Beech C90A

Service difficulty reports · 461

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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 = 'C90A'
  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 2006FA0000471Wheel Half · crackedLEFT MAIN WHEEL (INBOARD HALF) FOUND CRACKED. PROBLEM SHOWED ITSELF DUE TO WHEEL/TIRE ASSY SUFFERING A SLOW LEAK OF AIR PRESSURE. THIS IS NOT THE SAME PROBLEM REPORTED FOR THIS AIRCRAFT ON 4/27/2006. THIS IS A PREVIOUS OCCURRENCE ON THE OTHER SIDE. BOTH MAApr 12, 2006 · N164WS · Beech C90A · Wheel/Ski/FloatSDR CA060425009Engine · malfunctionedON APPROACH, ENGINE TORQUE AND FUEL FLOW WERE SEEN TO FLUCTUATE. THE ENGINE WAS SUBSEQUENTLY SHUT DOWN IN FLIGHT. P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.Apr 9, 2006 · Beech C90A · Engine (Turbine/Turboprop)SDR CA060317009Bearing · failedVISUAL INSPECTION CARRIED OUT IAW OPERATION FOUR. NOTICED METAL DUST ON BACK OF THE ACCESSORY GEARBOX AND FOUND IT TO BE MAGNETIC. REMOVED STARTER GENERATOR AND FOUND THE QUILL SHAFT BEARING HAD FAILED. UNIT WAS REMOVED FROM SERVICE.Mar 17, 2006 · Beech C90A · Starter-GeneratorSDR CA060320001Seal · damagedIN CRUISE 16,000 FT, NOTICED OIL LEAK ON TOP RT FWD ENG COWL. LEAK PROGRESSIVELY GOT WORSE, PILOTS ELECTED TO RETURN TO BASE. EVEN THOUGH ENG OIL TEMP AND PRESS NORM, PILOTS SHUTDOWN RT ENG. CREW DECLARED EMERG. BECAUSE QTY OF OIL LOST, PROP SHAFT SEAL SHOULMar 16, 2006 · Beech C90A · Propeller AssemblySDR CA060403014Seal · leakingDURING FLIGHT, AN ENGINE OIL LEAK WAS OBSERVED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A LEAKING PROPELLER SHAFT SEAL AND A LOOSE BETA VALVE RETAINING NUT.Mar 16, 2006 · Beech C90A · Propeller AssemblySDR CA060317008Pump · leakingVISUAL INSPECTION CARRIED OUT IAW SERVICEABILITY CHECK. PRE-DISPATCH CHECK NOTICED FUEL UNDER THE RT ENGINE. INSPECT FUEL FILTER AND DRAINS WITH THE BOOST PUMP ON AND NO LEAKAGE WAS FOUND. REMOVED FUEL PUMP DRAIN HOSE AND A LARGE AMOUNT OF FUEL WAS EXPELLED Mar 15, 2006 · Beech C90A · Engine Fuel PumpSDR CA060130002Windscreen · failedWHILE IN CRUISE FLIGHT AT FL230, THE LT WINDSHIELD INNER PANE SHATTERED. THE WINDSHIELD ANTI-ICE HAD BEEN SELECTED AT NORMAL SINCE DEPARTURE AND THE OAT WAS –38°C. THE CREW CONTACTED ATC TO DECLARE AN EMERGENCY AND REQUESTED RETURN TO AIRPORT. THE CREW THENJan 25, 2006 · Beech C90A · Flight Compartment WindowsSDR CA060125006Shaft Seal · leaking(CAN) WHILE DOING A GROUND RUN TO VERIFY THE COMPASS SYSTEM, TECH NOTICED UNCOMMANDED ACCELERATION AND DECELERATION OF THE RT ENGINE. VISUAL INSPECTION IDENTIFIED BLUE DYE WASHOUT FROM THE FUEL PUMP TO FUEL CONTROL UNIT SEAL AREA AND CONFIRMED A FAULT. THE FUJan 13, 2006 · Beech C90A · Fuel Control/Reciprocating EnginesSDR CA060110003Resistor · overheatedDURING SPECIAL INSPECTION AS PER CAMPAIGN 681-33-21-018, FOUND RESISTOR R145 (ATA 33-21-01 PAGE 4) OVERHEATED. INSULATION ABOVE THE RESISTOR WAS SCORCHED AND BURNED. THE SYSTEM WAS DEACTIVATED AND DEFERRED.Jan 6, 2006 · Beech C90A · Flight Compartment LightingSDR CA060110001Resistor · overheatedDURING SPECIAL INSPECTION AS PER CAMPAIGN 681-33-21-018, FOUND RESISTOR R145 (ATA 33-21-01 PAGE 4) OVERHEATED. INSULATION ABOVE THE RESISTOR WAS SCORCHED AND BURNED. THE SYSTEM WAS DEACTIVATED AND DEFERRED.Jan 6, 2006 · Beech C90A · Flight Compartment LightingSDR CA051222009Resistor · overheatedVISUAL INSPECTION CARRIED OUT AS PER CAMPAIGN NOTICE 681-33-21-018. RESISTOR VISUAL INSPECTED OKAY. SCORCHING FOUND ON INSULATION BLANKET. SYSTEM CB PULLED AND PLACARDED.Dec 22, 2005 · Beech C90A · Passenger Compartment LightingSDR CA060106002Engine · failedWHILE IN FINAL DESCENT, THE FLIGHT CREW DISCOVERED THAT THEY DID NOT HAVE FULL AUTHORITY OVER THE LEFT ENGINE. THE LEFT ENGINE COULD NOT BE REDUCED BELOW 800 LBS TORQUE. ENGINE CONTROL WAS STILL AVAILABLE IN A RANGE FROM 800 LBS TO MAX TORQUE. FLIGHT CREW OPTDec 20, 2005 · Beech C90A · Engine (Turbine/Turboprop)SDR CA051222007Resistor · overheatedRESISTOR R145 FOR FLUORESCENT LIGHT CIRCUIT FOUND SHOWING SIGNS OF OVERHEATING WHILE CARRYING OUT COMPANY CAMPAIGN 681-33-21-018. SYSTEM DISABLED AND DEFFERED.Dec 20, 2005 · Beech C90A · Passenger Compartment LightingSDR CA051222006Resistor · overheatedWHILE CARRYING OUT COMPANY CAMPAIGN 681-33-21-018, RESISTOR R145 FOR FLUORESCENT LIGHT CIRCUIT FOUND SHOWING SIGNS OF OVERHEATING. SYSTEM DISABLED AND DEFERRED.Dec 20, 2005 · Beech C90A · Light System WiringSDR CA051216003Resistor · overheatedDURING ROUTINE INSPECTION, FOUND RESISTOR R145 (ATA 33-21-01 PAGE 4) OVERHEATED. INSULATION ABOVE THE RESISTOR WAS SCORCHED AND BURNED.Dec 15, 2005 · Beech C90A · Passenger Compartment LightingSDR 2005FA0001576Manual · incorrectTHIS ENG MODEL HAS BEEN INSTALLED ON THIS AC. FG OAW TRAD STC SA02238AT. THIS STC HAS NO REFERENCES FOR A GROUND PWR ASSURANCE RUNS. NO GRAPHS ARE AVAILABLE THROUGH STC TO CHART ENG PARAMETERS FOR ACCEPTABLE GROUND PERFORMANCE DATA ON THIS INSTALLATION. IT Dec 7, 2005 · N1114Z · Beech C90A · Standard Practices/StructuresSDR 2005FA0001575Sense Line · wornP3 AIR LINE CONNECTS COMP TO P3 AIR FLTR. LINE ATTACHES TO GAS OPER CASE AT 5:00 POS LOOKING FWD, CONNECTS TO IS FITTING AT REAR FIREWALL. ENG INSTALLED, LINE RESTS FIRMLY ON ENG TRUSS. SUB ENG HAVE BEEN INSTALLED ON THIS AC FOR 300 HRS. P3 LINE IS ALREADYDec 7, 2005 · N1114Z · Beech C90A · Fuel Controlling SystemSDR 2005FA0001589Wire · chafedINVESTIGATED REPEATED INTERMITTENT LANDING GEAR RETRACT/ EXTENSION SYSTEM FAULTS. FOUND WIRES G45F22 AND G10L22 FOR NOSE LANDING GEAR DOWNLOCK SWITCH CHAFING ON ENVIRONMENTAL AIR CROSS-OVER DUCT IN LOWER RT NOSE KEEL AREA. REPAIRED DAMAGED WIRING AS REQUIREDNov 29, 2005 · N5641X · Beech C90A · Landing Gear System WiringSDR E812005F00001Brace · corrodedDURING INITIAL 6 YEAR/8000 CYCLE INSPECTION OF MAIN GEAR ASSY, FOUND INTERNAL SURFACE OF UPPER BRACE PITTED AND CORRODED AT AREA IN CONTACT WITH UPPER MAIN GEAR STRUT. CORROSION APPEARS UNUSUAL FOR A CLEAN, NEWER, LOW-TIME AIRCRAFT THAT IS HANGARED IS A NON SNov 16, 2005 · N439PW · Beech C90A · Main Landing GearSDR 2005FA0001560Brace · corrodedDURING INITIAL 6-YEAR/8000 CYCLE INSPECTION OF MAIN GEAR ASSY FOUND INTERNAL SURFACE OF UPPER BRACE PITTED AND CORRODED AT AREA IN CONTACT WITH UPPER MAIN GEAR STRUT. CORROSION APPEARS UNUSUAL FOR A CLEAN, NEWER, LOW-TIME AIRCRAFT THAT IS HANGARED IN A NON SANov 16, 2005 · N439PW · Beech C90A · Main Landing GearSDR 2005FA0001559Bushing · seizedDURING COMPLIANCE WITH ELEVATOR TAB TO ACTUATOR PUSHROD INSPECTION FOR SAFETY NR 243, FOUND ELEVATOR TAB HORN BUSHING SEIZED. REPLACED TAB HORN BUSHING AND ACTUATOR PUSHROD TO HORN ATTACH BOLT BUSHING, VERIFIED TAB HORN TO ACTUATOR PUSHROD OPERATIONS NORMAL INov 16, 2005 · N439PW · Beech C90A · Elevator, Spar/RibSDR 2005FA0001558Bushing · seizedDURING COMPLIANCE WITH ELEVATOR TAB TO ACTUATOR PUSHROD INSP FOR SAFETY NR 243 FOUND ELEVATOR TAB HORN BUSHING SEIZED. REPLACED TAB HORN BUSHING AND ACTUATOR PUSHROD TO HORN ATTACH BOLT BUSHING VERIFIED TAB HORN TO ACTUATOR PUSHROD OPERATIONS NORMAL IAW SAFETNov 16, 2005 · N439PW · Beech C90A · Elevator, Tab StructureSDR CA050915004Bolt · broken(CAN) CREW ENTERED DEFECT IN JOURNEY LOGBOOK, (RT ANTI-ICE LIGHT ON. VISUAL INSPECTION INDICATES BY-PASS DOOR FULLY DOWN, DEFLECTOR DOOR HALF WAY DOWN). MAINTENANCE CREW FOUND A BOKEN BOLT IN LINKAGE P/N AN3H-32A. (REFER TO IPC 30-20-02 PAGE 0 ITEM 35) RT ENSep 15, 2005 · Beech C90A · Air Intake Anti/De-Ice SystemSDR DYV2005F00000Blower · seizedPILOT NOTICED A BURNING SMELL AND SUBSEQUENT SMOKE ACCUMULATION IN THE COCKPIT. AFTER BEING UNABLE TO BE CERTAIN OF THE CAUSE, HE TURNED OFF ALL ELECTRICAL POWER AND LANDED AT OUR MAINTENANCE BASE. THE CABIN ENVIRONMENTAL VENTALATION BLOWER MOTOR WAS FOUND SAug 6, 2005 · N13GZ · Beech C90A · Air Distribution FanSDR CA050621011Hydromech Unit · damaged(CAN) DURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER CHANGE WITH NO SUBSEQUENT RESPONSE TO THROTTLE LEVEL INPUT. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT-OF-DEPATURE. SUBSEQUENT INSPECTION REVEALED A DAMAGED HYDROMECJun 12, 2005 · Beech C90A · Fuel Control/Reciprocating EnginesSDR CA050520001Bushing · migrated(CAN) ON A ROUTINE FLT THE PILOTS COULD HEAR A NOISE IN THE CONTROL COLUMN WHEN MOVING IT BACKWARDS AND FORWARDS. WHEN THE AIRCRAFT RETURNED MAINTENANCE FOUND THE LEFT ELEVATOR TAB BINDING AT THE CONTROL ROD TO TAB HORN ATTACHMENT. THE BUSHING HAD MIGRATED SMay 19, 2005 · Beech C90A · Elevator Tab Control SystemSDR CA050519005Clevis · out of rig(CAN) ON INITIAL GEAR EXTENSION DURING APPROACH RT MLG DOWNLOCK LIGHT DID NOT ILLUMINATE. THE PILOTS OPERATED THE EMERGENCY GEAR EXTENSION SYSTEM HOWEVER LIGHT STILL NOT ILLUMINATE. ONLY ONCE AIR SPEED WAS REDUCED JUST PRIOR TO TOUCHDOWN DID LIGHT ILLUMINATE IMay 13, 2005 · Beech C90A · Landing Gear Retraction/Extension SystemSDR CA050506001Windshield · broken(CAN) COPILOT INNER WINDOW PANE SHATTERED (LOUD BANG) DURING CRUISE AT 24,000 FT. IAS WAS 175 KNOTS , O.A.T. -32C. WINDSHIELD ANTI-ICE SELECTED OFF. NO LOSS OF PRESSURIZATION, CREW FOLLOWED CHECKLIST PROCEDURES FOR UNEVENTFUL LANDING. WINDOW HAD DELAMINATIONMay 3, 2005 · Beech C90A · Flight Compartment WindowsSDR 2005FA0000583Switch · overheatedDISCREPANCY ORIGINALLY AN INOPERATIVE LT BOOST PUMP. DURING THE OPS CHECK OF REPLACEMENT BOOST PUMP, SWITCH WAS NOTED TO BE INTERMITTENT. AFTER GAINING ACCESS TO SWITCH TERMINALS BY REMOVING THE LT FUEL BOOST PUMP SWITCH, TERMINALS WERE FOUND IN AN OVERHEATEDApr 22, 2005 · N6028Y · Beech C90A · Fuel Boost PumpSDR CA050527006Coupling · fracturedDURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED TORQUE AND TEMPERATURE INCREASE. THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL PUMP COUPLING SHAFT.Apr 21, 2005 · Beech C90A · Engine Fuel PumpSDR CA050408009Case · damaged(CAN) DURING AVIONICS UPGRADE PROCEDURES IT WAS FOUND THAT THE PILOTS RADAR ALTITUDE INDICATOR P/N 622-4160-018 WOULD CHAFE ON THE WINDSHIELD CENTER POST STRUCTURAL DOUBLER P/N 50-420066-281. THE CHAFFING WAS SERIOUS ENOUGH TO DAMAGE THE DOUBLER BEYOND ACCEPTApr 8, 2005 · Beech C90A · Ground Proximity SystemSDR CA050401007Tee Fitting · loose(CAN) TEE FITTING SUPPLYING TORQUE PRESSURE READING TO AIRCRAFT INSTRUMENTS WAS LOOSE, CAUSING AN OIL LEAK. THE TEE FITTING WAS WITNESSED (WIRED) AND APPROX HALF TURN WAS NEEDED TO TIGHTEN. AIRCRAFT ENGINE WAS SHUTDOWN IN FLIGHT AND AIRCRAFT LANDED SAFELY. Mar 24, 2005 · Beech C90A · Fuselage Miscellaneous StructureSDR CA050311003Spline · lack of lube(CAN) ON APPROACH THE LANDING GEAR WAS SELECTED DOWN AND THE NOSE GEAR DID NOT FULLY EXTEND. AN EMERGENCY EXTENSION PROCEDURE WAS CARRIED OUT AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THAT THE SPLINE COUPLING CONNECTING THE HYDRAULICMar 9, 2005 · Beech C90A · Landing Gear Retraction/Extension SystemSDR CA050307002Fcu · malfunctioned(CAN) DURING CLIMB, THE ENGINE EXPERIENCED AN UNCOMMANDED INCREASE IN TORQUE AND FAILED TO RESPOND TO THROTTLE INPUT. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INVESTIGATION REVEALED A FRACTURED FUEL CONTROL COUPLING SHAFT.Feb 3, 2005 · Beech C90A · Fuel Control/Turbine EnginesSDR CA050120007Windshield · broken(CAN) ENROUTE IN CRUISE FLIGHT AT 16000 MSL, OAT -38C THE LT WINDSHEILD SHATTERED. THE WINDSHIELD HEAT WAS OFF AND HAD NOT BEEN USED DURING THE FLIGHT. THE DEFOG AIR WAS ALSO OFF. THE CREW DECLARED AN EMERGENCY AND REQUESTED CLEARENCE AND IMMEDIATE DECENT TOJan 17, 2005 · Beech C90A · Flight Compartment WindowsSDR CA050308007Bushing · failed(CAN) BOLT, P/N 130909B172, ATTACHING RUDDER PEDAL TO RUDDER PEDAL ARM WILL NOT FIT PROPERLY THROUGH BUSHING. THE RUDDER PEDAL MUST THEN TURN ON THE BOLT AND THE BUSHING MUST TURN WITHIN THE RUDDER PEDAL ARM CAUSING PREMATURE WEAR AND/OR POSSIBLE FAILURE.Jan 13, 2005 · Beech C90A · Rudder Control SystemSDR CA041123001Pin · missing(CAN) THE PRIMARY CABLE FOR THE ELEVATOR CONTROL HAD JUMPED OUT OF THE PULLEY. THE (SPRING PIN) THAT PREVENTS THIS FROM HAPPENING WAS OUT OF POSITION (UNABLE TO STOP THE CABLE FROM LEAVING THE PULLEY). ABRASION OF THE ELEVATOR CABLE AT THE PULLEY AND ON SUPPORNov 19, 2004 · Beech C90A · Elevator Control SystemSDR 2005FA0000290Wire · brokenHEAT ELEMENT INOPERATIVE, DUE TO BROKEN WIRE AT TIP OF VENT TUBE WHERE IT IS GROUNDED. IT IS CAULED BY IMPROPER PROTECTIVE COATING ON THE WIRE. THE COATING WEARS OFF AND OPENS THE WIRE FROM GROUND. (K)Nov 9, 2004 · N100RU · Beech C90A · Fuel System WiringSDR 2005FA0000289Wire · inoperativeHEAT ELEMENT INOPERATIVE DUE TO BROKEN WIRE AT TIME VENT TUBE WHERE IS IS GROUNDED. IT IS CAUSED BY IMPROPER PROTECTIVE COATING ON WIRES. IT WEAR OFF AND OPENS THE WIRE FROM GROUND. (K)Nov 9, 2004 · N100RU · Beech C90A · Fuel System WiringSDR CA041015004Torque Knee · cracked(CAN) DURING A 8000 CYCLE TORQUE KNEE NDT INSPECTION IT WAS DETECTED THAT THE RT LOWER TORQUE KNEE ATTACH PIN, PN 50-810035-2 WAS CRACKED IN NUMBER OF PLACES. THE TORQUE KNEE IS POST S/B 32-3116 - IMPROVED STEEL. PRESENTLY THE PIN IS PLACED IN QUARANTINE. THEROct 15, 2004 · Beech C90A · Landing Gear Retraction/Extension SystemSDR CA040910001Fixture · meltedPLASTIC HOUSING OF THE LIGHT SHIELD P/N 101-530764-1 HAS MELTED DUE TO THE HEAT PRODUCED BY THE HIGH WATTAGE RESISTOR MOUNTED ON THE LIGHT ASSY PRINTED CIRCUIT BOARD P/N PW2014. IT HAD MELTED ENOUGH TO DISFIGURE THE SHIELD AND PRODUCE AN ELONGATED HOLE THE LENSep 9, 2004 · Beech C90A · Passenger Compartment LightingSDR CA040917003Cell · reversed(CAN) AIRCREW REPORTED LOAD METERS NOT INDICATING BATTERY CHARGE FOR NORMAL PERIOD OF TIME OR NORMAL LEVEL OF CHARGE. UPON INSPECTION NR 9 CELL FOUND INSTALLED IN REVERSE POLARITY ORIENTATION.Aug 30, 2004 · Beech C90A · Battery/Charger SystemSDR CA040917004Switch · failed(CAN) LANDING GEAR FAILED TO EXTEND WHEN SELECTED DUE TO FAILURE OF SWITCH IN LANDING GEAR CONTROL HANDLE.Aug 30, 2004 · Beech C90A · Landing Gear SelectorSDR IJAA016FDownlock Switch · dirtyRT MAIN GEAR DOWN LIGHT WOULD NOT COME ON WHEN LANDING GEAR WAS DOWN AND LOCKED. AIRCRAFT WAS LANDED WITHOUT INCIDENT. IT WAS DETERMINED THAT THE LANDING GEAR DOWN LOCK SWITCH WAS DIRTY WITH PAINT OVERSPRAY AND THE GEAR WAS RIGGED TO MIN TRAVEL OF DOWN LOCK Jul 19, 2004 · N424EM · Beech C90A · Landing Gear Position and WarningSDR CA040713001Shutoff Valve · failed(CAN) FAILED FUNTIONAL TEST IAW PILOTS CHECK LIST. REPLACEDJul 12, 2004 · Beech C90A · Fuel Selector/Shut-Off ValveSDR CA040705006Shutoff Valve · failed(CAN) DURING PILOTS START CHECKS RT HAND FUEL SHUT-OFF VALVE FAILED IN OPEN POSITION. UNABLE TO TURN LOW PRESSURE LIGHT ON. REPLACED VALVE. AIRCRAFT RETURNED TO SERVICE.Jun 30, 2004 · Beech C90A · Fuel Selector/Shut-Off ValveSDR CA040503001Shutoff Valve · failed(CAN) DURING PILOTS PREFLIGHT CHECK THE RT FUEL SHUTOFF VALVE FAILED. THE VALVE WAS REPLACED. TSO 75.4 HOURSApr 29, 2004 · Beech C90A · Fuel Selector/Shut-Off ValveSDR FCPR200400013Brake Assy · crackedTORQUE PLATE BROKE WHEN APPLYING BRAKES, APPEARS THAT CRACK STARTED UNDER BUSHING THAT CARRIES THE CALIPER PINS, DOES NOT HAVE A PROCEDURE TO REMOVE BUSHINGS TO CHECK FOR CRACKS.Apr 19, 2004 · N691AS · Beech C90A · BrakeSDR CA040405007Cowling · cracked(CAN) DURING PHASE 3 INSPECTION THE LT ENGINE LOWER AFT COWL WAS FOUND CRACKED A LONG A SEAM WELD. UNIT WAS REPAIRED IAW COMPANY PROCEDURE ASSY 681-71-10-0093.Mar 30, 2004 · Beech C90A · Engine Cowling SystemSDR CA040405006Hose · cracked(CAN) DURING PHASE 3 INSPECTION THE RT ENGINE IB INLET ANTI-ICE TUBE WAS FOUND CRACKED. UNIT REPLACED WITH NEW.Mar 30, 2004 · Beech C90A · Engine Anti-Icing System
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