Beech A100

Service difficulty reports · 472

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 = '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 99ZZZX1900Frame · crackedFOUND CRACKS ORIGINATING FROM HOLE IN FRAMES WHERE THE UPPER LATCH BOLTS GO THROUGH. THESE CRACKS WENT THROUGH THE TWO SCREW HOLES ADJACENT TO THE LATCH BOLT HOLE AND CONTINUED UP THE FRAMES.Apr 15, 1999 · N46BE · Beech A100 · Entrance StairsSDR 99ZZZX1899Frame · crackedFOUND CRACKS ORIGINATING FROM HOLE IN FRAMES WHERE THE UPPER LATCH BOLTS GO THROUGH. THESE CRACKS WENT THROUGH THE TWO SCREW HOLES ADJACENT TO THE LATCH BOLT HOLE AND CONTINUED UP THE FRAMES.Apr 15, 1999 · N46BE · Beech A100 · Entrance StairsSDR AU990430057Fcu · malfunctioned(AU) PILOT NOTED A LOSS OF POWER ON TAKEOFF. THE DIFFERENCE IN TORQUE AT 10,000 FEET WAS 200 POUNDS. ALL ENGINE PARAMETERS WERE TYPICAL OF LACK OF POWER: LOW ITT; FUEL FLOW; NG READINGS. THE FUEL CONTROL UNIT WAS REPLACED AND THE PROBLEM WAS CORRECTED.Mar 29, 1999 · Beech A100 · Fuel Control/Reciprocating EnginesSDR 99ZZZX2108Duct · failedTHE DEFECT WAS FOUND DURING A REGULAR INSPECTION. UPON VISUAL INSPECTION THROUGH THE EXHAUST DUCTS, NOTED THE INNER SECTION DUCT ASSY PN 3106820-01 HAD SPLIT, BROKE UP AND CURLED UP. THE END OF THIS CURLED UP METAL PIECE OF THE DUCT HAD COME IN CONTACT WITH Mar 24, 1999 · N900DN · Beech A100 · Turbine SectionSDR CA990323016Duct · contaminated(CAN) IN CLIMB THROUGH 9,700 FEET, THE CREW NOTICED SMOKE IN THE COCKPIT AND RETURNED TO LAND IMMEDIATELY. SMOKE DISSIPATED DURING DESCENT. MAINTENANCE FOUND THE RIGHT ENGINE HAD AN ACCUMULATION OF OIL IN THE COWLINGS COUPLED WITH A LOOSE OIL LINE AND AN OILMar 23, 1999 · Beech A100 · Air Distribution SystemSDR CA990330055Actuator · out of limits(CAN) AT FIRST END PLAY CHECK, PINION GEAR WAS FOUND TO BE OUT OF LIMITS. 0.10 THOUSAND PLAY IN PINION.Mar 22, 1999 · Beech A100 · Landing Gear Door ActuatorSDR CA990330019Torque Link · cracked(CAN) TORQUE LINK HAS A CRACK AT THE CENTER SINGLE BOLT LUG. CRACK IS LOCATED ON THE INBOARD RADIUS.Mar 17, 1999 · Beech A100 · Main Landing Gear Strut/Axle/TruckSDR CA990323010Bolt · damaged(CAN) WHILE COMPLETING AD CF-81-25R5, WING BOLT INSPECTION, THE RIGHT FORWARD LOWER BOLT WAS FOUND TO BE VERY TIGHT. AFTER REMOVAL OF THE BOLT, DISCOVERED THE BOLT AND NUT WERE DAMAGED WHICH MADE THE BOLT VERY DIFFICULT TO REMOVE. UPON FURTHER INVESTIGATION,Mar 9, 1999 · Beech A100 · Wing, Attach FittingsSDR CA990318034Bearing · failed(CAN) CREW REPORTED TORQUE FLUCTUATIONS, GROUND RUN CONFIRMED TORQUE FLUCTUATIONS ALONG WITH FUEL FLOW, PROPELLER SPEED AND ENGINE RPM FLUCTUATIONS. OIL PRESSURE AND TEMPERATURES WERE NORMAL. THE FCU WAS REMOVED TO INSPECT FCU DRIVE AND THE NG FLYWEIGHT BEARFeb 26, 1999 · Beech A100 · Fuel Control/Turbine EnginesSDR CA990308009Wire · failed(CAN) WHEN STARTING THE AIRCRAFT, SMOKE NOTED IN THE CABIN. AIRCRAFT SHUTDOWN. INSPECTION FOUND A BURNT WIRE FROM THE THRESHOLD LIGHT FUSE TO SWITCH; AND TO BAGGAGE COMPARTMENT LIGHT SWITCH TO AFT DOME LIGHT. AFT DOME LIGHT SOCKET WAS BROKEN, POSSIBLY FROM Feb 25, 1999 · Beech A100 · Light System WiringSDR CA990226005Door · damaged(CAN) DURING GEAR RETRACTION, THE GEAR INTRANSIT WARNING LIGHTS STAYED ON. GEAR CYCLED WITH NO RESPONSE. EMERGENCY EXTENSION USED. GEAR DOOR LEFT HAND MAIN INBOARD FOUND DAMAGED BY WHEEL ASSY. WHEN GEAR RETRACTED, MOTOR CIRCUIT BREAKER HAD ALSO TRIPPED. Feb 21, 1999 · Beech A100 · Landing Gear DoorsSDR CA990301006Wire · shorted(CAN) THE 90 DEGREE HEAT DUCT ON THE RIGHT HAND OF THE COPILOT'S RUDDER PEDALS DIRECTS HOT AIR ONTO THE NR 2 COMM, AND DME COAXIAL WIRE BUNDLES. OVER TIME , THIS CAUSED CABLE DAMAGE MELTING THE WIRE AND ALLOWING THE CENTER CONDUCTOR TO SHORT TO THE SHIELD. DFeb 17, 1999 · Beech A100 · Communications System WiringSDR CA990224009Control Cable · broken(CAN) RIGHT HAND PROPELLER CONTROL CABLE FOUND BROKEN APPROXIMATELY 14 INCHES FROM THE ROD END UNDER THE PEDESTAL.Feb 10, 1999 · Beech A100 · Propeller Controlling SystemSDR CA990219003Connector · misinstalled(CAN) CREW OBSERVED A DELAY IN THE ENGINE START TIME. MAINTENANCE INSPECTION FOUND POOR SOLDER CONNECTIONS AT THE IGNITION REGULATOR POWER INPUT CANNON PLUG. CONNECTIONS WERE REPAIRED AND IGNITION TIME GROUND CHECKED SERVICEABLE.Feb 3, 1999 · Beech A100 · Ignition Power SupplySDR CA981230038Switch · failed(CAN) AFTER TAKEOFF, THE LEFT HAND PROPELLER TENDED TO FEATHER. THE PILOT CONTROLLED THE FAILURE AND MADE AN EMERGENCY LANDING. INVESTIGATION REVEALED THE LOW PITCH SWITCH WAS NOT WORKING AND THERE WAS A WORN CARBON BRUSH IN THE MECHANISM.Dec 10, 1998 · Beech A100 · Propeller Controlling SystemSDR CA981230060Bolt · cracked(CAN) WHILE DOING AD CF-81-25R5, NDT TEST SHOWED A SMALL CRACK IN THE RADIUS OF THE BOLT HEAD. IT IS POSSIBLE THAT CRACK IS OVERLAP OF CAD PLATING.Dec 8, 1998 · Beech A100 · Wing, Attach FittingsSDR CA990115005Hub · worn(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE CYLINDER WAS FOUND WORN BEYOND LIMITS.Nov 11, 1998 · Beech A100 · Propeller Hub SectionSDR CA981125070Bellcrank · corroded(CAN) WHEN THE RUDDER BELLCRANK ASSEMBLY WAS REMOVED FOR INSPECTION, IT WAS NOTICED THERE WAS A DEEP PITTING AROUND THE ATTACHMENT BOLT HOLE. THE CORROSION RADIATED OUT FROM THE HOLE TWO INCHES. THIS LOCATION IS UNDER THE RUDDER TORQUE TUBE ATTACHMENT FITTINNov 4, 1998 · Beech A100 · Rudder StructureSDR CA981113011Door Frame · worn(CAN) THE DOOR FRAMES PART NUMBERS SO-440014-415, SO-440020-103, AND SO-440025-173 WERE REPLACED DUE TO EXCESSIVE WEAR. THE WEAR IS CAUSED BY THE DOOR SKIN AS IT MEETS THE FUSELAGE FRAME. A THIN LAYER OF PRC IS USED TO CUSHION THE DOOR SKIN TO FRAME CONTACT Nov 3, 1998 · Beech A100 · Passenger/Crew DoorsSDR CA981113010Turnbuckle · cracked(CAN) DURING THE INTERIOR INSPECTON OF THE AIRCRAFTS TAIL, A TURNBUCKLE ON THE RUDDER CABLE WAS FOUND CRACKED. THE CRACK RAN THE LENGTH OF THE SLOT THAT THE TURNBUCKLE SAFETY PIN FITS INTO. THE TURNBUCKLE WAS STILL IN SAFETY AND THE CABLE TENSION WAS CORRECTNov 3, 1998 · Beech A100 · Rudder Control SystemSDR 99ZZZX128Power Supply · failedAIRCRAFT WAS ON DOWN-WIND: CABIN FILLED WITH SMOKE. FOUND CABIN FLUORESCENT LIGHT POWER SUPPLY FAULTY, OVERHEATED, RUPTURED, BURNT, AND LEAKING. CIRCUIT BREAKER DID NOT TRIP. CHECKED CIRCUIT BREAKER FOR CORRECT OPERATION.Oct 5, 1998 · N753DB · Beech A100 · Passenger Compartment LightingSDR CA980928018Stringer · cracked(CAN) DURING THE INVESTIGATION OF DAMAGE TO THE LOWER SKIN OF THE CENTER SECTION, THE AUXILIARY FUEL CELL LINER WAS REMOVED, FOUND THE T-EXTRUSION WHICH TIES TOGETHER THE LOWER SKIN WITH THE NACELLE KEEL STRUCTURE CRACKED AT THE AFT END. PART TC: 11,414.Sep 23, 1998 · Beech A100 · Wing, Longeron/StringerSDR CA980930014Screw · corroded(CAN) DURING THE 13,000 CYCLE FUSELAGE INSPECTION, THREE SCREWS ON THE FORWARD SPAR CAP WERE FOUND CORRODED AND SHEARED OFF. FURTHER INVESTIGATION REVEALED THE PRC AROUND THE UPPER SPAR CAP AND FUSELAGE SKIN HAD WORKED LOOSE AND MAY BE THE SOURCE FOR THE CORRSep 18, 1998 · Beech A100 · Wing SparSDR CA981013001Warning System · failed(CAN) ON AUGUST 14, 1998, AIRCRAFT MADE A WHEELS UP LANDING. PRIMARY CAUSE WAS PILOT DID NOT SELECT GEAR DOWN. SINCE THEN, PILOTS HAVE REPORTED WARNING HORN DOES NOT GIVE WARNING UNTIL POWER IS REDUCED WELL BELOW TOUCH-DOWN POWER. BEECH CALLS FOR WARNING HOSep 14, 1998 · Beech A100 · Landing Gear Position and WarningSDR CA980814008Line · leaking(CAN) AFTER FUSELAGE STRINGER REPAIR, A LEAK CHECK OF THE PITOT STATIC SYSTEM WAS CARRIED OUT AND WAS FOUND TO HAVE AN EXCESSIVE LEAK RATE. A FURTHER CHECK REVEALED THAT THE CAUSE WAS DUE TO PIN HOLES IN EACH AFT STATIC LINE. THE PIN HOLES WERE ATTRIBUTED TOAug 6, 1998 · Beech A100 · Pitot/Static SystemSDR CA980819005Sense Line · cracked(CAN) ON MEDIVAC DEPARTURE, RIGHT HAND BLEED AIR FAILURE LIGHT CAME ON SHORTLY AFTER TAKE-OFF. RIGHT ENGINE SHUT DOWN. AIRCRAFT RETURNED TO BASE. MAINTENANCE CHECK REVEALED RIGHT BLEED AIR PRESSURE ANNUNCIATOR SENSE LINE CRACKED UNDER FLOOR AT BLEED AIR MANJul 31, 1998 · Beech A100 · Compressor Bleed ControlSDR CA980706001Line · cracked(CAN) FUEL LINE WAS LEAKING AT THE FITTING WELD.Jun 22, 1998 · Beech A100 · Engine Fuel DistributionSDR CA980623019Shaft · worn(CAN) ENGINE WAS CONSUMING OIL WHICH WAS EXITING FROM THE BREATHER. ACCESSORY GEARBOX WAS REMOVED AND SPLIT TO REPLACE THE CARBON SEAL. FURTHER INSPECTION OF THE GEARSHAFT ASSEMBLY SHOWED WEAR ON THE SPLINE SHAFT AND CRACKS ON THE CARBON SEAL FACE. THE STARJun 12, 1998 · Beech A100 · Turbine Engine Accessory DriveSDR CA980623018Impeller · worn(CAN) ENGINE WAS CONSUMING OIL, IT APPEARED TO BE COMING FROM THE BREATHER. THE ACCESSORY GEARBOX WAS SPLIT TO REPLACE THE CARBON SEAL. EROSION PITTING WAS FOUND ON THE LEADING EDGE OF THE IMPELLER VANES. THE IMPELLER AND GEARSHAFT ASSEMBLY WERE CHANGED AS Jun 12, 1998 · Beech A100 · Turbine Engine Accessory DriveSDR CA980930005Pulley · failed(CAN) AIR CONDITIONER COMPRESSOR PULLEY FAILURE. BOLT STARTED TO BACK OFF CAUSING THE PULLEY TO MIGRATE OFF SHAFT AND MOVE. STEEL WOODRUFF KEY BEGAN TO CHEW UP THE PULLEY. DUE TO THE LOOSENESS, PULLEY FAILED. THERE IS NO LOCKING DEVICES ON THE END BOLT TO Jun 8, 1998 · Beech A100 · Cabin Compressor SystemSDR 98ZZZX2008Lock · misinstalledREMOVED RIGHT ENGINE POWER SECTION FOR ACCESS TO PERFORM SCHEDULED HOT SECTION INSPECTION. UPON DISASSEMBLY, DISCOVERED TAB WASHERS (16 EACH) WERE NOT BENT TO THE SAFETY POSITION. THESE WASHERS SAFETY THE BOLTS THAT RETAIN THE CT VANE RING AND NR 2 BEARING CMay 19, 1998 · N96AU · Beech A100 · Turbine SectionSDR CA980529009Bolt · sheared(CAN) DURING THE HIGH CYCLE FUSELAGE INSPECTION, A SHEARED BOLT WAS FOUND INSIDE THE FUSELAGE IN THE AREA OF STA 190 RIGHT SIDE WHERE THE FORWARD SPAR PASSES THROUGH THE FUSELAGE. SUBMITTER STATED AS THIS ITEM IS IMPORTANT TO THE STRUCTURAL INTEGRITY OF THE AMay 14, 1998 · Beech A100 · Fuselage, Wing Attach FittingsSDR CA980512011Bushing · seized(CAN) AIRCRAFT STEERING FOUND TO BE STIFF AND JERKY. MAINTENANCE FOUND RT RUDDER PEDAL BUSHING SEIZED TO SHAFT P/N 50-524402-7, IPC 27-23-01, PG 4, FIG. 23-01, ITEM 25. RUDDER PEDAL ASSEMBLY REPLACED WITH OVERHAULED SET.May 8, 1998 · Beech A100 · Rudder Control SystemSDR CA980507012Window Retainer · corroded(CAN) WINDOW RETAINERS OF WINDOWS 2 AND 3 IN THE PASSENGER COMPARTMENT WERE FOUND TO BE CORRODED. THE CORROSION IS DIFFICULT TO SEE WHEN THE WINDOW SHADE ASSEMBLY IS INSTALLED BUT OBVIOUS WHEN SHADES ARE REMOVED. SUBMITTER STATED LEAKING SEALS OF THE WINDOW May 1, 1998 · Beech A100 · Passenger Compartment WindowsSDR CA980504022Intercostal · cracked(CAN) THE INTERCOSTAL BRACKET LOCATED UNDER THE CABIN DOOR POST BRACKET WAS FOUND CRACKED. THE CRACK IS ATTRIBUTED TO LOADS PLACED ON THE DOOR POST BY PASSENGERS AND CREW EXITING THE A/C AND USING THE DOOR POST FOR SUPPORT. THE INTERCOSTAL WAS FOUND CRACKED Apr 28, 1998 · Beech A100 · Fuselage Miscellaneous StructureSDR CA980504016Windscreen · cracked(CAN) AFTER TAKEOFF WHEN THE A/C BEGAN TO PRESSURIZE, THE CO-PILOT NOTICED THE RT WINDSHIELD BEGINNING TO CRACK ON THE OUTBOARD EDGE. A/C DEPRESSURIZED AND RETURNED SAFELY TO BASE. MAINTENANCE REPLACED THE CRACKED WINDOW AND NOTICED A SMALL CHIP ON IT. FLEEApr 24, 1998 · Beech A100 · Flight Compartment WindowsSDR CA980406047Support · cracked(CAN) RIVETS ATTACHING DOOR HINGE TO DOOR SUPPORT CRACKED AT RIVET HOLES. SUPPORT REPLACED.Mar 27, 1998 · Beech A100 · Passenger/Crew DoorsSDR CA980325024Brushes · worn(CAN) BRUSHES FOUND WORN PAST USABLE LIMIT. WHEN REPLACING BEARINGS FOUND WERE NOT OEM THEY SHOULD BE K271B202EL.Mar 23, 1998 · Beech A100 · Air Distribution FanSDR CA980330015Angle · cracked(CAN) ON ROUTINE WING INSPECTION, THE RT OUTBOARD FLAP INBOARD FLAP HANGER, LOWER CLIPS P/N 35-115 396-1 AND -3 WERE FOUND TO BE TORN AT HANGER RIVET ATTACHMENTS AND THE LOWER PORTION OF THE HANGER TO SPAR ATTACHMENT ANGLES P/N 35-115398-1 AND -3 WERE TORN AWAMar 18, 1998 · Beech A100 · Wing, Attach FittingsSDR CA980330014Nut · cracked(CAN) WHILE COMPLYING WITH AD CF-81-25R, FLUORESCENT PENETRANT INSPECTION SHOWED NUT ON THE RT UPPER AFT WING BOLT WAS CRACKED. THE NUT WAS ALSO FOUND TO BE THREAD BOUND WHEN TORQUED TO SPECIFICATIONS. A NEW WING BOLT KIT WAS INSTALLED WHICH CORRECTED THE PRMar 18, 1998 · Beech A100 · Wing, Attach FittingsSDR CA980325035Brushes · worn(CAN) ON DEPARTURE, SMOKE REPORTED COMING FROM THE EYELET. PILOT GANGBARED THE ELECTRICAL SYSTEM, CABIN DEPRESSURIZED AND AIRCRAFT RETURNED TO DEPARTURE BASE. VENT BLOWER REPLACED.Mar 17, 1998 · Beech A100 · Air Distribution FanSDR CA980317055Link · cracked(CAN) DURING ROUTINE INSPECTION THE NLG STEERING LINK BRACKET FOUND CRACKED. NEW LINK RECEIVED IS MADE OF MUCH HEAVIER MATERIAL. REPLACED.Mar 10, 1998 · Beech A100 · Landing Gear Steering SystemSDR CA980318003Fuel Control · surges(CAN) ENGINE SURGING ON TAKEOFF, AIRCRAFT RETURNED TO BASE. FUEL CONTROL UNIT REPLACED AND AIRCRAFT RETURNED TO SERVICE.Mar 9, 1998 · Beech A100 · Fuel Control/Reciprocating EnginesSDR CA980311021Piston · corroded(CAN) HYD FLUID LEAKING FROM MLG ACTUATOR AT POINT WHERE THE WIPER SEAL CONTACTS THE PISTON. PITTING DUE TO CORROSION. REPLACED.Mar 9, 1998 · Beech A100 · Landing Gear ActuatorSDR CA980311020Skin · cracked(CAN) 2 CRACKS FOUND IN SKIN AT OUTER MOST HUCK BOLT, 4.5 INCHES FROM PARTING LINE BETWEEN CENTRE SECTION AND L/H WING PANEL. ONE CRACK IS .750 INCH LONG AND RUNS FROM LEADING EDGE OF SKIN AROUND HUCK BOLT HEAD AND BEYOND. SECOND CRACK .250 COMES OUT FROM UNDEMar 9, 1998 · Beech A100 · Fuselage Main, Plate/SkinSDR CA980311019Shaft · corroded(CAN) HYD FLUID LEAKING FROM MLG ACTUATOR PISTON. PISTON PITTED WITH CORROSION AT CONTACT POINT OF FELT WIPER. REPLACD.Mar 9, 1998 · Beech A100 · Landing Gear ActuatorSDR CA980318014Actuator · binding(CAN) ACTUATOR BINDING/SLIPPING INTERNALLY. REPLACED.Feb 17, 1998 · Beech A100 · Landing Gear ActuatorSDR CA980225021Door · out of adj(CAN) PILOTS REPORTED GEARS STAYED IN TRANSIT ON UP/DOWN SELECTION. GEAR ALSO FAILED TO EXTEND MANUALLY. GEAR FINALLY SHOWED THREE GREEN AND AIRCRAFT LANDED OK. MAIN LANDING GEAR DOORS CLOSING TOO TIGHT, OUT OF ADJUSTMENT. REPAIRED.Feb 14, 1998 · Beech A100 · Landing Gear Retraction/Extension SystemSDR CA980318011Actuator · failed(CAN) NOTICEABLE BINDING WHEN ROTATING ACTUATOR AT .500 STROKE, END PLAY OK.Feb 11, 1998 · Beech A100 · Landing Gear ActuatorSDR CA980430026Frame · cracked(CAN) DURING FUSELAGE INSPECTION, CRACKS WERE FOUND ON FRAME AT STATION 207.35 AT FLOOR LEVEL RT AND LT SIDES. THE CRACK WAS FROM A RADIUS OF A CUT-OUT IN THE FRAME THAT ALLOWS A RIB TO PASS THROUGH IT. A DOUBLER WAS INSTALLED IAW MANUFACTURERS REPAIR.Jan 28, 1998 · Beech A100 · Fuselage Main, Frame
Back to Beech A100