# Service difficulty reports: U/A Canada PT6A-50

A list on [U/A Canada PT6A-50](https://openairdocs.org/engine/u-a-canada-pt6a-50.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 5 · 225 reports

- [SDR QMLA2026101320078](https://openairdocs.org/sdr/QMLA2026101320078.md): Synchrophaser · out of adjust · Oct 12, 2026 · N912SM · Beech B200GT · Engine (Reciprocating)
  > LEFT PROP LEVER ACTING LIKE IT WAS HOOKED UP BACKWARDS. PUSHING THE LEVER FORWARD INCREASED RPM, AND VICE VERSA. ADJUSTED LT ENGINE PROPELLER SYNCHROPHASER MAGNETIC PICKUPS IAW KING AIR B200GT AMM 61-23-01. PERFORMED REQUIRED FUNCTIONAL GROUND CHECKS. NO FAULT
- [SDR 2026FA0000537](https://openairdocs.org/sdr/2026FA0000537.md): Autothrottle Sys · abnormal · Jun 23, 2026 · Beech B200GT · Auto Throttle System
  > PILOTS HAVE REPORTED MULTIPLE INSTANCES OF AUTOTHROTTLE INDUCED WARNING/RED TORQUE INDICATIONS OCCURRING DURING TAKEOFF, GO-AROUND, AND CLIMB PHASES OF FLIGHT ON SIX DIFFERENT AIRCRAFT (S/N BY-472 AND UP). THREE INSTANCES WERE SEVERE ENOUGH TO ACTIVATE THE MAS
- [SDR 2025F00230](https://openairdocs.org/sdr/2025F00230.md): Brake · no discrepancy · Sep 24, 2025 · N680TW · Beech B200GT · Landing Gear Brake System
  > WHILE TAXIING OUT FOR AN AIR AMBULANCE FLIGHT, THE MED TEAM THOUGHT THEY OBSERVED SMOKE FROM THE LEFT MLG AREA. THE FLIGHT CREW RETURNED TO THE BLOCKS AND HAD MAINTENANCE INSPECT THE LEFT MAIN LANDING GEAR, WHEELS AND BRAKES. NO DEFECTS WERE FOUND. THE CREW AN
- [SDR 2023F00320](https://openairdocs.org/sdr/2023F00320.md): Hydraulic Line · ruptured · Oct 31, 2023 · N793DC · Beech B200 · Hydraulic System, Main
  > WHILE ON APPROACH INTO BFI FROM BIL, THE LANDING GEAR EXTENDED UN-COMMANDED, THE LANDING GEAR HANDLE LIGHT (IN-TRANSIT LIGHT) ILLUMINATED, THE "HYD LOW" ANNUNCIATOR LIGHT ILLUMINATED AND THE LANDING GEAR CIRCUIT BREAKER POPPED. THE THREE GREEN "GEAR DOWN AND L
- [SDR CA190621012](https://openairdocs.org/sdr/CA190621012.md): Buss · damaged · Jun 15, 2019 · Dhav DHC7103 · AC Power Distribution System
  > (CAN) DURING CRUISE, LEFT AC BUS CAUTION LIGHT ILLUMINATED. CAPTAIN ELECTED TO RETURN TO DESTINATION FOR TROUBLESHOOTING. MAINTENANCE FOUND THE LEFT AC BUS CONTACTOR WAS STICKING INTERMITTENTLY. THE CONTACTOR WAS REPLACED AND AIRCRAFT RELEASED BACK TO SERVIC
- [SDR CA190516015](https://openairdocs.org/sdr/CA190516015.md): Planetary Gear · failed · May 8, 2019 · Turbine Engine Reduction Gear
  > (CAN) ENGINE SENT TO STANDARDAERO AFTER THE OPERATOR REPORTED AN IN-FLIGHT SHUT DOWN WITH METAL IN OIL. THIS REPORT IS ISSUED TO DISCUSS THE INVESTIGATION AND TEARDOWN FINDINGS. IN ADDITION THE CUSTOMER ELECTED TO OVERHAUL THE ENGINE DURING THIS SHOP VISIT. S
- [SDR CA190211014](https://openairdocs.org/sdr/CA190211014.md): Circuit Board · damaged · Feb 7, 2019 · Engine Bleed Air System Wiring
  > (CAN) L/R BLEED AIR FAIL LIGHTS ON AFTER START. WHEN SWITCH`S (BLEED AIR) WERE CYCLED ON/OFF, L/H AND R/H BLEED AIR CONTROL AND RUDDER BOOST CIRCUIT BREAKERS TRIPPED. NOTE ON DEFECT: ELECTRICAL BURNING SMELL IN CABIN AFTER CIRCUIT BREAKERS POPPED. A118 RELAY P
- [SDR CA180808026](https://openairdocs.org/sdr/CA180808026.md): Compressor · leaking · Jul 29, 2018 · Beech B200GT · Cabin Compressor System
  > (CAN) AIR CONDITIONING COMPRESSOR WEEPING OIL FROM AFT SEAL. ADDITIONAL AIRCRAFT IN THE COMPANY FLEET HAVE ENCOUNTERED THIS SAME PART NUMBER OF COMPRESSOR TO HAVE FAILED. THE SYSTEM WAS DEFERRED IN ACCORDANCE WITH COMPANY PROCEDURES FOR PARTS ON ORDER. (TC#
- [SDR CA180808021](https://openairdocs.org/sdr/CA180808021.md): Display · inoperative · Jul 25, 2018 · Beech B200GT · Flight Management Computing Hardware System
  > (CAN) ROCKWELL COLLINS PROLINE FUSION EQUIPPED AIRCRAFT, ADAPTIVE FLIGHT DISPLAY AFD-3700. DEFECT REPORTED AS CHECK MAINTENANCE CAS MESSAGE GNSS-1 FAILURE FLAG CAME ON. TROUBLESHOOTING INCLUDED REMOVAL AND REPLACEMENT OF AFD WITH ORIGINAL UNIT (NOT EXCHANGED
- [SDR CA180808022](https://openairdocs.org/sdr/CA180808022.md): Display · inoperative · Jul 19, 2018 · Beech B200CGT · Flight Management Computing Hardware System
  > (CAN) ADAPTIVE FLIGHT DISPLAY AFD-3700. DEFECT REPORTED AS CHECK MAINTENANCE CAS MESSAGE AND FMS 2 FAILURE FLAG CAME ON. TROUBLESHOOTING FAULT CODES 000-0632:AC1, 000-0468:AC1, 000-0336AC1, 000-373:AC1, 000-0590:AC1, 000-2027:AC1, 000-1059:AC1, 000-1060:AC1,
- [SDR CA160203019](https://openairdocs.org/sdr/CA160203019.md): Heater · burned · Feb 2, 2016 · Dhav DHC7* · Propeller/Rotor Anti-Ice/De-Ice System
  > (CAN) MAINTENANCE DISCOVERED A BURN HOLE THROUGH THE PROPELLER BLADE DE-ICE ELEMENT ON THE NR 4 PROPELLER, NR 3 BLADE. MAINTENANCE REPLACED THE PROPELLER BLADE AND CHECKED THE SYSTEM SERVICEABLE.
- [SDR CA160108007](https://openairdocs.org/sdr/CA160108007.md): Line · ruptured · Jan 4, 2016 · Dhav DHC7103 · Hydraulic System, Main
  > (CAN) ON APPROACH, WHEN FLAP 25 WAS SELECTED, HAD A MASTER CAUTION AND NOTICED, HYDRAULIC PUMPS NR 1 AND NR 2 HAD FAILED AND HYDRAULIC SYS PRESSURE ON NR 1 WAS LOST. A GO-AROUND WAS THEN CONDUCTED AND RETURNED TO DEPARTURE. LANDED AND TAXIED IN WITHOUT INCID
- [SDR CA151009001](https://openairdocs.org/sdr/CA151009001.md): Indicator · malfunctioned · Oct 8, 2015 · Dhav DHC7102 · Engine Temperature Indicating System
  > (CAN) DURING CRUISE THE DECIMAL PART OF T5 GAUGE OF ENGINE 2 STOPPED GIVING INFORMATION. AFTER RECYCLING THE BREAKER THE CREW NOTICED THAT EVEN WITH BREAKER PULLED THE GAUGE WAS STILL POWERED. SHORTLY AFTER STARTING DESCENT, THE T5 GAUGE OF ENGINE 2 STOPPED G
- [SDR CA150714007](https://openairdocs.org/sdr/CA150714007.md): Sleeve · inoperative · Jul 14, 2015 · Engine (Turbine/Turboprop)
  > (CAN) ENGINE WAS SENT FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED THAT THE REVERSE ARM AND THE BETA SLEEVE WILL NOT MOVE. DUE TO THE LOW TIME REMAINING UNTIL O/H, THE OPERATOR ELECTED TO O/H THE ENGINE. THIS REPORT IS ISSUED TO DISCUSS THE INVEST
- [SDR CA150701009](https://openairdocs.org/sdr/CA150701009.md): Garlock Seal · damaged · Jun 4, 2015 · Dhav DHC7102 · Turbine Engine Oil System
  > (CAN) EN-ROUTE AT 15,000 FEET WHEN THE CREW RECEIVED A LOW OIL PRESS INDICATION FOR ONE OF THE LT ENGS. PT6A, & SHUT THE ENG DOWN AS A PRECAUTION. THE ACFT DIVERTED FOR A SAFE LANDING. IT WAS REPORTED THAT MX IDENTIFIED THE GARLOCK OIL SEAL ON THE HYD PUMP W
- [SDR CA150515011](https://openairdocs.org/sdr/CA150515011.md): Pump · failed · May 13, 2015 · Dhav DHC7102 · Hydraulic Pump (Electric/Engine), Main
  > (CAN) THE AIRCRAFT WAS ON A CREW CHANGE FLIGHT FOR A CUSTOMER, UPON START UP FOR DEPARTURE, THE FLIGHT CREW SAW THE HYDRAULIC QUANTITY FALL TO 0. THEY DISEMBARKED THEIR PASSENGERS AND CALLED MAINTENANCE. MAINTENANCE ARRIVED AND FOUND THAT THE NR 3 PUMP, SN 16
- [SDR CA150422004](https://openairdocs.org/sdr/CA150422004.md): Connector · broken · Apr 19, 2015 · Dhav DHC7103 · Landing Gear System Wiring
  > (CAN) ON ARRIVAL AT DESTINATION ON FINAL APPROACH, CREW WERE UNABLE TO LOWER THE GEAR USING NORMAL PROCEDURE. ACFT DID NOT LAND BUT RETURNED & WENT INTO HOLD POSITION & CARRIED OUT A SUCCESSFUL EMER GEAR LOWERING PROCEDURE. ACFT THEN LANDED UNEVENTFULLY. FA
- [SDR CA150318015](https://openairdocs.org/sdr/CA150318015.md): Spoiler · separated · Mar 16, 2015 · Dhav DHC71 · Drag Control System
  > (CAN) DURING TOWING OPS MAINTENANCE DISCOVERED THE RT ROLL SPOILER ASSY SEPARATED FROM THE ACFT. THE ROLL SPOILER IS BELIEVED TO HAVE SEPARATED DURING THE PREVIOUS FLIGHT. FLIGHT CREW REPORTED NO CHANGE TO THE FLIGHT CONTROL CHARACTERISTICS AND NO INDICATION
- [SDR CA141209005](https://openairdocs.org/sdr/CA141209005.md): Fuel Control · failed · Dec 4, 2014 · Dhav DHC7102 · Fuel Control/Turbine Engines
  > (CAN) WHILE IN THE DESCENT, THE POWER LEVER WAS REDUCED AND THE NUMBER 1 ENGINE TORQUE REMAINED AT CRUISE POWER SETTING OF 3800 FT-LBS. THE CREW VERIFIED THAT THE ENGINE AND GAUGES WERE RESPONSIVE ABOVE 3800 FT-LBS TORQUE BUT WOULD NOT REDUCE. A DIVERSION WAS
- [SDR CA150113007](https://openairdocs.org/sdr/CA150113007.md): Fcu · faulted · Dec 4, 2014 · Dhav DHC7102 · Fuel Control/Turbine Engines
  > (CAN) WHEN THE CREW REDUCED ENGINE POWER FOR THE DESCENT, THE LT ENGINE REMAINED AT CRUISE POWER OF 3800 FT-LBS. THE CREW VERIFIED THE ENGINE WAS RESPONSIVE ABOVE 3800 FT-LBS BUT WOULD NOT REDUCE BELOW, THEN THE PILOT REQUESTED TO RETURN TO THE AIRPORT. WHEN
- [SDR CA141126003](https://openairdocs.org/sdr/CA141126003.md): Strap · corroded · Nov 25, 2014 · Dhav DHC7102 · Nacelle/Pylon, Main Frame
  > (CAN) FOLLOWING REMOVAL OF THE FOUR (4) ENGINE NACELLE INLET DEICE BOOTS, MISSING AND CORRODED RIVET HEADS WERE DISCOVERED ON THE FIBERGLASS INLET LIPS. FURTHER CORROSION WAS FOUND ON THE FOUR (4) ENGINE NACELLE STRAPS BENEATH THE FIBERGLASS INLET LIPS. MAI
- [SDR CA141024001](https://openairdocs.org/sdr/CA141024001.md): Engine · power loss · Oct 1, 2014 · Beech A36 · Engine (Turbine/Turboprop)
  > (CAN) DURING TAKEOFF CLIMB, AT AROUND 9000 FT, ENGINE ROLLED BACK AND ALL PARAMETERS WENT DOWN. CREW ELECTED TO SHUTDOWN THE AFFECTED ENGINE AND PERFORMED AN UNEVENTFUL LANDING WITH THE REMAINING ENGINES.
- [SDR CA140906001](https://openairdocs.org/sdr/CA140906001.md): Seal · cracked · Sep 5, 2014 · Dhav DHC8103 · Turbine Engine Oil System
  > (CAN) AFTER ABNORMAL OIL CONSUMPTION REPORTED TO MAINTENANCE ON THE NR 2 ENGINE, THE REPLACEMENT OF THE HYDRAULIC PUMP GARLOC SEAL, REPLACEMENT OF THE OIL TO FUEL HEATER, REPLACEMENT OF THE OIL FILTER HOUSING/RELIEF VALVE, WAS CONDUCTED OVER A SERIES OF FLIGHT
- [SDR CA140713001](https://openairdocs.org/sdr/CA140713001.md): Vortex Gen · missing · Jul 13, 2014 · Dhav DHC7103 · Wing Miscellaneous Structure
  > (CAN) ON A PRE-FLIGHT 4 VORTEX GENERATORS WERE FOUND MISSING ON THE WING TOP. THE CREW REVIEWED THE CDL AND THE AIRCRAFT COULD OPERATE WITH NO PERFORMANCE PENALTY. MAINTENANCE WAS MADE AWARE AND GENERATED A WORK CARD FOR WHEN IT RETURNS TO REPLACE THE UNITS MI
- [SDR CA140701014](https://openairdocs.org/sdr/CA140701014.md): Engine · malfunctioned · Jun 26, 2014 · Beech B200 · Engine (Turbine/Turboprop)
  > (CAN) WHEN APPROACHING AIRPORT, THE PILOT HEARD A LOUD BANG ON LT ENGINE, ASSOCIATED WITH ACFT TENDENCY TO THE LT. LEFT ENGINE LOST POWER AND ITT INCREASED. THE PILOT ELECTED TO SHUTDOWN ENGINE AND PERFORM A SINGLE ENGINE LANDING. TROUBLESHOOTING ONGOING.
- [SDR CA140529007](https://openairdocs.org/sdr/CA140529007.md): Garlock Seal · failed · May 27, 2014 · Dhav DHC7103 · Hydraulic Pump (Electric/Engine), Main
  > (CAN) SHORTLY AFTER LEVELING OFF AT FL170 NR 1 ENGINE OIL PRESSURE WAS OBSERVED FLUCTUATING, CAUTION LIGHT ILLUMINATED AND THE ENGINE WAS SHUTDOWN. ENGINE HYDRAULIC PUMP GARLOC SEAL REPLACED AND ACFT WAS RETURNED TO SERVICE.
- [SDR CA140402004](https://openairdocs.org/sdr/CA140402004.md): Arm · cracked · Mar 24, 2014 · Beech B200 · Power Lever
  > (CAN) WHEN DISASSEMBLING THE RT ENGINE POWER LEVER ASSY FOR FRICTION BRAKE REPAIR A CRACK WAS OBSERVED IN THE ARM ASSEMBLY BUSHING, AROUND WHICH THE POWER LEVER AND THE FRICTION BRAKE PIVOT.
- [SDR CA131218027](https://openairdocs.org/sdr/CA131218027.md): Switch · failed · Dec 16, 2013 · Dhav DHC7103 · Nose/Tail Landing Gear
  > (CAN) THERE HAVE BEEN 4 OCCURRENCES, THE 4TH WAS A TEST FLIGHT, WHERE THE ACFT TOOK OFF AND THE LANDING GEAR WOULD NOT RETRACT. THE WEIGHT ON WHEELS SWITCHES WERE CLEANED, THE CABIN SAFETY VALVES WOULD NOT CLOSE DUE TO A FAULT IN THE WEIGHT ON WHEELS SYSTEM,
- [SDR CA131217009](https://openairdocs.org/sdr/CA131217009.md): Windscreen · arced · Dec 15, 2013 · Dhav DHC7102 · Flight Compartment Windows
  > (CAN) THE LT WINDSCREEN BEGAN ARCHING JUST AFTER TAKEOFF, THE WINDSHIELD HEAT WAS TURNED OFF AND THE ACFT RETURNED TO BASE, DURING THE RETURN TO DEPARTURE THE WINDSCREENS ICED UP REDUCING THE FLIGHT CREWS VISIBILITY. CADORS, 2013C5268 REFERENCES THIS INCIDENT
- [SDR CA131218012](https://openairdocs.org/sdr/CA131218012.md): Gcu · failed · Nov 19, 2013 · Dhav DHC7102 · AC Generator-Alternator
  > (CAN) RETURNED DUE TO AN ELECTRICAL PROBLEM (RT DC BUSS FAULT). ENGINE 1 THRU 4 GROUND RUN. DC SYSTEM BROUGHT ONLINE. NR 4 DC GEN OPENS DC BUS TIE AND AFTER A SHORT DELAY THERE WAS A RIGHT DC BUS FAULT. REPLACED NR 4 DC GCU. SYSTEM FUNCTION CHECKED, NO FAU
- [SDR CA131030005](https://openairdocs.org/sdr/CA131030005.md): Actuator · failed · Oct 23, 2013 · Dhav DHC7103 · Landing Gear Retraction/Extension System
  > (CAN) AFTER O/H, MLG ACTUATOR WAS INSTALLED AND WHEN JACKED, FUNCTIONED ON RETRACTION, BUT FAILED ON EXTENSION DURING GEAR SWING.
- [SDR CA130918010](https://openairdocs.org/sdr/CA130918010.md): Engine · surges · Sep 13, 2013 · Dhav DHC7103 · Engine (Turbine/Turboprop)
  > (CAN) ON CLIMB THROUGH 15 000 FT NR 4 ENGINE BEGAN TO SURGE WITH ASSOCIATED FLUCTUATIONS IN TORQUE, ITT AND FUEL FLOW. WHEN THE FLIGHT CREW CLOSED THE NR 4 AIRFRAME BLEED VALVE AND REDUCED POWER THE ENGINE STABILIZED. NO FURTHER ISSUES WERE NOTED FOR THE RES
- [SDR CA130918008](https://openairdocs.org/sdr/CA130918008.md): Acm · failed · Sep 9, 2013 · Dhav DHC7103 · Cabin Cooling System
  > (CAN) SHORTLY AFTER TAKEOFF, F/A CALLED COCKPIT, STATING THERE WAS SMOKE IN THE CABIN. CREW RETURNED TO AIRPORT AND ON FINAL APPROACH, SMOKE CLEARED. FLIGHT CREW REPORTED THERE WAS A SMELL LIKE ENGINE OIL. MAINTENANCE CARRIED OUT TROUBLESHOOTING AND FOUND OI
- [SDR CA130625001](https://openairdocs.org/sdr/CA130625001.md): Engine · unknown · Jun 24, 2013 · Engine (Turbine/Turboprop)
  > (CAN) ENGINE WAS SENT FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED POOR PERFORMANCE. THE OPERATOR REPORTED THAT THE ENGINE STARTED HOTTER THAN NORMAL AND WAS SURGING.
- [SDR CA130620011](https://openairdocs.org/sdr/CA130620011.md): Oil System · leaking · Jun 18, 2013 · Dhav DHC7103 · Turbine Engine Oil System
  > (CAN) ON START OF NR 4 ENGINE AT CDK2, ENGINE OIL WAS OBSERVED EXITING FROM THE ENGINE BREATHER OVERBOARD VENT, COMPRESSOR DRAIN AND GAS GENERATOR DRAIN. THE START WAS ABORTED AND MAINTENANCE WAS CONTACTED. ON INSPECTION THE ENGINE WAS DETERMINED TO BE UNSER
- [SDR CA130607015](https://openairdocs.org/sdr/CA130607015.md): Actuator · failed · Jun 4, 2013 · Dhav DHC7103 · Trailing Edge Flap Actuator
  > (CAN) ON APPROACH THE T/E FLAPS WOULD NOT EXTEND WHEN SELECTED. ON INSPECTION MAINTENANCE PERSONNEL FOUND THE FLAP BALLSCREW ACTUATOR RT MID POSITION DIFFICULT TO ROTATE, ADEQUATE LUBRICATION WAS PRESENT. THE ADDED TORQUE REQUIRED TO ROTATE THE SCREWJACK CAU
- [SDR CA130531014](https://openairdocs.org/sdr/CA130531014.md): Starter Gen · malfunctioned · May 31, 2013 · Dhav DHC7103 · Starter-Generator
  > (CAN) WHEN REMOVING THE STARTER/GENERATOR DURING A SCHEDULED ENGINE CHANGE THE GENERATOR DRIVESHAFT STAYED IN THE ACCESSORY GEARBOX. ON INSPECTION IT WAS NOTED THE RETAINING NUT FOR THE DRIVESHAFT HAD BACKED OFF AND PASSED THROUGH THE COOLING FAN WHILE THE STA
- [SDR CA130430009](https://openairdocs.org/sdr/CA130430009.md): Engine · power loss · Apr 22, 2013 · Beech B200 · Engine (Turbine/Turboprop)
  > (CAN) THE FLIGHT CREW REPORTED NG DROP DURING CRUISE WITH THE PROP RPM AT 1700 AND PULLING BACK ON THE POWER LEVERS TO APPROXIMATELY 1100 ON BOTH ENGINES. THE RIGHT ENGINE DROPPED TO 300 LBS OF TORQUE AND THE FUEL FLOWS DID FOLLOW. THE AIRCRAFT DID YAW AND THE
- [SDR CA130128019](https://openairdocs.org/sdr/CA130128019.md): Blade · cracked · Jan 24, 2013 · Dhav DHC7103 · Propeller Blade Section
  > (CAN) BLADE SHANK WAS REWORKED FOR CORROSION TO MAXIMUM LIMITS IN ZONE 1, QUADRANT 2. LPI INSPECTION SUBSEQUENTLY REVEALED WHAT LOOKS TO BE A CRACK.
- [SDR CA130124025](https://openairdocs.org/sdr/CA130124025.md): Garlock Seal · leaking · Jan 23, 2013 · Dhav DHC7103 · Turbine Engine Oil System
  > (CAN) NR 2 ENGINE SHUTDOWN ON FINAL APPROACH DUE TO LOSS OF ENGINE OIL PRESSURE. FAULTY HYDRAULIC PUMP GARLOC SEAL REPLACED, CHECKED SERVICEABLE.
- [SDR CA130125004](https://openairdocs.org/sdr/CA130125004.md): Wire · damaged · Jan 14, 2013 · Dhav DHC7102 · Fire Protection System Wiring
  > (CAN) BOTH NR 4 ENGINE FIRE DETECTION ELEMENTS FOUND TO HAVE CHAFE DAMAGE FROM CONTACT WITH AIRFRAME STRUCTURE CAUSING ACTIVATION OF THE FIRE WARNING. BOTH DETECTION ELEMENTS REPLACED, CHECKED SERVICEABLE.
- [SDR CA121210009](https://openairdocs.org/sdr/CA121210009.md): Oil System · low pressure · Dec 4, 2012 · Dhav DHC7103 · Engine Oil Pressure
  > (CAN) ACFT DEPARTED FOR A MAINTENANCE TEST FLIGHT. PART WAY THROUGH THE CVR TEST, THE PILOTS RECEIVED THE MASTER CAUTION, NR 2 LOW OIL PRESSURE CAUTION LIGHT. THE GAUGE CONFIRMED LOW OIL PRESSURE SO THEY SHUTDOWN NR 2 ENGINE AND RETURNED TO DEPARTURE AIRPORT
- [SDR CA121228002](https://openairdocs.org/sdr/CA121228002.md): Oil System · low pressure · Dec 4, 2012 · Dhav DHC7103 · Engine Oil Indicating System
  > (CAN) NR 2 ENGINE WAS SHUTDOWN FOR PRECAUTIONARY MEASURES. THE PILOT REPORTED THAT THE ENGINE OIL PRESSURE WAS DROPPING OFF AND THE LOW OIL PRESSURE LIGHT WAS FLICKERING. UPON A MAINTENANCE INSPECTION, MAINTENANCE WAS UNABLE TO START THE EFFECTED ENGINE FOR
- [SDR CA121005005](https://openairdocs.org/sdr/CA121005005.md): Engine · power loss · Oct 3, 2012 · Dhav DHC7103 · Engine (Turbine/Turboprop)
  > (CAN) DURING CRUISE, THE NR 4 ENGINE T5 ROSE ABOVE 800 DEGREES C ILLUMINATING THE ASSOCIATED WARNING LIGHT WITH A CORRESPONDING YAW TO THE RT AND THE TORQUE DROPPED TO A MINIMUM POWER LEVEL, NG DROPPED TO APPROXIMATELY 60 PERCENT AND AN ODOR WAS DETECTED IN TH
- [SDR CA120920006](https://openairdocs.org/sdr/CA120920006.md): Strut · broken · Sep 18, 2012 · Dhav DHC7103 · Main Landing Gear Strut/Axle/Truck
  > (CAN) DURING POST FLIGHT INSPECTION, THE RT MLG UPPER LOCK STRUT WAS FOUND TO BE BROKEN AT THE UPPER, LOCK STRUT ACTUATOR, ATTACH POINT. THE LIFE LIMIT FOR THIS PART IS 60,000 LANDINGS AND IT HAD 15,949 LANDINGS REMAINING. THERE HAVE BEEN 3 SB ISSUED, 7-32-21
- [SDR CA120905011](https://openairdocs.org/sdr/CA120905011.md): Contactor · failed · Sep 5, 2012 · Dhav DHC7103 · Propeller/Rotor Anti-Ice/De-Ice System
  > (CAN) WHEN THE FLIGHT CREW SELECTED PROP DE-ICE IT FAULTED. UPON INSPECTION THE AC CONTACTOR FOR THE NR 2 PROP, IN THE NR 2 WHEEL WELL ELECTRICAL BOX, HAD FAILED. THE CONTACTOR AND SEVERAL TERMINALS WERE REPLACED AND THE SYS FUNCTION CHECKED WITH NO DEFECTS
- [SDR CA120605006](https://openairdocs.org/sdr/CA120605006.md): Turbine Blades · fractured · May 29, 2012 · Dhav DHC7102 · Turbine Section
  > (CAN) SHORTLY AFTER LEVELING OFF AT CRUISE ALTITUDE, THE FLIGHT CREW OBSERVED A DECREASE IN TORQUE FROM THE NR 2 ENGINE. THE ENGINE WAS SHUTDOWN AND THE FLIGHT RETURNED TO THE DEPARTURE POINT WHERE AN UNEVENTFUL LANDING WAS ACCOMPLISHED. POST FLIGHT INSPECTIO
- [SDR CA120528009](https://openairdocs.org/sdr/CA120528009.md): Blade · separated · May 24, 2012 · Dhav DHC7102 · Turbine Engine Compressor Section
  > (CAN) APPROXIMATELY 40 NM NORTH OF AIRPORT, SHORTLY AFTER LEVELING OFF AT CRUISE ALTITUDE, THE FLIGHT CREW OBSERVED A DECREASE IN TORQUE FROM THE NR 2 ENGINE. THE NR 2 ENGINE WAS SHUTDOWN AND THE CREW RETURNED TO DEPARTURE. VISUAL INSPECTION OF THE 1ST STAGE
- [SDR CA120522005](https://openairdocs.org/sdr/CA120522005.md): Wire · chafed · May 14, 2012 · Dhav DHC71 · Electrical Power System Wiring
  > (CAN) WHILE PERFORMING A ROUTINE TASK FOR EWIS INSPECTIONS IT WAS NOTICED THAT THERE WERE NUMEROUS WIRE CHAFING INSIDE THE LT AND RT AC CONTACTOR BOXES. THE CHAFING WAS CAUSED BY INSUFFICIENT WIRE PROTECTION AND POOR ROUTING OF BUNDLES THROUGHOUT THE CONTACTO
- [SDR CA120502013](https://openairdocs.org/sdr/CA120502013.md): Housing · cracked · Apr 30, 2012 · Dhav DHC7100 · APU Core Engine
  > (CAN) DURING THE ROUTINE SSI INSPECTION OF THE APU MOUNT AND STRUCTURE, IT WAS NOTICED THAT THE APU, PN 160371-201, SN 897402, HAD A SIGNIFICANT JAGGED CRACK ON THE FWD FACE OF THE COMBUSTION HOUSING, PN 160184-100, AFT OF THE V-BAND CLAMP WHICH SECURES THE CO

Next page: https://openairdocs.org/engine/u-a-canada-pt6a-50/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 = 'PT6A50'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/engine/u-a-canada-pt6a-50/reports

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