U/A Canada PT6A-28

Service difficulty reports · 944

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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 engine_model_key = 'PT6A28'
  ORDER BY difficulty_date DESC"

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SDR CA060731002Planetary Gear · making metal(CAN) METAL CONTAMINATION WAS FOUND ON THE CHIP DETECTOR. METAL ORIGINATED FROM RGB AND WAS THE RESULT OF SIGNIFICANT MATERIAL LOSS BETWEEN THE 1ST STAGE SUN GEAR AND THE 1ST STAGE PLANETARY GEARS. THIS IS OUR 2ND SUCH CASE WITH TIME CONTINUED GEARS. (TC NR 2Jul 13, 2006 · Beech 99 · Turbine Engine Reduction GearSDR TIMR200600002Fcu · malfunctionedPILOT NOTICED THAT THE LT TORQUE INDICATION SLOWLY AND CONTINUALLY DECREASED. WHEN POWER ADJUSTMENTS PRODUCED NO EFFECT AND ADVERSE YAW CONFIRMED POWER LOSS THE PILOT FEATHERED THE PROP AND SHUTDOWN THE ENGINE. SUBSEQUENT INVESTIGATION DETERMINED THAT THE FCJul 6, 2006 · N326CA · Beech 99A · Fuel Control/Turbine EnginesSDR CA060712008Support Beam · cracked(CAN) UNDER THE PILOTS FLOOR BOARDS AT FLIGHT STATION 107 THE PILOTS RUDDER QUADRANT SUPPORT BEAM WAS FOUND CRACKED. THESE CRACKS WERE FOUND AT (2) OF THE (4) NUT PLATES. WE HAVE FOUND THESE SAME CRACKS ON 4 OTHER OF OUR AIRCRAFT AROUND THE SAME LOCATIONS. THEJul 6, 2006 · Beech A100 · Fuselage Main, StructureSDR CA060622002Drain · broken(CAN) AFTER FUELING THE AIRCRAFT THE FIRST OFFICER HEARD A SPLASH AND FOUND FUEL LEAKING FROM UNDER THE LEFT WING. THE T PORTION OF THE FUEL DRAIN HAD FALLEN OUT AND THERE WAS NO WAY TO SHUT THE QUICK DRAIN VALVE OFF. THE TOP PART OF THE VALVE AND ORING WEREJun 20, 2006 · Beech 99 · Fuel StorageSDR CA060613004Bearing · misinstalledDURING ACT ENDPLAY CHECK AND LUBE OF N/G ACT 50-820208-5, NOTICED THRUST BEARING IMPROPERLY INSTALLED. INSTRUCTIONS IN COMPONENT MM ARE TO INSTALL BEARING WITH P/N AWAY FROM GEAR, THIS BEARING HAD BEARING MANUF P/N AND WORD THRUST ON ONE SIDE AND RAYTHEON P/Jun 12, 2006 · Beech A100 · Landing Gear ActuatorSDR CA060613001Support Beam · crackedUNDER THE PILOTS FLOORBOARDS AT FLIGHT STATION 107, THE PILOTS RUDDER QUADRANT SUPPORT BEAM WAS FOUND CRACKED. THESE CRACKS WERE FOUND AT 2 OF THE 4 NUT PLATES. FOUND THESE SAME CRACKS ON 3 OTHER OF OUR AIRCRAFT AROUND THE SAME LOCATIONS. THE BEAM WAS REPLAJun 8, 2006 · Beech A100 · Fuselage Main, Attach FittingsSDR CA060601002Duct · cracked(CAN) CRACK DEVELOPED IN THE DOMED PORTION OF THE SMALL EXIT DUCT BESIDE THE WELD. FOUND DURING THE BOROSCOPE INSPECTION. (TC NR 20060601002)May 31, 2006 · Beech A100 · Turbine Engine Air Inlet SectionSDR CA060619012Frame · cracked(CAN) FRAME, F.S. 227 LOWER FLANGE CRACKED AT RADIUS. CRACK WAS APPROX 4.5 INCHES LEFT AND RIGHT OF A/C CENTRELINE. (TC# 20060619012)May 30, 2006 · Beech 100BEECH · Fuselage Main, FrameSDR CA060619013Skin · corroded(CAN) INNER SURFACE LOWER CENTER AREA BETWEEN WINDOW AND LOWER FRAME. CORROSION SPOT 1CM WIDE. WHEN BLENDED MATERIAL THICKNESS WAS INSUFFICIENT. (TC NR 20060619013)May 30, 2006 · Beech 100BEECH · Emergency ExitsSDR CA060619014Skin · cracked(CAN) SKIN P/N 50-120068-96 CRACKED AT HIGH SHEAR FASTENERS ATTACHING SKIN TO WING ATTACH FITTING. CRACKS (2) ORIGINATE FROM EDGE OF FASTENER COUNTERSINKS AND HEAD TOWARD NEXT FASTENER LOCATION. (TC NR 20060619014)May 30, 2006 · Beech 100BEECH · Wing, Plate/SkinSDR CA060531012Engine · making metal(CAN) IN CRUISE, THE CHIP LIGHT ACTIVATED ON THE LT ENGINE. THE ENGINE WAS SHUTDOWN AS A PRECAUTION AND THE AIRCRAFT DIVERTED TO NEAREST FIELD FOR NORMAL LANDING. CFR WAS REQUESTED TO BE ON STANBY. THERE WAS NO OTHER INDICATIONS OF ENGINE PROBLEMS. THE CHIPMay 27, 2006 · Beech 99 · Engine (Turbine/Turboprop)SDR CA060704002Gearbox · spalled(CAN) THE ENGINE CHIP DETECTOR WARNING ANNUNCIATED IN FLIGHT. THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT DIVERTED TO AN ALTERNATE AIRPORT. SUBSEQUENT INSPECTION REVEALED SPALLING OF THE FIRST STAGE REDUCTION GEARBOX GEARING. (TC# 20060704002)May 27, 2006 · Beech 99 · Turbine Engine Reduction GearSDR CA060512002Boot · departed(CAN) DURING MAINT WALK AROUND, COMPLETE PROP BLADE DE-ICE BOOT HAD DEPARTED AC. AIRFRAME, ENG WAS INSPECTED FOR FOD DAMAGE FROM DE-ICE BOOT. DETERMINED THAT BOOT HAD SEPERATED FROM AC DAY BEFORE DURING TAKE-OFF. PILOT FELT VIBRATION FROM LT ENG DURING RUN-UMay 10, 2006 · Beech 99 · Propeller Deice Boot SectionSDR CA060510013Rib · crackedDURING A ROUTINE INSPECTION, THE LT OB STABILIZER RIB WAS FOUND CRACKED NEAR THE HINGE ATTACH AREA. THE RIB WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.May 9, 2006 · Piper PA31T · Horizontal Stabilizer, Spar/RibSDR CA060502000Skin · cracked(CAN) SKIN CRACKED AT HILOC FASTENERS ATTACHING SKIN TO AFT FLANGE OF WING ATTACH FITTING. CONDITION EVIDENT ON BOTH LT AND RT SKINS OF WING CENTER SECTION. MFG HAS A FIELD REPAIR TO DEAL WITH THESE CRACKS. CRACKS FOUND VISUALLY WITH WING BOLT COVERS REMOVED.Apr 24, 2006 · Beech 100BEECH · Wing, Plate/SkinSDR CA060404005Wire · brokenIN CRUISE, PILOT NOTICED THAT THE RIGHT GENERATOR ANNUNCIATOR WAS ON AND THERE WAS NO INDICATION ON THE RIGHT AMMETER. THE GENERATOR WOULD NOT COME ONLINE AND THE GENERATOR WAS SWITCHED OFF. THERE WAS NO FURTHER EVENTS AND THE AIRCRAFT LANDED WITHOUT INCIDENApr 3, 2006 · Piper PA31T · Electrical Power System WiringSDR CA060406003Duct · disconnectedDURING A ROUTINE INSPECTION OF THE CABIN HEATING DUCTS THE HOT AIR DUCT ASSEMBLY P/N 97-555011-15 ITEM NR 22 IN PICTURE NR 1 WAS FOUND DISCONNECTED AT THE AFT END. 2 DUCTS FURTHER FWD WERE FOUND CRACKED ALLOWING THEM TO MOVE FWD AND ALLOWING THIS DUCT TO DISCMar 30, 2006 · Beech A100 · Ice/Rain Protection SystemSDR AXS2006F00000Starter Gen · unserviceableENROUTE, AT 9000 FT MSL. THE LT GEN TRIPPED OFF LINE, AND MOMENTARILY CAME BACK ON. THE VOLT AMMETER SHOWED THE LT GEN ACCEPTING A LOAD. THEN THE PROCESS REPEATED, WITH THE LT COMING BACK ON LINE. FOR A THIRD TIME, THE LT GEN TRIPPED AND THIS TIME DID NOT Mar 27, 2006 · N91RK · Beech A100 · Starter-GeneratorSDR CA060402001Skin · crackedTRAILING EDGE SKIN, RT SIDE CRACKED APPROX 1 INCH AT MAIN SPAR STATION. CRACK STARTS AT ONE JO BOLT FASTENER LOCATION AND GOES DOWN TO EDGE OF SKIN. MOST OF THE CRACK WAS HIDDEN BY THE LOWER RIGHT STABILIZER ATTACH/FAIRING ANGLE P/N 97-440025-14.Mar 27, 2006 · Beech 100BEECH · Vertical Stabilizer, Plate/SkinSDR CA060320003Support Bracket · cracked(CAN) CRACK FOUND ON IB SUPPORT BRACKET WHILE CARRYING OUT REPETITVE INSPECTION MSB 2145. TORQUE TUBE REPLACED WITH NEW. (TC NR 20060320003)Mar 9, 2006 · Beech A100 · Elevator StructureSDR 2006FA0000312Hose · damagedDURING CLIMB, PILOT NOTED RT OIL PRESS FLUTUATING SLIGHTLY & SLOWLY FALLING. ENGINE SHUTDOWN & RETURNED TO BASE. INVESTIGATION REVEALED A LEAKING OIL COOLER HOSE. LEAK POINT COVERED BY FIRESLEEVING. HOSE REMOVED & SLEEVING CUT OPEN REVEALING WIRE BRAID. EXFeb 24, 2006 · N220FS · Piper PA31T · Turbine Engine Oil SystemSDR CA060216003Frame · crackedUPON BEGINNING A PHASE 3 INSPECTION, A TECHNICIAN DISCOVERED A SMALL CRACK ON THE RIGHT FORWARD LOWER SPAR HINGE CAP. THE CRACK WAS OUT FROM THE FOURTH FASTENER FORWARD TOWARD THE HINGE EDGE. A SMALL AREA OF PAINT HAD BEEN FLAKED AWAY IN THIS AREA. MORE PAIFeb 15, 2006 · Beech C90 · Wing SparSDR CA060227018Engine · leakingDURING CLIMB, THE ENGINE EMITTED A NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER AND INCREASE IN TURBINE TEMPERATURE. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. GROUND INSPECTION REVEALED AN ENGINE OIL LEAK. Feb 13, 2006 · Emb EMB110* · Turbine Engine Oil SystemSDR CA060207002Support Beam · cracked(CAN) UNDER THE PILOTS FLOOR BOARDS AT FLIGHT STATION 107 THE PILOTS RUDDER QUADRANT SUPPORT BEAM WAS FOUND CRACKED. THESE CRACKS WERE FOUND AT THE TOP BEND RADIUS AND AT SOME HOLES FOR NUT PLATES. WE HAVE FOUND THESE SAME CRACKS ON 3 OTHER OF OUR AIRCRAFT AROFeb 7, 2006 · Beech A100 · Rudder Control SystemSDR CA060217002Actuator · damagedNOSE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF. MAINTEANCE DID MULTIPLE GEAR SWINGS BUT COULD NOT DUPLICATE THE PROBLEM. THE ACTUATOR WAS REMOVED AND PUT IN A TEST STAND WHERE IT FINALLY FAILED STAYING IN THE LOCKED POSITION. A OVERHAULED ACTUATOR WAS INFeb 7, 2006 · Beech A100 · Landing Gear ActuatorSDR CA060201004Hinge Bracket · crackedA 3/4 INCH CRACK WAS DISCOVERED WHEN MAINTENANCE WENT TO CHANGE A BUSHING.Jan 29, 2006 · Beech 100BEECH · Fuselage, Door HingeSDR CA060127004Switch · unserviceable(CAN) FLOAT SWITCH FAILED INTERNALLY CAUSING THE EPA CAN TO DRAIN OVERBOARD ON SHUTDOWN. (TC NR 20060127004)Jan 26, 2006 · Beech A100 · Standard Practices/StructuresSDR CA060126001Torque Tube · cracked(CAN) DURING THE 100 HR INSPECTION THE TAIL CONE WAS REMOVED TO INSPECT THE TORQUE TUBES IAW INSPECTION PACKAGE. THE LT TORQUE TUBE WAS FOUND CRACKED AROUND HALF THE TUBE BRACE. IT HAD BEEN 100 HRS SINCE THE LAST INSPECTION. THE PN OF THE BRACKET IS 115-6100Jan 25, 2006 · Beech 99 · Elevator StructureSDR CA060307003Accumulator · failed(CAN) THE ABOVE P/N FAILED SENT FOR REPAIR THEN FAILED AGAIN WITH IN 5.3 HRS. SERVICEABLE ACTUATOR INSTALLED WITH NO MORE PROBLEMS. (TC NR 20060307003)Jan 25, 2006 · Beech A100 · Autopilot Trim ServoSDR CA060127002Elt · intermittent(CAN) ELT FAILED THE ACTIVATION TEST DURING THE ROUTINE INSPECTION. THE UNIT HAD THE BATTERY REPLACED AND RECERTIFIED 21 DAYS EARLIER. AVIONICS SHOP FOUND THE PROBLEM TO BE A INTERMITTENT ON/OFF SWITCH. (TC NR 20060127002)Jan 23, 2006 · Beech A100 · Emergency Locator BeaconSDR CA060124001Pinion Gear · broken(CAN) THE GEAR ACTUATOR WAS REMOVED FROM THE AIRCRAFT FOR A RELUBE AND END PLAY CHECK IAW AD72-10-04R2 PART B AND C. WHEN IT WAS CLEANED UP THE MECHANIC NOTICED THAT SEVERAL OF THE TEETH ON THE PINION GEAR WERE BROKEN OFF. THERE WAS NO OBVIOUS REASON FOR FAIJan 21, 2006 · Beech 99 · Landing Gear ActuatorSDR CA060219001Seal · cutRUBBER SEAL DETERIORATED ALLOWING METAL SPRING TO CUT A LARGE GROOVE IN THE TORQUE SHAFT.Jan 17, 2006 · Beech 100BEECH · Elevator StructureSDR CA051208005Pipe · looseCABIN DEPRESSURIZED AT 13000 FEET, CABIN RATE OF CHANGE SPIKED +6500 FEET AND DIFF TO ZERO. FRESH AIR PIPE DISCONNECTED IN FLIGHT. PIPE REPOSITIONED, CLAMP TIGHTENED AND CHECKED OK.Dec 2, 2005 · Piper PA31T · Cabin Pressure Control SystemSDR CA051206004Intercostal · crackedDURING A SPECIAL INSPECTION AFTER FINDING DAMAGE ON OTHER AIRCRAFT, THE AFT PRESSURE BULKHEAD WAS FOUND CHAFED BY BOTH THE CENTER INTERCOSTAL AND THE OUTBOARD INTERCOSTAL ADJACENT TO THE TAIL ACCESS DOOR. NDT WAS COMPLETED AND A CRACK FOUND AT THE OUTBOARD LODec 1, 2005 · Beech A100 · Fuselage Main, BulkheadSDR 2005FA0001591Motor · inoperativeAFTER DEPARTING, PILOT, SELECTING GEAR UP. AFTER THIS THE PILOT NOTED A STRONG ELECTRICAL BURNING SMELL. THE PILOT ELECTED TO RETURN TO DEPARTURE. ON VERY SHORT FINAL APPROACH, THE PILOT NOTED THE GEAR WAS NOT FULLY LOCKED INTHE DOWN POSITION AS INDICATED BNov 28, 2005 · N199WA · Beech B99 · Landing Gear Retraction/Extension SystemSDR CA051202001Wire · looseWIRE G13A22 CAME OFF AT V3-1 EMERGENCY EXTENSION HANDLE SAFETY SWITCH. THIS CAUSED THE GEAR TO NOT RETRACT WHEN SELECTED TO THE UP POSITION. POSSIBLE CAUSE OF LOOSE WIRE, MAY BE THAT THE WIRE WAS MOVED DURING FUSELAGE INSPECTION, WHICH MAY HAVE LOOSENED ATTANov 24, 2005 · Beech 100BEECH · Landing Gear System WiringSDR 2005FA0001570Wire · chafedAC EXPERIENCED A FALSE FIRE WARNING ON THE LT ENGINE ENROUTE. WHILE FLYING THROUGH HEAVY PRECIPITATION. THE PILOT VISUALLY CHECKED THE ENGINE AND MONITORED ALL RELATED INSTRUMENTS AND SYSTEMS TO VERIFY NORMAL INDICATIONS THUS CONCLUDING THE INDICATION WAS FANov 21, 2005 · N192WA · Beech 99 · Fire Protection System WiringSDR CA051122001Nut · mismanufacturedTHE CREW WENT TO INSTALL A WING BOLT RETAINING NUT ON THE AIRCRAFT. IT WAS NOTICED THAT THE NUT WAS MISSING ONE OF THE TWO PLASTIC LOCKING DEVICES. IT APPEARS THE PLASTIC WAS NEVER INSTALLED IN ONE HOLE. THIS IS THE SECOND NUT THAT WAS FOUND WITH PROBLEMS. Nov 21, 2005 · Beech 99 · Wing StructureSDR CA051122003Inverter · failedTHE PILOT IN COMMAND REPORTED THE NR 2 INVERTER CIRCUIT BREAKER POPPED. ON INVESTIGATION, THE NR 2 INVERTER AND ASSOCIATED RELAY WIRING SHOWED SIGNS OF OVERHEATING. THE WIRING FOR THE RELAY OVERHEATED TO THE POINT THAT ONE OF THE WIRES SEPARATED FROM THE POLNov 19, 2005 · Beech A100 · AC InverterSDR CA051117009Control Cable · brokenUPON WALK AROUND, OUTSIDE RECIRCULATED, PRESSURIZED CONTROL LEVERS FOUND WITHOUT ANY TENSION. CONTROL LEVER CONTROL CABLE REPLACED.Nov 13, 2005 · Piper PA31T · Cabin Pressure Control SystemSDR 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 CA051107004Resistor · openLT GEN FAIL ANNUNCIATOR LIGHT ILLUMINATED IN CRUISE. ATTEMPED RESET BY SWITCHING LT GEN OFF, WAITED 10 SECONDS, THEN SWITCHED BACK ON. RESULT WAS BRIEF SMALL PUFF OF SMOKE FROM INSTRUMENT PANEL, SUBSEQUENTLY FOUND TO BE BURN OF GPS ANNUNCIATOR BRT/DIM/TEST MNov 1, 2005 · Beech A100 · AC RegulatorSDR CA051103012Evaporator · malfunctionedDURING DESCENT, PILOT ADJUSTED CABIN CONTROLLER AND VERY SHORTLY AFTER HEARD A BANG FOLLOWED BY A DECOMPRESSION. DROPPED DOWN TO THEIR CLEARED ALTITUDE AND LANDED UNEVENTFULLY. UPON FURTHER INSPECTION IT WAS DISCOVERED THAT THE FRESH AIR DISTRIBUTION HOSE ONOct 28, 2005 · Piper PA31T · Cabin Pressure Control SystemSDR CA051025002Indicator · stuckON CLIMB OUT, CO-PILOT NOTICED THE OIL PRESSURE INDICATOR FOR THE RIGHT HAND ENGINE DROP TO 10PSI AND STAY THERE. ALL OTHER INDICATIONS WERE NORMAL. THE AIRCRAFT RETURNED TO BASE AND LANDED SAFELY. THE INDICATOR WAS REPAIRED AND RE-INSTALLED.Oct 24, 2005 · Beech 100BEECH · Engine Oil PressureSDR 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 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 CA051012003Cable · jammedTHE FLIGHT CREW REPORTED THAT THE ELEVATOR TRIM WAS JAMMED IN THE FORWARD POSITION. UPON INSPECTION, A LOOSE RIVET TAIL WAS FOUND LODGED ON TOP OF THE LEFT ELEVATOR TRIM DRUM AT THE CABLE STOP BOLT.Oct 8, 2005 · Piper PA31T · Elevator Tab Control SystemSDR CA051012002Pump · damagedTHE FLIGHT CREW REPORTED THAT THE LANDING GEAR WAS SLOW TO RETRACT/EXTEND. UPON INSPECTION, A RETURN (SUCTION) LINE FOR THE LEFT HYDRAULIC PUMP WAS FOUND CHAFED AND PIERCED INSIDE THE LEFT WING LEADING EDGE. THE HOLE IN THE LINE WAS CAUSED BY THE VOLTAGE REGOct 6, 2005 · Piper PA31T · Hydraulic Pump (Electric/Engine), MainSDR 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, Bulkhead
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