Rolls-Royce SPEY-511-8
Service difficulty reports · 80
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 = 'SPEY5118' 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.
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 = 'SPEY5118' ORDER BY difficulty_date DESC
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR N382003F00000Actuator · crackedLEAKING ACTUATOR OR LINE CAUSED EXCESSIVE LESS OF COMBINED HYDRAULIC FLUID. FOUND THE END CAP CRACKED APPROXIMATELY .3333 OF THE CAP CIRCUMFERENCE.SDR RO32003F00000Ribbon Heater · failedDURING AN INSPECTION DISCOVERED MELTED GALLEY DRAIN HEAT TAPE. REMOVED THE DAMAGED HEAT TAPE AND REPLACED. AIRCRAFT WAS INSPECTED FOR PROPER INSTALLATION OF THE EXISTING HEAT TAPE AND MODIFIED AS NECESSARY TO ENSURE PROPER INSTALLATION AND CONTINUED AIRWORTHSDR O2G2003F00004Doubler · corrodedCORROSION PRESENT ON DOUBLERS FORWARD OF BATTERY BOX AND AFT OF BAGGAGE DOOR. REPAIR REQUIRED PULLING BACK SKIN FROM STRINGER 19 TO STRINGER 11 AND FORWARD TO THE FAIRINGS BELOW THE BAGGAGE DOOR AND SPLICING NEW DOUBLER INTO PLACE.SDR 030002161Window · crackedOUTER PANE OF CABIN WINDOW WAS FOUND CRACKED .5000 INCHES DURING VISUAL INSPECTION. WINDOW WAS REPLACED.SDR ZLW2002F00000Controller · failedWINDSHIELD HEAT CONTROLLER, INTERNAL FAILIURE.SDR ZLW2002F00001Controller · crackedCRACKED WINDSHIELD ON COPILOT SIDE. AFTER THE NEW WINDSHIELD WAS INSTALLED A FUNCTIONAL CHECK WAS PERFORMED AND IT WAS NOTED THAT THE WINDSHIELD STAYED FULL HOT. THE WINDSHIELD HEAT CONTROLLER WERE SWAPPED AND THE WINDSHIELD HEATED NORMALLY.SDR 02050241Clip · crackedSHEAR CLIP CRACKED AT FS 757.562 BETWEEN STRINGER 3R AND 4R.SDR CA020813006Compressor · failed(CAN) CREW REPORTED 3. MILS VIBRATION AT DECENT AT 70 PERCENT. LATER A LOUD BUZZ AT CRUISE, AND VIBRATION WAS 1.8 MILS. BOROSCOPED ENGINE, A GROUND RUN VIBRATION WAS WITHIN LIMITS. A ONE HOUR FLT AND A BUZZING COULD BE HEARD FROM A/C. AC/DC GENERATORS & HYDRASDR CA020531006Nut · loose(CAN) THE NUT AS20625 HOLDING THE OUTLET GUIDE VANE RING BETWEEN THE LOW PRESSURE COMPRESSOR ROTOR AND THE HIGH PRESSURE COMPRESSOR ROTOR HAD UN-TORQUED ITSELF AND ENTERED INTO THE HIGH PRESSURE COMPRESSOR ROTOR DAMAGING THE HP COMPRESSOR BLADES. THE BOLT K186SDR 2002FA0000530Adc · failedAIR DATA COMPUTER, INTERMITTENT, FAILED.SDR 2002FA0000348Throttle Cable · brokenDURING NORMAL MAINTENANCE INSPECTION THE NR 2 ENGINE THROTTLE CABLE (FS-512 R) WAS FOUND TO BE SEVERELY FRAYED WITH APPROXIMATELY 50 PER CENT OF THE STRANDS BROKEN. THE OTHER CABLES DID NOT HAVE ANY BROKEN STRANDS BUT DID HAVE SOME WIRES BROKEN.SDR 2002FA0000403Control Valve · leakingTHE VALVE DESCRIBED AT LEFT, WAS INSTALLED DUE TO THE UNIT INSTALLED PRIOR HAVING AN EXTERNAL LEAK. DURING INSTALLATION THE VALVE WAS ADJUSTED TO THE SPECIFICATION DESCRIBED IN THE CMP CODE (ATA CODE) ABOVE. THE AIRCRAFT WAS THEN PUT THROUGH A GEAR SWING (10SDR BTV2001F00003Cooler · failedDURING A HIGH POWER GROUND MAINTENANCE RUN-UP, THE MECHANIC IN THE COCKPIT OBSERVED THAT THE BLEED AIR PRESSURE SUDDENLY DROPPED TO NEAR ZERO, FROM 40 AND PSI. INVESTIGATION REVEALED THE LEFT HP AIR PRECOOLER HAD FAILED (BLOWN), EFFECTIVELY OPENING THE BLEED SDR CA010907019Windshield · cracked(CAN) DURING CRUISE AT FL410 PILOT HEARD A "BANG" AT WHICH POINT HE NOTICED THE LEFT SIDE FORWARD WIND SCREEN WAS CRACKED. AIRCRAFT SPEED, ALTITUDE AND PRESSURE DIFFERENTIAL WAS REDUCED AS PER THE AFM AND AN UNEVENTFUL LANDING WAS COMPLETED. SUSPECT CRACKINGSDR BTVR194756Clip · crackedVHF ANTENNA WAS FOUND LOOSE ON THE LOWER FUSELAGE FAIRING, JUST FWD OF THE WING. AFTER DISASSEMBLY, IT WAS DETERMINED THAT THE ANTENNA ATTACHMENT STRUCTURE TO THE FUSELAGE WAS CRACKED IN SEVERAL AREAS. FATIGUE/ VIBRATION MAY HAVE BEEN THE CAUSE.SDR 2001F00015Fuel Line · rupturedRIGHT MAIN FUEL LINE RUPTURED ON TAKEOFF WHICH CAUSED ENGINE TO SPOOL DOWN TO FLIGHT IDLE. REPLACED FUEL LINE ON ENGINE. HP FUEL PUMP WAS ALSO DAMAGED AND REPLACED. ENGINE WAS BORESCOPED AND RETURNED TO SERVICE.SDR 20010517CW011Transformer · defectiveDURING MAINTENANCE OPERATION, POSITIVE TERMINAL ON TRANSFORMER RECTIFIER WAS GLOWING RED WHEN INSTALLED WITH POWER APPLIED. THIS WAS FOUND DURING A ROUTINE INSPECTION. THERE WAS NO INDICATION THAT THE AIRCRAFT WIRING HAD AN EFFECT ON THIS MALFUNCTION. THE SDR CA010307003Compressor · damaged(CAN) DURING ROUTINE POST FLIGHT INSPECTION FOD IMPACT DAMAGE WAS FOUND ON INBOARD LEADING EDGE/WING ROOT AREAS IN ADDITION TO DAMAGE ON BOTH ENGINE INLETS AND 1ST STAGE COMPRESSOR BLADES. DAMAGE IS SUSPECTED TO HAVE BEEN CAUSED FROM NOSE WHEEL SPRAY DURING TASDR 20010508CW007Bolt · brokenAN AFTER LANDING, POST FLIGHT INSPECTION, REVEALED 2 BROKEN WHEEL BOLTS ON RIGHT OUTBOARD WHEEL ASSEMBLY. WHEEL AND TIRE ASSEMBLY REMOVED AND ALL WHEEL BOLTS DISCARDED.SDR CA001005004Nut · damaged(CAN) THE NUT AS20625 HOLDING THE OUTLET GUIDE VANE RING BETWEEN THE LOW PRESSURE COMPRESSOR ROTOR AND THE HIGH PRESSURE COMPRESSOR ROTOR WAS UNTORQUE AND ENTERED INTO THE HIGH PRESSURE COMPRESSOR ROTOR DAMAGING THE HP COMPRESSOR BLADES. THE BOLT K1861114 ATTASDR 20000505SH022Engine · seizedDURING ENGINESTART, ENGINE SEIZED, NO LP ROTATION. (X)SDR CA981230044Blade · damaged(CAN) DURING START AT 16 PERCENT, PILOT HEARD A LOUD BANG. THE FUEL FLOW WAS GOOD, TEMP AT 410 CELSIUS. THEN A SECOND BANG AND TEMP AT 700 CELSIUS (MAX IS 570 CELSIUS). ENGINE WAS SHUTDOWN. INSPECTION FOUND LP TURBINE BLADES DEFORMED WITH PIECES OF STAGE 2 SDR 98ZZZX3704T1 Canister · crackedDURING A ROUTINE INSPECTION, A CRACK WAS FOUND AT THE BASE OF THE CAPILLARY TUBE MOUNT BOSS ON THE T1 CANISTER OF THE LEFT HAND ENGINE. THE CRACKED PART WAS REMOVED AND A SERVICEABLE UNIT WAS INSTALLED IAW ROLLS ROYCE MAINTENANCE MANUAL, CHAPTER 75. THERE HASDR 97ZZZM1103Cable Assy · wrong partEN ROUTE FROM DET TO MMU, THE LOW FUEL LIGHT FLICKERED ON. THE FUEL GAUGES INDICATED MORE THEN SUFFICIENT FUEL WITH RESERVES TO COMPLETE THE FLIGHT. THE FLIGHT CREW ELECTED TO DIVERT TO ELM AND LANDED WITHOUT INCIDENT. SUBSEQUENT INVESTIGATION REVEALED THATSDR 98ZZZX325Igniter · failedIGNITER UNIT OVERHAULED 11 MONTHS, 138 HOURS, 66 CYCLES AGO. FAILED OPS INSPECTION WITH DISCHARGE ONLY EVERY 5-6 SECONDS. SHOULD BE APPROXIMATELY 1 SECOND.SDR 97ZZZX1962Blade · brokenCREW REPORTED HIGH ENGINE VIBRATION ON THE RIGHT ENGINE. A BORESCOPE INSPECTION OF THE L.P. COMPRESSOR REVEALED A FIFTH STAGE L.P. COMPRESSOR BLADE DAMAGED (APPROXIMATELY THREE INCHES OF THE BLADE WAS BROKEN OFF).SDR 96ZZZX1953Regulator · malfunctionedENGINE WAS INSPECTED FOR SUSPECTED OVERTEMPERATURE PER CREW REPORT. INSPECTION ACCOMPLISHED PER ROLLS ROYCE OVERHAUL MANUAL. RESULTS SHOWED NO OVERTEMPERATURE EFFECTS. PRIOR TO DISASSEMBLY, NOTED THE P2 TOWER ON THE FUEL FLOW REGULATOR WAS LOOSE. THREE MOUSDR 96ZZZX821Bushing · shiftedENGINE HAD INTERMTTENT HIGH VIBRATION READINGS. CREW REPORTED A BUZZ ON DESCENT AT 79 PERCENT HI PRESS ROTOR SPEED. IN-FLT VIB SURVEY SHOWED VIB PEAK OF 1.3 MILS CORRESPONDING TO HP ROTATIONAL FREQ AT THAT POWER SETTING. SECONDARY SMALLER PEAK CORRESPONDINGSDR 95ZZZX1521Strap · fracturedENGINE WOULD NOT DEVELOP TAKEOFF THRUST. BLEED VALVE STRAP FOUND FRACTURED. AN EVALUATION (CONDITION REPORT) INDICATES FAILURE DUE TO FLUTTER AND HIGH-CYCLE FATIGUE BROUGHT ABOUT BY EXCESSIVE LOADING OF ONE OR MORE BLEED VALVE SPHERICAL BEARINGS. THIS APPEASDR 95ZZZX375Line · leakingDURING AN INSPECTION OF THE LT ENGINE, FOUND FUEL DRAIN LINE LEAKING. ORDERED NEW LINE FROM GULFSTREAM AEROSPACE. DURING THE RECEIVING INSPECTION, FOUND FLARED END OF LINE BY B-NUT CORRODED AND MISSING MATERIAL DUE TO PITTING. NOTE: THE LINE WAS A NEW UNIT
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