Beech B100

Service difficulty reports · 200

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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 = '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 CA021015010Bolt · cracked(CAN) DURING INSPECTION OF WING AND BOLTS, IN CONJUNCTION WITH AD. DYE PENETRANT INSPECTION FOUND CRACK IN LOWER FORWARD LT WINGBOLT. CRACK FOUND ON BOLT SHAFT/FLANGE AREA. NO OTHER CRACKS FOUND DURING INSPECTION. BOLT REPLACED. ORIGINAL FAILED BOLT INSOct 13, 2002 · Beech B100 · Wing, Attach FittingsSDR CA021002006Bolt · cracked(CAN) WING BOLTS INSPECTED AS PER BEECH S.I.R.M. 57-16 INDEX 10. INDEX 1-11 DONE IN CONJUNCTION WITH CF-1981-25R6. CRACK FOUND IN LT UPPER AFT WING BOLT. CRACK FOUND WHERE SHAFT CONNECTS TO BOLT HEAD. WING BOLT REPLACED WITH NEW. CRACK FOUND 1 YEAR/324 HOURS ASep 24, 2002 · Beech B100 · Wing, Fuselage Attach FittingsSDR 2002FA0001194Bolt · crackedLEFT AFT UPPER WINGBOLT CRACK FOUND WHERE SHAFT CONNECTS TO BOLT HEAD. WINGBOLT INSPECTION CARRIED OUT IAW AD. BOLT WAS INSPECTED 1 YEAR/ 324 HOURS, PRIOR. BOLT, TT 2716.5 HOURS, 2544 A/C CYCLES. INSTALLED APRIL 1991.Sep 20, 2002 · Beech B100 · FastenersSDR CA020905001Bearing · damaged(CAN) ENGINE DISMANTLE TO FIND FAILURE CAUSE OF BEARING. FOUND DAMAGE TO TORQUE SENSOR AND ALL GEAR RELATED. BEARING LOOSENESS WAS THE CAUSE OF THE BEARING DAMAGE.Aug 20, 2002 · Beech B100 · Turbine Engine Accessory DriveSDR CA020903006Gear · broken(CAN) DURING CRUISE THE LT ENGINE QUIT AS IF NO MORE FUEL COULD REACH IT. THE PILOT TURNED AROUND AND LANDED AT ITS ORIGINAL DEPARTING POINT WITHOUT ANY PROBLEM. THE FCU GEAR THAT ENGAGES THE FCU WAS FOUND BROKEN.Aug 12, 2002 · Beech B100 · Fuel Control/Turbine EnginesSDR CA020903005Switch · broken(CAN) WHILE THE LANDING GEAR WAS BEING STRETCHED, THE LANDING GEAR STAYED DOWN AND THE AIRCRAFT RETURNED TO ITS BASE. SWITCH WAS FOUND BROKEN IN THE CONTROL RELAY IN THE GEAR MOTOR. THE SWITCH WAS REPLACED AND LANDING GEAR RETRACTIONS WERE PERFORMED.Jul 26, 2002 · Beech B100 · Landing Gear Retraction/Extension SystemSDR CA020724002Check Valve · open(CAN) FOLLOWING A FLIGHT WHILE UTILIZING THE AUXILIARY RESOURCES, A CHECK VALVE STAYED PARTIALLY OPEN. THE MAIN RESERVOIR TRANSFERRED TO THE AUXILIARY AND THE FUEL (TOO FULL) EXITED BY THE VENT AND LEAKED TO THE GROUND. THE PILOT ACTIVATED THE BOOST PUMP WITH Jul 2, 2002 · Beech B100 · Fuel Transfer ValveSDR CA020729009Brushes · failed(CAN) WHILE LANDING GEAR WAS BEING EXTENDED DURING AN APPROACH, LANDING GEAR DID NOT COME OUT AFTER A FEW TRIES (GEAR UP, GEAR DOWN), IT DID FINALLY EXTEND. THE AIRCRAFT WAS CHECKED AND IT SEEMED THAT THE ENGINE WAS FORCING DURING RETRACTION. THE BRUSHES WERE Jun 27, 2002 · Beech B100 · Landing Gear Retraction/Extension SystemSDR D4O2002F00000Circuit Breaker · trippedWHILE IN FLIGHT, POWER WAS LOST TO RT SIDE OF INSTUMENT PANEL. PILOT TRIED TO EXTEND LANDING GEAR. GEAR DID NOT EXTEND. EMERGENCY WAS DECLARED AND PILOT RETURNED TO ALTITUDE AND MANUALLY EXTENDED LANDING GEAR. PILOT COMUNICATED WITH ANOTHER PILOT WHO TOLD Jun 14, 2002 · N19DA · Beech B100 · AC Power Distribution SystemSDR R2J2002F00008Rib · crackedDURING PHASE INSPECTION FOUND CRACK IN SHIM UNDER RIGHT INBOARD FLAP IN AREA OF ACTUATOR ATTACH BRACKET. SKIN WAS CRACKED BECAUSE THE FLAP RIB HAD BROKEN. THIS RIB IS WHAT THE FLAP ACTUATOR FOR INSPECTION. THE CRACKED SHIM WAS A RESULT OF RIB FAILURE. INSMay 28, 2002 · N78DA · Beech B100 · Trailing Edge FlapsSDR R2J2002F00007Bracket · crackedWHILE COMPLETING INSPECTION OF CABIN ELEVATOR PULLEY BRACKET PER MFG SB. FOUND BRACKET CRACKED AND STOP DRILLED NOT APPROVED REPAIR SB CALLS FOR NEW HEAVIER BRACKETS INSTALLED PER KIT.May 28, 2002 · N78DA · Beech B100 · Fuselage Miscellaneous StructureSDR R2J2002F00006Tube · damagedWHILE COMPLYING WITH MFG SB, BOTH ENGINE HAD DAMAGE TO ENGINE ANTI-ICE TUBING AT THE FLARES, WHICH REQUIRED REPLACEMENT. ENGINE BLEED AIR FOR ENGINE ANTI-ICE WAS DUMPING INTO COWL INSTEAD OF GOING INTO DEICE MANIFOLDS. CAUSE WAS LOOSE (B) NUTS. NEED TO BE SMay 28, 2002 · N78DA · Beech B100 · Ice/Rain Protection SystemSDR R2J2002F00005Hinge · crackedDURING PHASE INSPECTION RIBS AT LEFT ELEVATOR OUTBOARD HINGE FOUND CRACKED. NEW PARTS INSTALLED AND ELEVATOR REINSTALLED AND ELEVATOR REINSTALLED. INSPECTORS SHOULD PAY PARTICULAR ATTENTION TO THIS AREA. MORE CRACKING WAS FOUND, AFTER ELEVATOR REMOVAL TO REMay 28, 2002 · N78DA · Beech B100 · Elevator StructureSDR TCH2002F00004Turbine Wheel · crackedTOW CRACKS AT RIVET HOLES, AND DISK DAMAGE ON AFT SIDE. THIS ISA 5400 HOUR TBO ENGINE. A PREMATURE FAILURE.Mar 7, 2002 · N949SW · Beech B100 · Turbine SectionSDR TCH2002F00002Turbine Wheel · crackedSIXTEEN CRACKS AT RIVET HOLES IN TURBINE WHEEL. RIVET HOLES IN TURBINE WHEEL. THIS IS A 5400 HOUR TBO ENGINE. A PREMATURE FAILURE.Mar 7, 2002 · N949SW · Beech B100 · Turbine SectionSDR TCH2002F00001Turbine Wheel · crackedFOURTEEN CRACKS FOUND IN TURBINE WHEEL AT RIVET HOLES. THIS IS A 5400 HOUR TBO ENGINE. A PREMATURE FAILURE.Mar 7, 2002 · N949SW · Beech B100 · Turbine SectionSDR TCH2002F00000Turbine Wheel · crackedSEVENTY CRACKS FOUND IN TURBINE WHEEL AT RIVET HOLES. THIS IS A 5400 HOUR TBO ENGINE. A PREMATURE FAILURE.Mar 7, 2002 · N949SW · Beech B100 · Turbine SectionSDR 2002FA0000330Bellcrank · corrodedREMOVED RUDDER FROM AIRCRAFT FOR OTHER MAINTENANCE. DISCOVERED RUDDER BELLCRANK SEVERELY CORRODED IN THE AREA BENEATH THE RUDDER ATTACH FITTING. REPLACED PART WITH NEW ITEM.Feb 20, 2002 · N568K · Beech B100 · Rudder Control SystemSDR CA020220009Wire · chafed(CAN) TWO DAYS RUNNING THE AIR DATA COMPUTER CIRCUIT PROTECTION FUSE OPENED CAUSING LOSS OF THECAPTAINS ALTIMETER, THE ALTITUDE PRE-SELECT, AND THE MODE C TRANSPONDER FUNCTION. ON THE FIRST DAY THE FAILURE OCCURRED WHILE THE AIRCRAFT WAS AWAY FROM BASE, AND HAFeb 14, 2002 · Beech B100 · Electrical Power System WiringSDR ODAR018HTorque Link · brokenRT MLG TORQUE KNEE FAILED AT UPPER PIVOT PIN. TORQUE KNEE WAS FOUND WITH SECTION MISSING ON INBOARD HALF AND BROKEN ON OUTBOARD SIDE. CRACKS WENT THROUGH GREASE FITTING HOLES IN BOTH CASES. GREASE FITTINGS WERE BOTH LOST. POSSIBLY CAUSED BY EXCESSIVE SIDE Feb 14, 2002 · N19DA · Beech B100 · Landing Gear Retraction/Extension SystemSDR DBC2002F00000Pump · failedWHILE ENROUTE, PILOT NOTED VIBRATION WITH VARYING INTENSITIES. PILOT RETURNED TO AIRPORT WITHOUT INCIDENT. TROUBLESHOT, SUSPECT SCAVENGE PUMP CAVITATION. BLED SCAVENGE SYSTEM PER MFG. SOAP SAMPLE TAKEN. AIRCRAFT GROUND RAN AND CHECKED FOR LEAKS. POST MAIFeb 5, 2002 · N36WH · Beech B100 · Accessory GearboxesSDR ZES2002F00002Panel · burnedSHORTLY AFTER TAKEOFF, PILOT NOTICED SMOKE COMING FROM PEDISTOL TRIM SWITCH SUB PANEL. PEDESTOL LITES, CIRCUIT BREAKER POPPED, SHORT, SMOKE QUIT. PILOT LANDED AIRCRAFT UNEVENTFULL. FOUND LAMP SHORTED ON LIGHT STRIP.Dec 10, 2001 · N777DQ · Beech B100 · Flight Compartment LightingSDR CA011212003Windshield · cracked(CAN) WINDSHELD CRACKED / CRAZED DURING CRUISE FLIGHT. THE CREW LOWERED CABIN PRESSURE, DISCOUNTINUED HEAT AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THE INNER LAMINATE LAYER OF THE WINDSHIELD PRC SEALED TO THE WINDOW FRAME STRUCTURE WHICH PREVENTDec 2, 2001 · Beech B100 · Flight Compartment WindowsSDR EGQ2002F00000Actuator · failedDURING A TRAINING FLIGHT, PILOTS RETRACTED THE LANDING GEAR. A BANG WAS HEARD. THE RIGHT GEAR STAYED DOWN AND LOCKED WHILE THE NOSE GEAR AND LEFT MAIN GEAR RETRACTED NORMALY. PILOTS EXTENDED THE NOSE AND LEFT MAIN GEAR USING THE EMERGENCY SYSTEM. A NORMAL Nov 9, 2001 · N105VY · Beech B100 · Landing Gear ActuatorSDR CA011120010Windshield · cracked(CAN) WHILE AT CRUISE ALTITUDE THE NR 1 (PILOT'S) WINDSHIELD STARTED CRAZING AND CONTINUED PROGRESSIVELY UNTIL OUTWARD VISION WAS SEVERELY IMPAIRED. CABIN PRESSURIZATION WAS LOWERED, WINDSHIELD HEAT WAS DISCONTINUED AND THE AIRCRAFT CONTINUED ON TO DESTINATIONNov 9, 2001 · Beech B100 · Flight Compartment WindowsSDR 2001F00164Duct · failedWHILE TROUBLESHOOTING POOR CABIN PRESSURIZATION, FOUND FAILED HOSE IN LEFT ENGINE AIR SUPPLY LINE TO CABIN. THIS CAUSED PRESSURIZATION TO WORK POORLY, BECAUSE THERE WAS NO INPUT TO CABIN FROM LEFT FLOW PACK. SUSPECT DUCT FAILED DUE TO AGE.Jun 22, 2001 · N78DA · Beech B100 · Air Distribution SystemSDR CA010706009Door Frame · cracked(CAN) DOOR FRAME AFT FOUND CRACKED AROUND REAR BAYONET.May 5, 2001 · Beech B100 · Fuselage Main, StructureSDR 2001F00038Controller · defectiveINTERNAL RELAYS FAILED TO CONTACT WHEN GEAR SELECTED DOWN. REPLACED UNIT, SYSTEM WORKED NORMAL. NO RECOMMENDATION.Apr 12, 2001 · N264PA · Beech B100 · Landing Gear Retraction/Extension SystemSDR 20010411CW014Tube · disconnectedDURING TAXI FOR TAKEOFF, THE RIGHT ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN. AIRCRAFT WAS TAXIED BACK AND TURNED OVER TO MAINTENANCE. INSPECTION REVEALED THE P3 LINE DISCONNECTED AT THE FUEL CONTROL. THE LINE WAS RECONNECTED AND THE ENGINE GROUND RUN NORMFeb 26, 2001 · N105VY · Beech B100 · Engine Fuel DistributionSDR CA001205022Fitting · cracked(CAN) DURING SCHEDULED MAINTENANCE CRACKS WERE DISCOVERED EMANATING FROM THE TAPER PIN HOLES ON THE ELEVATOR TORQUE TUBE MIDDLE FITTINGS (BOTH SIDES). (ONE CRACK PER FITTING - TWO FITTING TOTAL). TAPER PINS WERE ALSO FOUND TO BEYOND THE .060 INCH MAX PROTRUSINov 17, 2000 · Beech B100 · Elevator StructureSDR 20000920SH005Bolt · corrodedDURING ROUTINE INSPECTION, FOUND THE RETAINING HARDWARE FOR THE EXHAUST DUCT WITHIN BOTH ENGINE COWLINGS WAS CORRODED BEYOND SERVICEABLE LIMITS. BOLTS AN4-4A AND NUTS MS21042L4. THIS INSPECTION TOOK PLACE AT 310.5 HOURS FROM OVERHAUL OF BOTH ENGINES. (X)Sep 20, 2000 · N120MG · Beech B100 · Engine Collector/Tailpipe/NozzleSDR 20000920SH006Drive Shaft · wornDURING ROUTINE INSPECTION, STARTER DRIVESHAFT WAS FOUND WORN BEYOND SERVICEABLE LIMITS AT 310.5 HOURS AFTER ENGINE OVERHAUL. (X)Aug 31, 2000 · N120MG · Beech B100 · Engine StarterSDR 20000814SH012Engine · making metalDURING A PHASE INSPECTION, THE LEFT ENG OIL FILTER WAS FOUND TO HAVE EXCESSIVE METAL IN OIL FILTER. ANALYSIS ON OIL AND FILTER WAS COMPLETED. METAL WAS FOUND TO BE MAGNESIUM. (X)Jul 25, 2000 · N3699B · Beech B100 · Engine Oil Distribution (Airframe Furnished)SDR CA000824027Accumulator · failed(CAN) 1 HOUR INTO RETURN LEG, MOTOR LIGHT STARTED TO ILLUMINATE MORE OFTEN, FINALLY RUNNING CONTINUOUSLY BEFORE 60 AMP BREAKER IN FLOOR OPENED. PILOT PERFORMED NORMAL GEAR BLOW DOWN AND LANDED. - MAINTENANCE FOUND GEAR SYSTEM ACCUMULATION PRESSURE LOW.- SYSTEMJul 13, 2000 · Beech B100 · Hydraulic Accumulator, AuxiliarySDR CA000714032Skin · cracked(CAN) CRACK DISCOVERED ON THE TOP OF THE AILERON SKIN.SKIN REPLACED.AILERON REINSTALLED.Jun 22, 2000 · Beech B100 · AileronsSDR CA000824021Bolt · cracked(CAN) UPPER FORWARD WING - BOLT FOUND CRACKED DURING ROUTINE INSPECTION.Jun 4, 2000 · Beech B100 · Wing Main, Frame StructureSDR CA000606013Landing Gear · failed(CAN) PILOT SELECTED GEAR UP AFTER TAKEOFF WITH NO GEAR RESPONSE. PILOT CHECKED CONTROL AND POWER CIRCUIT BREAKER AND RECYCLED GEAR, NO RESPONSE. EMERGENCY GEAR EXTENSION AND LANDING C/O-NORMAL. AIRCRAFT PLACED ON JACKS, NO POWER TO GEAR MOTOR. AFTER APPROMay 31, 2000 · Beech B100 · Landing Gear Retraction/Extension SystemSDR CA000511012Bellcrank · loose(CAN) PILOT COMPLAINED OF WING ROCKING PROBLEM. INVESTIGATION FOUND 1/4 PLAY AT RUDDER TRAILING EDGE WHILE PEDALS BEING HELD AT FULL DEFLECTION. PLAY FOUND TO ORIGINATE FROM BELLCRANK FITTING (P/N 50-600016) AND LOWER SUPPORT TUBE ATTACHMENT POINT (RIVETS). Apr 28, 2000 · Beech B100 · Rudder StructureSDR 20000531SH008Channel · corrodedCABIN DOOR WAS OPENED FOR ACCESS TO AIRCRAFT. THE CHANNEL, WHICH FORMS THE BOTTOM OF THE DOOR AND ATTACHES TO THE DOOR HINGE, FAILED AT ITS AFT END. UPON INSPECTION, THE CHANNEL WAS FOUND TO HAVE INITIAL CORROSION, (INSIDE THE DOOR STRUCTURE) DUE TO THE SEALEApr 14, 2000 · N400AC · Beech B100 · Entrance StairsSDR 20000508SH012Mount · wornWHILE DOING A HOT SECTION INSPECTION ON THE RIGHT ENGINE AFTER REMOVAL FROM THE AIRCRAFT, NOTICED DAMAGE TO THE TUBULAR ENGINE MOUNT CROSS-MEMBER. AFTER FURTHER INVESTIGATION, FOUND AN ENGINE MOUNT BRACKET RUBBING AGAINST THE TUBULAR CROSS-MEMBER. (X)Mar 29, 2000 · N818PA · Beech B100 · Engine Mount SectionSDR CA000329016Bolt · cracked(CAN) CF 81-25R5 WAS BEING CARRIED OUT EARLY, 417.2 HRS. FOUND LEFT WING TOP REAR BOLT (P/N 81786-10-18) WAS INSPECTED AND FOUND CRACKED AND REJECTED. NEW BOLT INSTALLED.Mar 14, 2000 · Beech B100 · Wing, Attach FittingsSDR CA991231064Windshield · cracked(CAN) IN CRUISE, THE PILOT NOTICED A 2 INCH CRACK AT THE TOP RIGHT OF THE LEFT WINDSCREEN.THEY DEPRESSURIZED AND CONTINUED TOWARDS THE MAINTENANCE BASE.THE WINDSCREEN HAD ONLY 2 1/2 YEARS SINCE INSTALLATION. WE COMMUNICATED WITH THE AIRCRAFT BUILDER AND WERE Dec 8, 1999 · Beech B100 · Flight Compartment WindowsSDR 99ZZZX4418Terminal End · failedPILOT REPORTED THAT LEFT GENERATOR FAILED IN-FLIGHT. RE-SETTING LEFT GENERATOR CAUSED RIGHT GENERATOR TO FAIL. PILOT COULD USE EITHER GENERATOR ALONE, BUT NOT BOTH AT THE SAME TIME. MAINTENANCE FOUND A BAD TERMINAL END CONNECTING WIRE NR P7A12 TO TERMINAL DNov 16, 1999 · N86TR · Beech B100 · AC Generation SystemSDR 99ZZZX4321Duct · leakingFLIGHT CREW REPORTED AIRCRAFT WOULD NOT PRESSURIZE. TROUBLESHOOTING REVEALED THE AIR CONDITIONING NOSE DISTRIBUTION DUCT LEAKING. THE 'CROSSOVER DUCT' (WELDED ALUMINUM SECTION) CRACKED AND SEPARATED 10.2 INCHES LONG AT THE UPPER FORWARD LATERIAL WELD. THIS Nov 2, 1999 · N4490M · Beech B100 · Air Distribution SystemSDR 99ZZZX4194Generator · failedPILOT REPORTED LEFT GENERATOR FAILED IN-FLIGHT. AFTER RE-SETTING LEFT GENERATOR. BOTH GENERATORS WENT OFF-LINE. IT WAS ALSO REPORTED THAT RIGHT OR LEFT GENERATOR WORKED ALONE, BUT REGARDLESS OF WHICH ONE WAS ON-LINE, BRINGING THE SECOND GENERATOR ON-LINE CAOct 1, 1999 · N86TR · Beech B100 · Starter-GeneratorSDR CA991007062Seal · leaking(CAN) OIL FOUND IN AIR INTAKE AND ON COMP. IMPELLOR. SEAL KIT REPLACEDSep 18, 1999 · Beech B100 · Turbine Engine Compressor SectionSDR 99ZZZX3759Wheel Assy · crackedUPON ROUTINE CLEANING OF THE AIRCRAFT, A CRACK WAS DISCOVERED ALONG THE OUTBOARD END RADIUS OF THE INBOARD WHEEL HALF RUNNING HORIZONTALLY APPROXIMATELY 3.75 INCHES. THE WHEEL WAS MOUNTED ON THE INBOARD LEFT MAIN POSITION. THE WHEEL HALF WAS MANUFACTURED IN Sep 12, 1999 · N136MB · Beech B100 · Wheel/Ski/FloatSDR CA990630095Control Unit · malfunctioned(CAN) INTERMITTANT PROBLEM ON THE LANDING GEAR RETRACTION SYSTEM IN THE UP POSITION ONLY. SOMETIMES THE 'GEAR IN TRANSITION' LIGHT STAYED LIT AND, ON ONE OCCASION, THE GEAR DOWN SELECTION COULD NOT BE DONE OTHER THAN BY THE MANUAL SYSTEM. MANY GEAR RETRACTIJun 9, 1999 · Beech B100 · Landing Gear ActuatorSDR 99ZZZX2340Duct · splitTAIL DE-ICE BOOTS WOULD NOT INFLATE. FOUND DE-ICE SUPPLY LINE COLLAPSED AND PINCHED CLOSED DUE TO HEAT DUCT BELOW FLOOR TO HAVE A SPLIT SEAM ALLOWING HOT AIR TO HEAT PLASTIC DE-ICE HOSE, SOFTEN, THEN BE SUCKED CLOSED FROM THE NORMAL VACUUM SUPPLIED TO BOOTS. May 25, 1999 · N311CM · Beech B100 · Heating SystemSDR 99ZZZX2260Switch · failedLEFT ENGINE STARTED, WOULD NOT ENGAGE. TROUBLESHOT AND FOUND THE LEFT MLG SQUAT SWITCH CONTACTS DEFECTIVE INTERRUPTING THE CONTROL CIRCUIT TO THE START RELAY CONTROL BOX.May 25, 1999 · N311CM · Beech B100 · Landing Gear Position and Warning
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