U/A Canada PT6A-21

Service difficulty reports · 310

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 = 'PT6A21'
  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.

SDR CA971028007Push Rod · worn(CAN) DURING A PHASE 3 INSPECTION, IT WAS FOUND THAT THE PILOTS RUDDER ARM ASSEMBLY (P/N 50-524415-10) HAD APPROXIMATELY 0.020 INCHES DEEP WEAR ON THE INNER SURFACE OF THE FORK LUG WHERE THE PUSH ROD ATTACHES RH ARM. UPON REMOVAL OF THE PUSH ROD, IT WAS FOUND Oct 20, 1997 · Beech C90A · Rudder Control SystemSDR CA970612005Hub · corroded(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. CUSTOMER OPTED FOR EARLY AD 96-18-14 COMPLIANCE. PROPELLER HUB WAS FOUND CORRODED, HUB REPLACED WITH HUB S/N BUA 19988.Jun 4, 1997 · Beech C90 · Propeller Hub SectionSDR CA970609025Hub · corroded(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. HUB FOUND CORRODED. NEW HUB S/N BUA 19986 INSTALLED AND EARLY COMPLIANCE WITH FAA AD 96-18-14 CARRIED OUT.May 30, 1997 · Beech C90 · Propeller Hub SectionSDR CA961105003Fuel Line · blocked(CAN) DURING CLIMB PILOT REPORTED FUEL LEAK AT THE TRAILING EDGE OF THE RIGHT HAND WING. RH ENGINE SHUT DOWN AND SINGLE ENGINE LANDING CARRIED OUT. EVENTUALLY FOUND THAT WHEN LINE WAS REMOVED FOR OBSTRUCTION TEST, THE LINE WAS FOUND BLOCKED. DURING MANUFACTURIOct 28, 1996 · Beech C90A · Aircraft Fuel Distribution SystemSDR 96ZZZX5325Retain Ring · detachedON ENGINE START-UP TO IDLE, ENGINE OIL PRESSURE GAUGE SHOWED NO OIL PRESSURE. FOUND OIL PRESSURE RELIEF VALVE RETAINING RING WAS NOT SEATED IN HOUSING AND RELIEF VALVE HAD FALLEN PART WAY OUT OF HOUSING. SUBMITTER STATED WHEN INSTALLING PRESSURE RELIEF VALVEOct 3, 1996 · N3263C · Beech C90 · Turbine Engine Oil SystemSDR CA960729007Piston · cracked(CAN) DURING ROUTINE MAINTENANCE IT WAS OBSERVED THAT THE RIGHT HAND INBOARD FLAP ACTUATOR PISTON WAS CRACKED ALONG ITS LENGTH. CRACK ORIGINATED AT THE PLUG HOLE. REFERENCE BEECH IPC 27-50-30, FIG 50-30, ITEM 15. SDR 960807007 PERTAINS TO SAME CONDITION.Jul 17, 1996 · Beech C90A · Trailing Edge Flap ActuatorSDR CA960731001Switch · failed(CAN) ON LANDING GEAR DOWN AND LOCKED, PILOT SELECTED FULL FLAPS AND THE RED LIGHT IN THE GEAR HANDLE CAME ON, WITH GEAR WARNING HORN ACTIVATED. AIRCRAFT LANDED OK AFTER TOWER CONFIRMATION OF GEAR DOWN. INVESTIGATION FOUND THE LEFT MAIN DOWN LOCK SWITCH ASSEMBJul 13, 1996 · Beech C90A · Landing Gear Position and WarningSDR CA960614007Retaining Clip · failed(CAN) ON INSPECITON OF THE ENGINE FIRE EXTINGUISHER ELECTRICAL SYSTEM, IT WAS NOTED THAT THE FIRE EXTINGUISHER MICROSWITCH ON THE PANEL ACTIVATING BUTTON HAD COME OFF THE HOLDING CLIP RENDERING THE BUTTON INOPERATIVE. THE SWITCH MANUFACTURER - RAYTHEON - INDICJun 6, 1996 · Beech C90A · Extinguishing SystemSDR CA960711015Retaining Clip · failed(CAN) ON INSPECTION OF THE ENGINE FIRE EXTINGUISHER ELECTRICAL SYSTEM, IT WAS NOTED THAT THE FIRE EXTINGUISHER MICROSWITCH ON THE PANEL ACTIVATING BUTTON HAD COME OFF THE HOLDING CLIP, RENDERING THE BUTTON INOPERATIVE. THE SWITCH MANUFACTURER - RAYTHEON - INDIJun 6, 1996 · Beech C90A · Extinguishing SystemSDR CA960507003Flux Valve · oil soaked(CAN)AIRCRAFT COMPASS SYSTEM REPORTED UNRELIABLE. EXAMINATION OF COMPASS COMPONENTS AND WIRING REVEALED THAT THE FLUX VALVE WAS SATURATED WITH INSTRUMENT OIL. COLLINS CONFIRMED THAT THE LOSS OF OIL COULD R ESULT IN FAILURE OF THE COMPONENT. FLUX VALVE REPLACEDFeb 8, 1996 · Beech C90A · Directional Gyro and Indicating System
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