Beech A100

Service difficulty reports · 472

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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 = '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 CA051103003Bulkhead · cracked(CAN) DURING A SPECIAL INSPECTION AFTER FINDING DAMAGE ON 4 OTHER AIRCRAFT, (SDR 20050829003, 20050928001, 20051013007 AND 20051025004) THE AFT PRESSURE BULKHEAD WAS FOUND CHAFFED BY BOTH THE CENTER INTERCOSTAL AND THE OB INTERCOSTAL ADJACENT TO THE TAIL ACCESNov 1, 2005 · Beech A100 · Fuselage Main, BulkheadSDR CA051025004Bulkhead · crackedDURING A SPECIAL INSPECTION AFTER FINDING DAMAGE ON THREE OTHER AIRCRAFT, (SDR 20050829003, 20050928001 AND 20051013007) THE AFT PRESSURE BULKHEAD WAS FOUND CHAFFED BY THE CENTER INTERCOSTAL ADJACENT TO THE TAIL ACCESS DOOR. NDT WAS COMPLETED AND A CRACKS FOUOct 24, 2005 · Beech A100 · Fuselage Main, BulkheadSDR CA051024007Beam · cracked(CAN) DURING ROUTINE INSPECTION THE RUDDER SUPPORT BEAM UNDER THE PILOTS RUDDER PEDALS WERE FOUND CRACKED. PART WAS REPLACED.Oct 21, 2005 · Beech A100 · Fuselage Miscellaneous StructureSDR DIX2005F00000Turbine Blades · activatedNR 2 ENGINE EXPERIENCED AN INTERNAL HOT SECTION FAILURE RESULTING IN COMPLETE LOSS OF POWER AND FLAMEOUT. ALL ENGINE INDICATIONS WERE NORMAL PRIOR TO THE FAILURE. A ROUTINE HOT SECTION BORESCOPE INSPECTION HAD BEEN PERFORMED. 10.2 HOURS PRIOR TO FAILURE. TOct 13, 2005 · N324EC · Beech A100 · Turbine SectionSDR CA051013007Bulkhead · crackedDURING A SPECIAL INSPECTION AFTER FINDING DAMAGE ON TWO OTHER AIRCRAFT, (SDR 20050829003 AND 20050928001) AFT PRESSURE BULKHEAD WAS FOUND CHAFFED BY THE CENTER INTERCOSTALS ADJACENT TO THE TAIL ACCESS DOOR. NDT WAS COMPLETED AND A CRACK FOUND.Oct 12, 2005 · Beech A100 · Fuselage Main, BulkheadSDR CA050928001Bulkhead · cracked(CAN) DURING A SPECIAL INSPECTION AFTER FINDING DAMAGE ON ANOTHER AIRCRAFT, (SDR 20050829003) THE SAME TWO AREAS OF THE AFT PRESSURE BULKHEAD WERE FOUND CHAFED BY THE TWO INTERCOSTALS ADJACENT TO THE TAIL ACCESS DOOR. NDT WAS COMPLETED AND THERE WERE NO CRACKSSep 23, 2005 · Beech A100 · Fuselage Main, BulkheadSDR CA050912001Support · cracked(CAN) DURING ACCOMPLISHMENT OF SB 2145 CRACK WAS DETECTED ON TORQUE TUBE ASSEMBLIES (P/N 115-610015-325). FOUND AT IB SUPPORT (P/N 115-610015-1). TORQUE TUBE REPLACED.Sep 9, 2005 · Beech A100 · Elevator StructureSDR CA050829003Bulkhead · cracked(CAN) DURING THE CONTINUING AIRWORTHINESS STRUCTURAL INSPECTION CHAFFING DAMAGE WAS FOUND ON THE AFT SIDE OF THE AFT PRESSURE BULKHEAD. THE LOWER CENTER AND THE LOWER RT INTERCOSTALS RUBBING ON THE BULKHEAD DURING PRESSURIZATION CAUSED THE DAMAGE. FURTHER INVEAug 25, 2005 · Beech A100 · Fuselage Main, BulkheadSDR CA050829001Doubler · cracked(CAN) DURING THE CONTINUING AIRWORTHINESS STRUCTURAL INSPECTION A CRACK WAS FOUND IN THE FLOOR LEVEL DOUBLER FOR THE LT FRAME AT FUSELAGE STATION 207.00, THE CRACK MOVED LATERALLY ACROSS THE DOUBLER FROM THE IB SIDE THOUGH 2 RIVET HOLES AND A BEND. THE PROBABLAug 25, 2005 · Beech A100 · Fuselage Main, FrameSDR CA050607008Bracket · cracked(CAN) DO TO A CRACK BEING FOUND ON ONE OF OUR AIRCRAFT, A FLEET CAMPAIGN IS BEING COMPLETED TO INSPECT ALL THE FLAP ACTUATOR ATTACHMENT BRACKETS. DURING THIS SPECIAL INSPECTION, THE LT IB BRACKET WAS FOUND TO HAVE 4 SMALL CRACKS IN THE AREA AROUND THE FWD HOLEJun 2, 2005 · Beech A100 · Trailing Edge FlapsSDR CA050606001Frame · cracked(CAN) DURING INSP 3 CRACKS WERE FOUND IN LT FRAME AT FUSELAGE STATION 207.00. ONE OF CRACKS (CRACK NR 1) MAY HAVE BEEN CAUSED BY A SMALL HOLE THAT WAS DRILLED WITHOUT ANY EDGE DISTANCE, CRACK TRAVELED FROM DRILLED HOLE, AROUND CORNER TO LOWEST LIGHTING HOLE IJun 1, 2005 · Beech A100 · Fuselage Main, FrameSDR CA050606004Controller · malfunctioned(CAN) AFTER TAKEOFF, L G WAS SELECTED UP AND GEAR TRAVELED MOST OF WAY UP, STOPPED WITH GEAR IN TRANSIT LIGHT STILL ILLUMINATED. MANUAL EXTEN WAS COMPLETED, AC LANDED W/O FURTHER INCIDENT. DURING INSP, DAMAGE WAS DISCOVERED ON SKIN OF LT IB GEAR DOOR, LT IB CJun 1, 2005 · Beech A100 · Landing Gear Retraction/Extension SystemSDR CA050526003Bracket · cracked(CAN) DURING A ROUTINE INSPECTION A CRACK WAS NOTICED ON THE LT INBOARD FLAP ACTUATOR ATTACHMENT BRACKET, BRACKET WAS REMOVED AND A TOTAL OF 4 CRACKS WERE FOUND ON THE BRACKET SURROUNDING THE UPPER BOLTHOLE. THE FLAP WAS ALSO CRACKED UNDER THE FORWARD END OF TMay 23, 2005 · Beech A100 · Trailing Edge FlapsSDR CA050412003Diode · failed(CAN) NO POWER ON RT SUBPANEL BUSS DUE TO BOTH FEEDER DIODES NOT PASSING CURRENT. DIODES REPLACED, SERVICABLE.Apr 11, 2005 · Beech A100 · Electrical Power SystemSDR CA050418002Bulkhead · crackedAFT PRESSURE BULKHEAD FOUND CRACKED AT INTERSECTION OF FRAME 50-440014-595. PATCH MADE AND INSTALLED.Apr 9, 2005 · Beech A100 · Fuselage Main, FrameSDR CA050412002Control Box · failed(CAN) NO AURAL WARNING TONE OF THE TRIM IN MOTION FROM THE CONTROL BOX. BOX FAILURE.Mar 25, 2005 · Beech A100 · Auto Flight SystemSDR CA050303005Hose · leakingON APPROACH, PILOT APPLIED BRAKE AND HAD NONE. TRIED REVERSE, BUT DUE TO TAIL WIND WAS INEFFECTIVE. TRIED TO AVOID FUEL BOWSER BUT WAS UNABLE AND RAN INTO LADDER AND PUMP OFF FUEL BOWSER AS HE PUT PROPS IN FEATHER. AIRCRAFT RT PROP SEVERELY DAMAGED, RT ENJan 25, 2005 · Beech A100 · Landing Gear Brake SystemSDR CA050124011Governor · defective(CAN) DURING DESCENT, ENGINE POWER COULD NOT BE REDUCED BELOW 1000 LBS TORQUE. THE AIRCRAFT DIVERTED TO BASE AND THE PILOT SHUT THE ENGINE DOWN IN FLIGHT AND ACCOMPLISHED A SINGLE ENGINE LANDING. SUBSEQUENT INSPECTION DETERMINED A DEFECTIVE OVERSPEED GOVERNOJan 9, 2005 · Beech A100 · Turbine GovernorSDR CA050111005Governor · failed(CAN) ON APPROACH, WHEN THE CREW TRIED TO THROTTLE BACK, THE LT ENGINE WOULD NOT GO BELOW 1000 LB. OF TORQUE. THE CREW MOVED THE THROTTLE FORE AND AFT SEVERAL TIMES BUT NO CHANGE. THE CREW DECLARED AN EMERGENCY AND SHUT DOWN THE LT ENGINE ON FINAL APPROACH. Jan 9, 2005 · Beech A100 · Turbine GovernorSDR LJJ2005F00001Spar · corrodedCORROSION FOUND AT HOLE B, LWS 90.35, DURING INSPECTION OF LT S AND K SPAR STRAP. DER WAS CONSULTED FOR REPAIR. RECOMMEND CLOSE INSPECTION OF HOLES DURING REPETITIVE INSPECTIONS. ALSO RECOMMEND THE USE OF ANTI-CORROSION LUBRICANT DURING BOLT INSTALLATION. (Dec 31, 2004 · N601LM · Beech A100 · Wing SparSDR LJJ2005F00000Strap · corrodedCORROSION FOUND AT HOLE B, LWS 90.35, DURING INSPECTION OF LT S AND K SPAR STRAP. DER WAS CONSULTED FOR REPAIR. RECOMMEND CLOSE INSPECTION OF HOLES DURING REPETITIVE INSPECTIONS. ALSO RECOMMEND THE USE OF AN ANTI-CORROSION LUBRICANT DURING BOLT INSTALLATIONDec 31, 2004 · N601LM · Beech A100 · Fuselage Main, StructureSDR CA041209014Actuator · failed(CAN) DURING A ROUTINE ENDPLAY CHECK, THE ACTUATOR S ENDPLAY WAS AT THE MAX ALLOWABLE 0.018 INCH, THESE ACTUATORS HAVE A 7500 CYCLE OVERHAUL REQUIREMENT AND THIS ONE ONLY HAD 1636 CSO.Dec 9, 2004 · Beech A100 · Landing Gear ActuatorSDR CA041130012Starter Gen · failed(CAN) DURING CRUISE FLIGHT AT 12000 FEET THE PILOTS NOTICED THE LT GENERATOR FAIL LIGHT CAME ON. ALSO A PASSENGER INDICATED THAT HE NOTICED SPARKS COMING FROM THE ENGINE. THE GENERATOR WAS SELECTED OFF AND AIRCRAFT RETURNED TO BASE FOR INSPECTION. MAINTENANCNov 29, 2004 · Beech A100 · Starter-GeneratorSDR CA041122004Tire · blistered(CAN) AFTER A PILOT REPORTED THAT THE NR 3 TIRE WAS FLAT, MAINTENANCE REPLACED THE WHEEL ASSY. DURING THE REMOVAL IT WAS NOTICED THAT THE IB SIDEWALL HAD A LARGE BLISTER. IT APPEARS THAT AN AREA (3 INCHES IN DIAMETER) OF THE OUTSIDE LAYER OF RUBBER (.0625 IFNov 17, 2004 · Beech A100 · TireSDR CA041122011O-Ring · displaced(CAN) FUEL LEAK ON LT ENGINE IN FLIGHT. CAUSE BEING, DISPLACED O-RING ON FCU FUEL BOWL. VARIFIED BOWL HAD BEEN TORQUED TO SPECS IAW MM, CHAPTER 73-10-02 FOR ARGO-TECH PUMPS.Nov 16, 2004 · Beech A100 · Fuel Control/Reciprocating EnginesSDR CA040929008Cover · out of adjust(CAN) PILOTS NOTED THE ENGINE OIL GETTING DARKER AND THE ENGINE ITT GETTING HIGHER. MAINTENANCE INSPECTED THE ENGINE AND FOUND THAT THE NR3 BRG COVER HAD TURNED AND CAUSED THE EXHAUST DUCT TO CRACK AND SEPARATE INTERNALLY. THE PT BLADES HAD RUB MARK AND ALSO Sep 13, 2004 · Beech A100 · Turbine SectionSDR CA040915006Actuator · malfunctioned(CAN) ON APPROACH FOR A MX CHECK, FLAPS WERE EXTENDED IAW CHECKLIST. A RUDDER CORRECTION REQUIRED TO KEEP ACRFT ON APPROPRIATE TRACK. AN UNEVENTFUL LANDING COMPLETED AND ACRFT SNAGGED. UPON INSPECTION IT WAS DETERMINED THAT THE FLAP ACTUATOR FOR THE LT, I/B FSep 10, 2004 · Beech A100 · Trailing Edge Flap ActuatorSDR CA050802004Nut · loose(CAN) AFTER TAKE OFF, THE CREW NOTICED THE LT ENGINE TORQUE WAS OVER RED LINE, POWER WAS REDUCED. MAINTENANCE LATER DISCOVERED THAT PART OF THE LOW PITCH ARM WAS BROKEN OFF. IT WAS DETERMINED THAT THE NUT PN MS21042L4 HOLDING THE PIN PN 100-960036-1 HAD BECAug 27, 2004 · Beech A100 · Propeller Controlling SystemSDR CA040803008Casting · separated(CAN) ENGINE WAS FOUND SAGGING. UPON INVESTIGATION THE UPPER ENGINE MOUNT WAS FOUND BROKEN OFF. ALL 3 MOUNTS REPLACED AND CHECKED OK NOTE THESE MOUNTS WERE INVOLVED IN A SUDDEN STOPPAGE, 243 HOURS PRIOR.Jul 30, 2004 · Beech A100 · Engine Mount SectionSDR CA040719003Relay · intermittentCREWS REPORT THAT DURING CRUISE, THE MAIN ELECTRIC STABILIZER TRIM WOULD NOT TRIM NOSE DOWN. CREW THEN DEACTIVATED THE MAIN TRIM SYSTEM AND ENGAGED STANDBY TRIM SYSTEM. STANDBY SYSTEM FUNCTIONED NORMAL. AIRCRAFT CONTINUED AND LANDED WITH NO FURTHER FAULTS. Jul 19, 2004 · Beech A100 · Elevator Tab Control SystemSDR CA040730008Hsi · overheated(CAN) ON CLIMB, BURN ODOR, SMOKE WHERE DETECTED IN COCKPIT. PILOT ADVISED ATC, DIVERTED TO ALTERNATE AIRPORT WHICH HAD VFR CONDITIONS AT TIME. WHILE FLYING INTO HEAVY RAIN, TURBULENT AIR, RT ENG FIRE WARNING LIGHT ILLUMINATED. RT ENG WAS IMMEDIATELY SHUTDOWN.Jun 21, 2004 · Beech A100 · Integrated Flight SystemSDR CA040705001Nut · damagedDURING RECTIFICATION OF A SNAG GEAR HANDLE LIGHT STAYING ON WHEN GEAR RETRACTED, A/C JACKED UP AND L/G SWINGS WERE COMPLETED. NOTED THAT LT L/G DOORS WAS HANGING OPEN WITH GEAR RETRACTED. ACT REMOVED DUE TO SUSPICION IT HAD SLIPPED INTERNALLY, CAUSING IT TO Jun 10, 2004 · Beech A100 · Landing Gear ActuatorSDR CA040608002Torque Tube · out of limits(CAN) DURING THE INSTALLATION OF A NEW ELEVATOR TORQUE TUBE, IT WAS NOTICED THAT ONE OF THE TAPERED PINS WAS INSTALLED BEYOND THE MANUFACTURES LIMITS. THE MM 27-30-00 PAGE 202 A, STATES IN PART THE SMALL END OF THE TAPER PIN BODY SHOULD EXTEND .000 TO 0.060 IJun 3, 2004 · Beech A100 · Elevator Control SystemSDR CA040604009Adapter · cracked(CAN) DURING A ROUTINE HOT SECTION INSPECTION MAINTENANCE FOUND THE P2.5 BLEED ADAPTER (LOCATED AT APPROXIMATELY 1 O'CLOCK ON THE GAS GENERATOR CASE) WITH OBVIOUS CRACKS. THE RETAINING LUGS WERE BOTH CRACKED AND ONE OF THE ADAPTER WELDING JOINTS WAS CRACKED OJun 2, 2004 · Beech A100 · Engine Bleed Air SystemSDR BAQR361CWheel · damagedWHEEL HAD 64.9 HOURS, 106 LANDINGS SINCE OVERHAULED.Jun 2, 2004 · N777GS · Beech A100 · Wheel/Ski/FloatSDR CA040510006Fitting · cracked(CAN) DURING A PHASE INSPECTION THE TAIL CONE WAS BEING REINSTALLED WHEN A CRACK WAS NOTICED ON THE LT TORQUE TUBE. THE CRACK EXTENDS FROM THE TAPER PIN HOLE TO THE EDGE OF THE FITTING. THESE FITTINGS ARE NDT EVERY 1000 HRS AND THIS TUBE WAS DONE AT 142.5 HMay 6, 2004 · Beech A100 · Elevator StructureSDR CA040510007Door Frame · cracked(CAN) DURING A PHASE INSPECTION A CRACK WAS FOUND ON THE CABIN DOOR FRAME, WHICH EXTENDED FROM THE CUT-OUT FOR THE UPPER FWD BAYONETTE TO THE BAYONETTE SUPPORT BRACKET SCREW HOLE.May 6, 2004 · Beech A100 · Fuselage Main, StructureSDR CA040428006Aileron · out of rigDURING TROUBLESHOOTING OF A PILOT REPORTED SNAG, THE CONTROL COLUMN IS BANKED SLIGHTLY TO THE LEFT IN ORDER FOR THE AIRCRAFT TO FLIGHT STRAIGHT AND LEVEL, CHECKED THE AILERON RIGGING AND FOUND THAT IF THE PROCEDURES FROM THE MM ARE FOLLOWED THE AIRCRAFT WILL BApr 28, 2004 · Beech A100 · Aileron Control SystemSDR CA040329002Rib · cracked(CAN) ON INSPECTION OF THE HORIZONTAL STABILIZER THE UPPER SKIN WAS FOUND TO BE OIL CANNING. UPON FURTHER INSPECTION IT WAS FOUND THAT 6 RIBS WERE CRACKED INTERNALLY (PN 115-620010-325, 115-620010-210, 115-620010-355, 115-620010-255, 115-620010-215, 115-62001Mar 18, 2004 · Beech A100 · Horizontal Stabilizer, Spar/RibSDR ABO2004F00000Fitting · crackedWHILE PERFORMING ROUTINE 36 MONTH/1000 HOUR WING BOLT INSPECTION, A CRACK WAS DISCOVERED USING DYE PENETRANT INSPECTION METHOD. THE CRACK WENT FROM WING BOLT HOLE, THROUGH THE RADIUS UP TO THE FITTING (FLAT AREA).Mar 3, 2004 · N14CF · Beech A100 · Wing, Attach FittingsSDR CA040209001Blower · seized(CAN) JUST AFTER LEVELING OUT PILOT NOTICED SMOKE IN THE COCKPIT/CABIN AREA. AIRCRAFT WENT TO 10000 FT, DEPRESSURIZED AND ELECTRICAL POWER WAS REMOVED. POWER WAS RESTORED AND AIRCRAFT RETURNED TO BASE WITHOUT FURTHER INCIDENT. UPON INVESTIGATION IT WAS DETERMFeb 5, 2004 · Beech A100 · Air Distribution FanSDR CA040203010Windshield · cracked(CAN) DURING CRUISE, PILOT HEARD SMALL CRACK SOUND THOUGHT HE DROPPED SOMETHING, WHILE LOOKING AROUND, NOTICED RT WINDSHIELD CRACK DESCENDED AND CARRIED ON. LANDED WITHOUT INCIDENT.Jan 26, 2004 · Beech A100 · Flight Compartment WindowsSDR CA031203009Bolt · failed(CAN) ON DOING A SIRM WING BOLT INSP THE FWD UPPER RT WING BOLT SHOWED REJECTIONABLE INDICATIONS. BOLT WAS CHANGED AND RETURNED TO SERVICE. BOLT LIFE WAS 9YEARS.Nov 30, 2003 · Beech A100 · FastenersSDR CA031203008Bolt · failed(CAN) ON INSP OF A/C AT SIRM INSP FOUND REJECTIONABLE INDICATIONS ON THE FORWARD UPPER RT WING BOLT. REPLACED AND A/C RETURNED TO SERVICE. PART WAS 9 YEARS OLD.Nov 30, 2003 · Beech A100 · FastenersSDR CA031203007Bolt · failed(CAN) ON A SIRM INSP OF THE WING BOLTS THE RT FWD UPPER WING BOLT SHOWED REJECTIONABLE INDICATIONS. THE BOLT WAS REPLACED AND A/C RETURNED TO SERVICE.Nov 30, 2003 · Beech A100 · FastenersSDR CA031127003Attach Fitting · cracked(CAN) DURING AN UNSCHEDULED INSPECTION A SMALL CRACK WAS FOUND IN THE UPPER FORWARD WING ATTACH FITTING, THE CRACK WAS APPROXIMATELY .0625 OF AN INCH LONG STARTING AT THE TOOLING HOLE HEADING TOWARD THE TUB. THE AIRCRAFT IS GROUNDED WAITING FOR WING SPAR REPLNov 25, 2003 · Beech A100 · Wing SparSDR CA031127001Brace · cracked(CAN) AFTER FINDING TWO OTHER GEAR BRACES CRACKED (SDR 20031126008, 20031126004) WE INSPECTED THE LT GEAR AND FOUND A POSSIBLE CRACK AT THE UPPER END OF THE RADIUS OF THE UPPER TORQUE KNEEBOSS. LIQUID PENETRANT WAS REQUIRED TO CONFIRM THE CRACK. IT STARTED AT Nov 25, 2003 · Beech A100 · Main Landing GearSDR CA031126008Strut · cracked(CAN) AFTER FINDING THE RT MAIN GEAR BRACE CRACKED WE INSPECTED THE LT GEAR AND FOUND A SMALL CRACK AT THE UPPER END OF THE RADIUS OF THE UPPER TORQUE KNEEBOSS. LIQUID PENETRANT WAS REQUIRED TO CONFIRM THE CRACK. IT STARTED AT THE TOP OF RADIUS AND TRAVELED DONov 25, 2003 · Beech A100 · Main Landing Gear Strut/Axle/TruckSDR CA031126004Strut · cracked(CAN) AFTER A PILOT REPORTING THE RT MAIN GEAR OLEO WAS LOW, MAINTENANCE ATTEMPTED TO INFLATE THE OLEO WITH NITROGEN. THE NITROGEN IMMEDIATELY STARTED TO LEAK FROM A LARGE CRACK AROUND THE UPPER TORQUE KNEEBOSS ON THE BRACE ASSEMBLY. THE CRACK WAS APPROXIMATELNov 22, 2003 · Beech A100 · Main Landing Gear Strut/Axle/TruckSDR 2003FA0001190Line · failedPILOT REPORTED SMOKE IN CABIN IMMEDIATELY AFTER TAKEOFF. LANDED IMMEDIATELY AND FOUND FUEL DRAINING FROM LEFT ENGINE. FOUND SEVERED FUEL LINE JUST BEHIND FORWARD B-NUT FITTING. LINE FAILURE SEEMS TO BE A FATIGUE FRACTURE.Oct 31, 2003 · N601PC · Beech A100 · Engine Fuel Distribution
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