Allison 250-C20R/2
Service difficulty reports · 66
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 = '250C20R2' 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 = '250C20R2' 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 2019FA0000124Control Cable · bindingA/C EXPERIENCED STUCK RIGHT PEDAL IN FLIGHT RESULTING IN EMERGENCY LANDING. UPON INSPECTION OF ANTI-TORQUE SYSTEM, FOUND FORWARD AND AFT THRUSTER CONTROL CABLE ASSEMBLIES BOUND UP AT THE TAIL BOOM CONNECT/DISCONNECT POINT. THIS LOCATION IS WHERE THE FORWARD ANSDR CA160107008Turbine · failed(CAN) THE TURBINE HAD A CATASTROPHIC FAILURE.SDR CA141017005Cartridge · leaking(CAN) BOOST PUMP FUEL CARTRIDGE LEAKING FUEL AND REQUIRES O/H, REPLACED WITH TSO 0.0.SDR CA141016002Blade · debonded(CAN) TAIL ROTOR BLADES, L/E STRIPS FOUND DEBONDED AT BLADE TIPS. EDGE OF L/E STRIP SEPARATED FROM AIRFOIL. BOTH BLADES REMOVED FROM SERVICE AND REPLACED BY NEW UNIT SAME PN.SDR ZD4R20130530610Retaining Ring · dislodgedA CHIP LIGHT ILLUMINATED, CLEANED CHIP PLUGS AND RETURNED ENGINE BACK TO SERVICE. APPROX 11 HOURS LATER, CHIP LIGHT ILLUMINATED AND METAL WAS MORE SIGNIFICANT THAN BEFORE. DECIDED TO PULL THE ENGINE AND SEND IT IN FOR REPAIR. THE ENGINE WAS DISMANTLED AND IT SDR CA121019012Turbine · seized(CAN) WHILE DECENDING FOR AN APPROACH INTO CAMP, AT APPROXIMATELY 200 FEET AGL, PILOT HEARD A LOUD BANG FOLLOWED BY A YAW, AND A LOSS OF ENGINE POWER. PILOT ENTERED AN AUTOROTATION, AND ELECTED TO GO TO THE SHALLOW RIVER BED NEARBY AS OTHER OPTIONS WERE HEAVISDR 2012FA0000117Torque Tube · mismanufacturedDURING A 600 HR A/F INSPECTION, NOTICED 8 RIVETS SHOWING EVIDENCE OF LOOSENESS. THE AFFECTED RIVETS ARE LOCATED ON THE RT SIDE OF THE TORQUE TUBE AND GO AROUND. THE CIRCUMFERENCE OF THE COLLECTIVE TORQUE TUBE ASSY. AFTER MOVING THE PILOTS COLLECTIVE CONTROSDR 2011FA0000385Cover · crackedWITHIN 1 WEEK OF RECEIVING THIS UNIT BACK FROM O/H, IT STARTED SEEPING OIL. THOUGHT IT WAS LEAKING FROM THE SCAV PUMP, REMOVED THE PUMP AND INSTALLED NEW PACKINGS. UNIT STARTED TO SEEP OIL AGAIN SHORTLY AFTER REPAIR. CHECKED PACKINGS ON SCAV PUMP AGAIN & FOSDR CA091109007Indicator · misrepaired(CAN) RECEIVED THIS INDICATOR FROM O/H AND IT WAS FOUND TO BE INDICATING 300 DEGREES CELSIUIS TO HIGH UPON INSTALLATION AND TEST. WE ARE ASSUMING THIS PROBLEM WAS DUE TO POOR QC OR DAMAGE DUE TO SHIPPING BUT THE BOX THE T.O.T. INDICATOR CAME IN LOOKED UNDAMAGSDR CA090304008Bearing · damaged(CAN) RECEIVED MAIN ROTOR HUB FOR REPLACEMENT OF TIME EXPIRED COMPONENTS. WHEN DISASSEMBLED FOUND THAT BOTH OTBD EXCLUDERS IN GRIP ASSEMBLIES WERE NO LONGER RETAINING THE LUBRICANT AND ALLOWING IT TO PASS INTO THE YOKE SPINDLE BORES. THE INBD BEARING CONTACT ASDR CA081017007Governor · malfunctioned(CAN) UPON REMOVAL OF THE GOVERNOR IT WAS NOTED THAT THE DRIVE GEAR HAD COME SEPARATED. ALL PARTS WERE FOUND IN THE DRIVE GEAR FOR THE GOVERNOR. THERE WAS DIFFICULTY GETTING FULL RANGE OF THE GOVERNOR, COULD NOT ADJUST FOR 100 PERCENT ON THE GROUND. THE DRIVE SDR CA080625005Blade · delaminated(CAN) DELAMINATION AT ROOT OF BLADE ON UPPER SURFACE OF THE GIP PLATE FINGER. VISUAL SEPARATION NOTED ON DAILY INSP.SDR CA080603005Pump · malfunctioned(CAN) REINFORCED PAPER WIPERS LEFT IN THE FUEL TANK AFTER WORK CARRIED OUT. DURING A 300 HOUR INSP, THERE WAS SIGNIFICANT FUZZ LIKE DEBRIS FOUND IN THE ENGINE DRIVEN FUEL PUMP FILTER THAT WAS A BLUISH COLOR. WHEN PICKING UP THE HELICOPTER AT THE SERVICE CTRSDR CA080103007Bolt · broken(CAN) ON INSPECTION OF THE AIRCRAFT IT WAS NOTED THAT THE (1) OF THE (3) BOLTS WAS BROKEN AND THE OTHERS SHOWED SIGNS OF CORROSION ALL (3) BOLTS WHERE REPLACED WITH NEW. (TC NR 20080103007)SDR CA071029004Housing · cracked(CAN) OIL FOUND ON TRANSMISSION DECK AFTER BRIEF DAILY INSPECTION, OIL LEAK FOUND FROM THE BOTTOM OF THE TRANSMISSION. UPON FURTHER INVESTIGATION TRANSMISSION REMOVED AND BOTTOM CASING FOUND TO BE CRACKED AT LOWER MAST SUPPORT BRG. (TC NR 20071029004)SDR CA070726003Sleeve · cracked(CAN) PILOT STARTING A/C, THROTTLE OPENED, NO ENGINE LIGHT OFF OCCURED. OPENED ENGINE COWL TO INVESTIGATE, NOTICED FUEL DRIPPING FROM AROUND START DE-RICHMENT ADJUSTMENT OF FCU, ONTO THE STARTER GENERATOR. CONTACTED MAINTENANCE PERSONNEL TO INVESTIGATE. FUEL CSDR CA070327009Gearbox · leaking(CAN) OIL LEAK. SHIPPED TO AUTHORIZED SERVICE CENTER FOR REPAIR AND RE-INSTALLATION. (TC NR 20070327009)SDR CA061120001Switch · leaking(CAN) REMOVED LT FUEL FLOW SWITCH DUE TO LEAKING. INSTALLED FUEL FLOW SWITCH PN 205-061-635-005 SN 9607 (TC NR 20061120001).SDR CA061117001Transducer · reads low(CAN) UNDER READING FUEL PRESSURE. REMOVED AND INSTALLED REPLACEMENT PRESSURE TRANSDUCER PN BSE 206-30G SN2617-1-251 (TC NR 20061117001)SDR CA051012007Hinge · brokenON APPROACH WITH A SLING LOAD THE BATTERY DOOR OPEN AT A SPEED OF 60 MPH AND THE DOOR HINGE BROKE. THE DOOR STAYED ATTACH TO THE AIRCRAFT BY THE SPRING P/N 206-031-155-005. NO OTHER DAMAGES HAVE BEEN FOUND ON THE AIRCRAFT. AFTER INVESTIGATION, THE HINGE P/NSDR CA050617004Seal · leaking(CAN) REPLACED SEAL DUE TO LEAKING OIL. (FREEWHEEL)SDR CA050511004Fan · damagedTHE COOLING FAN IN THE STARTER GEN DEVELOPED A CRACK IN THE FAN BLADE PART (4 BLADES ARE STAMPED FROM ONE ALUMINUM PIECE, AND SWAGED ON A STEEL HUB) AT THE NOTCH BETWEEN TWO BLADES. UNDER CENTRIFUGAL FORCE AT 12,000 RPM, THE BLADES SPLIT IN TWO AND CAME OFF TSDR CA041222006Turbine · failed(CAN) CHIP LIGHT AND ENGINE VIBRATION. PRECAUTIONARY LANDING. ON SUBSEQUENT INSPECTION, TURBINE FOUND TO HAVE FAILED. EXHAUST STACKS AND COMBUSTION LINER FOUND CRACKED. REMOVED TURBINE AND INSTALLED SERVICEABLE TURBINE, EXHAUST STACKS AND COMBUSTION LINERSDR CA040623009Blade · perforated(CAN) WHILE CARRYING OUT REQUIREMENTS OF AD CF-2004-05(BHTC ASB 206L-04-127 REV A) A PIN HOLE IN THE EPOXY FILLER, APPROXIMATELY .012 IN. DIA, INTRUDING INTERNALLY, WAS FOUND. WATER WAS OBSERVED DRAINING FROM THE HOLE. BLADE HAS BEEN SCRAPPED.SDR CA040727008Washer · missing(CAN) AFTER FINDING MISSING CARRIAGE ROLLER WASHERS ON ANOTHER LONG RANGER, INSPECTED AND FOUND IT TO BE THE SAME, NO WASHERS.SDR CA040603007Turbine · locked(CAN) TURBINE HAD AN N2 LOCK UP. SUSPECT UNKNOWN AT THIS TIME. TURBINE SENT TO OVERHAUL SHOP FOR ASSESSMENT.SDR CA040428004Elt · failed(CAN) UPON ANNUAL RE-INSPECTION FOR RE-CERTIFICATION PURPOSES, AVIOINICS SHOP REPORTED ELT S/N 353494 FAILS TEST PROBABLY DUE TO A BAD CRYSTAL. UPON BEING ADVISED THAT A COMPANY DOES NOT SUPPLY PARTS, OPERATOR PURCHASED AND INSTALLED A NEW ELT ONTHE AIRCRAFT.SDR CA040806007Fitting · misinstalled(CAN) AFTER A VISUAL INSPECTION, ENGINE GB MOUNT FITTING 206-063-110-003 (RT) AND FITTING 206-063-110-001 (BOTTOM) WERE FOUND INTERMIXED. BOTTOM FITTING IS 0.4 INCH LONGER THAN THE SIDE ONES. REINSTALLED THE FITTINGS PROPERLY AFTER INSPECTION OF THE A/F ENGSDR CA040427014Coupling · worn(CAN) UPON INSPECTION, SPLINE/COUPLING P/N 9A1424 WAS FOUND WORN. REMOVED OIL PUMP AND TACH GENERATOR AND MATING COUPLING P/N 9A1424 FOR INSPECTION AND REPAIR. REPLAC ED WITH NEW GLOBE TACH GEN P/N 22A650 S/N 6209 AND OHC OIL PUMP P/N 206-140-190-005 S/N SPFSDR 2004FA0000269Gauge · inaccuratePILOT REPORTED OPERATIONAL EXCEEDANCE DURING FLIGHT RETURNED AC TO HELIPORT. UPON FURTHER INSPECTION AND EVALUATION IT WAS DETERMINED THAT THE DIAMOND J. TORQUE GAUGE WAS READING APPROX 15 LBS. LOW. AT 60 KNOTS AIRSPEED TORQUE READING 26-27 LBS. NORMAL READISDR CA031126009Pin · broken(CAN) BLADE PIN FOUND TO BE BROKEN WHERE THREAD MEETS THE PIN.SDR CA031017004Fuel Control · failed(CAN) AFTER LANDING, THROTTLE WAS SNAP ROLLED TO IDLE. N2 WAS NR IMMEDIATELY INCREASED TO 105 PERCENT AND STABILIZED. ENGINE WAS SHUT DOWN BY ROLLING THROTTLE TO CUT OFF. NOTE: ENGINE WAS DUE FOR HOT SECTION, SO RENTAL WAS INSTALLE4D. SUSPECT ENGINE, FCU AND GSDR CA030903005Bearing · failed(CAN) AS DESCRIBED ABOVE ROLLER BEARING PN 369D25146 INNER RACE FAILURE. IN THIS CASE THIS FAILURE WAS DETECTED BY THE AIRCRAFTS WARNING SYSTEM. THE AIRCRAFT WAS FOR CED TO MAKE AN UNSCHEDULED LANDING. THE FAILURE OF THIS P/N BEARING HAS BEEN SEEN ON MORE THANSDR CA030612005Case · cracked(CAN) ROUTINE INSPECTON AND CHANGING FUEL NOZZLE IT WAS SUSPECTED THAT THERE WAS A CRACK ALONG THE WELD WHERE THE FUEL NOZZLE ADAPTER IS ATTATCHED TO THE END OF OUTER COMBUSTION CASE. ON CLOSER INSPECTION IT WAS NOTED THAT THE CRACK COVERED OVER HALF OF THE WSDR CA030612006Case · cracked(CAN) AFTER INPSECTION WITH THE ENGINE RUNNING A LEAK CHECK WAS CARRIED OUT BY PLACING A HAND IN AREA OF THE FUEL NOZZLE AND AIR WAS FELT. THE ENGINE WAS SHUT DOWN AND A CLOSE INSPECTION WAS CARRIED OUT IN THE AREA OF WHERE THE NOZZLE ADAPTER PLATE IS WELDED TSDR CA031031006Governor · failed(CAN) NR DROOPING TO 97 WITHOUT RECOVERY UNDER POWER AND OVER SPEEDING TO 107 WHEN POWER REDUCED.SDR CA030312016Bearing · making metal(CAN) DURING A FLIGHT THE ENGINE CHIP LIGHT ILLUMINATED, THE PILOT LANDED AND THE LOWER CHIP PLUG WAS INSPECTED AND HAD SHINY PARTICLES ON IT. THE AIRCRAFT WAS GROUND RUN FOR 15 MINUTES AND SENT BACK FLYING. THE NEXT DAY HE FLEW FOR 1 HOUR AND HAD ANOTHER CHISDR CA030210004Servo · leaking(CAN) HYDRAULIC SERVO LEAKING. REMOVED FOR REPAIR.SDR CA030127001Turbine · seized(CAN) DURING FIRST START OF THE ENGINE, FOLLOWING A TURBINE CHANGE, MAIN ROTOR BLADES INITIALLY STARTED TURNING BUT THEN STOPPED BEFORE ENGINE ACCELERATED TO IDLE SPEED. THE START WAS ABORTED.AME ATTEMPTED TO TURN THE MAIN ROTOR BLADES BACKWARDS BUT WAS UNABLESDR CA020412012Bushing · worn(CAN) TRANSMISSION STOP MOUNT HAS WORN BUSHINGS. REPLACED.SDR CA011211013Strut · cracked(CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE.SDR CA010725022Arm · damaged(CAN) FOUND NUT OF ACTUATOR ARM LOOSE IN ARM. UNIT REPLACED AND AIRCRAFT RETURNED TO SERVICE AFTER ADJUSTMENTS.SDR CA010725023Fitting · cracked(CAN) THE FITTING HAD TO BE REPLACED DUE TO CRACK. IT APPEARS TO HAVE CRACKED DUE TO INCORRECT INSTALLATION. THERE WAS A 100 INCH GAP BETWEEN THE LONGERON AND THE FITTING AND THIS PLACED THE FITTING UNDER STRESS. THE FITTING WAS REPLACED BY A NEW PART WITH CARSDR CA010725031Hose · leaking(CAN) DURING REFUELING OPERATION, FUEL WAS OBSERVED LEAKING FROM TANK VENT HOSE ASSEMBLY WHEN TANK WAS FILLED TO CAPACITY. HOSE APPEARS TO HAVE DETERIORATED WITH AGE ALLOWING FUEL TO LEAK. DUE TO THIS DEFECT ANOTHER AIRCRAFT WAS VERIFIED BY PRESSURE TESTING THSDR CA010704025Shaft · corroded(CAN) DURING AN UNSCHEDULED MAINTENANCE REMOVAL OF THE UNIT IT WAS NOTED THAT THERE WAS EXCESSIVE PITTING CORROSION ON THE INNER SHAFT IN THE AREA WHERE THE FELT WIPER OF THE FORWARD SEAL RIDES. THE WIPER APPEARS TO ABSORB MOISTURE AND HOLDS IT IN CONTACT WITHSDR CA000511016Bearing · making metal(CAN) NR 1 COMPRESSOR ROLLER BEARING MAKING METAL.SDR CA000511026Hook · wrong part(CAN) ROTORCRAFT WAS CARRYING A SKIDOO ON THE CARGO HOOK WHEN THE PILOT FELT IT RELEASE. RETURNED TO BASE WHERE THE HOOK AND MECHANICAL AND ELECTRICAL RELEASES WERE CHECKED. AS A PRECAUTIONARY MEASURE, THE HOOK WAS REPLACED. THE REMOVED ASSY WAS TESTED AS PSDR CA000209070Mast · blistered(CAN) INTERNAL EXAMINATION OF THE MAST REVEALED CORROSION APPROX 1/2 TO 2/3 UP FROM THE BOTTOM SIDE OF THE MAST BORE. CADMIUM PLATING APPEARED TO BE SEPARATING AND BLISTERING THE ZINC CHROMATE PRIMER. MAST WAS THEN STRIPPED, CLEANED, INSPECTED AND GIVEN A COASDR CA990817025Igniter · failed(CAN) ROTORCRAFT WOULD NOT START. PROBLEM WAS WITH FAULTY IGNITER PLUG.SDR CA990531004Compressor · failed(CAN) IN CRUISE AT 5,300 FEET, WITH AUTO-LIGHT AND ANTI-ICE SELECTED ON, A LOUD EXPLOSION WAS HEARD FOLLOWED BY AN IMMEDIATE YAW TO THE LEFT. THE ENGINE HORN ALSO BECAME AUDIBLE, SO AN AUTO ROTATION WAS CARRIED OUT. ON DESCENT, THE TAIL ROTOR CONTACTED THE T
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