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 DXTA201808231283Controller · malfunctionedDURING ENGINE START AT DESTINATION, HAD BOTH CYAN LEFT AND RIGHT BLEED FAULT CAS MESSAGES AFTER ENGINE START. VERIFIED ON GO, NO GO, OK. AFTER TAKEOFF AND AFTER WING ANTI-ICE SWITCH WAS PLACED ON THE TRIM AIR FAULT CAS MESSAGE AND WING ANTI-ICE CAS MESSAGSDR CA180718008Controller · burned(CAN) THE CUSTOMER IS REPORTING AN ELECTRICAL BURNING SMELL IN THE BAGGAGE BAY AREA COMING FROM THE ACPC. NO FAULT ON THE AIRCRAFT, A VISUAL INSPECTION OF THE ACPC WAS CARRIED OUT AND SSPC NR 8 WAS SHOWING DISCOLORATION. IT WAS SWAPPED WITH A SSPC NR 4 (SPARSDR HALA2018061100290Probe · failedRIGHT ENGINE SELECT ALTERNATE FADEC ANNUNCIATOR ILLUMINATED INFLIGHT. QRH PROCEDURE REQUIRED BOTH FADEC ALTERNATE DUE TO NO RESET. FOUND P2/T2 PROBE FAILED. REMOVE AND REPLACED THE NR 2 ENGINE P2/T2 PROBE IAW AMM 73-21-05. RETURNED TO SERVICE PASSED AND SECURSDR CA190412008Skin · crackedDURING ROUTINE MAINTENANCE WORK (18-JANUARY-2018) ON A/C MSN 9404/REG. 14+02) A DISCREPANCY WAS RAISED DUE TO MISSING COVER PLATE P/N GM127-1658-73 ON L/H WING NO. 1 SLAT PANEL (REFERENCE: AIPC 27-53-17 FIG 10, PAGE 3, ITEM 745). A GENERAL VISUAL INSPECTION OSDR 2017FA0000628Stator Vane · unserviceableON SEPTEMBER 22, 2017, N618WF INITIATED A DEPARTURE FROM KMEZ FOR KPHF. AFTER ENG START UP, THE GEN 1 FAIL CYAN MESSAGE DISPLAYED, THE FLIGHT CREW DETERMINED THAT THE ITEM WAS LISTED IN THE BD-700-1A/10 MMEL UNDER ITEM NUMBER 24-21-01 AND DEPARTED KMEZ AT 20SDR WWQA2016111500001Engine · contaminatedTHE CREW APPLIED POWER FOR TAKEOFF. IMMEDIATELY AS POWER MADE TAKEOFF THRUST THE CREW NOTICED SMOKE FILLING THE CABIN AND COCKPIT. SHUT DOWN THE ENGINES. AN OIL ANALYSIS FROM THE LEFT ENGINE WAS SENT TO MANUFACTURER AND IT WAS DETERMINED THAT THE ENGINE HAD ANSDR DXTA2016030406232Bolt · brokenLEFT ENG LOWER AFT ENG MOUNT RETAINING BOLT IS BROKE & MOUNT PIN IS BACKING OUT OF ENG SN 22081. REPLACED FWD ENG MOUNT LINKS & RETAINING HARDWARE WITH NEW & REPLACED AFT UPPER ENG MOUNT LINK & RETAINING HARDWARE WITH NEW, SERVICED LT ENG RENTAL ENG WITH 9 QUSDR CA160304007Bolt · sheared(CAN) ON MARCH 3 OPERATOR REPORTED THAT DURING A TROUBLESHOOTING EVENT, WHEN THEY OPENED THE LT ENGINE COWLING ON THE ACFT, THEY FOUND THE AFT LOWER MOUNT BOLT BROKEN AND THE MOUNT PIN BACKED OUT. THIS BOLT IS APPROXIMATELY .3125 IN DIAMETER AND SERVES TO RETSDR CA160226002Skin · damaged(CAN) THE HORIZONTAL STAB IN-BOARD LEADING EDGE PN GS253 0035 011 HAS BEEN FOUND WITH OUT-OF-SPECIFICATION SKIN THICKNESS. IS (0.091"), SHOULD BE CONDITION (0.100"). THIS ISSUE IS CURRENTLY UNDER BOMBARDIER ENGINEERING EVALUATION. (TC# 20160226002)SDR CA160218006Igniter · worn(CAN) ON A RECENT TRIP TO SEVERAL REMOTE AIRFIELDS, THE FLIGHT CREW EXPERIENCED REPEATED PROBLEMS WITH GETTING THE NR 1 ENGINE STARTED, SOMETIMES TAKING 2 OR 3 ATTEMPTS TO GET STARTED. AFTER THE ACFT RETURNED TO HOME BASE, WE WERE UNABLE TO START NR 1 ENGINE,SDR CA151221015Fairing · missing(CAN) FIELD SERVICE REPORTED THAT THE ACFT LANDED WITH THE AFT BELLY FAIRING ACCESS PANELS MISSING. A SERVICE REQUEST FOR PRODUCT SUPPORT ACTION, SRPSA, SUBMITTED TO CUSTOMER SUPPORT REPORTS THAT THE MISSING PANELS ARE PN GS297-0137-7 AND GS297-0137-8 ALSO KNSDR CA151215018Unknown · odor(CAN) THE AIRCRAFT WAS AT CLIMB AT APPROXIMATELY 3000 FT WHEN THE CREW FIRST OBSERVED LIGHT SMOKE/HAZE WITH AN OILY ODOR IN THE CABIN. THE ACFT CONTINUED TO CLIMB AND WHEN AT APPROXIMATELY 12,000 FT THE SMOKE/HAZE HAD NOT DISSIPATED, THE CREW ELECTED TO RETUSDR CA151127004Fairing · missing(CAN) BELLY FAIRING PANELS 185BL AND 186BR DEPARTED IN FLIGHT DURING CLIMB AFTER TAKEOFF. ATTACHED SRPSA FORM, PHOTOS AND FAULT RECORDING TABLES FROM INSPECTION AFTER ACFT SER 9570 LANDED AT WITHOUT PANELS 185CL + 186CR. WE HAVE INSPECTED THE SURROUNDING STRUSDR CA151103006Fms · malfunctioned(CAN) FLIGHT CREWS FROM SEVERAL ACFT HAVE REPORTED ISOLATED OCCURRENCES OF UNEXPECTED OR UNANTICIPATED ROLL DURING AUTO FLIGHT OPERATION. TYPICALLY, THE ACFT IS OPERATING UNDER LNAV GUIDANCE OF THE FLIGHT MANAGEMENT SYSTEM, FMS. THE GUIDANCE CUE IS OBSERVED MSDR CA151016010Autothrottle Sys · malfunctioned(CAN) ACFT EXPERIENCED AN AUTOTHROTTLE HUNTING CONDITION WHEN IN CRUISE AND TRYING TO HOLD A CONSTANT AIRSPEED. AUTOTHROTTLE HUNTING RESULTS IN OSCILLATION OF THE ENGINE PARAMETERS, ENGINE PRESSURE RATIO, SPOOL SPEEDS, TURBINE GAS TEMPS. MFGS ARE ANALYZING TSDR CA150922004Sink · leaking(CAN) UPON CLIMBOUT THE CREW OBSERVED AN UN-COMMANDED TRIM WITHOUT THE ASSOCIATED PHYSICAL CHARACTERISTICS BUT AUDIBLE TONES WERE HEARD. ADDITIONALLY, SEVERAL MESSAGES APPEARED TO INCLUDE AN AMBER FLIGHT SPOILER FAILURE WITH AN ASSOCIATED SLAT/FLAP HALF SPEEDSDR CA150915007Buckle · inoperative(CAN) A MFG FIELD SERVICE REPRESENTATIVE REPORT TO CUSTOMER SUPPORT ENGINEERING MULTIPLE EVENTS ON SEAT BELT ASSEMBLIES. THE NEW EJECTOR BASE SAME AS PART ON VSB 504443-25-02 WAS FOUND DEFECTIVE, BROKEN ON 7 SEATS. INVESTIGATION STILL IN PROGRESS.SDR CA150831001Gcu · failed(CAN) A NR OF GENERATOR CONTROL UNITS, FAILED FTP ON MFG PRODUCTION LINE. UNIT WILL NOT GO ONLINE AFTER BATTERY ISOLATION TEST AND COLD START FAULT CODE AF. AS DISCLOSED BY SAFRAN (LABINAL POWER SYSTEM, GCU SN 7010 TO 7167 ARE SUSPECT. AFFECTED UNITS ARE ISDR CA150814008Sensor · false indication(CAN) AFTER TAKE OFF BRAKE TEMPERATURE INDICATION ON COCKPIT DISPLAY INCREASED RAPIDLY AFTER GEAR WAS SELECTED UP. CREW EXTENDED THE GEAR AND OBSERVED THE TEMPERATURE INDICATION TO DROP AND THEN SUBSEQUENTLY RISE. CREW ELECTED TO RETURN TO THE DEPARTURE AIRPORSDR CA150716005Electrical Sys · malfunctioned(CAN) DURING APPROACH, UPON SELECTION OF FLAP/SLAT LEVER DOWN, CREW HAD A DC ESS BUSS FAIL, AND THEY LOST ALOT OF AVIONICS SYSTEMS. THE DC POWER CENTER, DCPC, DOESN`T RECONFIGURE ITSELF TO PROVIDE POWER ON THE ESS BUSS. THE NAVIGATION AIDS WERE NOT AVAILABLE SDR CA150721002Sensor · faulty(CAN) THE OPERATOR REPORTED THAT THE AIRCRAFT LANDED WITH THE LANDING GEAR UNSAFE INDICATION. THE EICAS MESSAGES WERE L-R MAIN GEAR DOOR (AMBER), NOSE DOOR (AMBER), GEAR DISAGREE (AMBER), BRAKE FAULT (CYAN). THE AIRCRAFT LANDED WITH ALL 3 LANDING GEARS IN THE SDR CA150710019Rod · fractured(CAN) QTY 2 THREADED RODS IN THE OTBD SHOCK MOUNTS OF AC MOTOR PUMP WERE FOUND FRACTURED. AN INITIAL MFG MATERIAL ANALYSIS INDICATES THE RODS HAVE FAILED DUE TO HYDROGEN EMBRITTLEMENT. THE CONDITION IS STILL UNDER HYDRAULIC SYSTEMS DIVISION INVESTIGATION. ASDR CA150629009Engine · vibration(CAN) INITIAL REPORTS STATED INCREASED N1 VIBRATION ON BOTH ENGS. CREW DECIDED TO SHUT DOWN THE RT ENG & DIVERT BACK. AN UNEVENTFUL SINGLE ENG LANDING WAS CONDUCTED. THE N1 VIBRATION EXCEEDANCE OCCURRED BETWEEN FL 369 & FL 410. DURING TAKEOFF & CLIMB TO A CSDR CA150619009Fms · malfunctioned(CAN) SHORTLY FOLLOWING DEPARTURE, THE CREW WAS NOTIFIED THAT THE ACFT WAS NOT ON THE CLEARED PLAN. THE ERROR WAS CORRECTED & THE FLIGHT CONTINUED UNEVENTFULLY. UPON INVESTIGATION, IT WAS DETERMINED THAT THE FMS DID NOT PROPERLY LOAD SEVERAL POINTS BETWEEN TSDR CA150320006Drive Unit · failed(CAN) DURING SCHEDULED MAINTENANCE: AT ACFT POWER UP, TECH NOTICED CAS MESSAGE STAB CH1 FAIL AND CB B6 ON THE ACPC OUT, PRESSED IN CB AND AT THE SAME TIME HEARD LOUD BANG SOUND AT THE AFT PART OF THE FUSELAGE. BOX LOCATED UNDER FLOOR NEAR BAGGAGE BAY DOOR ARESDR CA150330003Contactor · burned(CAN) IN FLIGHT, MARCH 15 AT 23:00, THE CREW REPORTED GEN 3 FAIL MSG ON EICAS & ON THE PBA. THEY FOLLOWED THE QRH PROCEDURES, BUT THE FAIL REMAINED. FLIGHT CONTINUED UNEVENTFUL. AFTER LANDING & THE APU RUNNING, THE CREW SHUTDOWN THE ENGS, AT THIS TIME THE APSDR OJ4R2015FA0000120Control Switch · shortedDURING POSTFLIGHT INSPECTION, FOUND AFT CABIN VIP SEAT SWITCHING PANEL ASSY, LOCATED ON DRINK RAIL, TO BE INOPERATIVE AND COULD SMELL ODOR CAUSED BY AN INTERNAL SHORT TO THE SWITCHING PANEL ASSY. THE SWITCHING PANEL IS NOT THERMALLY PROTECTED AND THE ELECTRICSDR CA150227004Battery · failed(CAN) DURING INITIAL ACFT POWER UP, THE CREW NOTICED SMOKE COMING FROM THE FWD AVIONICS EQUIP AREA & FURTHER INSPECTION CONFIRMED THAT THE SMOKE WAS COMING FROM THE AVIONICS BATTERY WHICH IS DISPLAYING BLACK MARKS & SIGNS OF OVERHEATING ON THE SIDE.SDR CA150213002Engine · malfunctioned(CAN) PILOT REPORTED THAT AFTER TAKEOFF OUT OF KONT CLIMBING OUT OF FL 180 THEY HEARD A LOUD BANG ON RIGHT ENGINE AND NOTICED N1 ON RIGHT ENGINE DROP TO HALF OF LEFT ENGINE AND FELT THE A/C YAW. HAPPENED VERY QUICK AND THEN EVERYTHING CAME BACK TO NORMAL REST SDR CA150126001Cable · broken(CAN) DURING CRUISE FLIGHT, AILERON TRIM LWD EICAS CAUTION POSTED INTERMITTENTLY AND AUTOPILOT CONTROL WAS REPORTED UNRELIABLE ON LEFT TURNS. PILOT DISENGAGED AUTO PILOT TO HAND FLY THE AIRCRAFT AND CONTINUED TO HAVE FULL CONTROL (MINOR AILERON INPUTS ARE REQUSDR CA150116004Gps · failed(CAN) ON POWER UP THE AIRCRAFT EXPERIENCED A FAILURE OF BOTH GPS RECEIVERS (GNSSU) AS THEY REMAINED IN ACQUISITION MODE. AW 700-34-0465 WAS APPLIED (RE SET CB`S 6 TIMES NO EFFECT) WITH NO SUCCESS AS BOTH GNSSU REMAINED IN ACQUISITION MODE. THE AIRCRAFT WAS RELSDR CA150213013Control Panel · burned(CAN) OPERATOR CALLED TO REPORT THE REFUEL DEFUEL CONTROL PANEL WAS INOPERATIVE. ORDERED A REPLACEMENT PART & THE DEFECTIVE UNIT WAS RETURN TO THE VENDOR. DURING THE TESTING OF THE ASSEMBLY, VENDOR HAS DISCOVERED BURNT BOARDS 548-337-001 & 548-338-001.SDR CA141216004Wire · damaged(CAN) POST APU BATTERY REPLACEMENT, APU BATT OP TEST WAS ATTEMPTED TO BE CARRIED OUT. DURING POWER ON, APU BATTERY VOLTAGE, TEMP AND AMPS WERE NOTED TO BE UNUSUAL, WITH A RAPID INCREASE IN TEMP AND CURRENT AFTER SHORT TIME WITH POWER APPLIED. POWER REMOVED TO SDR CA141208011Latch · defective(CAN) THE SEAT BELT LATCH FOR THE CREW REST DOES NOT LATCH PROPERLY AND POPS LOOSE UNDER PRESSURE. BLE 12-3-14, DEFECT CONFIRMED BY ONSITE FSR AT EVERY LOCATIONS.SDR CA141127003Battery Pack · melted(CAN) DURING EMERGENCY LIGHTS OPS TESTING, FOUND THAT ELPS NR 4 SMELLING BURNED AND INTERNAL BATTERY MELTED.SDR CA141121001Transceiver · faulty(CAN) DURING A STABLE ILS APPROACH , AROUND 700 FT RA, THE AUTO-THROTTLE WENT IN RETARD MODE. BEFORE IT HAPPENED ALL WAS FINE, ILS FREQUENCY WAS INSERTED VIA FMS WITH THE ILS IDENTIFIER IAW ADVISORY WIRE, DUE TO WIND, ALSO, VREF+10 WAS APPLIED ACCORDING AFM. SDR CA141016004Spigot · damaged(CAN) THE FORWARD SPIGOT TUBE BUSHING LOCATED AT THE AUXILIARY RIB OF THE INNER FLAP ASSY HAS BEEN FOUND MIGRATED.ALSO FURTHER INVESTIGATION REVEALED THAT ADJACENT CLOSING RIB ATTACHMENT BOLT OF THIS VERY SAME SPIGOT TUBE HAS BEEN SHEARED (HEAD SHEARED OFF).DESDR CA140829003Frequency Gen · failed(CAN) AIRCRAFT RECENTLY HAD A NR 1 VFG OIL PUMP FRACTURE FAILURE. AIRCRAFT LANDED WITHOUT ANY ADDITIONAL ISSUES FOLLOWING THE DISINTEGRATION OF THE NR 1 GENERATOR AFTER APPROX. ONE HOUR INTO THE FLIGHT. THE VFG INSTALLED WAS A -5. THERE WAS COWLING DAMAGE DUESDR CA140826018Generator · failed(CAN) EXPERIENCED A GEN 1 FAIL ADVISORY MESSAGE DURING FLIGHT, NOT RESETTABLE BUT PILOT CONFIRMED NO NOISE FROM THE ENGINE OR OTHER PARAMETER CHANGES DURING THE EVENT. NO OTHER FAULT APPEARED FOR THE REST OF THE FLIGHT AND THE AIRCRAFT LANDED NORMALLY. DURSDR CA140818005Rib · cracked(CAN) DURING A 120 MONTH INSPECTION, FOUND A CRACKED RIB. RIB IS A SUB ASSEMBLY OF THE STRUCTURAL SHEET METAL BOX ASSY.SDR CA140820002Torque Bridge · chafed(CAN) ON THE BRAKE UNIT, THE TORQUE PLATE SEEMS TO HAVE EITHER BACK OFF OR WAS NOT TORQUE PROPERLY ONTO THE PISTON HOUSING ASSY. ON BRAKE APPLICATION THE TORQUE PLATE WOULD COME IN CONTACT WITH THE INNER FACE OF THE WHEEL CAUSING DAMAGES TO BOTH PARTS. OPERATOSDR CA140715003Fitting · leaking(CAN) IT WAS DISCOVERED THAT 3 FUEL FITTINGS (FUEL TRANSFER LINE, FUEL FEED, AND REFUEL LINE) AS INSTALLED PER DESIGN HAVE APPROX. 2 THREAD ENGAGEMENTS INTO THE DOME NUT. IT SHOULD BE ONE TO HALF TREADS PROTRUDING ABOVE THE NUT AS PER REQUIREMENTS. 629 AIRCRAFSDR CA141023005Display · failed(CAN) DURING FLIGHT, NR 4 DISPLAY UNIT FAILED & WENT BLANK IMMEDIATELY FOLLOWED BY AN ELECTRICAL BURNING ODOR . AIRCRAFT DIVERTED & MADE AN EMERGENCY LANDING. NR 4 DISPLAY REPLACED, INSPECTION OF DISPLAY ON REMOVAL, FOUND NO PHYSICAL DAMAGE BUT A STRONG OSDR CA140619004Duct · disconnected(CAN) FLEX DUCT ASSY SEPARATED AT THE MIDDLE JOINT. THE FLIGHT COMPARTMENT DUCT DISCONNECTING AT JOINT DUE TO INCORRECT APPLICATION OF THE TAPE.SDR CA140610002Oil System · low(CAN) HAD LOW OIL QTY MESSAGE ON BOTH ENGINES IN FLIGHT PLEASE SEE THE SEQUENCE OF EVENTS BELOW. ENROUTE, IN CRUISE 5 HRS INTO FLIGHT RT LOW QTY MESSAGE. +10 MINUTES LT LOW QTY MESSAGE. ACFT DIVERTS, DURING DESCENT MESSAGES DISAPPEAR 4. AFTER LANDING BOTH SDR CA141006019Radio · failed(CAN) RADIO TUNING SYSTEM APPLICATION (RTSA) INSTABLE AND UNSUABLE WHEN FLYING.SDR CA140411001Air Filter · dirty(CAN) A POTENTIAL DESIGN COMPLIANCE ISSUE HAS BEEN DISCOVERED DURING SCHEDULED MAINTENANCE ON THE ADAPTIVE FLIGHT DISPLAY (AFD) FAN "AIR FILTER KIT". THE TLMC REPLACEMENT CYCLE OF 1000 FH HAS BEEN DISCOVERED TO BE INADEQUATE. DUE TO DIRTY FILTERS, A POTENTIASDR CA140407010Fms · warning light(CAN) THE ACFT DISPLAYED FMS 1 FAIL, FMS 2, FMS 3, FAIL CAS MESSAGES AND RED FMS FLAGS ON THE ASSOCIATED PRIMARY FLIGHT DISPLAYS AND MAPS. FMS MESSAGES POSTED: FMS NAV INVALID AND CROSS-TALK. AUTOPILOT REVERTED TO BASIC MODES AND AUTOTHROTTLE DISCONNECTED. WSDR CA140211002Fitting · mismanufactured(CAN) IT WAS DISCOVERED THAT THE TOTAL OF EIGHT FUEL VENT FITTINGS AS INSTALLED IAW DESIGN HAVE APPROXIMATELY 2 THREAD ENGAGEMENT INTO THE DOME NUT. IT SHOULD BE 1.5 TREADS PROTRUDING ABOVE THE NUT IAW REQUIREMENTS. AIRCRAFT`S ARE AFFECTED BY THIS ISSUE. TRISDR CA140407009Fms · warning light(CAN) THE ACFT DISPLAYED FMS 1 FAIL AND FMS 2 FAIL CAS MESSAGES AND RED FMS FLAGS ON THE ASSOCIATED PRIMARY FLIGHT DISPLAYS AND MAPS. ACFT RETURN TO DEPARTURE, PASSENGERS ON BOARD, DUE TO THE FMS 1 & FMS 2 FAIL RE-OCCURRING ONCE MORE IN FLIGHT. THE FLIGHT CRE
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