESSURE GOING TO ZERO WITH ASSOCIATED SYS LOW PRESSURE CAUTION MESSAGES. THE NR 1 HYD SYS PRESSURE LINE IN THE AFT EQUIPMENT BAY WAS FOUND CHAFED THROUGH. IT APPEARS TMay 24, 2011 · Cndair CL6002B19 · Hydraulic System, MainSDR CA110507001Fitting · corroded(CAN) WHILE CARRYING OUT A DETAILED INSPECTION OF THE HORIZONTAL STABILIZER PIVOT FITTINGS IAW TASK NR RJ2-55-320-502, THE AME OBSERVED IRON OXIDE COLORED SUBSTANCE ON AND AROUND THE STABILIZER PIVOT PINS. UPON FURTHER CLEAN UP OF THE AREA AND CLOSER INSPECTIMay 3, 2011 · Cndair CL6002B19 · Fuselage, Stabilizer Attach FittingsSDR CA110502001Oil Tank · cracked(CAN) DURING ROUTINE MAINTENANCE, HIGH OIL CONSUMPTION WAS NOTED ON THE RH ENGINE (CF34-3A1, S/N 807264, TSR 7858, CSR 6203). INITIAL INVESTIGATION INDICATED AN OIL LEAK ON THE ENGINE. THE ENGINE WAS CLEANED AND GROUND RUNS CARRIED OUT. A CRACK AT THE TOP WELDApr 29, 2011 · Cndair CL6002B19 · Turbine Engine Oil SystemSDR CA110511008Controller · failedAFTER TAKEOFF, SEVERAL CAUTIONS APPEARED: PITOT BASE HEAT, LT AOA HEAT, STATIC HEAT, LT PITOT HEAT AND SUBSEQUENTENT "MACH TRIM". AFTER COMPLETION OF THE QRH, AND NORMAL CHECKLIST, RETURNED TO DEPARTURE. AIR DATA SENSOR HEATER CONTROLLER NR 1 REPLACED IAW AMApr 26, 2011 · Cndair CL6002B19 · Pitot/Static Anti-Ice SystemSDR CA110623004Cabin Pressure · unknownDURING CLIMB THROUGH FL250, CREW FOUND THE CABIN ALTITUDE WAS CLIMBING. EMERGENCY DESCENT TO 10000 FTApr 5, 2011 · Cndair CL6002B19 · Cabin Pressure Control SystemSDR CA110407003Filter · clogged(CAN) A REJECTED TAKEOFF WAS PERFORMED AFTER THE FLIGHT CREW HAD RECEIVED A WING ANTI-ICE & RT WING ANTI-ICE CAUTION MSG. THE FLIGHT CREW TAXIED BACK TO GATE & THE ACFT WAS REMOVED FROM SERVICE. DURING TROUBLESHOOTING, BOTH WING ANTI-ICE MODULATING SHUTOFF Apr 4, 2011 · Cndair CL6002B19 · Air Intake Anti/De-Ice SystemSDR MASA2011040502328Engine · fireNUMBER 2 ENG FIRE. MX R2 ENGINE.Apr 2, 2011 · N77302 · Cndair CL6002B19 · Engine (Turbine/Turboprop)
Back to GE CF34-3A1