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 CA971231015Control Cable · misinstalled(CAN) ON LANDING, THE RUDDER CABLES JAMMED. INVESTIGATION REVEALED THAT THE CABLES WERE ROUTED UNDER THE RUDDER SERVO ATTACH BRACKET. THE SWAGED ENDS CAUGHT THE EDGE OF THE BRACKET AND COULD NOT BE MOVED. CABLES REROUTED.Dec 10, 1997 · Beech A100 · Rudder Control SystemSDR CA971216066Window · bubbled(CAN) PILOTS SIDE WINDOW FOUND BUBBLED ON THE EDGE OF THE WINDSHIELD.Dec 10, 1997 · Beech A100 · Flight Compartment WindowsSDR CA971216063Pinion Gear · loose(CAN) INTRANSIT LIGHT ON IN-FLIGHT. LANDED OK. NOSE ACTUATOR HAD EXCESSIVE PLAY IN THE PINION GEAR AND WAS VERY NOISY. PART TC: 317.Nov 27, 1997 · Beech A100 · Landing Gear ActuatorSDR CA971216059Duct · misaligned(CAN) BLEED AIR DUCTS FOUND MISALIGNED UNDER THE COPILOT'S FLOOR AFTER MAINTENANCE.Nov 25, 1997 · Beech A100 · Pneumatic Distribution SystemSDR CA971216058Distribution Box · pin hole(CAN) AIRCRAFT RETURNED TO POINT OF ORIGIN WHEN A BLEED AIR WARNING INDICATION WAS RECEIVED. INSPECTION FOUND A PIN HOLE IN THE BELLY OF THE DISTRIBUTION BOX.Nov 25, 1997 · Beech A100 · Engine Bleed Air SystemSDR CA971216056Line · melted(CAN) BLEED AIR WARNING LINE HAD MELTED WHICH GAVE READING OF BLEED AIR FAIL LIGHT. NO FAILURE OF BLEED AIR SYSTEM JUST LACK OF INSULATION BY DISTRIBUTION BOX.Nov 20, 1997 · Beech A100 · Bleed Air Indicating SystemSDR CA971216052Flow Divider · leaking fuel(CAN) AFTER TAKEOFF, PILOT NOTED FUMES IN THE COCKPIT AND SMOKE FROM INBOARD EXHAUST STACK ON NR 1 ENGINE. AFTER FLIGHT, MAINTENANCE SPOOLED THE ENGINE AND FOUND FUEL LEAKING FROM THE FLOW DIVIDER. IT IS THOUGHT WHEN THE ELBOW FITTINGS WERE TRANSFERRED TO THNov 19, 1997 · Beech A100 · Fuel DividerSDR CA971216053Skin · cracked(CAN) AIRCRAFT SKIN FOUND CRACKED ON THE BOTTOM OF FUSELAGE AFT OF THE MAIN SPAR ON EACH OUTBOARD SIDE. CRACKS OUTSIDE OF BELLY SPLICE PLATES. AIRCRAFT TT: 17,540 HOURS.Nov 14, 1997 · Beech A100 · Fuselage Main, Plate/SkinSDR CA971118011Bolt · wrong part(CAN) DURING AN HSI ON THE NR 2 ENGINE, THERE WERE SEVEN P/N MS9574-04 BOLTS FOUND INSTALLED ON THE COMPRESSOR TURBINE SHROUD HOUSING. THESE BOLTS ARE THE WRONG MATERIAL FOR THIS INSTALLATION. THE PROPER BOLTS SHOULD BE P/N 3012061 OR P/N MS9714-04.Nov 13, 1997 · Beech A100 · Turbine SectionSDR CA971020011Circuit Board · shorted(CAN) SMOKE NOTED AND SMELT COMING FROM BEHIND INSTRUMENT PANEL DURING DESCENT. BATTERY AND BOTH GENERATORS WERE SHUT OFF AND THE SMOKE STOPPED AVIONICS MASTER RESELECTED ON AND SMOKE OBSERVED AGAIN INVESTIGATION FOUND THE GPS RECEIVER CIRCUIT BOARD HAD OVEOct 15, 1997 · Beech A100 · Global Positioning SystemSDR CA970904036Spar · cracked(CAN) REAR SPAR CRACKED UNDER MIDDLE AND UPPER HINGE AT ANCHOR NUT LOCATION.Aug 18, 1997 · Beech A100 · Rudder, Spar/RibSDR CA970815008Hinge · corroded(CAN) CORROSION FOUND ON THE LOWER RUDDER HINGE BOLT HOLES. CORROSION ALSO FOUND ON THE BRACKET.Aug 7, 1997 · Beech A100 · Rudder/Tab, Attach FittingsSDR CA970728001Frame · cracked(CAN) FRAME AT STA 207 APPROXIMATELY EIGHT INCHES ABOVE FLOOR LEVEL ON LEFT SIDE CRACKED FROM LOWER TWO LIGHTING HOLES TO THE STRINGER CUT-OUT. REPAIRED.Jul 22, 1997 · Beech A100 · Fuselage Main, FrameSDR CA970715025Fuel Cap · departed(CAN) AIRCRAFT HAD BEEN REFUELED AND PREPARED FOR DEPARTURE WHEN THE PILOT NOTICED THE LEFT HAND AUXILIARY FUEL CAP MISSING. AIRCRAFT RETURNED TO BASE AND IT WAS DETERMINED THAT THE CAP COULD BE LOCKED AND STILL RELEASE FROM THE TANK. NEW CAPS WERE INSTALLED OJun 26, 1997 · Beech A100 · Fuel StorageSDR CA970620010Bleed Air Tube · cracked(CAN) ON CLIMB THROUGH 5,000 FEET THE LEFT HAND "BLEED AIR DETECT" WARNING LIGHT ILLUMINATED ON THE GLARE SHIELD. LEFT HAND ENGINE SHUTDOWN AS PER PROCEDURES. AIRCRAFT LANDED SAFELY. MAINTENANCE FOUND A CRACKED BLEED AIR LEAK DETECT TUBE IN THE LEFT HAND WHEELJun 13, 1997 · Beech A100 · Pneumatic Indicating SystemSDR CA970609018Governor · faulty(CAN) WHILE IN CRUISE THE #2 PROPELLER BEGAN TO FLUCTUATE BETWEEN MAX AND MIN AND THEN STARTED TO GO TO FEATHER. THE ENGINE WAS SHUTDOWN AND THE PROPELLER FEATHERED. THE GOVERNOR WAS RECENTLY INSTALLED TO REPLACE A T/X'D UNIT. THIS AND THREE OTHER PROPELLER GOJun 6, 1997 · Beech A100 · Propeller GovernorSDR CA970603011Shim · loose(CAN) ACTUATOR FAILED EARLY IN LIFE.May 28, 1997 · Beech A100 · Landing Gear ActuatorSDR CA970603010Pinion Shim · loose(CAN) PINION SHAFT LOOSE AFTER SHORT TIME IN SERVICE.May 28, 1997 · Beech A100 · Landing Gear ActuatorSDR CA970528030Bolt · loose(CAN) BORESCOPE INSPECTION FOUND A BOLT LODGED IN THE CT VANE. THE BOLT WAS IN THE GAS PATH AND WAS SLOWLY ERODING, IT WOULD HAVE HIT THE CT DISK AND THE ENGINE WOULD HAVE DESTRUCTED. THE CAUSE OF THIS FAILURE IS THE SERRATIONS ON THE LOCKWIRE PLIERS JAWS, WHIMay 27, 1997 · Beech A100 · Turbine SectionSDR CA970520004Piston Rod · corrosion(CAN) PISTON ROD FOUND CORRODED AT CONTACT POINT OF FELT WIPER IN DOWN POSITION. REPLACED. PART TC: 879.May 13, 1997 · Beech A100 · Landing Gear ActuatorSDR 97ZZZX2933Toruqe Tube · crackedFOUND DURING AIRCRAFT PRIMARY INSPECTION. SMALL CRACK FOUND IN RIGHT ELEVATOR TORQUE TUBE FITTING NEXT TO TAPER PIN. REPLACED TORQUE TUBE ASSEMBLY.May 9, 1997 · N100GV · Beech A100 · Elevator Control SystemSDR CA970513011Wire · broken(CAN) WHILE ON TRAINING, THE CREW SELECTED THE GEAR DOWN AND THE AIRCRAFT RESPONDED NORMALLY, EXCEPT RT GEAR DOWN LIGHT FAILED TO ILLUMINATE. FLY-BY CONFIRMED THAT GEAR DOWN. A/C LANDED. FOUND BROKEN WIRE, REPAIRED.May 7, 1997 · Beech A100 · Landing Gear System WiringSDR CA970624028Pressure Switch · shorted(CAN) WATER CONTAMINATION IN THE CANNON CONNECTOR IN THE LEFT HAND MAIN WHEEL WELL CAUSED A GROUND WHICH KEPT THE HYDRAULIC MOTOR RUNNING AND EVENTUAL OVERHEAT.Apr 29, 1997 · Beech A100 · Hydraulic Pump (Electric/Engine), MainSDR CA970423021Cockpit Window · shattered(CAN) AIRCRAFT WAS IN LEVEL CRUISE AT 14,000 FEET AND APPROXIMATELY 4.5 PSI. WITHOUT WARNING THE CAPTAIN'S SIDE "D" WINDOW DISINTEGRATED, CAUSING A RAPID DECOMPRESSION. EMERGENCY DESCENT WAS ACCOMPLISHED AND AIRCRAFT LANDED SAFELY. INVESTIGATION FOUND APPROXIMApr 14, 1997 · Beech A100 · Flight Compartment WindowsSDR CA970312007Cam · failed(CAN) ON PREFLIGHT, PILOT COULD NOT GET THE MAIN DOOR LOWER BAYONETS TO RETRACT ALLOWING HIM TO SHUT THE DOOR. THE WELD THAT HOLDS THE SHAFT TO THE DOOR FAILED ALLOWING THE SHAFT TO SPIN FREELY. REPLACED.Mar 5, 1997 · Beech A100 · Passenger/Crew DoorsSDR CA970312006Lintel · chafed(CAN) DOOR CHAFING ON THE UPPER DOOR LINTEL CAUSING LINTEL TO WEAR THIN. LINTEL REPLACED AND DOOR ADJUSTED.Mar 5, 1997 · Beech A100 · Fuselage Main, StructureSDR CA970226062Switch · failed(CAN) ON DESCENT, NOSE GEAR DID NOT INDICATE GREEN. GEAR SWUNG THREE OR FOUR TIMES, NO GO. FLY-BY CONFIRMED GEAR DOWN. AIRCRAFT LANDED OK. NOSE DOWN LOCK SWITCH REPLACED AS NO PROBLEM COULD BE FOUND, AND SWITCH HAD BEEN A PROBLEM A FEW DAYS EARLIER.Feb 20, 1997 · Beech A100 · Landing Gear Position and WarningSDR CA970226061Windshield · cracked(CAN) WINDSHIELD CRACKED DURING CRUISE. PART TT: 17,086 HOURS.Feb 19, 1997 · Beech A100 · Flight Compartment WindowsSDR CA970226059Switch · out of adjust(CAN) WHEN GEAR SELECTED DOWN, NOSE GEAR DID NOT SHOW GREEN. EMERGENCY PROCEDURES GOT GREEN. AIRCRAFT LANDED OK. FOUND NOSE GEAR SWITCH REQUIRED ADJUSTMENT.Feb 17, 1997 · Beech A100 · Landing Gear Position and WarningSDR CA970226058Regulator · not engaged(CAN) SHORTLY AFTER TAKEOFF THE #1 ENGINE LOST OIL PRESSURE AND HAD TO BE SHUTDOWN. INSPECTION OF THE OIL PRESSURE REGULATOR FOUND THE CLIP ON THE OIL PRESSURE HOUSING WAS NOT FULLY ENGAGED. THE REGULATOR WAS DISASSEMBLED AND INSPECTED, NO FAULT WAS FOUND. THEFeb 17, 1997 · Beech A100 · Turbine Engine Oil SystemSDR 97ZZZX752Support · brokenAFTER READING A REPORT IN THE JAN ISSUE ABOUT AIR STAIR STRUCTURE CRACKS, EXAMINED OUR (ACFT DOOR). FOUND THAT THE AIR STAIR DAMPNER UPPER ATTACH POINT WAS FLEXING DURING TRANSITION. FURTHER INVESTIGATION REVEALED THAT THE STRINGERS THAT THE ATTACH POINT IS Jan 28, 1997 · N115DT · Beech A100 · Fuselage Miscellaneous StructureSDR CA970128007Indicator · faulty(CAN) AIRCRAFT WAS IN CRUISE WHEN THE RIGHT HAND OIL PRESSURE INDICATOR WAS FLICKERING, ALL OTHER PARAMETERS WERE NORMAL. SEVERAL MINUTES LATER THE OIL PRESSURE WENT TO "0". THE #2 ENGINE WAS SHUTDOWN. POST FLIGHT INSPECTION FOUND THE OIL PRESSURE/TEMPERATURE Jan 20, 1997 · Beech A100 · Engine Oil PressureSDR CA970121009Switch · intermittent(CAN) DURING APPROACH, PILOTS UNABLE TO GET GEAR DOWN INDICATION. RETURNED TO BASE AND FLYBY CONFIRMED GEAR DOWN. MAINTENANCE FOUND THE DOWNLOCK SWITCH TO BE INTERMITTENT.Jan 13, 1997 · Beech A100 · Landing Gear Position and WarningSDR CA961218008Engine · failed(CAN) DURING FLIGHT LOUD BANGS WERE HEARD FROM THE #1 ENGINE WITH FLAMES COMING FROM THE EXHAUST STACKS. AN ENGINE FIRE DRILL WAS CARRIED OUT AND THE ENGINE SHUTDOWN. THE AIRCRAFT RETURNED TO BASE WITHOUT INCIDENT. THE ENGINE WAS REMOVED FOR INVESTIGATION. REPDec 6, 1996 · Beech A100 · Engine (Turbine/Turboprop)SDR CA961205001Tube Assembly · cracked(CAN) THE PILOT NOTICED A SUBSTANTIAL INCREASE IN FUEL FLOW PRIOR TO LANDING. POST FLIGHT INSPECTION FOUND THE FUEL SYSTEM BYPASS LINE CRACKED AT THE SLEEVE, WHICH IS SILVER SOLDERED ONTO THE END OF THE STAINLESS STEEL LINE. THE SUBMITTER STATES THIS SAME FAULNov 26, 1996 · Beech A100 · Engine Fuel DistributionSDR CA961203007Skin · cracked(CAN) LEFT AILERON UPPER AND LOWER SKINS CRACKED ALONG SPAR AT TRAILING EDGE OF LEADING EDGE SKIN. RIGHT AILERON LOWER SKIN CRACKED SAME PLACE. ALSO, P/N 99-13000-197 AND -199.Nov 18, 1996 · Beech A100 · AileronsSDR CA961112028Latch Receiver · bent(CAN) AT 11,000 FEET, PILOT NOTICED A LARGE VIBRATION AND A PITCH DOWN ATTITUDE. CREW DETERMINED THAT THE RIGHT WING LOCKER WAS OPENED. EMERGENCY DECLARED AND AIRCRAFT LANDED OK. BOTH LATCH RECEIVER ASSEMBLIES WERE BENT NOT ALLOWING THE LATCH ASSEMBLY PIN TO EOct 31, 1996 · Beech A100 · Wing Miscellaneous StructureSDR CA961030002Spar · cracked(CAN) AT THE SPAR CUTOUT WHICH THE INBOARD FLAP TRACK PASSES AS THE FLAP IS RETRACTED, A .50 INCH CRACK WAS FOUND, EXTENDING FROM THE TOP INBOARD CORNER INTO THE BEND RADIUS BETWEEN THE WEB AND FLANGE. PART TC: 10,196. AIRCRAFT TT: 10,017 HOURS.Oct 28, 1996 · Beech A100 · Trailing Edge FlapsSDR CA961029006Spar · cracked(CAN) SMALL CRACK, APPROXIMATELY 0.750 INCH IN LENGTH FOUND ON INBOARD FLAP SPAR. CRACK LOCATED AT INBOARD FLAP TRACK ATTACHMENT POINT IN THE MAIN SPAR. FURTHER INVESTIGATION FOUND A LARGER CRACK ABOUT 6 INCHES LONG FURTHER OUTBOARD IN THE UPPER SPAR RADIUS.Oct 25, 1996 · Beech A100 · Trailing Edge FlapsSDR CA961025012Torque Knee · cracked(CAN) BOLT P/N 99-810061-3 FOUND LOOSE AT THE TORQUE KNEE UNION. WHEN DISASSEMBLED TO ADD WASHERS FOR SHIMMING, THE LOWER KNEE WAS FOUND CRACKED AT THE INSIDE RADIUS OF KNUCKLE. LPI CONFIRMED CRACK. BUSHING AT STRUT ATTACH POINT WAS WORN, POSSIBLY RESULTING INOct 12, 1996 · Beech A100 · Main Landing Gear Strut/Axle/TruckSDR CA960923017Controller · burnt(CAN) GEAR WOULD NOT EXTEND. EMERGENCY EXTENSION CARRIED OUT. FOUND THE GEAR MOTOR CONTROLLER BURNT. THE UNIT HAD JUST BEEN OVERHAULED.Sep 13, 1996 · Beech A100 · Landing Gear Retraction/Extension SystemSDR CA960826028Tube · no flare(CAN) WHILE PERFORMING A STATIC SYSTEM LEAK CHECK IT WAS FOUND THAT THE TUBE DID NOT HAVE A FLARE ON THE END.Aug 12, 1996 · Beech A100 · Pitot/Static SystemSDR CA960712101Arm Assembly · bent(CAN) ON TAKEOFF THE #2 PROP RPM WAS OBSERVED TO BE DECREASING, TORQUE WAS INCREASING. THROTTLE WAS RETARDED AND PROPELLER WENT TO FEATHER. INVESTIGATION FOUND THE LOW PITCH ARM WAS BENT AND INTERFERING WITH THE PROXIMITY SWITCH AND CREATING A CONTINUOUS LOW PJul 29, 1996 · Beech A100 · Propeller Controlling SystemSDR CA960808104Support · cracked(CAN) ON INSPECTION PER SB 2145, THE LEFT AND RIGHT ELEVATOR TORQUE TUBES CENTRE SUPPORTS WERE BOTH FOUND CRACKED. A SISTER SHIP FOUND ONE SUPPORT CRACKED. CRACKS COME FROM INBOARD TAPER PIN HOLES. ALL THREE TORQUE TUBE ASSEMBLIES REPLACED WITH NEW P/N'S.Jul 22, 1996 · Beech A100 · Elevator Control SystemSDR CA960729006Plate · bent(CAN) RIGHT HAND DOWN LOCK PLATE BENT ON LANDING GIVING UNSAFE GEAR.Jul 22, 1996 · Beech A100 · Landing Gear Retraction/Extension SystemSDR CA960722005Engine · making metal(CAN) DURING FLIGHT THE #1 ENGINE OIL PRESSURE WAS LOWER AND THE OIL TEMPERATURE HIGHER THAN NORMAL, WITH THE TORQUE INDICATION FLUCTUATING. THE ENGINE OIL SCREEN WAS PULLED AND FOUND CONTAMINATED WITH BRASS/BRONZE AND STEEL FLECKS OF METAL. ENGINE WAS REMOVEDJul 14, 1996 · Beech A100 · Engine (Turbine/Turboprop)SDR CA960725104Motor · intermittent(CAN) LANDING GEAR MOTOR INTERMITTENT WHEN SELECTED DOWN. BRUSHES FOUND IMPROPERLY INSTALLED.Jul 11, 1996 · Beech A100 · Landing Gear Retraction/Extension SystemSDR 96ZZZX5545Intercostal · crackedTHIS PART SUPPORTS THE AFT CABIN DOOR CABLE POST BRACKET (PN 50-430043-1259). OVERLOADING OF DOOR IS THE SUSPECT CAUSE. SUBMITTER SUGGESTS MANUFACTURING INTERCOSTAL FROM STRONGER MATERIAL.Jul 11, 1996 · N4475W · Beech A100 · Fuselage Miscellaneous StructureSDR CA960703004Skin · cracked(CAN) SKIN CRACKS FOUND FROM THREE (3) FASTNER LOCATIONS AT THE UPPER INBOARD BATHTUB FITTING. BEECH CONTACTED AND REPLIED WITH A 25 HOUR INSPECITON AS PER BEECH MESSAGE 52-5870.Jun 18, 1996 · Beech A100 · Wing, Plate/SkinSDR 96ZZZX3396Bearing · failedBEARING (AFT) FAILED. PART NUMBER AS ORDERED FROM BEECH WOULD BE 9000-11. BEARING SUPPLIED BY BEECH IS IDENTIFIED AS (PEER CHINA 600ZD). SUBMITTER SUSPECTS QUALITY CONTROL MAY BE LACKING.Jun 18, 1996 · N100GV · Beech A100 · Landing Gear Retraction/Extension System
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