Lycoming ALF502R-5

Service difficulty reports · 784

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 engine_model_key = 'ALF502R5'
  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 AUS20040405Frame · corroded(AUS) LT FUSELAGE FRAME 43 CONTAINED LEVEL 2 CORROSION ON THE FORWARD FACE AT FLOOR LEVEL. DAMAGE WAS LOCATED AT ZONE 20 FRAME 43 STA 726.9 AND WAS 38.1MM (1.5IN) LONG BY 38.1MM (1.5IN) WIDE AND 4.546MM (0.179IN) DEEP. CAUSE OF DAMAGE WAS ASSESSED AS ENVIRONMEMay 17, 2004 · Bag BAE146300A · Fuselage Main, FrameSDR AUS20040410Intercostal · corroded(AUS) AFT CABIN FLOOR INTERCOSTAL CONTAINED LEVEL 2 CORROSION ON THESIDE AND UPPER SURFACES. THE INTERCOSTAL DAMAGE WAS LOCATED INZONE 251 BETWEEN FRAMES 41 AND 53 AT BL9 LH. AREA OF CORROSION MEASURED 38.1MM (1.5 IN) IN LENGTH BY 3.175MM (0.125 IN) IN WIDTH AMay 17, 2004 · Bag BAE146300A · Fuselage Miscellaneous StructureSDR AUS20040414Seal · leaking(AUS) RT MAIN LANDING GEAR ACTUATOR RESTRICTOR SEAL LEAKING.May 15, 2004 · Bag BAE146200A · Landing Gear ActuatorSDR AUS20040372Angle · corroded(AUS) RT REAR ENTRY SILL PLATE ATTACHMENT ANGLE CONTAINED LEVEL 2 CORROSION ON THE UPPER SURFACE. AREA OF CORROSION 48.26MM (1.9IN) LONG BY 20.8MM (0.82IN) WIDE AND 0.584MM (0.023IN) DEEP. LOCATION OF CORROSION, ZONE 252 STRINGER 19, BETWEEN FRAMES 41AND 43May 7, 2004 · Bag BAE146300A · Fuselage Miscellaneous StructureSDR AUS20040345Bolt · corroded(AUS) FORWARD OUTER ATTACHMENT SPECIAL BOLT SHAFT CORRODED AND PLATING MISSING. CORROSION WAS LOCATED APPROXIMATELY 12.7MM (0.5IN) DOWN FROM THE BOLT HEAD. AREA OF CORROSION 25.4MM (1IN) IN LENGTH BY 9.39MM (0.370IN) IN WIDTH BY0.127MM (0.005IN) DEPTH.BOLTS AMay 6, 2004 · Bag BAE146300A · FastenersSDR AUS20040351Seat Track · corroded(AUS) SEAT TRACKS CORRODED. PN HC538J0343-001 RT IB SEAT TRACK FOUND CORRODED ON UPPER SURFACE. CORROSION MEASURES 106.68MM (4.2IN) LENGTH, 24.13MM (0.95IN) WIDTH WITH DEPTH OUT OF LIMITS. LOCATION, ZONE 251, FRAME 40, RBL 21 RT. REPORTED CAUSE OF DEFECT,May 6, 2004 · Bag BAE146300A · Fuselage, Seat/Cargo Attach FittingsSDR AUS20040339Plate · corroded(AUS) INSP OF REAR CABIN WET AREA AT FLOOR LEVEL FOUND CORROSION IN FOLLOWING PLATES: SHEAR PLATE PN HC538H1183-000 LOCATED ON TOP OF LONGITUDINAL BEAM FRAME 43 RBL 34. CORROSION WAS LOCATED ON UPPER SURFACE MEASURING 17.018MM (0.67IN) LENGTH, 16.002MM (0.63May 5, 2004 · Bag BAE146300A · Fuselage Main, StructureSDR AUS20040357Frame · cracked(AUS) CABIN CROWN FRAME TO SKIN STRUCTURE ANGLE CLEATS (8OFF) CRACKED FROM BEND RADIUS EDGE. THE ANGLE CLEATS ARE LOCATED IN FOLLOWING AREAS: FRAME 19A BETWEEN STRINGERS 1 AND 2 LT. FRAME 19A BETWEEN STRINGERS 2 AND 3 LT 3. FRAME 19B BETWEEN STRINGERS 1 AND May 5, 2004 · Bag BAE146300A · Fuselage Main, FrameSDR AUS20040379Seat Track · corroded(AUS) CABIN FLOOR STRUCTURE CONTAINED LEVEL 2 CORROSION IN THE FOLLOWING AREAS: PN HC536H1063-001 RT OB SEAT TRACK END ON UPPER SURFACE. AREA OF CORROSION MEASURED 38.1MM (1.5IN) IN LENGTH BY 12.7MM (0.5IN) IN WIDTH WITH A DEPTH OF 2.54MM (0.10IN). CORROSIMay 5, 2004 · Bag BAE146300A · Fuselage, Seat/Cargo Attach FittingsSDR CA040505001Wheel · crackedA/C IN HEAVY MX IN YHZ AND HAD JUST BEEN TAKEN OFF THE JACKS WHEN ENGINEERS NOTED THAT NR 3 MAIN WHEEL WAS FLAT. THE WHEEL WAS REPLACED ALONG WITH ITS MATE AS PER COMPANY POLICY, THE WHEEL WAS ROUTED TO WHEEL/BRAKE SHOP AND WENT THROUGH A BUILD (22) INSPECTIOMay 1, 2004 · Bac 146200A · Wheel/Ski/FloatSDR AUS20040305Oil System · failed(AUS) ENGINE SHUTDOWN DUE TO LOW OIL PRESSURE WARNING AND ZERO OIL QUANTITY. INVESTIGATION CONFIRMED ENGINE OIL TANK CONTENTS EMPTY BUT COULD NOT FIND ANY SOURCE OF LEAKAGE. ENGINE WAS REMOVED DUE TO FAILING WINDMILL CRITERIA.Apr 29, 2004 · Bac 146100A · Turbine Engine Oil SystemSDR AUS20040317Shaft · wrong part(AUS) NR 1 MAIN WHEEL TIRE DAMAGED AND DEFLATED. INVESTIGATION FOUND THAT THE TIRE DEFLATED DUE TO WHEEL LOCKUP ON LANDING ROLL. THE WHEEL LOCKUP WAS CAUSED BY A BENT ANTI-SKID TRANSDUCER DRIVESHAFT WHICH CAUSED THE ANTI-SKID SYSTEM ON THIS WHEEL POSITION TO BApr 27, 2004 · Bac 146200A · Brake Anti-Skid SectionSDR CA040426009Apu · failed(CAN) DURING START OF NR 4 ENGINE, THE APU GENERATOR WENT OFF LINE CAUSING AN ABORTED START. ON SECOND ATTEMPT FLAMES CAME OUT OF THE EXHAUST. THE CREW WAS REPORTED OF THIS INCIDENT AND A/C WAS RETURNED TO GATE FOR INSPECTION BY MAINTENANCE. FOLLOWING THE IApr 25, 2004 · Bac 146200A · APU Core EngineSDR AUS20040309Hose · ruptured(AUS) ROLL SPOILER ACTUATOR PRESSURE HOSE RUPTURED. LOSS OF YELLOW HYDRAULIC SYSTEM FLUID.Apr 20, 2004 · Bac 146100A · Hydraulic System, MainSDR CA040430005Wheel · broken(CAN) ENGINEERS RETURNING TO HANGAR FROM LINE, CAME UPON A PIECE OF DEBRIS ON APRON TO HANGAR. THEY RETRIEVED THE OBJECT AND FOUND THAT IT WAS A 10-INCH SECTION OF A WHEEL BEAD FLANGE. AC HAD BEEN OUT FOR ENGINE RUNS AFTER AN ENGINE CHANGE AND WAS IN THE HANGApr 17, 2004 · Bac 146200A · Wheel/Ski/FloatSDR AUS20040274Shutoff Valve · failed(AUS) NR 1 ENGINE FUEL SHUTOFF VALVE FAILED TO OPERATE WHEN THE FIRE HANDLE WAS PULLED.Apr 8, 2004 · Bac 146200A · Fuel Selector/Shut-Off ValveSDR AUS20040237Pin · cracked(AUS) FAIL SAFE PIN ASSEMBLY OF THE RT FLAP TAB NR 2 HINGE BOLT CRACKED. FOUND DURING NDT INSPECTION.Mar 31, 2004 · Bag BAE146300A · Trailing Edge Flap Control SystemSDR AUS20040241Skin · corroded(AUS) WING TOP SKIN SUSPECT CORRODED. REMOVAL OF PAINT FINISH AND FURTHER INSPECTION FOUND THE SKIN TO BE SERVICEABLE WITH NO CORROSION OR CRACKING EVIDENT. INSPECTION CARRIED OUT IAW AD/BAE146/61 AMDT2.Mar 31, 2004 · Bac 146200A · Wing, Plate/SkinSDR AUS20040322Ptu · seized(AUS) HYDRAULIC POWER TRANSFER UNIT (PTU) SEIZED.Mar 19, 2004 · Bac 146200A · Hydraulic System, MainSDR AUS20040281Diaphragm · cracked(AUS) NOSE LANDING GEAR ACTUATOR MOUNTING BOSS DIAPHRAGM CRACKED. FOUND DURING INSPECTION IAW AD/BAE146/71.Mar 17, 2004 · Bac 146200A · Fuselage, Landing Gear Attach FittingsSDR AUS20040253Frame · cracked(AUS) FUSELAGE FRAME 29 RHS CRACKED FROM RIVET IN AREA LOCATED ABOVE STRINGER NR 13.Mar 16, 2004 · Bac 146200A · Fuselage Main, FrameSDR CA040401003Controller · failed(CAN) ACFT WAS IN CRUISE WHEN CREW REPORTED THAT THE NR 3 ENGINE LOST POWER & SPOOLED DOWN BY ITSELF, SEVERAL ASSOCIATED MWS CAUTION LIGHTS ILLUMINATED. ACFT LANDED SAFELY AT ITS INTENDED DESTINATION. ACFT FERRIED HOME ON THREE ENGINES. MX FOUND THE NR 3 ENGINMar 13, 2004 · Bac 146200A · Fuel Controlling SystemSDR A6WA200460006Turbine Wheel · damagedNR 4 ENGINE, 4TH TURBINE WHEEL LOST HEAD OF RIVET WHICH HOLDS BLADE IN PLACE, CAUSING IMPACT DAMAGE TO 4TH NOZZLE CONTAINMENT RIGHT. MAINTENANCE REMOVED AND REPLACED 4TH T-WHEEL ASSEMBLY. (M)Mar 10, 2004 · N181US · Bag BAE146200A · Turbine SectionSDR CA040315009Skin · cracked(CAN) A PILOT IN THE PROCESS OF DOING HIS DAILY INSPECTION OF THE AIRCRAFT NOTICED A CRACK (2.5 INCHES) IN THE LT FORWARD FUSELAGE SKIN JUST BELOW A LAP JOINT BETWEEN FRAMES 10 AND 11 NEAR THE WATER LINE. THE AIRCRAFT WAS REMOVED FOR SERVICE, A SECTION OF SKINMar 6, 2004 · Bac 146200A · Fuselage Main, Plate/SkinSDR AUS20040148Plate · corroded(AUS) RT ELEVATOR TAB NR 1 HINGE UPPER REINFORCEMENT PLATE CONTAINED LEVEL 2 CORROSION. CORROSION DIMENSIONS WERE 25.4MM (1IN) BY50.8MM (2IN) AND PENETRATING TO FULL DEPTH.Mar 3, 2004 · Bag BAE146300A · Elevator, Tab StructureSDR AUS20040129Bolt · cracked(AUS) RUDDER FIXED HINGE BOLT CRACKED UNDER BOLT HEAD. BOLT IS LOCATED AT VERTICAL STABILISER RIB 5. CRACK LENGTH 2.286MM (0.090IN). FOUND DURING NDT INSPECTION.Feb 26, 2004 · Bag BAE146300A · FastenersSDR A6WA200460003Fuel Control · malfunctionedNR 2 ENGINE FLAMED OUT DURING CRUISE FLIGHT. EMERGENCY CHECKLIST COMPLIED WITH. ENGINE WINDMILLED FOR 10 TO 15 MINUTES. REMVOED AND REPLACED FUEL CONTROL IAW AMM 73-20-01-401. REMOVED AND REPLACED OVERSPEED VALVE, UNDER FURTHER INVESTIGATION. (M)Feb 24, 2004 · N608AW · Bac 146200A · Fuel Control/Turbine EnginesSDR AUS20040095Circuit Breaker · failed(AUS) RT WINDSCREEN HEAT CIRCUIT BREAKER OVERHEATED CAUSING LOSS OF AC POWER AND SMOKE IN THE COCKPIT. WIRING, BUSBAR AND CB LA5 LOCATED ADJACENT TO CB ALSO REPLACED DUE TO DAMAGE.Feb 12, 2004 · Bac 146100A · AC Power Distribution SystemSDR CA040129004Head · contaminated(CAN) THIS DUAL OUTLET CARGO BAY EXTINGUISHER WAS RECEIVED FOR OVERHAUL AFTER HAVING BEEN DISCHARGED THROUGH ONE OUTLET. UPON REMOVAL OF THE DISCHARGE HEAD FROM THE FIRED OUTLET, A SIGNIFICANT AMOUNT OF AN UNIDENTIFIED COARSLY CRYSTALLINE CONTAMINANT WAS FOUNDJan 27, 2004 · Bac 146200A · Fire Protection SystemSDR CA040109006Pump · leaking(CAN) IN FLIGHT SHUT DOWN OF NR 2 ENGINE DUE TO LOSS OF OIL PRESSURE AND QUANTITY. MAINTENANCE FOUND EVIDENCE OF HYD FLUID MIGRATION INTERNALLY FROM HYDRAULIC PUMP TO THE PUMP SHAFT. SUSPECT THAT HYD FLUID CAUSED DETERIORATION OF THE PUMP SHAFT SEAL (O-RING) TJan 7, 2004 · Bac 146200A · Hydraulic Pump (Electric/Engine), MainSDR CA040123006Wire Harness · chafed(CAN) DURING APPROACH WHEN ATTEMPTING TO START APU , LOST AC BUSS 1 AND ESSAC , NR 1 GENERATOR WOULD NOT RE-SET, AIRCRAFT LANDED NORMALLY. MAINTENANCE INSPECTION FOUND CHAFING OF THE 'B' PHASE (YELLOW STRIPE) NR 1 ENGINE GENERATOR WIRING CHAFED TO GROUND AT TJan 5, 2004 · Bac 146200A · Electrical Power System WiringSDR AUS20031293Engine · failed(AUS) NR 2 ENGINE UNCOMMANDED SHUTDOWN.Dec 24, 2003 · Bac 146200A · Engine (Turbine/Turboprop)SDR AUS20031342Display · wrong part(AUS) ELECTRONIC DISPLAY UNIT (EDU) WAS INCORRECT PART. MANUFACTURERS AME PLATE WAS IN RED WHICH INDICATED THAT IT WAS AN ENGINEERING EVALUATION UNIT. THE AIRWORTHY UNITS HAVE A BLACK NAMEPLATE. AND CARRY THE PN 4066192-901. PERSONNEL/MAINTENANCE ERROR. UDec 12, 2003 · Bag BAE146300A · Flight Environment DataSDR AUS20031285Engine · failed(AUS) NR 3 ENGINE FAILED.Dec 4, 2003 · Bac 146200A · Engine (Turbine/Turboprop)SDR AUS20031138Circuit Breaker · burned out(AUS) LT INNER FUEL BOOST PUMP CIRCUIT BREAKER BURNED OUT.Nov 7, 2003 · Bac 146100A · Fuel System WiringSDR CA031104004Gearbox · worn(CAN) DURING CLIMB , RED MASTER WARNING , RED NR 4 OIL PX WARNING, NR 4 OIL PX GUAGE IN RED. CREW ELECTED TO SHUTDOWN NR 4 ENGINE. AIRCRAFT RETURNED TO DEPARTING AIRPORT FOR NORMAL LANDING. INSPECTION FOUND OIL PUMP DRIVE GEAR IN GEARBOX SPLINES WORN, ALONGNov 1, 2003 · Bac 146200A · Turbine Engine Oil SystemSDR AUS20031063Indicator · failed(AUS) CAPTAINS ATTITUDE DIRECTION INDICATOR (ADI) FAILED.Oct 14, 2003 · Bac 146100A · Integrated Flight SystemSDR AUS20031037Engine · leaking(AUS) ENGINE SHUT DOWN DUE TO TOTAL LOSS OF OIL. DETAILED INVESTIGATION COULD FIND NO SOURCE OF LEAK. ENGINE HAD ONLY BEEN FITTED THREE DAYS PREVIOUSLY FOLLOWING HSI SO WAS REMOVED AND FORWARDED TO MANUFACTURER FOR FURTHER INVESTIGATION/REPAIR.Oct 13, 2003 · Bac 146200A · Turbine Engine Oil SystemSDR CA031014006Fan Blade · damaged(CAN) WHEN CLIMBING THROUGH 1200 FT AFTER TAKEOFF, BIRDSTRIKE WAS NOTED AND NR 2 ENGINE VIBRATION CLIMBED TO 1.0. AIRCRAFT RETURNED FOR NORMAL LANDING. MAINTENANCE INSPECTION FOUND BENT AND TORN BLADES ON THE NR 2 ENGINE MAIN FAN. BIRD FEATHERS AND OTHER RESIDOct 12, 2003 · Bac 146200A · Turbine Engine Compressor SectionSDR AUS20030984Windshield · cracked(AUS) COPILOTS B-WINDSHIELD OUTER PLY CRACKED.Sep 22, 2003 · Bac 146100A · Flight Compartment WindowsSDR AUS20030874Frame · cracked(AUS) NR 2L PASSENGER DOOR CRACKED IN UPPER HINGE ARM ATTACHMENT BOSS.Aug 28, 2003 · Bac 146200A · Passenger/Crew DoorsSDR CA030728002Pressure Panel · cracked(CAN) DURING GROUND PRESSURIZATION RUN FOR T/S. VISUAL INSPECTION FOUND 12 INCH CRACK IN UPPER WHEEL WELL PRESSURE SKIN ALONG AIRCRAFT CENTER LINE AT EDGE OF STRINGER BETWEEN FRAMES 29 TO FRAME 32. AIRCRAFT WAS PREVIOUSLY SUBJECT TO A COMPANY SPECIAL INSPECTIOJul 27, 2003 · Bac 146200A · Fuselage Main, BulkheadSDR AUS20030861Lever · corroded(AUS) NOSE LANDING GEAR WOULD NOT RETRACT. INVESTIGATION FOUND SEVERE CORROSION IN THE FOLLOWING LOWER PLUNGER LEVER ASSEMBLY COMPONENTS: 1. LEVER PN 2011386052. LEVER PN 2011386063. SHAFT PN 200876762Jul 24, 2003 · Bac 146200A · Nose/Tail Landing GearSDR AUS20030740Main Bearing · failed(AUS) ENGINE CHIP DETECTOR METAL CONTAMINATION. INVESTIGATION FOUND THE METAL TO BE M50 MATERIAL FROM THE MAIN ENGINE BEARINGS.Jul 23, 2003 · Bac 146200A · Engine (Turbine/Turboprop)SDR AUS20030751Uplock Sensor · dirty(AUS) LT MLG UNSAFE LIGHT AND GEAR HANDLE WARNING LIGHT ILLUMINATED IN CRUISE AFTER 45 MINUTES IN FLIGHT. LIGHT REMAINED ON FOR 60 MINUTES BEFORE EXTINGUISHING 15 MINUTES PRIOR TO LANDING. BOTH LT DOOR AND GEAR UPLOCK SENSORS FOUND TO BE DIRTY. LT DOOR UPLOCK Jul 22, 2003 · Bac 146100A · Landing Gear Retraction/Extension SystemSDR AUS20030886Indicator · failed(AUS) FIRST OFFICER'S ATTITUDE DIRECTOR INDICATOR (ADI) FAILED. INVESTIGATION FOUND FAULT WAS CAUSED BY A DRY SOLDER JOINT ON THE MULTI-LAYER FLEX CABLE CONNECTING MODULES A1-A4.Jul 18, 2003 · Bac 146100A · Integrated Flight SystemSDR AUS20031182Splice · damaged(AUS) IDG FEEDER CABLE INLINE SPLICE WAS PRE SB-24-85-01253A. PRE MOD SPLICES PN 12197/2 WERE FITTED INSTEAD OF PN 12198/2 SPLICES.Jul 15, 2003 · Bac 146200A · Electrical Power System WiringSDR AUS20030704Windshield · failed(AUS) RT WINDSHIELD SHATTERED.Jul 12, 2003 · Bac 146200A · Flight Compartment WindowsSDR AUS20030739Generator · failed(AUS) NR 1 GENERATOR FAILED.Jun 26, 2003 · Bac 146200A · AC Generator-AlternatorSDR AUS20030570Line · leaking(AUS) YELLOW HYDRAULIC SYSTEM QUANTITY LOW. INVESTIGATION FOUND PIPELEAKING FROM SWAGE ADJACENT TO T' PIECE CONNECTION FOR THE YELLOW SYSTEM PRESSURE SUPPLY TO THE HP MANIFOLD.Jun 7, 2003 · Bac 146200A · Hydraulic System, Main
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