Pratt & Whitney Canada PW207E
Service difficulty reports · 45
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 = 'PW207E' 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 = 'PW207E' 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 CA160121022Hose · cracked(CAN) AFTER SHUT DOWN FOLLOWING A SHORT UNRELATED TEST FLIGHT, TRANSMISSION OIL WAS DISCOVERED COVERING THE TRANSMISSION DECK AND FLOWING DOWN THE SIDES OF THE FORWARD FUSELAGE. APPROXIMATELY 5 QUARTS OF THE 10 QUART CAPACITY IN THE MAIN TRANSMISSION HAD LEAKESDR CA151007018Compressor · leaking(CAN) THE CREW OF THE HELICOPTER WAS FORCED TO MAKE AN EMERGENCY LANDING ON THE OUTSKIRTS OF PARIS DUE TO LEFT ENGINE LOW OIL PRESSURE AND SMOKE IN THE CABIN. TROUBLESHOOTING FOUND THE COMPRESSOR WET WITH OIL (POSSIBLY LEAKING FROM THE NR 3 BEARING CAVITY) ANDSDR CA150911004Engine · power loss(CAN) DURING A FLIGHT TEST, AFTER ANNUAL CHECK, THE NR 1 ENGINE EXPERIENCED A LOSS OF TORQUE. NO OTHER DETAILS ARE AVAILABLE ON THE CIRCUMSTANCES. THE OPERATOR IS CURRENTLY DOWNLOADING ENGINE AND AIRFRAME DATA, TROUBLESHOOTING IS ON-GOING.SDR CA141008011Throttle · malfunctioned(CAN) UPON LANDING, THE PILOT LOWERED THE COLLECTIVE AND 1 ENGINE BEGAN TO ACCELERATE. THE PILOT RAISED THE COLLECTIVE TO APPLY TORQUE TO REDUCE ENGINE SPEED. THIS SEEMED TO LOWER THE SPEED MOMENTARILY. THE ENGINE THEN BEGAN TO ACCELERATE AGAIN, THE PILOT TUSDR QMLA2014012214010Transmission · making metalMULTIPLE MAIN TRANSMISSION CHIP LIGHTS, AFTER FOLLOWING CSP 900RMM 2 CHAPTER 63-20-00 & TABLE 601. CHIPS INDICATED ALL UNDER THE LIMITS OF THE CHAPTER BUT COME ON EACH AIRCRAFT RUN UP.SDR CA130729002Engine · power loss(CAN) AFTER DROPPING A SLINGED LOAD, THE NR 2 ENGINE FROZE AT HIGH TORQUE FOR 20 SEC. THE NR 1 ENGINE REDUCED POWER ACCORDINGLY BUT THE MAIN ROTOR OVERSPED TO 104 PERCENT. TROUBLESHOOTING IS ON-GOING.SDR CA130617002Engine · shutdown(CAN) THE PILOT REPORTED AN ELECTRONIC ENGINE CONTROL SHUTDOWN FROM THE LT ENGINE. THE PILOT REQUESTED MORE POWER FROM RT ENGINE TO FLY OVER THE CABLES IN FRONT OF HIM. THE PILOT COMPLETED AN UNEVENTFUL LANDING AND SHUTDOWN THE ENGINES.SDR CA130508014Screw · missing(CAN) FOD DAMAGE TO NOTAR FAN. STATOR BLADE RETAINER SCREW FOUND MISSING.SDR CA121211003Compressor · seized(CAN) CREW COMPLAINED OF POPPING NOISE WHEN GOING FROM IDLE TO FLY CONDITION. MECHANIC CONFIRMED NOISE AND COMMENCED COMPRESSOR WASHES AND RINSES. DURING THE RINSE CYCLE SPOOL DOWN THE MECHANIC NOTED A LOUD AND ABRUPT GRINDING NOISE. HE TRIED TO ROTATE THE CSDR CA120716009Blade · fractured(CAN) AFTER TAKINGOFF FROM THE ROOF OF A HOSPITAL, DURING THE TRANSITION PHASE, THE CREW HEARD A LOUD NOISE FOLLOWED BY A POWER LOSS AND NR 1 ENGINE SHUTDOWN. THE CREW FLEW THE ACFT SINGLE ENGINE (OEI) AND PERFORMED AN UNEVENTFUL RUN-ON LANDING AT AIRPORT. SDR QMLA2011050911056Impeller · damagedPART OF THE GASKET OF THE INLET SCREEN CAME LOOSE AND WAS INGESTED INTO THE ENGINE. ONE BLADE ON THE COMPRESSOR HAD DAMAGE THAT CAUSED A LOUD WHINING NOISE WHEN THE ENGINE WAS OPERATED. THE ONLY DAMAGE THAT CAN BE OBSERVED IS THE COMPRESSOR BLADES. IT IS BESDR 2009FA0000440Drive Shaft · corrodedDURING AN ANNUAL INSP THE MAIN ROTOR DRIVE SHAFT AND DRIVE PLATE WHERE REMOVED TO
SATISFY THE 12 MONTH REQUIREMENT. WHILE REMOVING THE DRIVE SHAFT IT WAS FOUND THAT THE GREASE COATING ON LWR DRIVE SPLINE WAS DISCOLORED AND DEGRADED. FURTHER INSP SHOWED MOISSDR 2006FA0000620Hose · crackedPILOT NOTICED TRANSMISSION OIL PRESSURE INDICATION DROPPED FROM GREEN TO YELLOW TO RED. MADE UNSCHEDULED LANDING. FOUND FWD LT TRANSMISSION OIL COOLER HOSE LEAKING. HOSE IS A FLEXIBLE STAINLESS STEEL HOSE WITH A STAINLESS STEEL OUTER BRAID. HOSE WAS INSPECTEDSDR 2006FA0000503Hose · crackedDISCOVERED MAIN TRANSMISSION OIL HOSE FROM OIL COOLER TO MAIN TRANSMISSION LEAKING FROM STEEL BRAIDING. PULLED BACK BRAIDING AND FOUND HOSE TO BE CRACKED. REPLACED LINE WITH NEW. LEAK CHECK OF NEW LINE WAS SATISFACTORY, P/N 900D3409526-105.SDR 2006FA0000506Hose · crackedDISCOVERED MAIN TRANSMISSION OIL HOSE FROM OIL COOLER TO MAIN TRANSMISSION LEAKING FROM STEEL BRAIDING. PULLED BACK BRAIDING AND FOUND HOSE TO BE CRACKED. REPLACED LINE WITH NEW. LEAK CHECK OF NEW LINE WAS SATISFACTORY. P/N 900D3409526-105.SDR 2006FA0000507Beam · crackedDURING SCHEDULED INSPECTION FOUND FLEXBEAM CRACKED IN LEG OF FLEXBEAM. REJECTED FLEXBEAM IAW INSPECTION CRITERIA IN MAINTENANCE MANUAL. REPLACED WITH NEW FLEXBEAM.SDR 2006FA0000508Beam · crackedDURING SCHEDULED INSPECTION FOUND FLEXBEAM CRACKED IN LEG OF FLEXBEAM. REJECTED FLEXBEAM IAW INSPECTION CRITERIA IN MM. REPLACED WITH NEW FLEXBEAM.SDR 2006FA0000501Oil Cooler · leakingFOUND WETTING OIL MAIN TRANSMISSION/ENGINE OIL COOLER CORE. REMOVED AND SENT OUT FOR EVALUATION. COOLER FOUND TO HAVE INTERNAL CORROSION THAT CAUSED MATERIAL LOSS AND SUBSEQUENT LEAKING. REPLACED COOLER WITH NEW. LEAK CHECK WAS SATISFACTORY.SDR L192006F00000Line · wornON TRAINING FLIGHT, RT ENG FIRELIGHT CAME ON. PILOT COMPLIED WITH EMERGENCY PROCEDURES, THEN SHUT RT ENG DOWN AND DISCHARGED RT ENG FIRE BOTTLE, LANDED AC AND FIRE LIGHT WENT OUT. AC WAS CHECKED FOR FIRE IN ENG COMPT, NONE WAS FOUND. NO EVIDENCE OF FLAMES ISDR 2006FA0000274Hose · crackedHOSE IS INSTALLED ON MD902 HELICOPTERS. MD P/N IS 900D3409526-105. HOSE IS USED FOR MAIN TRANSMISSION OIL COOLING. FOUND LARGE ACCUMULATION OF OIL ON TRANSMISSION DECK AFTER FLIGHT. HOSE WAS FOUND TO BE CRACKED IN ONE OF THE BELLOWS. (CORE OF HOSE IS STAINSDR 2005FA0000816Hub · crackedDURING ACCOMPLISHMENT OF AD 2002-10-05- MAIN ROTOR UPPER HUB INSP FOUND (2) BOLT HOLES CRACKED AS DEPICTED IN MD HELICOPTERS SERVICE BULLETIN 900-072. CRACKS WERE FOUND USING MAGNIFIED VISUAL METHOD. HUB WAS SUBSEQUENTLY INSPECTED BY EDDY CURRENT METHOD TO VSDR 2004FA0000938Hub · crackedDURING ACCOMPLISHMENT OF AD 2002-10-05 "MAIN ROTOR UPPER HUB INSP" FOUND BOLT HOLES CRACKED AS DEPICTED IN MD HELICOPTERS SERVICE BULLETIN 900-072. PART TOTAL TIME: 1852 HRSSDR 2004FA0000940Hub · crackedDURING ACCOMPLISHMENT OF A.D. 2002-10-05 " MAIN ROTOR UPPER HUB INSP." FOUND (3) OUT OF (10) BOLT HOLES CRACKED AS DEPICTED IN MD HELICOPTERS SERVICE BULLETIN 900-072. PART TOTAL TIME: 292 HRSSDR 2004FA0000939Beam · crackedDURING 100 HOUR INSPECTION, FOUND FLEX BEAM CRACKED IN AREA OF LEG GOING INTO UPPER HUB. REPLACED PART WITH UPDATED SERVICEABLE PART.SDR 2004FA0000934Fuel Cell · leakingDURING TROUBLESHOOTING A FUEL LEAK FOUND THAT WHEN THE FUEL CELL WAS FLEXED, FUEL WOULD WEEP FROM EXTERIOR SURFACE. REMOVED FUEL CELL AND SENT OUT FOR TEST AND REPAIR. EVALUATION RESULTS SHOWED WEEPING/ POROUS CONDITION OVER 80 PERCENT OF THE CELL AND CELL TO SDR PG9R097903Line · leakingFOUND TO BE LEAKING A SMALL QUANTITY OF OIL/REPLACED OIL HOSE ASSY.SDR PG9R97903Line · leakingFOUND TO BE LEAKING A SMALL QUANTITY OF OIL/ REPLACED OIL HOSE ASSY. (K)SDR 2004FA0000877Rotor Head · crackedHAD VIBRATION (.7 IPS) CAUTION ON IDS DURING FLIGHT AND HIGH VIBRATION ON SHUT DOWN BETWEEN 30-40 PERCENT NR. INSPECTED MAIN ROTOR SYSTEM IAW MAINTENANCE MANUAL AND FOUND (3) OUT OF (5) FLEXBEAMS CRACKED. REPLACING FLEXBEAMS WITH NEW UPDATED FLEXBEAMS.SDR 2004FA0000802Drive Shaft · wornDURING ACCOMPLISHMENT OF A 300 HR INSPECTION FOUND MAIN ROTOR DRIVE SHAFT UPPER DRIVE SPLINES WORN BEYOND MAINTENANCE MANUAL LIMITS. PART TOTAL TIME: 1478.9 HRS. REPLACED DRIVE SHAFT WITH NEW PART.SDR 2004FA0000578Hub · crackedDURING ACCOMPLISHMENT OF A.D. 2002-10-05, (MAIN ROTOR UPPER HUB INSP.) FOUND (2) OUT OF (10) HOLES CRACKED IN UPPER HUB FLANGE AS DEPICTED IN MFG SERVICE BULLETIN 900-072.SDR 2004FA0000876Rotor Head · crackedDURING ACCOMPLISHMENT OF AD 2002-10-05, "MAIN ROTOR UPPER HUB INSP", FOUND (2) OUT OF (10) HOLES CRACKED IN UPPER HUB FLANGE AS DEPICTED IN MD HELICOPTERS SERVICE BULLETIN 900-072 PART TOTAL TIME: 91.23 HRS.SDR 2004FA0000324Hub · crackedDURING ACCOMPLISHMENT OF AD 2002-10-05 (MAIN ROTOR UPPER HUB INSPECTION), FOUND (3) OUT OF (10) BOLT HOLES TO BE CRACKED AS DEPICTED IN MFG SERVICE BULLETIN 900-072. CRACKS START IN BOLT HOLE CHAMFER. PART TOTAL TIME: 102.0HOURS. REMOVED AND REPLACED UPPER HUBSDR 2004FA0000322Hub · crackedDURING ACCOMPLISHMENT OF AD2002-10-05 (MAIN ROTOR UPPER HUB INSP.) FOUND (3) OUT OF (10) BOLT HOLES CRACKED AS DEPICTED IN MFG SERVICE BULLETIN 900-072. CRACKS START IN BOLT HOLE CHAMFER. PART TOTAL TIME: 102.0 HRS.SDR 2004FA0000323Hub · crackedDURING ACCOMPLISHMENT OF AD2002-10-05 (MAINROTOR UPPER HUB INSP.) FOUND (3) OUT OF (10) BOLT HOLES CRACKED AS DEPICTED IN MFG SERVICE BULLETIN 900-072. CRACKS START IN BOLT HOLE CHAMFER. PART TOTAL TIME: 102.0 HRS.SDR 2004FA0000332Hub · crackedDURING ACCOMPLISHMENT OF AD2002-10-05 (MAINROTOR UPPER HUB INSP.) FOUND (3) OUT OF (10) BOLT HOLES CRACKED AS DEPICTED IN MFG SERVICE BULLETIN 900-072. CRACKS START IN BOLT HOLE CHAMFER. PART TOTAL TIME: 102.0 HRS.SDR 2004FA0000331Hub · crackedDURING ACCOMPLISHMENT OF AD 2002-10-05 (MAIN ROTOR UPPER HUB INSP.) FOUND (3) OUT OF (10) BOLT HOLES CRACKED AS DEPICTED IN SERVICE BULLETIN 900-072. CRACKS START IN BOLT HOLE CHAMFER. PART TOTAL TIME: 102 HRS.SDR 2004FA0000801Hub · crackedDURING ACCOMPLISHMENT OF AD 2002-10-05, MAIN ROTOR UPPER HUB INSP. FOUND (3) OUT OF (10) BOLT HOLES CRACKED AS DEPICTED IN SB 900-072. CRACKS START IN BOLT HOLE CHAMFER. PART TOTAL TIME: 102.0 HRS.SDR 2004FA0000330Hub · crackedDURING ACCOMPLISHMENT OF AD 2002-10-05 INSP. (MAIN ROTOR UPPER HUB INSP.) FOUND (2) OUT OF (10) FLANGE BOLT HOLES WITH CRACKS AS DEPICTED IN MFG SERVICE BULLETIN 900-072. CRACKS RUN RADIALLY FROM BOLT HOLE INWARD TO FLANGE EDGE. PART TOTAL TIME WAS 399.65 HRS.SDR 2004FA0000163Line · crackedAIRCRAFT EXPERIENCED LOW TRANSMISSION OIL PRESSURE. DURING RUN-UP AND LEAK CHECK FOUND TRANSMISSION OIL COOLER LINE P/N 900D3409526105 TO BE LEAKING FROM UNDER STEEL BRADE. REPLACED OIL COOLER LINE, OPS AND LEAK CHECK WERE GOOD. CUT BACK STEEL BRADE ON OLD SDR 2004FA0000095Hub · crackedDURING ACCOMPLISHMENT OF A.D. 2002-10-05(MAIN ROTOR UPPER HUB INSPECTION)FOUND (6) OUT OF (10) UPPER FLANGE BOLT HOLES TO BE CRACKED. CRACKS RUN RADIALLY FROM BOLT HOLE TO INNER EDGE AS DEPICTED IN SB 900-072. PART TOTAL TIME: 435 HRS SINCE NEW. REPLACED UPSDR 2003FA0000190Filter · contaminatedBYPASS PIN POPPED ON NR 1 HYDRAULIC RETURN FILTER. REMOVED FILTER AND INSPECTED FOR CONTAMINATION. REPLACED FILTER. OPS AND LEAK CHECK GOOD.SDR 2003FA0000188Indicator · defectiveAFTER INSTALLING NEW HYDRAULIC FILTER, THE RETURN SIDE BYPASS INDICATOR POPPED WITH NO PRESSURE APPLIED. AFTER RESETTING THE INDICATOR, INDICATOR POPPED AGAIN. REPLACED IMPENDING BY-PASS INDICATOR PN 071142-258. OPS CHECK GOOD.SDR 2003FA0000187Drive Link · wornMAIN ROTOR UPPER DRIVE LINK BEARING PLAY EXCEEDS MAINTENANCE MANUAL LIMITS.SDR 2003FA0000186Drive Link · wornMAIN ROTOR UPPER DRIVE LINK BEARING PLAY EXCEEDS MAINTENANCE MANUAL LIMITS.SDR 2003FA0000184Transmission · making metalMAIN TRANSMISSION PRODUCING METAL CHIPS. CHIP SIZE EXCEED MAINTENANCE MANUAL LIMITS.
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