BMW Rolls BR700-710A220
Service difficulty reports · 189
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 = 'BR700710A220' 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 = 'BR700710A220' 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 CA140110008Autothrottle Sys · malfunctioned(CAN) GLOBAL EXPRESS G5000 ACFT SN 9164, EXPERIENCED AN AUTO THROTTLE MOMENTARY FAILURE, WITH DUAL ENG THROTTLE LEVER ROLL BACK, POWER DECREASE, DURING CLIMB FROM 41,000 TO 45,000. THIS OCCURRED WHILE IN ALT SEL & VS MODE, WITH A 1000 FT RATE OF CLIMB SELECTESDR CA131219011Torque Tube · misinstalled(CAN) THE FLAP TORQUE TUBE WAS FOUND NOT PROPERLY CONNECTED TO THE POWER DRIVE UNIT (PDU) SPLINE SHAFT HOLE.SDR KKVA20131204001Unknown · smokeUNIDENTIFIED SMOKE ON TAKEOFF.SDR CA131206004Oil System · leaking(CAN) DURING TAKEOFF AT HIGH POWER, COCKPIT AND CABIN FILLED WITH SMOKE. TAKEOFF WAS NORMAL. EMERGENCY DECLARED AND ACFT CIRCLED THE AIRFIELD AND HAD AN UNEVENTFUL LANDING. ACFT SYSTEMS INVESTIGATED WITH NO FINDINGS. IDLE GROUND RUN NORMAL. OIL LEVEL CHECKESDR CA131213010Rod · broken(CAN) ON LANDING, RT ENGINE THRUST REVERSER UPPER DOOR ACTUATOR ROD BROKE.SDR CA150210005Manifold · cracked(CAN) DURING THE FUELING PROCESS, FUEL LEAKAGE WAS FOUND UNDER THE BELLY FAIRING AREA. FUELING PROCEDURE WAS STOPPED AND INVESTIGATION REVEALED THAT THE FUEL MANIFOLD HAD DEVELOPED A CRACK BETWEEN THE CENTER AND LEFT WING PORTS. THE MANIFOLD WAS REPLACED AND TSDR 2013FA0000719Spherical Bearin · fracturedBEFORE TAKEOFF , CREW WAS ALERTED WITH A WARNING ILLUMINATION, THRUST REVERSER UNLOCKED (RED), ACFT RETURNED TO RAMP. RIGHT UPPER THRUST REVERSER DOOR WAS OPEN, RIGHT LOWER DOOR CLOSED. INSPECTION REVEALED RIGHT UPPER THRUST REVERSER DOOR, ACTUATOR AFT ROD ESDR CA140527007Autothrottle Sys · locked(CAN) AIRCRAFT EXPERIENCED A THROTTLE LOCKOUT ON APPROACH. CREW REPORTED THAT THE APPROACH STARTED NORMALLY, BUT DUE TO NORTHERLY WINDS, TURBULENCE ENCOUNTERED IN THE LOWER LEVELS, NORMAL FOR THIS WIND, DUE TO ROLL OFF FROM THE TREES/BUILDINGS NORTH OF THE RUSDR 2013FA0000516Generator · failedEICAS POSTED A CYAN GENERATOR 2 FAIL CAS MESSAGE. DC SYNOPTIC PAGE VERIFIED ITS VALIDITY. COMPLETED GEN 2 FAIL MESSAGE CHECKLIST AND WAS UNABLE TO RESET. THREE MINUTES LATER A "THUMP" WAS HEARD AND IT WAS SUSPECTED THAT POSSIBLY THE EVENTS CONTAINED IN AW700SDR CA130913002Sump · fractured(CAN) THE EICAS POSTED A CYAN GENERATOR 2 FAIL CAS MESSAGE. DC SYNOPTIC PAGE VERIFIED ITS VALIDITY. CREW PROCEEDED TO COMPLETE THE GENERATOR 2 FAIL MSG CHECKLIST AND WAS UNABLE TO RESET. 3 MINUTES LATER A THUMP WAS HEARD THE EICAS POSTED A CYAN LT ENGINE FISDR CA130829007Fairing · damaged(CAN) DURING ENGINE ASSY, 2 NON-CONFORMANCES HAVE BEEN NOTED: GAP BETWEEN THE INLET AIR DUCT TCC SEAL OF THE CENTER REMOVABLE FAIRING KH12289 AND THE UNDERNEATH TCC COOLING MANIFOLD 2. GAP BETWEEN UNDERSIDE OF THE AFFECTED FWD REMOVABLE FAIRING KH12263 AND THSDR CA130725002Guide Vane · damaged(CAN) DURING THE INTRODUCTION OF THE GX VFG (BA05801-06), 6 VFG FAILURES OCCURRED EITHER AT THE FIRST ENGINE STARTUP OR WITHIN 2.5HR. INITIAL INVESTIGATION HAS SHOWN THAT THE ESD WASHERS HAVE FAILED ELECTRICALLY (SHORTED). THE ESD WASHERS WERE INTRODUCED TO PRSDR CA130726002Disc · ruptured(CAN) THE OXYGEN CYLINDER SAFETY OUTLET ASSEMBLY CONTAINS SAFETY DISC THAT HAS RUPTURED ON FEW UNITS AT PARTS LOGISTICS FACILITY TEARDOWN ANALYSIS REVEALED BY THE SUPPLIER DICTATES 2 SPACERS WERE RESURFACED. FROM MAY 1, 2013 TO JULY 1, 2013, 25 SPACERS WERE RSDR CA130610016Sump · ruptured(CAN) PILOT REPORT IS AS FOLLOWS, ABOUT 1.5 TO 2 HRS AFTER T/O. THE PILOT FELT A HARD BUT SHORT JOLT SIMILAR TO A TURBULENCE. THIS WAS FOLLOWED BY A CHIME ANNOUNCING A GENERATOR HAVING GONE OFFLINE. ON THE EICAS WAS AN ELECTRONIC SYS FAULT MESSAGE AND GENERSDR CA130610010Control Unit · failed(CAN) THE FLIGHT CREW HAD A SLAT FLAP HALFSPEED MESSAGE WITH NR 2 SFCU POWER CB POPPED THAT WILL NOT RESET. TECH FOUND NR 2 SFCU WITH BURN MARKS ON COVER AND BURNED ELECTRONIC ODOR. THE FLIGHT CREW COULD SMELL THE SMOKE IN THE COCKPIT AND THE "SMOKE" EICAS WSDR CA130516007Pitot System · misinstalled(CAN) DURING TAKEOFF ROLL AT APPROXIMATELY 75 KTS, AN, ADC 1 MISCOMPARE AND STALL PROTECT FAIL, CAUTION MESSAGE POSTED. COPILOT PFD INDICATED 30 KTS. ADC 3 SELECTED ON CO-PILOT SIDE WHICH ALSO INDICATED 30 KTS. A REJECTED TAKEOFF WAS CARRIED OUT AND ACFT TASDR CA130411008Generator · failed(CAN) DURING THE CRUISE, A CYAN GEN 1 FAIL CAPTION WAS SEEN ON THE CAS. THE AC ELECTRICAL SYNOPTIC PAGE CONFIRMED A GENERATOR 1 FAIL. THE QRH GEN 1 FAIL DRILL WAS ACTIONED, HOWEVER THE GENERATOR WAS NOT RECOVERED. GENERATOR 1 WAS THEN SELECTED OFF AND THE ASDR CA130130005Lock · broken(CAN) THE CREW REPORTED PROBLEMS WITH BOTH CREW SEAT VERTICAL ADJUSTMENT, AFTER INVESTIGATION, FOUND TWO HYDROLOCKS BROKEN AT THE END OF THE THREADED PORTION. (SEE PICTURES) ON THE PILOT SEAT THE SECOND HYDROLOCK WAS EMPTY, AND THE ONLY THING THAT AVOID THE SESDR CA121211010Rib · cracked(CAN) DURING 4C, 60 MONTH INSPECTION, FOUND CRACKED RIB. RIB REPLACED.SDR CA121206004Wheel · damaged(CAN) AFTER LANDING, CREW FOUND LACK OF MLG NR 3 WHEEL LOST AFTER TAKE OFF. LANDING WAS WITHOUT ANY ABNORMAL VIBRATION/FEELINGS. AFTER LANDING, VISUAL INSPECTION WAS PERFORMED OF SURROUNDING STRUCTURE, NO DAMAGE TO BRAKES AND SURROUNDS, NOT ANY DAMAGE OR LEASDR CA121127005Skin · corroded(CAN) FOUND CORROSION ON THE VERTICAL STABILIZER LT AND RT EXTERNAL SKINS NEAR MULTIPLE SCREW HOLES OF THE RAM AIR INLET FAIRING. CONDITION REPORTED TO ACFT MFG.SDR 2012FA0000516Control Cable · frayedDURING COMPLIANCE OF SB 7001A11-22-003 (AUTOPILOT SYSTEM CHECK), FOUND RT ELEVATOR LOWER A/P TRIM CABLE FRAYED AT THE UPPER BELLCRANK. SENT CABLE TO TECH REP FOR EVALUATION.SDR CA121009014Acm · odor(CAN) DURING THE ENGINEERING PRE-FLIGHT, THE APU WAS SWITCHED ON, BLEED AIR AND ELECTRICAL POWER WERE BEING SUPPLIED BY THE APU. AFTER APPROXIMATELY 10 MINUTES, THERE WAS HAZE AND BURNING ODOR IN THE CABIN AT WHICH POINT THE ACFT WAS POWERED BACK UP AND APU BSDR CA120629001Fuel Control · failed(CAN) BOTH ENGINES HAVE FAILED TO START. ABORTED CURRENT RT ENGINE START, ATTEMPTED ANOTHER START AND IT FAILED AGAIN, RESET THE BREAKERS AND CLEARED THE PROBLEM. CAIMS SHOWED RT FMU, HP SOV FOR BOTH CHANNELS A & B. SIMILAR ISSUE OCCURRED ON LT ENGINE. USE OSDR CA120516003Wire · damaged(CAN) REPLACED WIRES LEADING TO DENSITOMETER IN LT WING TANK IAW GUIDELINES OF SRPSA 42163 AND MITSUBISHI HARNESS DWG GM598-2510-101, REV "C".SDR CA121126012Skin · corroded(CAN) LT LOWER VERTICAL STABILIZER SKIN CORRODED AROUND FASTNER HOLES AT 2" FORWARD OF STR 1 & 3. VERTICAL STABILIZER BS .200" TO 12.00 BS. CORROSION DEPTH - PENETRATED SKIN THICKNESS. REF SRPSA 43816 FOR REPORTING TO OEM AND REPAIRS INCLUDED REPLACEMENT OFSDR CA120123002Tire · failed(CAN) THREE TIRES BLEW, 1, 2 & 4, ON LANDING. THE ACFT APPARENTLY TAXIED TO THE RAMP ON 1 TIRE AND 3 RIMS. THERE IS POSSIBLY DAMAGE TO THE FLAPS TOO. THE ISSUE IS CURRENTLY UNDER INVESTIGATION. MOBILE REPAIR TEAM SENT ON SITE, WAITING FOR DATA TO ANALYZE SDR CA120111006Circuit Card · burned(CAN) ELECTRICAL SYSTEM FAIL AND ELECTRICAL SYSTEM FAULT CAS POSTED ON THE GROUND WITH APU GEN ON-LINE. AC SYNOPTIC PAGE MISSES ALL FLOW LINES AND DC SYNOPTIC PAGE MISSES APU BATTERY INFO. FOLLOWING VISUAL INSPECTION OF SECONDARY SECTION OF THE ACPC, THERE WSDR CA111103002Actuator · damaged(CAN) DURING COMPLIANCE OF BD700 XRS MANDATORY 500 HR INSPECTION INTERVAL TASK 27-41-09-103 TO CARRY OUT "DETAILED INPSECTION PITCH TRIM ACTUATOR", FOUND SCREWJACK WITH SPALLING CONDITION REQUIRING REPLACEMENT. PITCH TRIM ACTUATOR BEING REPLACED.SDR CA111103004Tube · failed(CAN) LOSS OF HYD SYS, NR 2 FLUID DURING FLIGHT. INVESTIGATION ON LANDING REVEALED FAILED TUBE ASSY, PN GD478-1203-1. CONDITION REPORTED TO MFG VIA "SERVICE REQUEST FOR PRODUCT SUPPORT ACTION" (SRPSA) 48276. MX ACTIONS REQUIRED FOR ACFT RETURN TO SERVICE ARSDR CA120319005Sensor · shorted(CAN) AFTER 4 HOURS INTO FLIGHT, ELECTRICAL BURNING ODOR FROM CREW REST AREA WAS NOTICED. ODOR WAS CONFIRMED BY PILOTS AND CABIN SMOKE EMERGENCY PROCEDURE WAS INITIATED. AFTER PULLING GALLEY CIRCUIT BREAKERS AND TURNING RECIRC FAN OFF, SMELL DISSIPATED AND TSDR CA110928009Pcu · inoperative(CAN) FLIGHT CONTROL CHECKS ON GROUND, WITHOUT ANOMALY. TAXIING AND T/O WAS NORMAL. CLIMBING UP TO TO FL 410 , AT FL 355, SUDDENLY THE PLANE YAWED TO THE LEFT. THE FLIGHT SPOILER FAULT MSG APPEARED ON THE EICAS LCD. AIRPLANE LOST SIGNIFICANT SPEED AND LEVESDR CA110913001Windshield · cracked(CAN) EXPERIENCED A CRACK IN THE RT WINDSHIELD. THE FLIGHT CREW REPORTED THAT THE INITIAL CRACK OCCURRED IN FLIGHT AND WAS A SINGLE CRACK ALONG THE CENTER POST AND BOTTOM. THE FLIGHT CREW REPORTED THAT THE WINDSHIELD HEAT FAILED AT THE SAME TIME. SUBSEQUENTLYSDR CA110725009Contactor · burnedTHE CREWS WERE ON GROUND JUST BEFORE DEPARTURE. THEY MOVED THE HYD PUMP 3A SWITCH TO ON TO PRESSURIZE SYS 3 TO USE PARKING BRAKE. WHEN THEY MOVED THE 3A SWITCH TO ON, THE CB FOR ASSOCIATED PUMP TRIPPED ON EMS CDU AND CAS MESSAGE HYD PUMP 3A FAILED APPEARED. SDR CA100722001Wire · damaged(CAN) CUSTOMER CALLED WITH ELECTRICAL SYSTEM FAIL/ELECTRICAL SYSTEM FAULT. CAIMS REPORTING SPDA1 RX EMSCDU2 FAULT. FOUND WIRING TO SPDA NR 1 HEAT DAMAGED. FOUND TRU 2 FEED WIRE TO THE DCPC IS THE ROUTE CAUSE OF DAMAGE. CABLE PB189A4 HAD COME LOOSE FROM THE FSDR CA110622007Sump · rupturedVFG FAILED APPROX 2 HRS INTO FLIGHT. UPON COMPLETION OF FLIGHT VFG DISCOVERED TO HAVE OIL SUMP SEPARATION. VENDOR AND ACFT MFG ON SITE TO INVESTIGATE. ADDITION OF HIGH CONDUCTIVITY OIL TO DISSIPATE ELECTRO STATIC DISCHARGE.SDR CA110628009Connector · burnedDURING TROUBLESHOOTING FOR LOW VOLTAGE AT LT AUX FUEL PUMP (15VDC), FOUND SPDA2 CONNECTOR P4, PIN H BURNED ON BOTH CONNECTORS (SPDA AND CONNECTOR SOCKET). SPDA AND DAMAGED CONNECTORS PIN AND SOCKET WERE REPLACED. NOTE: FOUND REDISH BROWN DEPOSITS ON PUMP CONSDR CA110520004Access Panel · departedTHE OPERATOR REPORTED TO MFG THAT DURING A PREFLIGHT WALKAROUND, THE FLIGHT CREW FOUND A SECTION OF THE AFT BELLY FAIRING MISSING. PHOTOGRAPHIC EVIDENCE PROVIDED BY THE OPERATOR SHOWED 2 BELLY FAIRING ACCESS PANELS 185CL (PN GS297-0137-7) & 186CR (PN GS297-01SDR CA110517003Handle · contaminatedAFTER LANDING AND FIVE MINUTE TAXI IN LOCAL AMBIENT TEMPERATURE OF PLUS 45 DEGREES C, THE PASSENGER DOOR COULD NOT BE OPENED FROM THE INSIDE OR OUTSIDE. THE PASSENGERS EXITED THE AIRCRAFT VIA THE BAGGAGE DOOR. LOCAL GROUND CREW WERE THEN ABLE TO OPEN THE DOORSDR CA100506001Ground Wire · out of position(CAN) GROUND WIRE FOR APU INLET DOOR WAS NOT PUT BACK IN THE GROOVE INTENDED FOR IT WHICH CAUSED DAMAGE ON THE SKIN OF THE TAIL CONE AND THE INLET DOOR. DISCOVERED ON POST FLIGHT INSPECTION. DOOR REPLACED AND GROUND WIRE INSTALLED IN GROOVE AND HELD WITH SEASDR CA110425007Warning Message · multiple fail(CAN) WHILE ENROUTE AT 40,000 FT THE FOLLOWING EICAS MESSAGES WERE ANNUNCIATED: HYD 3 LO PRESS, CAUTION MESSAGE, RECIRC FAN FAIL, ADVISORY MESSAGE AND RT PRI FUEL PUMP CAUTION MESSAGE. AS A RESULT OF HYD SYS NR 3 NOT AVAILABLE, THE LT AND RT INBD GROUND SPOILESDR CA110328001Wire · burned(CAN) DURING THE APU START, THE APU BATT VOLTAGE FALLS FROM 30V TO 3V WITH AN APU BATTERY FAULT LIGHT ILLUMINATED. THE INVESTIGATION CLARIFIED THAT THE APU BATTERY GROUNDING STUD ON THE AFT FUSELAGE FRAME STA 925.00 WAS BURNED AND MELTED.SDR CA110218005Shaft · shearedDURING THE TAKEOFF RUN, THE CREW HAD A RT ENGINE FLAMEOUT CAS MESSAGE APPROX 5 KTS BEFORE V1. AIRCRAFT WAS ABLE TO ABORT TAKEOFF AND RETURN TO THE RAMP WITHOUT ANY FURTHER INCIDENT.SDR CA110128002Wire · burned(CAN) THE AIRCRAFT WAS UNABLE TO ACCEPT EXTERNAL POWER. EXTERNAL POWER QUALITY MONITOR CARD WAS REPLACED BUT NOTHING CHANGE, THE PROBLEM WAS STILL THERE. DURING VISUAL INSPECTION OF THE ACPC, THEY FOUND A OVERHEATED POWER WIRE ON THE BOTTOM SECTION OF THE ACPSDR CA110125012Engine · flamed out(CAN) FLAMEOUT DURING LANDING ROLL, UPON SELECTING REVERSE, THE ENGINE FLAMED OUT. NO OTHER DETAILS ARE AVAILABLE AT THIS TIME, TROUBLESHOOTING IS ON-GOING.SDR CA110110011O-Ring · pinchedUPON PERFORMING UNSCHEDULED MAINTENANCE IN THE FORWARD NOSE SECTION OF THE AIRCRAFT (LT SIDE), ACCESSIBLE THROUGH PANEL 131AL, A TECHNICIAN SAW GREASE COMING OUT OF THE NOSE LANDING GEAR SHOCK - STRUT BEARING CAP (LT CAP). GREASE IN THAT AREA IS POTENTIALLY DSDR CA110112002Manifold · crackedAS REPORTED FROM THE OPERATOR: DEC 9/2010 REPORT OF FUEL SPILL DURING REFUELING IN DELHI ON DEC 8/2010 SPILL WAS OBSERVED DURING FULL FUEL LOAD IN DELHI, COMING OUT OF THE CENTER TANK AND VISIBLE LEAKING THROUGH THE BELLY FAIRING DRAIN HOLES (APPROX 100-200 LSDR CA101202010Yoke · frozenACFT DEPARTED IN HEAVY PRECIPITATION ENROUTE. OAT 17 C AT DEPARTURE. APPROX 25 MIN AFTER TO AT 35,000 FT -60 OAT AP ENGAGED. CAS MESSAGE POSTED "AP TRIM IS RWD". TRIMMED ACFT TO LEVEL AT 41000 FT. PILOT DISCONNECTED AUTOPILOT AND MESSAGE CLEARED. USING NORMSDR 2010FA0001062Turbine Blades · crackedDURING A ROUTINE BORESCOPE INSPECTION, FOUND (3) STAGE 1 HPT BLADES WITH MISSING MATERIAL ON THE BLADE PLATFORM. ONE OF THE BLADES WITH MISSING PLATFORM MATERIAL ALSO HAS A CRACK ON THE T/E OF THE BLADE. THE DETERMINATION WAS MADE TO REMOVE THE ENGINE AND SENSDR CA100708006Feeder Cable · damaged(CAN) COMPLETION INSTALLED INTERIOR IN BAGGAGE BAY HAD A UPPER INTERCOSTAL INSTALLED THAT IS USED TO SUPPORT BAGGAGE BAY HEADLINER GROSS POINT PANELING. THE INTERCOSTAL INSTALLED WAS FOUND WITH EXCESSIVELY LONG SCREWS/BOLTS AND 1 SCREW/BOLT WAS FOUND CHAFING
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