Beech A100

Service difficulty reports · 472

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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 aircraft_model_key = 'A100'
  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 CA130911005Skin · cracked(CAN) DURING A PHASE 3 INSPECTION, A CRACK WAS FOUND ON THE LT HORIZONTAL STABILIZER UPPER SURFACE. THERE WAS OIL CANNING ON THE UPPER SKIN, NEAR THE CRACK WHICH INDICATE PROBABLE DAMAGE AT THE RIB. DURING REPAIR, NO RIB WERE FOUND DAMAGED BUT ON SKIN STIFFESep 10, 2013 · Beech A100 · Horizontal Stabilizer, Plate/SkinSDR CA130906001Clevis · broken(CAN) UPON RETRACTION TEST, DURING PHASE 1 INSPECTION, MAINTENANCE PERSONNEL NOTICED THAT THE BOLT, PN AN24-23A, ATTACHING THE DRAG LEG TO THE RETRACTION ACTUATOR FORK WAS TOO LONG, NOT SEATING AGAINST THE YOKE. WHILE TRYING TO REMOVE THE BOLT, IT WAS FOUND BSep 3, 2013 · Beech A100 · Nose/Tail Landing Gear Strut/AxleSDR CA130808001Torque Shaft · corroded(CAN) ELEVATOR TORQUE SHAFT VISUAL INSPECTION INDICATED SOME CORROSION ON THE BOTTOM OF THE SHAFT AFTER REMOVAL IT WAS DISCOVERED THAT CORROSION HAD CREATED MULTIPLE HOLES IN THE SHAFT. NOTE THIS SHAFT GETS WET AFTER RAIN OR AIRCRAFT WASHING AND MAY STAY SUSPAug 7, 2013 · Beech A100 · Elevator StructureSDR CA130729001Torque Sensor · failed(CAN) TWO REJECTED TAKE OFFS WERE REPORTED DUE TO THE AUTOMATIC TAKEOFF POWER CONFIGURATION SYSTEM NOT ARMING. THE PILOT SAW THAT THE ENGINE ANALOG TORQUE GAGE INDICATED ZERO. TROUBLESHOOTING LED TO THE REPLACEMENT OF THE TORQUE SENSOR, AUTOFEATHER UNIT AND Jul 14, 2013 · Beech A100 · Engine (Turbine/Turboprop)SDR CA131103006Radar · failed(CAN) THE CREW NOTED THAT THE RADAR DISPLAY WOULD POSSIBLY PAINT INACCURATE IMAGES OF THE WEATHER SYSTEMS. MAINTENANCE INVESTIGATED THE PROBLEM TO BE IN THE DISPLAY MONITOR. THE UNIT WAS REPLACED AND THE SYS GROUND FUNCTION CHECKED SERVICEABLE.Jul 4, 2013 · Beech A100 · Weather Radar SystemSDR CA130704003Diaphragm · torn(CAN) DURING APROACH, THE PILOT FOUND THAT THE LT ENGINE POWER WAS LOW. AFTER A GROUND RUN IT APPEAR THAT THIS ENGINE WAS UNDER POWER. BLEED VALVE HAS BEEN REMOVE AND THE DIAPHRAGM FOUND TEAR WERE IT NORMALLY BEND. PART HAS BEEN REPLACE AND ACFT RETURN IN SJun 20, 2013 · Beech A100 · Compressor Bleed ValveSDR CA130607002Gear · damaged(CAN) DURING A PHASE INSPECTION WHILE COMPLETING THE LANDING GEAR SWINGS THE RT GEAR ACTUATOR WAS MAKING AN UNUSUAL NOISE. THE ACTUATOR WAS REPLACED AND TESTED SERVICEABLE. UPON DISASSEMBLE OF THE ACTUATOR THE GEAR TEETH WERE FOUND TO BE CHIPPED AND BROKEN.Jun 4, 2013 · Beech A100 · Landing Gear ActuatorSDR CA130606007Exhaust Duct · cracked(CAN) EXHAUST DUCT INNER SECTION CRACKED, THREAD AT TURBINE EXIT, AT BEARING NR 3, THIS CAUSE THE TO DAMAGE THE T/E OF TURBINE BLADE.Jun 4, 2013 · Beech A100 · Engine Collector/Tailpipe/NozzleSDR CA130430021Torque Tube · cracked(CAN) OUTBOARD CASTING CRACKED FROM TAPER PIN HOLE TO EDGE VISUAL INSPECTION COMPLETE TORQUE TUBE ASSEMBLY.Apr 29, 2013 · Beech A100 · Elevator Control SystemSDR CA130422012Spar · damaged(CAN) ON A ROUTINE NDT WING FITTING INSPECTION (AS PER THE SIRM), IT WAS FOUND THAT THE FASTENERS THAT HOLD THE FITTING ON THE SPAR HAD WORKED LOOSE AND HAD BEEN "SMOKING". IN ORDER TOO INVESTIGATE FURTHER, THE WINGS HAD TO BE REMOVED AS WELL AS THE WING END RApr 10, 2013 · Beech A100 · Wing SparSDR CA130412005Shaft · worn(CAN) WHILE DOING PHASE INSPECTION MAINTENANCE CARRIED OUT INSPECTION OF THE STARTER/GENERATOR DRY SPLINE AND FOUND IT TO BE CLOSE TO LIMITS. ENGINE WAS REMOVED, ACCESSORY GEARBOX SPLIT, GEARSHAFT, PN 3021565. REMOVED AND O/H GEARSHAFT INSTALLED. ENGINE REIApr 9, 2013 · Beech A100 · Accessory GearboxesSDR CA130328008Contact · corroded(CAN) AFTER TAKEOFF, PILOT SELECTED GEAR UP, GEAR DID NOT RETRACT, PILOT SELECTED GEAR HANDLE BACK TO DOWN POSITION AND CONTINUED TO DESTINATION. UPON INSPECTION BY MAINTENANCE FOUND LANDING GEAR REMOTE CIRCUIT BREAKER RELAY CONTACTS EXTREMELY PITTED. RELAY Mar 25, 2013 · Beech A100 · Landing Gear System WiringSDR CA130325018Arm · broken(CAN) PILOT REPORTED THAT THE ACFT WAS HARD TO STEER. MAINTENANCE FOUND THE PILOTS RT RUDDER PEDAL ARM HAD BROKEN OFF WHERE THE PEDAL IS ATTACHED TO THE ARM. THE ARM WAS REPLACED AND THE ACFT WAS RETURNED TO SERVICE. NOTE: THERE IS AN INSPECTION FOR THIS INMar 21, 2013 · Beech A100 · Rudder Control SystemSDR CA130325019Torque Link · cracked(CAN) DURING A SPECIAL NDT INSPECTION OF THE MLG TORQUE LINKS, A VERY SMALL CRACK WAS FOUND JUST STARTING TO FORM IN THE RADIUS OF THE UPPER LINK. THIS NDT IS A SELF IMPOSED ADDITIONAL INSPECTION, STARTED AFTER WE FOUND SIMILAR SMALL CRACKS IN THE SAME RADIUSMar 18, 2013 · Beech A100 · Landing Gear Retraction/Extension SystemSDR CA130307005Wire Harness · damaged(CAN) AIRCRAFT TURNED BACK SHORTLY AFTER TAKEOFF BECAUSE OF ITT INDICATION DROP TO 220 DEGREES. ENGINE SPLIT AND T5 THERMOCOUPLE HARNESS BLOCK WIRING FOUND INTERMITTENT, WHERE PEN SHOWS ON PIC, WHEN MOVED BY HAND HARNESS BLOCK REPLACED BY O/H UNIT.Mar 5, 2013 · Beech A100 · Engine Indicating System WiringSDR CA130402009Light · malfunctioned(CAN) ON A ROUTINE FLIGHT FROM THE CREW WAS IN THE CLIMBOUT WHEN THE CO-PILOT ADJUSTED THE COCKPIT LIGHTING FROM DIM TO BRIGHT. ALMOST IMMEDIATELY THE CREW EXPERIENCED SMOKE AND FUMES IN THE COCKPIT, THE CREW ELECTED TO RETURN TO DEPARTURE AND LANDED WITHOUT Feb 11, 2013 · Beech A100 · Flight Compartment LightingSDR CA130211004Motor · failed(CAN) UPON LANDING, THE FLIGHT CREW NOTICED SMOKE BUILDING IN THE PASSENGER CABIN. THE ACFT WAS STOPPED ON THE RUNWAY, THE CIRCUIT BREAKER FOR THE FLAP MOTOR WAS PULLED AND ALL POWER AND ENGINES WERE SHUTDOWN. MAINTENANCE PERSONNEL FOUND THE FLAP MOTOR TO BE Feb 8, 2013 · Beech A100 · Trailing Edge Flap ActuatorSDR CA130402008Rmi · malfunctioned(CAN) ON A ROUTINE FLIGHT, ON APPROACH THE CREW NOTICED THE RMI NOT PROPERLY INDICTING IN THE CO-PILOT SIDE. THE CAPTAIN CARRIED OUT THE LANDING FROM THE LT SIDE WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND A DEFECTIVE RMI, THE UNIT WAS REPLACED WITH AN O/H UJan 22, 2013 · Beech A100 · Navigation SystemSDR CA130124002Motor · inoperative(CAN) ON FINAL, CREW ATTEMPTED TO LOWER LANDING GEAR WITHOUT SUCCES. OVERSHOOT WAS INITIATED, LANDING GEAR EXTENDED MANUALLY AND UNEVENTFULL LANDING FOLLOWED. MAINTENANCE DISCOVERED LDG MOTOR WORKING ONLY IN RETRACT MODE. UNABLE TO LOWER LDG ON JACKS. LDG MOJan 22, 2013 · Beech A100 · Landing Gear ActuatorSDR CA130115004Computer · failed(CAN) PITCH TRIM COMPUTER HAS A 3 AMP FUSE INSTALLED. THE PITCH TRIM MOTOR IS RATED TO DRAW UP TO 6 AMPS UNDER HEAVY LOAD SITUATIONS. ANY TIME PITCH MOTOR DRAWS HEAVY LOAD, INTERNAL PITCH COMPUTER 3 AMP FUSE BLOWS, DISABLING AUTO PILOT SYSTEM. THE MFG IS AWAJan 15, 2013 · Beech A100 · Autopilot ComputerSDR CA121122001Bracket · cracked(CAN) DURING STABILIZER STABILIZER POINT INSPECTION, THE RT PIVOT WAS FOUND TO HAVE PLAY. DURING BEARING REPLACEMENT, IT WAS FOUND THE BRACKET PN 115-44031-2 WAS CRACKED. THE CRACK IS ONLY VISIBLE WHEN THE HINGE IS DISMANTLED. AS A PRECAUTION, THE LT HINGE Nov 20, 2012 · Beech A100 · Horizontal Stabilizer StructureSDR CA121025007Skin · damaged(CAN) DURING A ROUTINE PHASE INSPECTION MAINTENANCE, IT WAS DECIDED TO REPLACE THE UPPER FAIRINGS THAT MAKE THE TRANSITION FROM THE CENTER SECTION WING TO THE CABIN, BECAUSE OF THE AGE AND WE ARE CONSIDERING PAINTING THE ACFT THIS WINTER. ONCE THE FAIRING WASOct 19, 2012 · Beech A100 · Fuselage Main, Plate/SkinSDR CA121024003Rib · broken(CAN) DURING MAINTENANCE, IT WAS FOUND THAT THE LT STABILIZER UPPERSKIN WAS CRACKED AROUND BS 21.476. OPENING WAS PERFORMED UNDER THE STABILIZER AND IT WAS FOUND THAT THE RIB AFT PN 115-620010-255 WAS BROKEN AT SAT 21.470. THE RIB, PN 115-620010-209 AT BS 28Oct 19, 2012 · Beech A100 · Horizontal Stabilizer, Spar/RibSDR CA121023001Annunciator · false activation(CAN) DURING CRUISE AND OF COURSE GEAR UP POSITION, PILOTS NOTICED AN ANNUNCIATION LIGHT THAT SEEMED INTERMITTENT. DECIDED TO TRY TO FIX IT, RE-POSITION BULB OR REPLACE IT. TO DO SO, PUSHED ON PRESS-TO-TEST BUTTON TO TURN ALL ANNUNCIATOR LIGHTS ON. AS SOONOct 18, 2012 · Beech A100 · Landing Gear Retraction/Extension SystemSDR CA121022022Solenoid Valve · malfunctioned(CAN) DURING A FLIGHT, THE TRANSITION LIGHT CAME ON AND THE LIGHT INDICATING THAT THE HYDRAULIC PUMP IS WORKING WAS OFF. EMERGENCY GEAR EXTENSION CUTOUT. IT WAS LATER FOUND AT THE HANGAR THAT SOLENOID VALVE, PN 25400 WAS DIRTY AND WAS NOT CLOSING PROPERLY ASep 27, 2012 · Beech A100 · Landing Gear Retraction/Extension SystemSDR CA121022021O-Ring · cut(CAN) TRANSITION LIGHT CAME ON IN FLIGHT. EMERGENCY EXTENSION C/OUT. FOUND THAT ALL HYDRAULIC FLUID WAS LOST THRU THE LT LANDING GEAR ACTUATOR. O-RING AROUND THE ACTUATOR SHAFT WAS FOUND TO BE BROKEN. O-RING REPLACED AND RETRACTION TEST C/OUT WITHOUT ANY OSep 24, 2012 · Beech A100 · Landing Gear ActuatorSDR CA121025005Check Valve · sticking(CAN) ON A ROUTINE FLIGHT, THE CREW EXITED THE ACFT AND ON POST FLIGHT WALK AROUND AND DISCOVERED FUEL POURING FROM THE LT AUXILIARY TANK VENT. THE FBO CONTACTED EMERGENCY SERVICES AND THE PILOTS CONTACTED COMPANY MAINTENANCE. MAINTENANCE WENT INSIDE THE GEASep 7, 2012 · Beech A100 · Aircraft Fuel Distribution SystemSDR CA120911005Placard · missing(CAN) DURING AN INSPECTION, IT WAS NOTICED THAT THE CABIN DOOR PLACARD DID NOT MEET THE REQUIREMENTS OF SERVICE INSTRUCTION, NR 0818-016, REV II. THIS SERVICE INSTRUCTION IS MANDATED BY AD 76-10-10 WHICH REQUIRED DECAL 101-430124-1 BE ADDED TO THE DOOR INSTRUSep 6, 2012 · Beech A100 · Placards and MarkingsSDR CA120904011Screw · wrong part(CAN) IMPROPER LENGTH OF SCREW WAS USED TO ATTACH, PN 115-440029-601, TAIL CONE ASSY CAUSING THE HORIZONTAL STABILIZER. HINGE BRACKET, PN 115-440031-4 TO BE DAMAGED BEYOND REPAIRABLE LIMITS.Sep 4, 2012 · Beech A100 · Empennage StructureSDR CA120918011Blade · damaged(CAN) THE ENGINE HAD AN IFSD UNDER UNKNOWN CIRCUMSTANCES. POST FLIGHT INSPECTION FOUND A FRACTURED FUEL LINE AND COMPRESSOR TURBINE BLADE DAMAGE.Aug 17, 2012 · Beech A100 · Turbine Engine Compressor SectionSDR CA121022020O-Ring · cut(CAN) DURING THE FLIGHT, THE LANDING GEAR TRANSITION LIGHT DID COME ON. EMERGENCY LANDING GEAR EXTENSION C/OUT. LATER AT THE HANGAR, IT WAS FOUND THAT HYDRAULIC FLUID WAS ALL LOST. O-RING AROUND THE SHAFT WAS FOUND CUT ON RT MAIN HYDRAULIC ACTUATOR, PN: ADAug 5, 2012 · Beech A100 · Landing Gear ActuatorSDR CA120813009Control System · malfunctioned(CAN) AFTER STARTING THE NR 1 ENGINE, IN PREPARATION FOR A REVENUE FLIGHT , THE CLA WAS MOVED AND THE PROPELLER SPEED EXCEEDED 120 PERCENT. THE FLIGHT CREW SHUTDOWN THE ENGINE. PASSENGERS WERE DISEMBARKED SAFELY. NO FAULTS RECORDED IN ELECTRONIC ENGINE CONTROAug 5, 2012 · Beech A100 · Propeller Controlling SystemSDR CA120809002Line · cracked(CAN) AFTER TAKEOFF, ODOR OF FUEL IN COCKPIT. ACFT LANDED BYPASS FUEL LINE FROM FCU TO START CONTROL FOUND CRACKED. NOTE THIS IS THE THIRD LINE FOUND CRACKED IN THE LAST 3 MONTHS. LINE CHANGED, PROP BALANCED AND ADDITIONAL INSPECTIONS COMPLETED FOR VIBRATIOAug 5, 2012 · Beech A100 · Engine Fuel DistributionSDR CA120811002Bleed Valve · malfunctioned(CAN) PILOT REPORTED THAT THE RT ENGINE WAS NOT MAKING AS MUCH TORQUE AT ALTITUDE AS LT ENGINE. MAINTENANCE DISCOVERED A FAULTY BLEED VALVE, THE VALVE WAS REPLACED WITH AN O/H UNIT AND THE ENGINE WAS GROUND FUNCTION CHECKED SERVICEABLE.Aug 4, 2012 · Beech A100 · Compressor Bleed ValveSDR CA120811001Indicator · malfunctioned(CAN) ON A ROUTINE FLIGHT, THE PILOT NOTICED A 50 DEGREE SPLIT IN THE ITT INDICATION. MAINTENANCE DISCOVERED A FAULTY GAUGE, THE GAUGE WAS REPLACED AND THE SYS WAS GROUND FUNCTION CHECKED SERVICEABLE.Aug 1, 2012 · Beech A100 · Engine Temperature Indicating SystemSDR CA120727008Tube · cracked(CAN) WHILE PERFORMING HOT SECTION BOROSCOPE, AME DISCOVERED ONE COMPRESSOR TUBINE GUIDE VANE DAMAGED. ENGINE WAS SPLIT TO PERMIT HOT SECTION REPAIR. ONCE THE ENGINE OPEN, 1 DIFFUSER EXIT DUCT WAS FOUND CRACKED AND A PIECE OF THE DIFFUSER EXIT DUCT WAS FOUND Jul 24, 2012 · Beech A100 · Turbine Engine Compressor SectionSDR CA120626009Torque Tube · cracked(CAN) ELEVATOR TORQUE TUBE CRACKED, PREVIOUSLY REPLACE MARCH 2011, PN 115-610010-383.Jun 26, 2012 · Beech A100 · Elevator Control SystemSDR CA120629003Diffuser · cracked(CAN) AFTER RECEIVING ENGINE, SN PCE-51835, BACK FROM OVERHAUL APPROXIMATELY 300 HRS AFTER AN OPEN TREND REQUEST BECAME OPEN ON THAT ENGINE STATING THE TEMPERATURE HAD INCREASED BY 20 DEGREES. SEVERAL ATTEMPTS WERE MADE TO CORRECT THE CONDITION TARGETING CALIJun 26, 2012 · Beech A100 · Turbine Engine Combustion SectionSDR CA120504002Flap Track · cracked(CAN) ON MAINTENANCE WALKAROUND, THE RT OTBD FLAP HAD MORE PLAY THAN USUAL. FLAP WAS REMOVED AND THE INBD FLAP TRACK WAS FOUND TO BE CRACKED ON THE REAR TIP. TRACK REPLACED AND ACFT RETURNED TO SERVICE.May 1, 2012 · Beech A100 · Trailing Edge FlapsSDR CA120502014Brake Disc · damaged(CAN) FOLLOWING ROUTINE FLIGHT, THE CREW WAS PUSHING THE ACFT INTO THE HANGAR AND NOTICED THE NR 3 TIRE WAS SKIDDED AND SUBSEQUENTLY FLAT. WHEN MAINTENANCE WENT TO CHANGE THE TIRE THEY NOTICED THAT THE BRAKE DISC HAD ACTUALLY BROKEN INTO 4 PIECES JAMMED UP AGApr 25, 2012 · Beech A100 · Landing Gear Brake SystemSDR CA120326012Switch · intermittent(CAN) ON A ROUTINE FLIGHT, IT WAS OBSERVED THAT THE "GEAR IN TRANSIT LIGHT" WOULD FLICKER ON AND OFF. MAINTENANCE INSPECTED THE NLG AND FOUND THE SWITCH WAS NOT ADJUSTED CORRECTLY. FURTHER INSPECTION REVEALED THAT THE ACFT VOLTAGE WAS SET SLIGHTLY LOWER THAMar 23, 2012 · Beech A100 · Landing Gear Position and WarningSDR CA120326013Limit Switch · frozen(CAN) ON A ROUTINE FLIGHT, IT WAS OBSERVED THAT WHEN THE FLAP HANDLE WAS SELECTED TO APPROACH THE FLAPS DID NOT MOVE. THE CREW CONDUCTED A FLAPLESS LANDING WITHOUT INCIDENT. MAINTENANCE DISCOVERED THAT THE UP LIMIT SWITCH WAS FULL OF WATER A FROZEN, FURTHER Mar 20, 2012 · Beech A100 · Trailing Edge Flap Control SystemSDR CA120326011Drag Brace · damaged(CAN) ON A ROUTINE FLIGHT, IT WAS OBSERVED THAT THE GEAR IN TRANSIT LIGHT, WOULD FLICKER ON AND OFF. MAINTENANCE INSPECTED THE NLG AND FOUND HIGHER THAN NORMAL PLAY IN THE NLG DRAG BRACE. IT WAS BELIEVED THAT DUE TO MORE THAN NORMAL PLAY AND IF THE PLANE ENCMar 14, 2012 · Beech A100 · Landing Gear Retraction/Extension SystemSDR CA120312026Tire · damaged(CAN) DURING DAILY INSPECTION THE LT INBD TIRE WAS MISSING A SECTION OF TREAD APPROXIMATELY 12" X 2". TIRE WAS REPLACED AND CHECKED SERVICEABLE.Mar 5, 2012 · Beech A100 · TireSDR AXSA20120219001Module · not seatedCREW REPORTED THAT ON CLIMBOUT, NOTED RMI NR 1 HAD A NAV FLAG, CREW BRIEFLY TUNED IN GDM VOR. ONCE GDM WAS TUNED IN THEY NOTED THAT NAV NR 1 ALSO PRESENTED A NAV FLAG AND NAV NR 2 WAS FULLY OPERATIONAL. ON LEVEL OFF, CREW DECIDED TO ENGAGE AUTOPILOT. ONCFeb 19, 2012 · N91RK · Beech A100 · Autopilot SystemSDR CA120220008Controller · malfunctioned(CAN) ON A ROUTINE FLIGHT, THE CONTROL OF THE CABIN PRESSURE BECAME ERRATIC, THE ACFT LANDED WITHOUT INCIDENT. CREW REPORTED THAT THE CABIN REACHED MAX DIFFERENTIAL, THEY WERE NOT ABLE TO ADJUST THE CABIN ALTITUDE AND IN ORDER TO LAND THEY SHUT THE ENGINE BLFeb 9, 2012 · Beech A100 · Cabin Cooling SystemSDR CA120123010Handle · damaged(CAN) DURING ROUTINE FLIGHT ON THE CLIMB OUT THROUGH 10,000 FEET, THE CREW NOTICED A DOOR LIGHT COME "ON". THE CREW ELECTED TO TURN THE AIRCRAFT AROUND AND GO BACK TO AIRPORT TO INVESTIGATE. UPON INVESTIGATION, IT WAS NOTICED THAT THE DOOR HANDLE WAS NOT FULJan 19, 2012 · Beech A100 · Passenger/Crew DoorsSDR CA120123008Knob · broken(CAN) IT WAS MINUS 40 ON A ROUTINE FLIGHT FROM CYOJ TO CYXD ON LANDING THE CABIN FAILED TO DE-PRESSURIZE NORMALLY. MAINTENANCE DISCOVERED THAT THE PILOTS BROKE THE KNOB OFF THE RATE CONTROLLER WITH THEIR SAUSAGE FINGERS, (NO WONDER THE AIRCRAFT WOULD NOT DEPREJan 17, 2012 · Beech A100 · Air Conditioning SystemSDR CA120106004Circuit Breaker · failed(CAN) LEFT ENGINES STARTER WONT TURN, CONTROL CIRCUIT BREAKER REPLACED.Jan 2, 2012 · Beech A100 · Engine Starting System WiringSDR CA111219017Static Inverter · failed(CAN) ON A ROUTINE MAINTENANCE POST RUN INSPECTION IT WAS OBSERVED THE NR 1 INVERTER FAILED. O/H 42 HRS PREVIOUSLY BY DUCEY AVIONICS IT WAS VERIFIED THAT THE UNIT HAD FAILED. THE UNIT WAS R & R WITH OUT FURTHER INCIDIENT. WHAT ELSE IS NEW "DUCEY AVIONICS" HDec 14, 2011 · Beech A100 · AC Inverter
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