Pratt & Whitney Canada PW120A
Service difficulty reports · 2,399
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 = 'PW120A' 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.
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 = 'PW120A' ORDER BY difficulty_date DESC
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR CA190729013Pressure Switch · failed(CAN) #2 BLEED HOT ILLUMINATED DURING CRUISE. SYSTEM GOT TURNED OFF, AFTER THAT #1 SYSTEM FAILED. EMERGENCY DECENT WAS EXECUTED, PLANE DIVERTED TO YQT FOR MAINTENANCE. (TC# 20190729013)SDR CA190711001Valve · damaged(CAN) DURING CRUISE FLIGHT, #2 ENGINE WAS SHUTDOWN DUE TO HIGH ENGINE OIL TEMPS. THE OIL COOLER THERMO VALVE WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC# 20190711001)SDR CA190610009Outflow Valve · malfunctioned(CAN) CREW OBSERVED CABIN ALT FLUCTUATION (BOTH INCREASING AND DECREASING) WITH CAB RATE OF CLIMB 2000 FPM. THE AIRCRAFT DESCEND TO A/C ALT 7000 FT (WITH CAB ALT 6000 FT). AIR TURN BACK PERFORMED. CREW REPORTED EAR ACHE AND A KIND OF WHITE SMOKE MOMENTARILY. SDR CA190604014Eec · malfunctioned(CAN) AFTER DEPARTURE #2 ENGINE TORQUE ROLLED BACK 16 % TWO SEPARATE TIMES WITH NO ECU LIGHT. TORQUE INDICATION RETURNED TO NORMAL AFTER A FEW SECONDS. MOMENTARY DROP IN R/H PROP RPM ALSO OBSERVED. AIRCRAFT CONTINUED TO DESTINATION WITH NO FURTHER ISSUES. PERSDR CA190531011Hmu · failed(CAN) DURING CRUISE THE CREW REPORTED A #2 PROP OVER SPEED INDICATION AND SHUT DOWN THE ENGINE. THE CREW DECLARED AN EMERGENCY AND CONTINUED TO BASE, LANDING WITHOUT INCIDENT. MAINTENANCE CONDUCTED WIRING CHECKS BETWEEN THE HMU AND ECU AND HAVE CHANGED THE HMUSDR CA190521032Fitting · leaking(CAN) DURING POST FLIGHT INSPECTION, OIL WAS NOTED LEAKING FROM #1 ENGINE. MAINTENANCE FOUND THAT A FITTING WAS LOOSE ON THE ACCESSORY OIL PUMP DRIVE COVER. THE THREADS HAD PULLED OUT FROM THE COVER ALLOWING OIL TO LEAK OUT. (TC# 20190521032)SDR CA190516004Carbon Seal · cracked(CAN) CREW REPORTED OIL SMELL IN CABIN DURING FLIGHT WITH PASSENGERS ON BOARD. AIRCRAFT LANDED UNEVENTFULLY. THERE WAS NO REPORT OF CREW OR PASSENGER REQUIRING MEDICAL ATTENTION. DURING TROUBLESHOOTING, AGB BREATHER CARBON SEAL WAS FOUND CRACKED AND WILL BE RESDR CA190430007Feedback Unit · shorted(CAN) AFTER LANDING, THE FLIGHT CREW WAS UNABLE TO REPOSITION THE FLAPS FROM 30 DEGREES. ANY MOVEMENT OF THE FLAP HANDLE TO A DIFFERENT POSITION WOULD RESULT IN THE CIRCUIT BREAKER TRIPPING. IT WAS DISCOVERED THAT THE FLAP FEEDBACK UNIT HAD AN INTERNAL SHORT TSDR CA190422003Switch · failed(CAN) NR 1 ENGINE ECU MANUAL CAUTION ILLUMINATED AT 50FT AGL, TORQUE SPLIT IN CRUISE NOT WITHIN MEL CRITERIA, SOC ELECTED TO RETURN AC TO DEPARTURE AIRPORT. MAINTENANCE REPLACED 6121-S11 MICRO-SWITCH, C/O TEST IAW AMM 76-10-16. BETA BACKUP SWITCH 1&2 BACK TOSDR CA190417004Lead · broken(CAN) AIRCRAFT HAD EXPERIENCED A #2 DE-ICE FAULT IN FLIGHT. UPON INVESTIGATION FOUND THE #2 BLADE DE-ICE LEAD HAD BROKEN. THE LEAD THAT IS IN QUESTION IS PMA PART MANUFACTURED IN THE USA BY AEROCESS. THESE PROP DE-ICE LEADS HAVE BEEN IDENTIFIED BY OUR RELIABILSDR CA190403013Stator · damaged(CAN) ENGINE WAS RECEIVED FOR CONVERSION TO A PW121. DURING RECEIVING INSPECTION A METALLIC NOISE WAS HEARD WITHIN THE TURBOMACHINE AND THE ENGINE WAS PARTIALLY DISASSEMBLED IN ORDER TO INVESTIGATE.THE LP STATOR INNER BAFFLE WAS FOUND TO BE LIBERATED AND ABLE SDR CA190402006Control Panel · odor(CAN) ON INITIAL CLIMB OUT FLIGHT CREW REPORTED LIGHT ELECTRICAL BURN SMELL. MAINTENANCE IDENTIFIED THAT THE SMELL WAS COMING FROM #1 AUDIO CONTROL PANEL. PANEL REPLACED AND TESTED. AIRCRAFT RETURNED TO SERVICE. PN 5061-1-1, SN 560, AC HOURS: 67723 AC CYCLES:SDR CA190327001Gas Generator · damaged(CAN) ENGINE RECEIVED FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED A CRACKED GAS GENERATOR CASE WHICH WAS FOUND AFTER A HIGH INTER-TURBINE TEMPERATURE INDICATION. (TC# 20190327001)SDR CA190326008Impeller · damaged(CAN) DURING MAINTENANCE THE #2 ENGINE WAS DISCOVERED TO HAVE IMPELLER DAMAGE. AFTER A BOROSCOPE WAS CARRIED OUT FURTHER DAMAGE WAS FOUND ON THE DIFFUSER CHANNELS AND ENGINE CASING. AFTER CONSULTING WITH THE ENGINE MANUFACTURER, IT WAS DETERMINED THAT THE DAMASDR CA190301005Case · cracked(CAN) ENGINE WAS REMOVED DUE TO HIGHER THAN NORMAL ITT. AN APPROXIMATELY 4 INCH CRACK WAS FOUND ADJACENT TO THE NO. 1 FUEL NOZZLE IN THE GAS GENERATOR CASE.SDR CA180706015Control Unit · no test(CAN) AIRCRAFT TAXIED FOR DEPARTURE AND WAS HOLDING SHORT OF RUNWAY FOR TAKE OFF, FLIGHT CREW REPORTED TO MAINTENANCE CONTROL THAT THE AIRCRAFT WOULDN`T MOVE WHEN PARK BRAKE WAS RELEASED AND POWER APPLIED FROM A FULLY STOPPED POSITION. PARK BRAKE WAS RESET. SDR CA180723012Condenser · cracked(CAN) DURING FLIGHT, FLIGHT CREW REPORTED AN INTERMITTENT AIR COND PACK HOT AMBER CAUTION LIGHT. DURING TROUBLESHOOTING, THE CONDENSER MIXER WAS FOUND CRACKED AT THE HEAT EXCHANGER INLET PORT. THE CONDENSER MIXER WAS REPLACED AND THE SYSTEM TESTED SERVICEABLSDR CA180404019Oil Cooler · leaking(CAN) ON APPROACH THE NR 1 ENGINE OIL PRESSURE DROPPED TO APPROXIMATELY 40PSI WITH ASSOCIATED NR 1 ENGINE OIL PRESSURE WARNING LIGHT ILLUMINATED. WHILE TAXIING TO THE GATE THE OIL PRESSURE DROPPED TO ZERO AND FLUCTUATED. THE CREW THEN PERFORMED AN ENGINE SHUSDR CA180103007Pump · failed(CAN) SHORTLY AFTER TAKE-OFF THE NR 2 ENGINE DRIVEN HYDRAULIC PUMP FAILED. THE CREW TURNED BACK TO BASE AND LANDED WITHOUT INCIDENT. NO EMERGENCY WAS DECLARED. P/N: 570347 S/N: MX-494399CD TSN HOURS: 29470, CYCLES: 33246 TSR HOURS: 115, CYCLES: 98 A/C HOURSSDR HNAA2016102400333Rotor · seizedNR 2 ENGINE FAILS TO SPOOL DURING START CYCLE. REMOVED AND REPLACED THE NR 2 STARTER GEN IAW WORK CARD 24-30-02R. NO FIX. SLAVED NR 2 DC GCU. NO FIX. FOUND NR 2 HP NOT ABLE TO ROTATE.SDR HNAA2016061700186Tscu · malfunctionedDURING TAKEOFF ROLL AT 85 PERCENT TORQUE AUTO FX FAILED TO ARM, REJECTED T/O. LIGHT ILLUMINATED UPON REDUCED POWER. R & R NR 2 ENGINE TSCU IN REF TO 77-10-00 C/W CARDS 72-01-10X & 72-00-10Q. RAN ACFT, OPS CHECK GOOD.SDR HNAA2016062000191Unknown · malfunctionedDURING TAKEOFF ROLL, AUTO FX WOULD NOT ARM AUTOFEATHER SYSTEM. REPLACED RELAY 6121-K5 AS PRECAUTIONARY MEASURE, OPS CK GOOD AT THIS TIME, REF 61-26-00.SDR CA160304009Switch · failed(CAN) FLIGHT CREW REPORTED THAT, ON TAKEOFF AFTER GEAR UP SELECTION, THE NR 1 PROP CYCLED FROM 850 TO 1000 RPM WITH TORQUE FLUCTUATION FROM 40 TO 110 PERCENT. CHECKLIST FOLLOWED AND POWER REDUCED, PROP RPM STABILIZED AT 900. ACFT RETURNED TO AIRPORT FOR NORSDR CA160302014Transducer · failed(CAN) DURING CLIMB, BOTH CONTROL COLUMN STICK SHAKERS ACTIVATED. AIRSPEED INDICATIONS NORMAL. AN EMERGENCY WAS DECLARED AND THE FLIGHT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THE NR 2 STALL LIFT TRANSDUCER AT FAULT. THE TRANSDUCER HAS TSN 48222,SDR CA160224004Jackscrew · malfunctioned(CAN) FLIGHT CREW REPORTED FROZEN ELEVATOR TRIM IN DESCENT. AT 4,000 FT TRIM BEGAN TO MOVE AGAIN. ACFT LANDED WITH NO FURTHER FAULT. SYS INSPECTED WITH NO FAULTS FOUND. TRIM JACKS LUBRICATED. IT WAS NOTED THAT SINCE MFG REMOVED THE LOW UTILIZATION MAINTENANSDR CA160211006Brake · seized(CAN) THE CREW REPORTED SMOKE COMING FROM RT MAIN LANDING GEAR DURING TAXI IN AND INCREASED AT GATE. MAINTENANCE FOUND THE NR 4 BRAKE ASSEMBLY SEIZED AND LEAKING HYDRAULIC FLUID. ASSEMBLY REPLACED.SDR CA160129006Bearing · seized(CAN) FWD MLG DOOR ACTUATOR ROLLER BEARING FOUND DETERIORATED, SEIZED CAUSING GEAR DOOR MECHANISM TO JAM AND DRAG STRUT FAIRING TO CONTACT MLG DOOR HINGE. DAMAGE DETECTED ON FWD MLG DOOR ATTACH ROD. RT FWD MLG DOOR ACTUATOR MECHANISM REPLACED. RD 8-51-256 OPSDR HNAA2016012200016Wire · brokenAUTOFEATHER WILL NOT ARM. FOUND BROKEN WIRE AT NR 1 ENGINE POWER LEVER MICROSWITCH TERMINAL. RESOLDERED WIRE TERMINAL, PERFORMED OPS CHECKED. OPS CHECK GOOD. COMPLIED WITH ENGINE RUNS IAW SR MANUAL. OPS CHECKED GOOD.SDR CA160122003Pulley Bracket · cracked(CAN) DURING MAINTENANCE AND ADJUSTMENT OF THE ALTERNATE GEAR RELEASE SYS, THE PULLEY BRACKET IN THE LT NACELLE, FOR THE SYS CABLE, WAS FOUND CRACKED. PULLEY BRACKET REPLACED AND SYS TESTED SERVICEABLE. ACFT HRS: 60205, ACFT CYCLES: 61435.SDR CA160118017Servo · stuck(CAN) ROLL CONTROL SERVO STUCK IN, ON POSITION, IN-FLIGHT. THIS MADE ROLL CONTROL DIFFICULT. MAINTENANCE ACTIONS: AILERON SERVO DISABLED. CIRCUIT BREAKER PULLED. STANDBY ELEVATOR TRIM SYS, CONFIRMED OPERATIVE. BECAUSE THE SYSTEM WAS CONFIRMED OPERATIVE THE FSDR CA160112005B-Nut · loose(CAN) THE CREW EXPERIENCED A LOSS OF NR 2 HYDR, INFLIGHT, AN EMERGENCY WAS DECLARED AND AN ALTERNATE GEAR EXTENSION PERFORMED. MAINTENANCE DISCOVERED THE NR 2 EDP "B-NUT" PRESSURE LINE LOOSE. DURING THE SUBSEQUENT INSPECTION, THE SUCTION LINE AND RETURN LINSDR CA160111003Frame · corroded(CAN) DURING COMPLETION OF TASK 144-DH1, GVI OF BAGGAGE COMPARTMENT UNDERFLOOR, CORROSION FOUND ON THE AFT CARGO DOOR FRAME JUST ABOVE THE DOOR SILL AT STN X600. REPAIRED IAW REPAIR RD-53-14488.SDR HNAA2015123000377Selector Switch · inoperativeDURING AUTOFEATHER TEST, NR 2 PROP WILL NOT FEATHER. RPM DROPS FROM 650 TO 590. ALL OTHER PARAMETERS OK. R & R RELAYS 6121-K4, K2 AND K10. SLAVED IN NR 2 TSEU, NO FIX. ORIGINAL TSEU REINSTALLED. R & R NR 2 PCU IAW 61-10-10R. NO FIX. R & R AUTOFEATHER SELSDR CA151229001Turbine · damaged(CAN) DURING APPROACH THE ENGINE HAS AN IFSD UNDER UNKNOWN CIRCUMSTANCES. THE ACFT LANDED SAFELY AND POST FLIGHT BORESCOPE INSPECTION REVEALED HEAVY HOT SECTION DAMAGE. THE OPERATOR IS BEING ASSISTED BY THE SHOP THAT PERFORMED A HOT SECTION INSPECTION SOME 8SDR CA151210010Skin · cracked(CAN) FUSELAGE SKIN CRACK AND FRAME FLANGE CRACK AT NR 2 VHF ANTENNA BS 222.0 AND FS 253.40. UPON OPENING UP THE EXISTING STRUCTURE FOR INCORPORATION OF THE FIELD AVIATION EAST RDA O-RA14-057/D A FAIRLY SUBSTANTIAL CRACK WAS FOUND IN THE ACFT BELLY SKIN AND ASDR CA151123009Actuator · leaking(CAN) HYDRAULIC LEAK FOUND AT NOSE AREA OF ACFT. UPON INSPECTION IT WAS FOUND THAT THE NLG DOOR ACTUATOR ASSY WAS LEAKING. UPON FURTHER INVESTIGATION IT WAS FOUND THAT THE NLG DOOR ACTUATOR ASSY CYLINDER WAS CRACKED.SDR CA151120001Tscu · malfunctioned(CAN) DURING CLIMB OUT, NR 1 ENGINE TORQUE INDICATION WENT TO 165 PERCENT. POWER WAS REDUCED BUT TORQUE INDICATION REMAINED THE SAME, ALL OTHER ENGINE PARAMETERS APPEARED TO BE NORMAL AND NO ACFT YAW WAS NOTICED. FLIGHT CREW FOLLOWED THEIR QRH AND PERFORMED SDR CA160301007Indicator · malfunctioned(CAN) DURING CLIMB OUT, THE NR 1 ENGINE TORQUE INDICATION WENT TO 165%. THE POWER WAS REDUCED BUT THE TORQUE INDICATION REMAINED THE SAME. ALL OTHER ENGINE PARAMETERS APPEARED TO BE NORMAL AND NO AIRCRAFT YAW WAS NOTICED. THE FLIGHT CREW FOLLOWED THEIR QUICK RSDR CA151120007Hub · separated(CAN) NR 2 PROP ASSEMBLY REQUIRES REPLACEMENT DUE TO INTERNAL METAL DEBRIS AND DAMAGE FOUND. NR 2 PROP ASSY REPLACED IAW AMM 61-10-00 AND CHECKED SERVICEABLE. NR 2 PROP ASSY INSTALLATION AND CHECKED OK.SDR CA151112001Blade · cracked(CAN) MAINTENANCE FOUND A CRACK ON THE BACK OF THE RT PROPELLER NR 1 BLADE AT APPROXIMATELY STATION 45.00", MID WAY UP THE LENGTH OF THE BLADE. THE BLADE WAS REPLACED AND ACFT RETURNED TO SERVICE.SDR CA151112005Windshield · arced(CAN) DURING DESCENT THROUGH APPROXIMATELY 5000 FT ASL THERE WAS OBSERVED YELLOW ARCING AND FLAMES ON THE LOWER PORTION OF THE WINDOW. SHORTLY THEREAFTER THE LT FORWARD WINDOW OUTER LAYER FAILED. THE CREW IMMEDIATELY PUT ON PROTECTIVE EYE WEAR, SMOKE GOGGLESSDR CA151120008Smoke Detector · dirty(CAN) DURING CLIMB OUT, FLIGHT CREW OBSERVED THE SMOKE ANNUNCIATOR LIGHT ILLUMINATE SEVERAL TIMES. THEY ACTIONED THE QRH, DECLARED A PAN PAN IN THE INTEREST OF FLIGHT SAFETY, AND REQUESTED A RETURN. THE F/A CHECKED THE REAR BULKHEAD WHICH WAS NOT HOT, THERE WASDR CA151104004Generator · failed(CAN) AS ACFT LEVELED OFF AFTER DEPARTURE, THE FLIGHT CREW WITNESSED THE NR 2 DC GENERATOR HOT CAUTION LIGHT ILLUMINATE. THE FLIGHT CREW ACTIONED THE QRH AND TURNED THE GENERATOR OFF. HOWEVER, THE HOT CAUTION LIGHT REMAINED ILLUMINATED. THE ACFT RETURNED TO DSDR CA151105001Control Unit · malfunctioned(CAN) DURING TAKEOFF ROLL, THE NR 1 ENGINE ATTEMPTED TO AUTO FEATHER. TAKEOFF ABORTED. THE FLIGHT CREW DID AN AUTO FEATHER TEST AND NR 1 SEEMED TO WANT TO FEATHER IMMEDIATELY. MAINTENANCE ACTION: NR 2 TSCU WAS REPLACED.SDR CA160301006Propeller · malfunctioned(CAN) DURING TAKE-OFF ROLL THE NR 1 ENGINE ATTEMPTED TO AUTO FEATHER. THE TAKE-OFF WAS ABORTED. THE FLIGHT CREW DID AN AUTO FEATHER TEST AND THE NR 1 ENGINE SEEMED TO WANT TO FEATHER IMMEDIATELY. THE NR 2 TORQUE SIGNAL CONDITIONER UNIT WAS REPLACED AND THE AIRSDR CA151021010Wire · broken(CAN) SHORTLY AFTER TAKEOFF, FLIGHT CREW OBSERVED TORQUE FLUCTUATIONS ASSOCIATED WITH STRONG YAW INPUTS. THE ENGINE WAS SHUTDOWN AND AN EMERGENCY DECLARED. ACFT RETURNED AND LANDED WITHOUT FURTHER ISSUE. TROUBLESHOOTING REVEALED THE BETA LOCKOUT WAS ENGAGED SDR CA151015017Selector Panel · faulty(CAN) ENROUTE, CREW RECEIVED CABIN PRESSURE MASTER WARNING LIGHT, CREW ACTIONED CHECKLIST, CABIN PRESSURE WAS ABOVE 10,000 FT, CREW DESCENDED TO 14,000 FT AND ELECTED TO RETURN TO THE AIRPORT. AT 5,000 FT CREW DUMPED THE CABIN. NO ADVERSE PASSENGER REACTION. SDR CA150927009Inverter · overheated(CAN) PRIMARY INVERTER CAUTION LIGHT WITH ASSOCIATED ODOR OF SMOKE DURING DECENT, INVERTER SELECTED OFF AND ODOR DISSIPATED. INVERTER REPLACED. FULL PN DH1030-24-600-CS2B.SDR CA150924011Capacitor · burned(CAN) WHEN BATTERIES AND EXTERNAL POWER APPLIED, SMOKE WAS NOTICED COMING FROM LEFT DC CIRCUIT BREAKER PANEL. CREW REMOVED POWER ACFT. MAINTENANCE FOUND PRIMARY INVERTER FRIED AND REQUIRES REPLACEMENT. ONCE THE INVERTER, PN DH1030-24-600CIIB, WAS IN THE REPASDR CA150925015Anti-Skid Valve · cracked(CAN) HYDRAULIC LEAKAGE IN NACELLE NR 2 DISCOVERED BY CREW ON POST FLIGHT INSPECTION. TECHNICIANS WHO CAME TO THE AIRCRAFT COULD QUICKLY ASCERTAIN THAT "DUAL ANTI SKID VALVE NR 2" WERE CRACKED. NR 2 ANTI SKID VALVE REPLACED AND AIRCRAFT RELEASED TO SERVICE.
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