# Service difficulty reports: Pratt & Whitney Canada JT15D-1A

A list on [Pratt & Whitney Canada JT15D-1A](https://openairdocs.org/engine/pratt-whitney-canada-jt15d-1a.md).

Newest first. General aviation reporting is voluntary.

- [SDR FDIA2018122100001](https://openairdocs.org/sdr/FDIA2018122100001.md): Engine · flamed out · Dec 20, 2018 · N633AT · Cessna 500CESSNA · Engine (Turbine/Turboprop)
  > ENGINE FLAMED OUT AT 34000 FT. IN CRUISE. NO APPARENT REASON, ALL INDICATIONS WERE NORMAL AT THE TIME. ENGINE RESTART WAS NOT ATTEMPTED. AIRCRAFT DIVERTED AND THE LANDING WAS UNEVENTFUL. UNKNOWN CAUSE AT TIME OF REPORTING.
- [SDR FDIA20150619002](https://openairdocs.org/sdr/FDIA20150619002.md): Duplex Bearing · failed · May 5, 2015 · N622AT · Cessna 500CESSNA · Engine (Turbine/Turboprop)
  > CABIN FILLED WITH SMOKE CLAIMING THROUGH 25,000 FT. CREW DESCENDED TO AN UNEVENTFUL LANDING. LOW OIL PRESS ON TAXI IN ON LT ENG & NO OIL ON DIP STICK AFTER SHUTDOWN. CONFIRMED METAL CONTAMINATION IN THE OIL SYS. THE SOURCE OF THE METAL CONTAMINATION WAS TH
- [SDR FDIA20150505001](https://openairdocs.org/sdr/FDIA20150505001.md): Engine · malfunctioned · May 2, 2015 · N622AT · Cessna 500CESSNA · Engine (Turbine/Turboprop)
  > CABIN FILLED WITH SMOKE CLIMBING THROUGH 25,000 FT. PILOTS & CREW USED OXYGEN FOR AN QUICK DESCENT THROUGH 10,000 FT & THE CABIN CLEARED ENOUGH TO GO OFF OXYGEN. THEY DIVERTED & LANDED OTHERWISE UNEVENTFULLY. LT ENG OIL PRESS WAS IN THE YELLOW ARC TAXING IN
- [SDR FDIA20150618001](https://openairdocs.org/sdr/FDIA20150618001.md): Unknown · smoke · May 2, 2015 · N622AT · Cessna 500CESSNA · Air Distribution System
  > CABIN FILLED WITH SMOKE CLIMBING THROUGH 25,000 FT. PILOTS & CREW USED OXYGEN FOR A QUICK DESCENT THROUGH 10,000 FT & THE CABIN CLEARED ENOUGH TO GO OFF OXYGEN. THEY DIVERTED & LANDED OTHERWISE UNEVENTFULLY. LT ENG OIL PRESS WAS IN THE YELLOW ARC TAXING IN.
- [SDR CA150112011](https://openairdocs.org/sdr/CA150112011.md): Blade · damaged · Jan 12, 2015 · Turbine Section
  > (CAN) ENGINE FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED FINDING HP TURBINE BLADE DISTRESS.
- [SDR 2014FA0000112](https://openairdocs.org/sdr/2014FA0000112.md): Seat Frame · broken · Feb 12, 2014 · N501AF · Cessna 501 · Flight Compartment Equipment
  > STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAIR WAS REPAIRED IAW PROCEDURE STC STO1043WI AND DWG D-10392.
- [SDR CA130726008](https://openairdocs.org/sdr/CA130726008.md): Engine · vibration · Jul 25, 2013 · Engine (Turbine/Turboprop)
  > (CAN) ENGINE WAS SENT FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED AN UNUSUAL SOUND FOLLOWED BY VIBRATIONS AFTER ROLLOUT. SUBSEQUENT TESTING ON THE GROUND REVEALED THE ENGINE HAD UNUSUAL, HEAVY VIBRATIONS VERY LOW IN THE RPM BAND, BEFORE GROUND I
- [SDR CA130701005](https://openairdocs.org/sdr/CA130701005.md): Oil System · low pressure · Jun 13, 2013 · Cessna 500CESSNA · Engine Oil Indicating System
  > (CAN) THE PILOT OBSERVED ENGINE NR 2 LOST OF OIL PRESSURE DURING CRUISE. ENGINE POWER WAS REDUCED WHEN OIL PRESSURE GOT INTO THE YELLOW ARC ON THE GAUGE. THE PILOT ELECTED TO SHUTDOWN AND SECURE THE ENGINE WHEN OIL PRESSURE DROPPED BELOW 20 PSI. AN EVENTFUL
- [SDR CA130212006](https://openairdocs.org/sdr/CA130212006.md): Pump · leaking · Jan 28, 2013 · Cessna 501 · Engine Fuel Pump
  > (CAN) A FUEL LEAK AT THE ECOLOGY TANK WAS NOTICED. A LEAK WAS ALSO OBSERVED COMING FROM THE INTERFACE BETWEEN THE FUEL PUMP AND FUEL CONTROL UNIT. THE LEAK RATE WAS INCREASED BY INCREASING THE POWER DURING GROUND RUN TESTS. THE CUSTOMER WILL REPLACE THE FUE
- [SDR 2012FA0000819](https://openairdocs.org/sdr/2012FA0000819.md): Display · failed · Dec 4, 2012 · N999WS · Cessna 501 · Central Display
  > PILOT REPORTED, DURING FLIGHT, THE MULTIFUNCTION DISPLAY FAILED CAUSING SMOKE IN CABIN. ACFT LANDED, MULTIFUNCTION DISPLAY UNIT WAS REMOVED, WIRES SECURED AND ACFT RESUMED FLIGHT.
- [SDR 2012FA0000626](https://openairdocs.org/sdr/2012FA0000626.md): Frame · broken · Aug 27, 2012 · N41GT · Cessna 501 · Flight Compartment Equipment
  > FOUND SEAT BASE BROKEN.
- [SDR CA120827002](https://openairdocs.org/sdr/CA120827002.md): Engine · failed · Aug 16, 2012 · Engine (Turbine/Turboprop)
  > (CAN) DURING FLIGHT, PILOT HEARD A LOUD BANG AND SUDDENLY LOST ALL INDICATION AND THE ENGINE REPORTEDLY SHUT ITSELF DOWN IN-FLIGHT. UNKNOWN AT WHAT PHASE OF FLIGHT THIS OCCURRED. PILOT LANDED SAFELY. ON GROUND INVESTIGATION FOUND THE HP SPOOL CAN NOT ROTATE I
- [SDR E81RJT2307930](https://openairdocs.org/sdr/E81RJT2307930.md): Skin · damaged · Jul 21, 2011 · N501NY · Cessna 501 · Engine Air Intake System
  > DURING SCHEDULED PHASE INSP OF ACFT PREVIOUSLY MODIFIED, STC ST09559AC, ENGINE INSTALLATION NOTED (2) MISSING RIVET HEADS IN LT ENGINE INLET DUCT SKIN. SUBSEQUENT INVESTIGATION REVEALED MINOR CRACK FROM RIVET HOLE. NO FOD DAMAGE NOTED TO ENGINE. INLET DUCT SK
- [SDR K452011F00000](https://openairdocs.org/sdr/K452011F00000.md): Angle · cracked · Mar 2, 2011 · N82DT · Cessna 501 · Spoilers
  > DURING ROUTINE MX, THE RT LOWER SPEED BRAKE LOWER STIFFENER WAS FOUND CRACKED AT MID SPAN. THE COMPONENT WAS REPLACED IAW THE SRM. CAUSE UNKNOWN.
- [SDR K452011F00001](https://openairdocs.org/sdr/K452011F00001.md): Angle · cracked · Mar 2, 2011 · N82DT · Cessna 501 · Spoilers
  > DURING ROUTINE MX, THE LT LOWER SPEED BRAKE LOWER STIFFENER WAS FOUND CRACKED AT MID SPAN. THE COMPONENT WAS REPLACED IAW THE SRM. CAUSE UNKNOWN.
- [SDR 2010FA0000734](https://openairdocs.org/sdr/2010FA0000734.md): Line · leaking · Jul 12, 2010 · N17HA · Cessna 501 · Aircraft Fuel Distribution System
  > (EBVR) TROUBLESHOOT AND REPAIR FUEL LEAKING FROM BOTTOM OF NR 1 ENGINE BY THE FUEL CONTROL UNIT/ FUEL PUMP. TROUBLESHOT FUEL LEAK TO A CRACKED FUEL LINE. REMOVED EXISTING LINE AND INSTALLED O/H LINE. TORQUED AND SAFETIED.
- [SDR FDIA2010FA0000158](https://openairdocs.org/sdr/FDIA2010FA0000158.md): Bearing · failed · Feb 16, 2010 · N622AT · Cessna 500CESSNA · Engine (Turbine/Turboprop)
  > IN CRUSE AT 34,000 FEET A CHANGE IN ENG TONE WAS NOTED. WITHIN 20 SECONDS THICK SMOKE ENTERED THE CABIN. PILOT DECLARED EMERGENCY AND DESCENDED. LT ENG 'OIL PRESSURE LOW' LIGHT CAME ON AROUND 20,000 FEET AND ENG WAS SHUTDOWN. AFTER SHUTDOWN THE SMOKE IN TH
- [SDR 2010FA0000194](https://openairdocs.org/sdr/2010FA0000194.md): Wire · chafed · Jan 16, 2010 · N450KD · Cessna 550 · Auto Flight System Wiring
  > PILOT REPORTS AUTOPILOT CB TRIPPED. TROUBLESHOT PROBLEM AND FOUND WIRING INSIDE COPILOTS YOKE TO BE CHAFED AND SHORTING TO GROUND WHERE THE WIRING GOES FROM THE BACK OF THE YOKE INTO THE YOKE CONTROL WHEEL.
- [SDR 2009FA0000691](https://openairdocs.org/sdr/2009FA0000691.md): Turbine Blades · cracked · Jun 11, 2009 · Turbine Section
  > DURING HOT SECTION INSP, FOUND 2 HIGH TURBINE BLADES CRACKED ON THE T/E AT MID SPAN OF THE BLADE. WORST CRACK BEING APPROX.360 AND.200. (K)
- [SDR CA080423011](https://openairdocs.org/sdr/CA080423011.md): Engine · malfunctioned · Mar 30, 2008 · Cessna 500CESSNA · Engine (Turbine/Turboprop)
  > (CAN) THE CREW REPORTED VIBRATIONS SHORTLY AFTER TAKEOFF AND WAS ATTEMPTING TO RETURN TO POINT OF DEPARTURE. THE AC CRASHED. ALL ON BOARD WERE FATALLY INJURED. BOTH ENGINES SHOWED INDICATIONS CHARACTERISTIC OF THE ENGINES PRODUCING LOW POWER OR WINDMILLING UN
- [SDR CA070514005](https://openairdocs.org/sdr/CA070514005.md): Unknown · smoke · Feb 28, 2007 · Cessna 500CESSNA · Air Distribution System
  > (CAN) SMOKE WAS OBSERVED IN THE CABIN AIR FOLLOWING TAKE-OFF. OXYGEN MASKS WERE DEPLOYED AND AN EMERGENCY DECLARED. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514005)
- [SDR 2007FA0000222](https://openairdocs.org/sdr/2007FA0000222.md): Fuel Filter · separated · Feb 15, 2007 · N409S · Cessna 500CESSNA · Aircraft Fuel Filter/Strainer
  > THE RT FUEL FILTER ASSY SEPARATED FROM THE STANDPIPE DUE TO THE SNAP-RING BECOMING DISLOGED AND RESULTED IN A SUBSTANTIAL FUEL LEAK. (K)
- [SDR 2007FA0000224](https://openairdocs.org/sdr/2007FA0000224.md): Fuel Filter · separated · Feb 15, 2007 · N409S · Cessna 500CESSNA · Aircraft Fuel Filter/Strainer
  > THE RT FUEL FILTER ASSY SEPARATED FROM THE STANDPIPE DUE TO THE SNAP-RING BECOMING DISLODGED AND RESULTED IN A SUBSTANTIAL FUEL LEAK.
- [SDR CA060711001](https://openairdocs.org/sdr/CA060711001.md): Case · cracked · Jul 11, 2006 · Turbine Engine Combustion Section
  > (CAN) CRACKED GAS GENERATOR CASE WAS FOUND CRACKED AT THE LONGITUDINAL WELD AND CIRCUMFERENTIAL WELD. SB7240 IS AVAILABLE AND WILL REPLACE THE GAS GENERATOR CASE WITH A CASE WITH NO LONGITUDINAL WELDS. (TC NR 20060711001)
- [SDR 2006FA0000651](https://openairdocs.org/sdr/2006FA0000651.md): Blade · separated · Jun 28, 2006 · Turbine Section
  > DURING POST LEASE INSPECTION, FOUND 1 HIGH TURBINE BLADE SEPARATED AT MID SPAN. APPARENTLY NO OPERATIONAL PROBLEMS. MFG HAS PRODUCED REPLACEMENT BLADES UNDER SPARE PARTS BULLETIN 75. (K)
- [SDR CA050201001](https://openairdocs.org/sdr/CA050201001.md): Turbine · failed · Jan 26, 2005 · Turbine Section
  > (CAN) ENGINE WAS FOUND TO HAVE SUSTAINED A MAJOR INTERNAL FAILURE WITH EXTENSIVE DAMAGE TO THE IMPELLER AND THE ENTIRE TURBINE SECTION OF THE ENGINE. EVIDENCE OF A FAILED NR 2 BEARING, AN HP VANE ASSEMBLY WITH EXTENSIVE BURNING AND LOSS OF MATERIAL, AN HP TUR
- [SDR CA050127005](https://openairdocs.org/sdr/CA050127005.md): Seal · leaking · Jan 20, 2005 · Engine (Turbine/Turboprop)
  > (CAN) CAUSE OF SMOKE ODOR IN CABIN DUE TO OIL CONTAM OF GAS PATH AIRFLOW DUE TO A LARGE NR OF AIR/OIL SEALS HAD EXCESSIVE CLEARANCES, ALLOWING OIL TO ENTER SECONDARY AIR SYS. ENG DID HAVE A SIGNIFICANT AMOUNT OF FRETTING DAMAGE ON COMBUSION COMPONENTS, WHICH
- [SDR CA041001012](https://openairdocs.org/sdr/CA041001012.md): Engine · failed · Sep 21, 2004 · Engine (Turbine/Turboprop)
  > ENGINE WAS REMOVED FROM THE WING AFTER THE CUSTOMER THOUGHT THAT THE ENGINE HAD SUSTAINED A HIGH TURBINE BLADE FAILURE. THE ENGINE WAS SHIPPED TO ATLANTIC TURBINES FOR INVESTIGATION AND REPAIR. NO SIGNIFICANT DAMAGE WAS FOUND UPSTREAM OF THE HIGH PRESSURE TU
- [SDR CA040902006](https://openairdocs.org/sdr/CA040902006.md): Turbine Blades · failed · Aug 27, 2004 · Turbine Section
  > DISCOVERED HPT BLADE DAMAGE. CONFIRMED HPT BLADES DAMAGED WITH 1 BLADE MISSING ENTIRE TIP SECT. GAS GEN DEFLECTOR SEG FOUND MISSING SECTIONS & SIGNIFICANT NR OF RIVETS. EXAM OF FRACTURED BLADE SHOWED HIGH STRESS RAPID YIELD FRACTURE WITH NO EVIDENCE OF FATIG
- [SDR J7B2004F00000](https://openairdocs.org/sdr/J7B2004F00000.md): Blade · failed · Jul 15, 2004 · N409S · Cessna 500CESSNA · Turbine Section
  > HT BLADE FAILURE.
- [SDR 2004F00334](https://openairdocs.org/sdr/2004F00334.md): Turbine Blades · eroded · Jun 12, 2004 · N58TC · Cessna 500CESSNA · Turbine Section
  > ON APPROACH TO ATW, LT ENGINE INFLIGHT SHUTDOWN DUE TO LOW OIL PRESSURE. AIRCRAFT LANDED WITHOUT INCIDENT. PILOT CALLED DIRECTOR OF MAINTENANCE. DIRECTOR TRAVELED TO ATW, PERFORMED LOSS OF OIL INSPECTION. REPLACED OIL PUMP DUE TO SUSPECTED SCAVENGE FAILURE.
- [SDR BTA2004F00002](https://openairdocs.org/sdr/BTA2004F00002.md): Brake Assy · malfunctioned · May 16, 2004 · N223J · Cessna 550 · Landing Gear Brake System
  > LOSS OF BRAKE ACTUATING FORCE, NO PRIOR BRAKE PROBLEMS INDICATED. UTILIZED EMERGENCY HAND BRAKE TO STOP AIRCRAFT. BLED BRAKES PERFORMED OPS CHECKS NUMEROUS TIMES. PERFORMED ANTI-SKID CHECK AND TAXI CHECKED. COULD NOT DUPLICATE.
- [SDR CA040504002](https://openairdocs.org/sdr/CA040504002.md): Reservoir · leaking · May 4, 2004 · Cessna 501 · Hydraulic Reservoir, Main
  > (CAN) HYDRAULIC BRAKE RESERVOIR LEAKING. CRACK WELDED AND RETURNED TO SERVICE.
- [SDR 101703](https://openairdocs.org/sdr/101703.md): Blade · fractured · Oct 1, 2003 · N125DS · Cessna 500CESSNA · Turbine Section
  > HT BLADE FAILURE, 4 BLADES FRACTURED MID SPAN REMAINING SET HAS IMPACT DAMAGE, AS WELL AN IMPACT DAMAGE DOWNSTREAM IN THE ENGINE. ENGINE TIME SINCE OVERHAUL 1255.5 CYCLES SINCE O/H 843. THE BLADES ARE NEW AT THE OVERHAUL.
- [SDR CA030408001](https://openairdocs.org/sdr/CA030408001.md): Control Valve · malfunctioned · Apr 3, 2003 · Cessna 500CESSNA · Landing Gear Selector
  > (CAN) CESSNA 500 ON APPROACH, GEAR DID NOT EXTEND SO MANUAL GEAR EXTENSTION PROCEDURE CARRIED OUT. AIRCRAFT LANDED NORMALY. INSPECTED AIRCRAFT UNABLE TO DUPLICATE SNAG. SO CHANGED LANDING GEAR CONTROL VALVE AS A PRECAUTION.
- [SDR 2003FA0000286](https://openairdocs.org/sdr/2003FA0000286.md): Bellcrank · cracked · Feb 28, 2003 · N888MJ · Cessna 501 · Trailing Edge Flaps
  > RIGHT FLAP BELLCRANK FOLLOW-UP ROD ARM ATTACH POINT WAS CRACKED ON UPPER AND LOWER ARM. UPON INSPECTION OF OTHER BELLCRANKS; FOUND THAT SPACERS WERE MISSING BETWEEN FOLLOW-UP ROD-END AND BELLCRANK FOLLOW-UP ARM.
- [SDR CA020503001](https://openairdocs.org/sdr/CA020503001.md): Duct · cracked · Apr 3, 2002 · Cessna 500CESSNA · Turbine Engine Bypass Section
  > (CAN) DURING PHASE I & II INSPECTION, LT ENGINE FRONT & REAR INNER BYPASS DUCT FOUND CRACKED. PARTS REMOVED FROM ENGINE INSPECTED & FOUND PARTS HAD BEEN REPAIRED PREVIOUSLY, WELDED AT OVERHAUL & CRACK NEXT TO WELDED AREA.PROBABLE CAUSE, HI-TIME PARTS, PREVIOUS
- [SDR CA020215010](https://openairdocs.org/sdr/CA020215010.md): Duct · cracked · Feb 4, 2002 · Cessna 501 · Turbine Engine Bypass Section
  > (CAN) DURING DAILY INSPECTION, RT ENGINE FRONT & REAR INNER BYPASS DUCT FOUND CRACKED AND PIECE OF REAR UNDER BYPASS DUCT MISSING. AFTER REMOVAL OF THOSE ITEMS FROM THE ENGINE, THE INSPECTION REVEALED THAT THEY WERE PARTS WHICH WAS PREVIOUSLY WELDED/OVERHAUL A
- [SDR CA020114008](https://openairdocs.org/sdr/CA020114008.md): Engine · failed · Nov 16, 2001 · Engine (Turbine/Turboprop)
  > (CAN) ENGINE WAS UNABLE TO ACHIEVE THE RATED POWER WITHIN THE SPECIFIED TEMPERATURE LIMITS. THE OPERATOR DECIDED TO PERFORM AN HSI AND REMOVED THE HOT SECTION COMPONENTS FOR SHIPMENT TO ATLANTIC TURBINES FACILITY IN ATLANTA. AT THIS POINT IT WAS NOTED THAT TH
- [SDR CA011004008](https://openairdocs.org/sdr/CA011004008.md): Clamp · loose · Oct 3, 2001 · Cessna 500CESSNA · Pneumatic Distribution System
  > (CAN) CLIMBING THROUGH FLIGHT LEVEL 290, AIRCRAFT CABIN STARTED TO RAPIDLY CLIMB. FLIGHT CREW INITIATED A RAPID DECENT TO 10,000 FEET. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND CLAMP ON CABIN BLEED AIR SUPPLY LINE LOOSE AND THE AIR SUPPLY LIN
- [SDR CA011018024](https://openairdocs.org/sdr/CA011018024.md): Wire · shorted · Sep 20, 2001 · Cessna 500CESSNA · AC Inverter
  > (CAN) DURING A ROUTINE FLIGHT, ON ARRIVAL AT YYZ #2 INVERTER FAILED. SYSTEM WAS CHECKED AND FINDINGS WERE THAT THE 115 VAC OUTPUT FOR THE R/H BUS, RUNNING BETWEEN THE INVERTER AND THE FRONT PRESSURE BULKHEAD THE WIRE WAS FOUND SHORTED. THERE WAS EVIDENCE OF CO
- [SDR IY22001F00002](https://openairdocs.org/sdr/IY22001F00002.md): Blade · separated · Jul 30, 2001 · N15AW · Cessna 500CESSNA · Turbine Engine Compressor Section
  > PCE 76307, SUSTAINED HPT BLADE SEPARATION AND RESULTED IN DOWN STREAM HOT SECTION DAMAGE. THIS SEPARATION OCCURS AT 580.5 HOURS AFTER HOT SECTION, WHICH IS COMMON TO THE PREVIOUS FAILURES/MDRS SUBMITTED. THE GROWTH (NECKING) IS FROM.007 INCHES TO.012 INCHE
- [SDR 2001FA0000180](https://openairdocs.org/sdr/2001FA0000180.md): Fuel Control · malfunctioned · Jul 9, 2001 · N88GJ · Cessna 500CESSNA · Fuel Control/Turbine Engines
  > DURING A CLIMB THROUGH FL 290, THE RIGHT ENGINE FAN SPEED DECREASED TO 82 PERCENT. ENGINE IGNITION WAS SELECTED ON TO NO EFFECT. AN EMERGENCY WAS DECLARED AND A SAFE LANDING WAS MADE. SUSPECT THAT THE FUEL CONTROL UNIT MALFUNCTIONED.
- [SDR 2001FA0000248](https://openairdocs.org/sdr/2001FA0000248.md): Fuel Control · malfunctioned · Jul 8, 2001 · N88GJ · Cessna 500CESSNA · Fuel Control/Turbine Engines
  > DURING A CLIMB THROUGH FL 290, THE RIGHT ENGINE FAN SPEED DECREASED TO 82 PERCENT. ENGINE IGNITION WAS SELECTED ON TO NO EFFECT. AND EMERGENCY WAS DECLARED AND A SAFE LANDING WAS MADE. SUSPECT THAT THE FUEL CONTROL UNIT MALFUNCTIONED.
- [SDR 20010613CW012](https://openairdocs.org/sdr/20010613CW012.md): Blade · separated · May 30, 2001 · N511AT · Turbine Section
  > BACKGROUND: THE 3028601 TURBINE BLADE INSTALLED ON THE JT15D-1A ENGINE HAVE A 3500 HOUR LIFE LIMIT. THIS TURBINE BLADE TENDS TO CRACK AT THE AIRFOIL AND BREAK CAUSING EXTENSIVE DOWNSTREAM FAILURE/DAMAGE. THE BLADE WILL TYPICALLY GROW IN EXCESS OF.007 INCH
- [SDR IY22001F00003](https://openairdocs.org/sdr/IY22001F00003.md): Blade · broken · May 24, 2001 · N8DE · Cessna 500CESSNA · Turbine Section
  > HIGH TURBINE BLADE BROKE OFF APPROXIMATELY.500 INCH FROM THE BLADE TIP. ONE OTHER BLADE IS CRACKED ABOUT MID-CENTER OF THE BLADE. THESE BLADES HAVE A LIFE LIMIT OF 3500 HOURS.
- [SDR CA010314016](https://openairdocs.org/sdr/CA010314016.md): Solenoid Valve · failed · Feb 27, 2001 · Cessna 500CESSNA · Landing Gear Retraction/Extension System
  > (CAN) GEAR FAILED TO RETRACT AFTER TAKEOFF. REPLACED 4 WAY SOLENOID HYDRAULIC VALVE GEAR CYCLED TESTED OK. IAW C500 MM CH.32.

## 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 = 'JT15D1A'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/engine/pratt-whitney-canada-jt15d-1a/reports

---
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