# Service difficulty reports: Pratt & Whitney Canada PW120A

A list on [Pratt & Whitney Canada PW120A](https://openairdocs.org/engine/pratt-whitney-canada-pw120a.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 48 · 2,399 reports

- [SDR CA190729013](https://openairdocs.org/sdr/CA190729013.md): Pressure Switch · failed · Jul 17, 2019 · Dhav DHC8102 · Bleed Air Indicating System
  > (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 CA190711001](https://openairdocs.org/sdr/CA190711001.md): Valve · damaged · Jul 8, 2019 · Dhav DHC8102 · Engine Oil Cooler
  > (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 CA190610009](https://openairdocs.org/sdr/CA190610009.md): Outflow Valve · malfunctioned · Jun 3, 2019 · Dhav DHC8201 · Pressure Regulator/Outflow Valve
  > (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 CA190604014](https://openairdocs.org/sdr/CA190604014.md): Eec · malfunctioned · Jun 2, 2019 · Dhav DHC8102 · Fuel Controlling System
  > (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. PER
- [SDR CA190531011](https://openairdocs.org/sdr/CA190531011.md): Hmu · failed · May 30, 2019 · Dhav DHC8102 · Fuel Controlling System
  > (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 HMU
- [SDR CA190521032](https://openairdocs.org/sdr/CA190521032.md): Fitting · leaking · May 18, 2019 · Dhav DHC8102 · Turbine Engine Oil System
  > (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 CA190516004](https://openairdocs.org/sdr/CA190516004.md): Carbon Seal · cracked · May 7, 2019 · Aerosp ATR42300 · Turbine Engine Accessory Drive
  > (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 RE
- [SDR CA190430007](https://openairdocs.org/sdr/CA190430007.md): Feedback Unit · shorted · Apr 28, 2019 · Aerosp ATR42300 · Trailing Edge Flap Control System
  > (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 T
- [SDR CA190422003](https://openairdocs.org/sdr/CA190422003.md): Switch · failed · Apr 20, 2019 · Dhav DHC8102 · Power Lever
  > (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 TO
- [SDR CA190417004](https://openairdocs.org/sdr/CA190417004.md): Lead · broken · Apr 14, 2019 · Aerosp ATR42300 · Propeller/Propulsor System Wiring
  > (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 RELIABIL
- [SDR CA190403013](https://openairdocs.org/sdr/CA190403013.md): Stator · damaged · Apr 2, 2019 · Turbine Section
  > (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 CA190402006](https://openairdocs.org/sdr/CA190402006.md): Control Panel · odor · Mar 31, 2019 · Dhav DHC8102 · Audio Integrating System
  > (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 CA190327001](https://openairdocs.org/sdr/CA190327001.md): Gas Generator · damaged · Mar 26, 2019 · Turbine Engine Combustion Section
  > (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 CA190326008](https://openairdocs.org/sdr/CA190326008.md): Impeller · damaged · Mar 24, 2019 · Dhav DHC8102 · Turbine Engine Compressor Section
  > (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 DAMA
- [SDR CA190301005](https://openairdocs.org/sdr/CA190301005.md): Case · cracked · Feb 28, 2019 · Dhav DHC8102 · Turbine Engine Combustion Section
  > (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 CA180706015](https://openairdocs.org/sdr/CA180706015.md): Control Unit · no test · Jul 4, 2018 · Dhav DHC8102 · Brake Anti-Skid Section
  > (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 CA180723012](https://openairdocs.org/sdr/CA180723012.md): Condenser · cracked · Jun 18, 2018 · Dhav DHC8102 · Air Distribution System
  > (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 SERVICEABL
- [SDR CA180404019](https://openairdocs.org/sdr/CA180404019.md): Oil Cooler · leaking · Apr 1, 2018 · Dhav DHC8102 · Engine Oil Cooler
  > (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 SHU
- [SDR CA180103007](https://openairdocs.org/sdr/CA180103007.md): Pump · failed · Dec 30, 2017 · Dhav DHC8102 · Hydraulic Pump (Electric/Engine), Main
  > (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 HOURS
- [SDR HNAA2016102400333](https://openairdocs.org/sdr/HNAA2016102400333.md): Rotor · seized · Oct 24, 2016 · N936HA · Dhav DHC8102 · Turbine Section
  > NR 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 HNAA2016061700186](https://openairdocs.org/sdr/HNAA2016061700186.md): Tscu · malfunctioned · Jun 16, 2016 · N938HA · Dhav DHC8102 · Engine BMEP/Torque Indicating
  > DURING 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 HNAA2016062000191](https://openairdocs.org/sdr/HNAA2016062000191.md): Unknown · malfunctioned · Jun 15, 2016 · N938HA · Dhav DHC8102 · Propeller Feathering/Reversing
  > DURING 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 CA160304009](https://openairdocs.org/sdr/CA160304009.md): Switch · failed · Mar 3, 2016 · Dhav DHC8102 · Power Lever
  > (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 NOR
- [SDR CA160302014](https://openairdocs.org/sdr/CA160302014.md): Transducer · failed · Feb 28, 2016 · Dhav DHC8102 · Stall Warning System
  > (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 CA160224004](https://openairdocs.org/sdr/CA160224004.md): Jackscrew · malfunctioned · Feb 18, 2016 · Dhav DHC8102 · Elevator Tab Control System
  > (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 MAINTENAN
- [SDR CA160211006](https://openairdocs.org/sdr/CA160211006.md): Brake · seized · Feb 9, 2016 · Dhav DHC8102 · Brake
  > (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 CA160129006](https://openairdocs.org/sdr/CA160129006.md): Bearing · seized · Jan 25, 2016 · Dhav DHC8102 · Landing Gear Door Actuator
  > (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 OP
- [SDR HNAA2016012200016](https://openairdocs.org/sdr/HNAA2016012200016.md): Wire · broken · Jan 22, 2016 · N938HA · Dhav DHC8102 · Engine Control System Wiring
  > AUTOFEATHER 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 CA160122003](https://openairdocs.org/sdr/CA160122003.md): Pulley Bracket · cracked · Jan 14, 2016 · Dhav DHC8102 · Landing Gear Retraction/Extension System
  > (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 CA160118017](https://openairdocs.org/sdr/CA160118017.md): Servo · stuck · Jan 13, 2016 · Dhav DHC8102 · Aileron Tab Control System
  > (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 F
- [SDR CA160112005](https://openairdocs.org/sdr/CA160112005.md): B-Nut · loose · Jan 10, 2016 · Dhav DHC8102 · Hydraulic System, Main
  > (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 LIN
- [SDR CA160111003](https://openairdocs.org/sdr/CA160111003.md): Frame · corroded · Jan 8, 2016 · Dhav DHC8102 · Fuselage Main, Frame
  > (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 HNAA2015123000377](https://openairdocs.org/sdr/HNAA2015123000377.md): Selector Switch · inoperative · Dec 30, 2015 · N930HA · Dhav DHC8102 · Propeller Feathering/Reversing
  > DURING 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 SEL
- [SDR CA151229001](https://openairdocs.org/sdr/CA151229001.md): Turbine · damaged · Dec 18, 2015 · Turbine Section
  > (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 8
- [SDR CA151210010](https://openairdocs.org/sdr/CA151210010.md): Skin · cracked · Dec 1, 2015 · Dhav DHC8102 · Fuselage Main, Plate/Skin
  > (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 A
- [SDR CA151123009](https://openairdocs.org/sdr/CA151123009.md): Actuator · leaking · Nov 22, 2015 · Dhav DHC8102 · Landing Gear Door Actuator
  > (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 CA151120001](https://openairdocs.org/sdr/CA151120001.md): Tscu · malfunctioned · Nov 20, 2015 · Dhav DHC8102 · Engine BMEP/Torque Indicating
  > (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 CA160301007](https://openairdocs.org/sdr/CA160301007.md): Indicator · malfunctioned · Nov 20, 2015 · Dhav DHC8102 · Engine BMEP/Torque Indicating
  > (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 R
- [SDR CA151120007](https://openairdocs.org/sdr/CA151120007.md): Hub · separated · Nov 18, 2015 · Dhav DHC8102 · Propeller Hub Section
  > (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 CA151112001](https://openairdocs.org/sdr/CA151112001.md): Blade · cracked · Nov 11, 2015 · Dhav DHC8102 · Propeller Blade Section
  > (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 CA151112005](https://openairdocs.org/sdr/CA151112005.md): Windshield · arced · Nov 6, 2015 · Dhav DHC8102 · Flight Compartment Windows
  > (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 GOGGLES
- [SDR CA151120008](https://openairdocs.org/sdr/CA151120008.md): Smoke Detector · dirty · Nov 5, 2015 · Dhav DHC8102 · Smoke Detection
  > (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 WA
- [SDR CA151104004](https://openairdocs.org/sdr/CA151104004.md): Generator · failed · Nov 1, 2015 · Dhav DHC8102 · DC Generator-Alternator
  > (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 D
- [SDR CA151105001](https://openairdocs.org/sdr/CA151105001.md): Control Unit · malfunctioned · Oct 31, 2015 · Dhav DHC8102 · Propeller Controlling System
  > (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 CA160301006](https://openairdocs.org/sdr/CA160301006.md): Propeller · malfunctioned · Oct 31, 2015 · Dhav DHC8102 · Propeller Feathering/Reversing
  > (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 AIR
- [SDR CA151021010](https://openairdocs.org/sdr/CA151021010.md): Wire · broken · Oct 20, 2015 · Dhav DHC8102 · Engine Control System Wiring
  > (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 CA151015017](https://openairdocs.org/sdr/CA151015017.md): Selector Panel · faulty · Oct 13, 2015 · Dhav DHC8102 · Cabin Pressure Control System
  > (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 CA150927009](https://openairdocs.org/sdr/CA150927009.md): Inverter · overheated · Sep 25, 2015 · Dhav DHC8102 · AC Inverter
  > (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 CA150924011](https://openairdocs.org/sdr/CA150924011.md): Capacitor · burned · Sep 21, 2015 · Dhav DHC8102 · AC Inverter
  > (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 REPA
- [SDR CA150925015](https://openairdocs.org/sdr/CA150925015.md): Anti-Skid Valve · cracked · Sep 16, 2015 · Dhav DHC8* · Brake Anti-Skid Section
  > (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.

Next page: https://openairdocs.org/engine/pratt-whitney-canada-pw120a/reports.md?page=2

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
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
```

This list as a web page: https://openairdocs.org/engine/pratt-whitney-canada-pw120a/reports

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