Beech B100

Service difficulty reports · 200

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 aircraft_model_key = 'B100'
  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 2006FA0000586Starter Gen · seizedRT ENGINE WOULD NOT START. TROUBLESHOT AND FOUND RT STARTER GENERATOR SEIZED DUE TO BRUSHES WORN BEYOND LIMITS AND PIGTAILS ARCHING TO ARMATURE. (K)May 18, 2006 · N301TS · Beech B100 · Starter-GeneratorSDR CA060504006Torque Tube · wornWHILE CHECKING THE ELEVATOR SYSTEM FOR FREEDOM OF MOVEMENT, EXCESSIVE PLAY WAS NOTICED IN THE LEFT ELEVATOR. THE PLAY WAS ISOLATED TO THE ELEVATOR TORQUE TUBE FITTING. THE TORQUE TUBE WAS REPLACED WITH A NEW ASSEMBLY. THE TORQUE TUBE WAS INSPECTED AND FOUND May 3, 2006 · Beech B100 · Elevator StructureSDR CA060406002Torque Tube · corrodedDURING AN INSPECTION OF THE ELEVATOR TORQUE TUBE, THE PRIMARY ELEVATOR TORQUE TUBE WAS FOUND CORRODED. THE PART WAS REPLACED.Apr 3, 2006 · Beech B100 · Elevator StructureSDR CA060405003Adapter · crackedDURING AN INSPECTION OF THE "OIL FILTER ADAPTER", IT WAS FOUND CRACKED IN TWO PLACES. A SMALL OIL LEAK WAS EVIDENT. THE PART WAS REPLACED.Mar 16, 2006 · Beech B100 · Turbine Engine Oil SystemSDR CA051202003Control Panel · burnedA BURNT ODOR WAS NOTICED FOLLOWED BY SMOKE IN THE COCKPIT, COMING FROM THE TRIM INDICATOR LIGHT PANEL. THE PILOT CLOSED THE RHEOSTAT AND RETURNED TO BASE. AFTER INSPECTION OF THE LIGHT PANEL, HUMIDITY WAS FOUND UNDER THE PANEL, WHICH CAUSED A SHORT CIRCUIT. Nov 25, 2005 · Beech B100 · Flight Compartment LightingSDR CA051130004Fire Detector · failed(CAN) WHEN THE INDICATOR (LT ENGINE FIRE) ILLUMINATED, THE ENGINE WAS SHUTDOWN BY THE PILOT, AND PUT INTO FEATHER. AN EMERGENCY WAS DECLARED. THE AIRCRAFT RETURNEDTO BASE. AFTER VERIFICATION, NO ENGINE FIRE WAS EVIDENT. THE INDICATORS WERE VERIFIED AND THE AIRNov 22, 2005 · Beech B100 · Fire DetectionSDR CA051109002Stringer · crackedDURING AN INSPECTION OF THE ELEVATOR CABLES, AFT OF THE REAR PRESSURE BULKHEAD, THE ENGINEER DISCOVERED A CRACK IN THE NR 10 STRINGER OF THE AFT PRESSURE BULKHEAD. THIS AIRCRAFT HAS A CVR INSTALLED IAW STC 'SA-02-26' AND THE MOUNTING TRAY FOR THE CVR TIES INTNov 7, 2005 · Beech B100 · Fuselage Main, Longeron/StringerSDR CA051025007Barrel · brokenFLIGHT CREW REPORTED LOSS OF NOSE WHEEL STEERING DURING TAXI. MAINTENANCE FOUND THE NOSE WHEEL BARREL ASSY BROKEN. SLOTS WHICH HOLD IN SPRING RETAINER FOUND BROKEN ALLOWING SPRING TO LOSE TENSION. MX REPLACED THE ASSY AND RELEASED AIRCRAFT FOR RETURN TO SEROct 24, 2005 · Beech B100 · Wheel/Ski/FloatSDR CA051019004Trim Tab · debonded(CAN) DURING COMPLIANCE WITH RAYTHEON S/B 55-2365 REV.2 ISS. OCT 2005 MAINTENANCE FOUND THE RUDDER TAB DISBONDED ON LOWER END. MAINTENANCE REPLACED THE RUDDER TAB AND RELEASED THE AIRCRAFT. RESEARCH ON THIS AIRCRAFT DISCOVERED THAT RAYTHEON S/B 2 365R1 (A/D Oct 17, 2005 · Beech B100 · Rudder Tab Control SystemSDR CA051004006Fire Detector · failed(CAN) AFTER TAKE OFF AN (ENGINE FIRE) INDICATION FOR THE RT ENGINE ILLUMINATED. PILOT SHUT DOWN THE ENGINE AND LANDED ON ONE ENGINE. AFTER INSPECTION OF THE SYSTEM, NO FAULT FOUND, SYSTEM NORMAL. AIRCRAFT RETURNED TO SERVICE.Sep 26, 2005 · Beech B100 · Fire DetectionSDR CA050921001Door Frame · cracked(CAN) DURING A DAILY INSPECTION 2 CRACKS WERE DETECTED ON EACH SIDE OF THE UPPER ATTACHMENT FOR THE REAR DOOR. THE PART WAS REPLACED.Sep 16, 2005 · Beech B100 · Fuselage Main, StructureSDR CA050824012Torque Tube · cracked(CAN) WHILE CARRYING OUT A PHASE 2 AND 3 INSPECTION, THE RT ELEVATOR TORQUE TUBE HAD A .5 INCH CRACK. THE CRACK WAS DISCOVERED BETWEEN THE ELEVATOR AND TORQUE TUBE. THE TORQUE TUBE WAS REPLACED.Aug 3, 2005 · Beech B100 · Elevator Control SystemSDR CA050727007Skin · corroded(CAN) CORROSION WAS FOUND ON THE LEFT HAND AILERON UNDER THE STATIC WICKS. THE AILERO N WAS REMOVED AND DISASSEMBLED. AFTER REMOVING THE UPPER SKIN, IT WAS DISCOVEREDTHAT THE UPPER AND LOWER SKINS WERE CRACKED IN MULTIPLE LOCATIONS, JUST AFT OFTHE JOINT WHERE Jul 26, 2005 · Beech B100 · AileronsSDR CA050727009Skin · cracked(CAN) CORROSION WAS FOUND ON THE LEFT HAND AILERON UNDER THE STATIC WICKS. THE AILERO N WAS REMOVED AND DISASSEMBLED. AFTER REMOVING THE UPPER SKIN, IT WAS DISCOVEREDTHAT THE UPPER AND LOWER SKINS WERE CRACKED IN MULTIPLE LOCATIONS, JUST AFT OFTHE JOINT WHERE Jul 25, 2005 · Beech B100 · AileronsSDR CA050727008Skin · cracked(CAN) CORROSION WAS FOUND ON THE LEFT HAND AILERON UNDER THE STATIC WICKS. THE AILERO N WAS REMOVED AND DISASSEMBLED. AFTER REMOVING THE UPPER SKIN, IT WAS DISCOVEREDTHAT THE UPPER AND LOWER SKINS WERE CRACKED IN MULTIPLE LOCATIONS, JUST AFT OFTHE JOINT WHERE Jul 25, 2005 · Beech B100 · AileronsSDR CA050630009Rib · crackedWHILE REPAIRING OTHER CRACKS IN THE AREA OF THE RIB, CRACKS WERE FOUND IN THE RIB AT THE POINT WHERE THE BALANCE WEIGHT ATTACHMENT ANCHOR NUTS ARE RIVETED ON .Jun 29, 2005 · Beech B100 · Elevator StructureSDR CA050817004Indicator · smoke(CAN) ON TAKEOFF THE FLIGHT DIRECTOR INDICATOR STARTED TO SMOKE. THE PILOT RETURNED TO THE AIRPORT AND LANDED WITHOUT INCIDENT. THE FLIGHT DIRECTOR INDICATOR WAS REMOVED AND A LOANER UNIT WAS INSTALLED. THE AIRCRAFT DEPARTED AND COMPLETED THE FLIGHT WITHOUT Jun 26, 2005 · Beech B100 · Integrated Flight SystemSDR CA050623002Skin · crackedTHE ELEVATOR WAS REMOVED TO REPLACE THE TRAILING EDGE SPLINE AND REPAIR CRACKS IN THE LE SKIN NEAR THE OUTBOARD HINGE POINT. THE HORN AREA WAS DISMANTLED TO INSPECT THE INNER STRUCTURE. A TOTAL OF TWENTY CRACKS WERE FOUND IN THE VARIOUS PARTS OF THE STRUCTURJun 22, 2005 · Beech B100 · Elevator, Plate/SkinSDR CA050609014Link · cracked(CAN) DURING AN INSPECTION THE EMERGENCY GEAR EXTENSION LINK WAS DISCOVERED CRACKED. THE ONLY INSPECTION METHOD WAS TO REMOVE THE PILOT'S FLOORBOARD. THE PROBLEM WITH THIS DEFICIENCY IS THAT THE MECHANICAL PUMP WILL WORK AS A SINGLE ACTION PUMP INSTEAD OF DOUBJun 2, 2005 · Beech B100 · Landing Gear Retraction/Extension SystemSDR CA050531008Hub · unserviceable(CAN) DURING AN AUDIT OF AD'S IT WAS DISCOVERED THAT AN ERROR HAD BEEN MADE BY THE OVERHAULER WHEN INTERPRETING AD96-18-14 WHICH RESULTED IN AN EXPIRED HUB BEING INSTALLED ON THE PROP. DURING OVERHAUL THE HUB AND BLADES WERE REPLACED. THE HUB SN HAD AN EXTRA DMay 27, 2005 · Beech B100 · Propeller Hub SectionSDR CA050405002Speed Switch · malfunctioned(CAN) LT STARTER GENERATOR SYSTEM SPEED SWITCH MALFUNCTIONED. NO IGNITION WAS INITIALED AT THE PRESCRIBED PERCENTAGE N2. SWITCH REPLACED.Mar 16, 2005 · Beech B100 · Starter-GeneratorSDR CA050401014Fork · crackedWHILE PERFORMING NDT INSP CALL UP IN AD 2004-23-02, NOSE GEAR FORK FOUND TO BE CRACKED. NOSE GEAR FORK REPLACED WITH NEW STYLE FORK ASSY IN BEECH 101-8030-1S SERVICE KIT.Mar 9, 2005 · Beech B100 · Nose/Tail Landing Gear Strut/AxleSDR CA050321006Plenum · cracked(CAN) WHILE CONDUCTING AN ENGINE INSPECTION, A 2 INCH CRACK WAS DISCOVERED ON THE PLENUM NEAR THE BLEED AIR OUTLET. THE ENGINE WAS REMOVED AND THE CRACKED PART REPLACED. A FLEET WIDE ENGINE INSPECTION OF THE SAME DEFECT WAS CARRIED OUT. NO OTHER DEFECTS FOUMar 4, 2005 · Beech B100 · Turbine Engine Combustion SectionSDR 2005F00038Drive Shaft · strippedLT ENGINE FAILED TO START NORMALLY. IN MANUAL MODE START WAS SUCCESSFUL. SUBSEQUENT START, GENERATOR WAS INOPERATIVE. EXTENSIVE TROUBLESHOOTING FINALLY DETERMINED THAT THE STARTER-GENERATOR HAD SIEZED, STRIPPING PLASTIC DRIVE ADAPTER IN ENGINE. DRIVE ADAPTFeb 14, 2005 · N88FA · Beech B100 · Engine RPM Indicating SystemSDR XRR2005F00000Windshield · crackedINNER PANE OF CO-PILOTS WINDSHIELD CRACKED WHILE AT ALTITUDE.Feb 11, 2005 · N564CA · Beech B100 · Flight Compartment WindowsSDR 2005FA0000402Windshield · brokenINSIDE LAYER OF CO-PILOT WINDSHIELD CRACKED WHILE IN-FLIGHT AT 25,000 FT. AIRCRAFT RETURNED. NO PROBABLE CAUSE OR RECOMMENDATION CAN BE MADE TO PREVENT REOCCURRENCE. WINDSHIELD CRACKED FOR NO APPARENT REASON. (K)Feb 9, 2005 · N564CA · Beech B100 · Flight Compartment WindowsSDR 2005FA0000009Starter Gen · failedLEFT ENGINE FAILED ROTATE DURING START SEQUENCE INITIATION. MAINTENANCE DETERMINED BRUSHES BURNT, APPROXIMATELY 50 PERCENT LENGTH/LIFE REMAINING. STARTER/GENERATOR WAS REPLACE, ALONG WITH DC VOLTAGE REGULATOR. NR 1 INVERTER HAD FAILED COUPLE DAYS PRIOR, NO Jan 4, 2005 · N88FA · Beech B100 · Starter-GeneratorSDR 2004F00439Motor · damagedDURING TAKEOFF, LANDING GEAR FAILED TO RETRACT, THEN FAILED TO EXTEND, WAS MANUALLY EXTENDED VIA EMERGENCY PROCEDURES. MAINTENANCE DISCOVERED LANDING GEAR MOTOR CIRCUIT BREAKER TRIPPED, MOTOR ITSELF SUFFERED INTERNAL HEAT DAMAGE. TIME IN SERVICE SINCE OVERHADec 21, 2004 · N88FA · Beech B100 · Landing Gear ActuatorSDR CA041124008Windshield · broken(CAN) RT FRONT INNER PANE OF WINDSHIELD SHATTERED IN FLIGHT.Nov 17, 2004 · Beech B100 · Flight Compartment WindowsSDR CA040707003Manifold · crackedSLIGHT FUEL ODOR IN CABIN WHEN AIRCRAFT SLOWED FOR LANDING. THE CREW NOTICED FUEL DRIPPING FROM THE RT ENGINE AFTER SHUTDOWN. MAINTENANCE FOUND A CRACKED FUEL MANIFOLD INLET ELBOW. THE MANIFOLD WAS REPLACED.Jul 6, 2004 · Beech B100 · Engine Fuel DistributionSDR 400AC0401Bolt · failedPILOT REPORTED VIBRATION ON LANDING. INSP REVEALED THE LT MAIN GEAR TORQUE LINK PIVOT BOLT, MISSING. THE BOLT COULD NOT BE FOUND TO DETERMINE THE CAUSE. SUSPECT EITHER A FAILURE OF THE BOLT OR FAILURE OF THE SAFETY FEATURE TO PREVENT THE BOLT FALLING OUT. Jun 10, 2004 · N400AC · Beech B100 · FastenersSDR CA040429008Tire · chafed(CAN) MECHANIC NOTICED THAT TIRE SIDEWALL HAD RUBBED AGAINST BRAKE HOUSING, CREATING A GROOVE IN THE RUBBER. THERE WAS STATIC CLEARANCE BUT WHEN THE TIRE FLEXED ON LANDING IT COULD RUB AGAINST THE BRAKE HOUSING. CLEVELAND WHEELS AND BRAKES HAD BEEN INSTALLED IApr 15, 2004 · Beech B100 · TireSDR MCI2004F00000Attach Bolt · damagedPERFORMED INSPECTION ON HORIZONTAL STABILIZER ATTACH FITTINGS AND FOUND BOLT HEAD MISSING ON ONE BOLT ON LT AFT ATTACH POINT. REMOVED BOLT AND FOUND IT TO BE WORN AND CORRODED. REPLACED LT AND RT AFT ATTACH BOLTS, BOTH WERE WORN AND CORRODED. BOLT HEAD SHOWApr 7, 2004 · N236CP · Beech B100 · FastenersSDR CA040323007Circuit Breaker · tripped(CAN) THE 60 AMP BREAKER THAT PROTECTS THE HYDRAULIC LANDING GEAR PUMP MOTOR CIRCUIT TRIPPED WHEN THE GEAR WAS RETRACTED AFTER TAKE OFF. THE CREW ELECTED TO BLOW THE GEAR DOWN AND RETURNED TO BASE WITHOUT FURTHER INCIDENT. HYDRAULIC SYSTEM ON THIS AIRCRAFT OMar 22, 2004 · Beech B100 · Landing Gear Retraction/Extension SystemSDR CA040317004Spline · cracked(CAN) ON INSPECTION FOUND THREE VISUAL CRACKS IN OB SECTION OF THE ELEVATOR TRAILING EDGE SPLINE, AS DESCRIBED IN OTHER SDR'S /SERVICE DIFFICULTY ADVISORY.Mar 11, 2004 · Beech B100 · Elevator StructureSDR CA040303004Gusset · unbonded(CAN) WHILE REMOVING A BROKEN CO-PILOT WINDSHIELD IT WAS NOTED CHAFFING ON THE WINDSHEILD FRAME. INTERIOR TRIM THAT IS ATTACHED TO THE CENTER PILLAR HAD BECOME UNATTACHED AND FALLEN DOWN INTO CONTACT WITH THE WINDSHEILD PILLAR GUSSET. MFG WAS IMMEDIATELY COMar 2, 2004 · Beech B100 · Fuselage Main, StructureSDR CA040204012Downlock Switch · frozen(CAN) ON APPROACH THE PILOT SELECTED GEAR DOWN. THERE WAS NO NOSE GEAR INDICATION. AFTER CONFIRMING WITH THE TOWER THAT THE GEAR WAS DOWN, THE AIRCRAFT LANDED WITHOUT INCIDENT. THE DOWNLOCK SWITCH WAS FOUND DEFECTIVE AND SUBSEQUENTLY REPLACED. OAT WAS -25 TO Jan 14, 2004 · Beech B100 · Landing Gear Position and WarningSDR CA030925004Solenoid Valve · shorted(CAN) WHILE IN CRUISE, THE 5 AMPS CIRCUIT BREAKER (CABIN TEMP) TRIPPED. CREW RESET ONE TIME AND TRIPPED AGAIN. UPON INVESTIGATION FOUND RT AMBIENT SOLENOID SHUTOFF VALVE SHORTED CAUSING CIRCIUT BREAKER TO TRIPPED. SOLENOID VALVE REPLACED WITH NEW AND SYSTEM Sep 23, 2003 · Beech B100 · Cabin Temperature ControllerSDR BBC2003F00000Housing · crackedAUGUST 22, 2003 ENGINE LOST OIL PRESSURE INFLIGHT, PILOT COMMANDED SHUTDOWN, AIRCRAFT LANDED. SUBSEQUENT TEARDOWN OF GEARBOX REVEALED CRACKED OIL PUMP HOUSING. PUMP HOUSINGS ARE NOT STRONG ENOUGH DESIGN OR ALLOY.Sep 15, 2003 · N264PA · Beech B100 · Turbine Engine Oil SystemSDR CA030813005Relief Valve · leaking(CAN) THE LANDING GEAR HAD A SERIES OF 2 FAILURES WHERE THE 60 AMP BREAKER TRIPPED AS THE MLG WAS RETRACTING & WOULD NOT RESET THEREBY FORCING THE CREW TO LOWER THE GEAR WITH THE EMERGENCY SYS & RETURN TO BASE. THE FAILURE COULD NOT BE DUPLICATED WHEN THE GEARAug 8, 2003 · Beech B100 · Hydraulic System, MainSDR 84031Torque Sensor · malfunctionedTEMP, TORQUE AND FUEL FLOW ALL DECLINED. ENGINE WAS SECURED AND PROP FEATHERED AND AN UNEVENTFUL LANDING WAS MADE AT GJT. UPON ENGINE DISASSEMBLY, THE TORQUE SENSOR SHAFT WAS FOUND SHEARED.Aug 4, 2003 · N949SW · Beech B100 · Engine BMEP/Torque IndicatingSDR CA030808003Circuit Breaker · failed(CAN) THE LANDING GEAR FAILED TO RETRACT ON TAKE-OFF. THE 60 AMP HYD DRIVE MOTOR CIRCUIT BREAKER WAS FOUND TRIPPED. THE GEAR WAS LOWERED USING THE EMERGENCY SYSTEM AND THE AIRCRAFT RETURNED AND LANDED WITHOUT FURTHER INCIDENT. THE MOTOR WAS BENCH CHECKED AND FJul 30, 2003 · Beech B100 · Hydraulic Pump (Electric/Engine), MainSDR CA030428006Fire Loop · malfunctioned(CAN) DURING CLIMB AFTER TAKE OFF, THE RT FIRE WARNING LIGHT CAME ON, THE PILOT CONDUCTED AN ENGINE SHUT DOWN AND USED THE FIRE BOTTLE AND RETURN TO THE MAIN BASE AS PER FLIGHT MANUAL CHECKLIST . UPON INVESTIGATION, NO FIRE WAS FOUND, ALL THREE FIRE SENSORS DEApr 28, 2003 · Beech B100 · Fire DetectionSDR CA030428004Actuator · failed(CAN) CREW WAS UNABLE TO COOL THE CABIN TEMPERATURE DURING THE FLIGHT. BOTH THE AUTO AND MANUAL MODE SYSTEM WAS USED WITHOUT SUCCESS. FOUND THE LT BLEED AIR BYPASS VALVE/ACTUATOR STUCK IN THE FULL HOT POSITION.UNIT REPLACED WITH AN OVERHAULED UNIT AND SYSTEM TApr 28, 2003 · Beech B100 · Cabin Temperature Control SystemSDR CA030414003Torque Sensor · malfunctioned(CAN) TORQUE SPLIT IN FLIGHT. INCREASE TO APPROX 160 FT/LBS GREATER ON LT SIDE. ON RUN UP LOST TORQUE INDICATION COMPLETLY ON RT ENGINE. TROUBLESHOOTING: INSTALL TEST GAUGE BETWEEN TORQUE SENSOR AND TORQUE TRANSDUCER. ONLY GET APP 15 PSIOUT OF UNIT. SHOULD BE Apr 14, 2003 · Beech B100 · Engine BMEP/Torque IndicatingSDR CA030414002Insert · stripped(CAN) DURING SCHEDULED INSPECTION, REPLACING THE HORIZONTAL STAB AFT ATTACHMENT POINTS. WE REMOVED THE BOLTS THAT ATTACH TO THE CASTING TO GAIN ACCESS, THREE OF THE 12 BOLTS WOULD JUST SPIN IN PLACE.AFTER REMOVING THESE BOLTS WE FOUND THAT THE NUTS (INSERTS) Apr 14, 2003 · Beech B100 · Horizontal Stabilizer StructureSDR CA030408006Spline Adapter · cracked(CAN) DURING ROUTINE MAINTENANCE, ELEVATORS WERE REMOVED FOR SB 2145 ON ELEVATOR TORQUE TUBE. AFTER REVIEWING SERVICE DIFFICULTY ADVISORY AV-2003-01 FOR BEECH A100, WE FOUND SAME CRACKES ON THE RIGHT ELEVATOR ON OUR B100. AFTER DISASSEMBLE AT LOCAL SHEET METALApr 8, 2003 · Beech B100 · Elevator StructureSDR 0074567Clamp · corrodedCORRISION ON CLAMP ASSEMBLYMar 24, 2003 · Beech B100 · Propeller AssemblySDR 2004FA0000165Duct · meltedIN LATE JAN 1999, IN FLIGHT, THE TEMPERATURE CONTROL CIRCUIT BREAKER OPENED. AS A RESULT THE CREW EXPERIENCED AN OVERTEMP CONDITION OF THE ENVIRONMENTAL SYSTEM. THE ENVIRONMENTAL CONTROL WAS SELECTED OFF AND THE AIRCRAFT LANDED SAFELY. SUBSEQUENT INSPECTIONJan 20, 2003 · N45LU · Beech B100 · Air Distribution SystemSDR DTH2003F00000Engine · flamed outRT ENGINE FLAMED OUT DURING DESCENT TO LANDING. AUTO IGNITION RELIT, NORMAL OPERATION. YET TO DETERMINE IF MECHANICAL OR OPERATIONAL PROBLEM.Jan 2, 2003 · N75AP · Beech B100 · Engine (Turbine/Turboprop)
Back to Beech B100