Honeywell LTS101-700D-2
Service difficulty reports · 118
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 = 'LTS101700D2' 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 = 'LTS101700D2' 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 2022FA0000456Housing · wornLTS101-700D-2 ENGINE SN LE49043C WAS SMOKING SLIGHTLY FOR SOME TIME (POST HSI AT AIRWORK ON WO-123264), THIS WAS COMMUNICATED TO US BY THE CUSTOMER (SYDNEY HELICOPTERS). THE CUSTOMER HAS NOW FLOWN 427.4 HOURS. A FIELD JOB WAS ARRANGED (WO-127965) TO RECTIFY THSDR CA190626013Lock · broken(CAN) AFTER TAKE OFF MGB CHIP LIGHT ILLUMINATED, PILOT RETURNED TO LANDING PAD, CHIP PLUGS WERE INSPECTED, MAST CHIP DETECTOR WAS BROKEN OFF. (TC# 20190626013)SDR 2019F00114Display · malfunctionedEEMS(ELECTRONIC ENGINE MANAGEMENT SCREEN) FROZE ON START AT 12% NG, SCREENS GO INTO REVERSONARY MODE (FAILURE MODE) AND WILL NOT COME OUT OR FUNCTION. THIS CONTINUES ON SUBSEQUENT START ATTEMPTS. SYSTEM OPERATING SYSTEM MUST BE REFORMATTED AND LOADED MANUALLY SDR CA190312016Bearing · making metal(CAN) GEARBOX GENERATING METAL FLAKE. GEARBOX REPAIRED BY ORIGINAL EQUIPMENT MANUFACTURER WITHIN 8 HOURS. GEARBOX REMOVED AND RETURNED TO ORIGINAL EQUIPMENT MANUFACTURER COMPONENT SHOP FOR FURTHER INVESTIGATION AND REPAIR.SDR CA190307005Leaf Spring · cracked(CAN) WHILE CREW WAS LOWERING FORWARD BELLY COWLING, INSIDE THE HANGAR, A LOUD BANG OCCURRED AND THE COWLING WAS PULLED OUT OF THEIR HANDS. THE RIGHT HAND ANTI-VIBRATION WEIGHT ASSEMBLY FELL ON THE FLOOR. UPON FURTHER INSPECTION A LEAF WAS FOUND TO HAVE CRACKESDR CA190220031Line · leaking(CAN) HYDRAULIC LINE FOUND LEAKING THROUGH THE BRAID (TC# 20190220031)SDR EVCA2017111400001Line · leakingFLIGHT CREW REPORTED A FUEL ODOR IN THE CABIN. DURING MAINTENANCE INVESTIGATION THE FUEL FILTER LINE ON THE ENGINE WAS NOTED TO BE DRIPPING FUEL.SDR 2017FA0000395Turbine Wheel · failedDURING THE PRE PURCHASE INSPECTION, AN ISSUE WITH THE ENGINE WAS FOUND. DURING THE INSPECTION, IT WAS DISCOVERED THAT THE PT ROTOR HAD FOUR RIVETS THAT HAD FAILED AT THE BASE OF THE BLADE SHANK.SDR CA160224009Gearbox · making metal(CAN) METAL CONTAMINATION ON CHIP PLUG, ONLY 181.6 HRS SINCE O/H, GEARBOX ALMOST SEIZED ON WARM. NOTE: OIL PUMP IS PART OF THE MGB WHICH WAS O/H AT THE SAME TIME AS THE GEARBOX. THE MGB WILL BE SENT FOR A COMPLETE TEAR DOWN FOR A COMPLETED REPORT ANALYSIS. SDR CA151105002O-Ring · cut(CAN) ACFT HAD A CHIP INDICATION IN FLIGHT, THE PILOTS LANDED AT THE COMPANY BASE. THE ENGINEERS INVESTIGATED AND FOUND MINOR FUZZ ON THE ADC SCAVENGE OIL FILTER CHIP PLUG. THE CHIP PLUG WAS CLEANED AND THE ACFT RETURNED TO SERVICE IAW MM. THE ACFT WENT OUT SDR CA151202011Transducer · faulty(CAN) NEW PRESSURE TRANSDUCER INDICATED 4 BARS AT INSTALLATION WITH ACFT POWER ON, ACFT NOT RUNNING. REJECTED PART INSTALLED ANOTHER NEW PART SYS FUNCTION TESTED SERVICEABLE.SDR CA151214015Bracket · cracked(CAN) CRACK ON TAILBOOM FROM TAIL ROTOR GEARBOX COWLING BRACKET. CRACK STARTED FROM 1 OF THE RIVET HOLES THAT HOLDS THE BRACKET ONTO THE TAILBOOM.SDR CA150925012Hydraulic Line · leaking(CAN) PILOT NOTICED THE LINE WAS LEAKING AT THE LOWER END, THE ENGINEER ORIGINALLY SUSPECTED THE B-NUT AND TIGHTENED THE LINE. THIS DID NOT STOP THE LEAK SO THE ENGINEER HAD A MORE DETAILED LOOK AT THE LINE AND FOUND THE HYDRAULIC FLUID WAS COMING OUT OF THESDR CA150925006Fuel Control · faulty(CAN) ACFT WAS STARTED FOR A COMPANY FLIGHT. DURING RUN UP CHECKS, THE EOS, ELECTRONIC OVERSPEED SENSOR, CHECK WAS COMPLETED SATISFACTORILY. HOWEVER, UPON RETURNING THE EOS SWITCH TO THE OFF, NORMAL, POSITION, THE ENGINE AND NR SPEEDS RAPIDLY SURGED TO APPROXISDR CA151202012Gear · failed(CAN) ACFT ENCOUNTERED CHIP LIGHT, LANDED CLEANED CHIP PLUG IAW AMM GROUND RUN AND TEST FLIGHT C/O CHIP LIGHT ILLUMINATED AGAIN. ACFT LANDED TRANSMISSION SENT FOR REPAIR. UPON REPAIR FOUND EPICYCLIC TO HAVE LARGE AMOUNTS OF DAMAGE. PARTS SCRAPPED.SDR CA150902007Drive Shaft · damaged(CAN) STARTER WAS SENT IN FOR 900 HR O/H WITH THE DRIVESHAFT FAILING NDT FOR FLAWS AT THE SHEAR POINT. THIS ACFT IS MODIFIED IAW STC SR01647SE TO INSTALL ENGINE.SDR CA150727023Hose · leaking(CAN) DURING LAST FLIGHT OF THE DAY INSPECTION FOUND HYDRAULIC FLUID ON TRANSMISSION DECK. FAULT HOSE FOUND TO BE CAUSE, REPLACED HOSE WITH SERVICEABLE LINE.SDR CA150813003Flex Coupling · cracked(CAN) DURING SHUTDOWN, ROTORS TURNING LOUD CLICKING HEARD FROM COUPLING WHILE ROTORS WERE SLOWING DOWN. COUPLING FOUND CRACKED IN 3 PLACES ALL AROUND, AND GOING THROUGH THE CRIMPED BUSHINGS OF THE OUTER DISK.SDR CA150617002Hydraulic Line · blown(CAN) MECHANIC FOUND DURING HELICOPTER TURN AROUND THAT THERE WAS HYD FLUID ON TAIL BOOM. AFTER INVESTIGATION FOUND HYD HOSE PN 704A34-412-271A WAS BLEW UP & THAT THE HYD TANK WAS ALMOST EMPTY, WHICH WILL HAVE CERTAINLY LEAD TO AN HYD FAILURE ON THE FOLLOWINGSDR CA150616025Pump · leaking(CAN) FUEL PUMP FOUND LEAKING EXCESSIVELY FROM OVERBOARD DRAIN TUBE. REQUIRED REPLACEMENT, PUMP HAD ONLY 44.8 HRS SINCE 600 HR INSPECTION.SDR CA150520014Flex Coupling · cracked(CAN) DURING POST FLIGHT INSPECTION, FOUND FWD FLEX COUPLING BETWEEN ENGINE AND TRANSMISSION CRACKED ON DRIVE SHAFT SIDE OF COUPLING, WHILE REMOVING FLEX COUPLING, THE 3 BOLTS THAT ATTACH THE COUPLING TO THE BELT DRIVE PULLEY WERE FOUND SLIGHTLY LOOSE. DRIVE SDR CA150430006Line · leaking(CAN) ACFT JUST CAME OUT OF INSPECTION. IT HAD ALL HYDRAULIC LINES REPLACED FOR 6 YEAR REPLACEMENT. ACFT WAS GROUND RUN AND LEAK CHECKED SERVICEABLE. ACFT DEPARTED A DAY LATER, AFTER ARRIVING PILOT DID A POST FLIGHT INSPECTION AND FOUND HYDRAULIC FLUID LEAKSDR CA150413005Shaft · sheared(CAN) STARTER GENERATOR SHEARED SHAFT ON INITIATION OF START.SDR CA150316008Governor · malfunctioned(CAN) ENGINE CYCLED WHILE IN FLIGHT, MOMENTARELY LOST POWER. WHILE HOVERING, NG SPOOLED BACK UP 40 FT ABOVE TREES, LANDED IN CLEAR AREA. GOVERNOR WAS REPLACED AS A PRECAUTIONARY MEASURE, STIFFER THAN NORMAL LEVEL TRAVEL, PN 4-301-289-05 WITH LOW TIME REMAINISDR CA150210007Encoder · failed(CAN) DURING FLIGHT A BURNING ODOR WAS NOTICED WITH NO VISUAL SMOKE. THE PILOT DECIDED TO RETURN TO BASE FOR INVESTIGATION ON THE WAY THE TRANSPONDER/ENCODER CIRCUIT BREAKER TRIPPED THE PILOT CHOSE NOT TO RESET THE BREAKER AND LANDED SAFELY AT THE BASE. DURINSDR CA150210006Blade · delaminated(CAN) AFTER 7 DAYS OF SITTING OUTSIDE IN THE RAIN THE ACFT WAS STARTED UP FOR REPOSITIONING. ONCE THE ACFT WAS AT FLIGHT IDLE, A AIRFRAME VIBRATION WAS FELT & THE TAKEOFF WAS ABORTED & THE ENG WAS SHUT DOWN. UPON INSPECTION THE TAIL ROTOR BLADE WAS INSPECTEDSDR CA141208014Angle · cracked(CAN) INSPECTION BEING CARRIED OUT IAW EASB: 05.00.70 CRACKS WERE NOTED RADIATING FROM THE NR 7 BOLT HOLE IN REINFORCEMENT BRACKET. ANGLE TO BE REPLACED.SDR 7EMA20140930007Fuel Control · leakingON DAILY INSPECTION TECHNICIAN NOTICED FUEL PUMP LEAKING AT ENG MATING. UPON PUMP REMOVAL DISCOVERED FUEL CONTROL DRIVE BEARING BLUE GREASE LUBRICATION EXCESSIVELY WASHED OUT OF DRIVE. MM STATES IN 72-00-00 PAGE 7 OVERBOARD FUEL PUMP LEAKAGE MAY BE UP TO 4 DSDR CA140818006Shaft · seized(CAN) ENGINE FLAME OUT ON TAKEOFF. INVESTIGATION OF THE PROBLEM WAS DONE AND FOUND THAT THE GOVERNOR SHAFT IS SEIZED. THE BEARING WAS REPLACE ON THIS UNIT 335 HRS. THIS UNIT HAD SOME REPAIR DONE TO IT AT TSO 1338.8 HRS, BACK IN OCTOBER 23 2013 . TIME SINCE SDR CA140808009Engine · power loss(CAN) ON DEPARTURE, AT AN ELEVATION OF 900FT AGL PILOT NOTICED LOSS OF POWER AND SUBSEQUENT LOW ROTOR HORN ALARM. PILOT ENTERED AUTO-ROTATION, A/C LANDED WITH MINOR DAMAGE AND NO INJURY TO THE PILOT. PLUMES OF WHITE SMOKE WERE SEEN BY WITNESSES COMING FROM EXSDR CA140423013Shaft · broken(CAN) THE STARTER GENERATOR DRIVESHAFT, BROKE INFLIGHT ILLUMINATING GENERATOR FAIL LIGHT ON CAUTION PANEL.SDR CA140214005Starflex · debonded(CAN) FOUND THE STARFLEX DEBONDED BETWEEN THE BUSHING AND THE SPINDLE.SDR CA131101003Blade · loose(CAN) DURING AN 1800 HRS INSPECTION, PT ROTOR BLADE RETAINING RIVETS WERE FOUND LOOSE IN EXCESS OF PRESCRIBED LIMITS. LIMIT IS 0.010" AND A NUMBER WERE FOUND AT .011".SDR CA131023011Bushing · damaged(CAN) DURING A 100 HRS SCHEDULED INSPECTION, 1 OF THE TAIL ROTOR DRIVESHAFT, REAR SECTION OUTER BEARING BUSHING WAS FOUND WITH OVERHEAT DAMAGED CAUSED BY THE HOT ENGINE GASES, TO THE POINT WERE THE RUBBER MELTED AGAINST THE DRIVE SHAFT FAIRING. PART WAS REPLASDR CA131007026Power Supply · failed(CAN) THE STROBE LIGHT WAS NOTED AS BEING INTERMITTENT BY THE PILOT. UPON INVESTIGATION THE STROBE POWER SUPPLY HAD FAILED INTERNALLY. THE CIRCUIT BOARD APPEARS TO HAVE CAUGHT IN FIRE. THE WIRING TO THE STROBE LIGHT WAS INSPECTED FOR DAMAGE AND A NEW POWESDR C3OR201309270001Combust Chamber · damagedCUSTOMER REPORTED VIBRATION, CLUTCH SLIPPING AND OIL IN TAIL PIPE. INCOMING DELTA P JUST BELOW LIMIT 21.7 PERCENT, 2.6 PSI. R & R, NO FAULT FOUND, PERFORMED ANOTHER DELTA P, FOUND ABNORMALLY LOW, 40 PERCENT NORMAL FOR DRY RBSH, WITH ANOTHER GAGE SET 3.7 PSISDR CA130816003Pump · leaking(CAN) DURING AFTER LAST FLIGHT INSPECTION, FUEL IS FOUND LEAKING BELOW THE FUEL TANK. INSPECTION SHOWS THAT THE RT FUEL PUMP IS LEAKING AT THE IMPELLER AREA, DRAIN HOLE, PUMP REPLACED.SDR CA130816002Shaft · broken(CAN) WHEN THE PILOT PRESSED THE START BUTTON, THE NG STAYED AT ZERO, BUT THE STARTER WAS TURNING. SHAFT DISCOVERED BROKEN AT THE SHEAR POINT.SDR CA130814002Transmitter · intermittent(CAN) ENGINE OIL PRESSURE GAUGE WAS INTERMITTENT. RESISTANCE CHECK OF TRANSMITTER FOUND IT TO BE OPEN CIRCUIT. REMOVED TRANSMITTER CASE TO FIND THAT INTERNAL WIRE WAS MISROUTED CAUSING IT TO BE PINCHED AND EVENTUALLY CUT THROUGH. TRANSMITTER REPLACED.SDR CA130730003Pulley · failed(CAN) ON A DAILY INSPECTION AFTER A DAY OF FLYING THE ENGINEER ON THE MACHINE NOTICED SUBSTANTIAL PLAY ON THE HYDRAULIC PUMP DRIVE PULLEY. HE DISSASEMBLED THE UNIT TO FIND THAT THE INNER RACE OF THE BEARING HAD COMPLETELY WORN AWAY THE AREA OF THE PULLEY WHERSDR CA130624004Modulator · cracked(CAN) WHILE PERFORMING A 100 HRS INSPECTION, IT WAS NOTICED THAT THE BOTTOM ATTACHMENT ARM ON THE AIRFLOW MODULATOR WAS CRACKED. ONCE THE UNIT WAS REMOVED, THE ARM BROKE OFF WITH FINGER FORCE ONLY.SDR CA130525002Starter Gen · failed(CAN) REPORTED UPON START UP A LOAD NOISE COMING FROM ENGINE AREA. START UP ABORTED. UPON INSPECTION IT WAS FOUND TO HAVE LOST THE COOLING FAN. NUT HAD BACKED OFF AND THE FAN HAD COME OFF AND DAMAGED THE SPLINES AND THREADS. A REPLACEMENT STARTER WAS INSTASDR CA130521011Yoke · broken(CAN) DURING 100 HR INSPECTION, 1 OF THE 3 DROOP RING RETAINING YOKES FOUND BROKEN BUT STILL KEPT IN PLACE BY THE CLAMP. NO OTHER DAMAGE. PART REPLACED BY A NEW ONE.SDR CA130521020Transmitter · failed(CAN) LOSS OF ENGINE OIL PRESSURE ON ACFT ENGINE INSTRUMENTS IN FLIGHT. EACH INCIDENT WAS RECTIFIED BY REPLACEMENT OF OIL PRESSURE TRANSMITTER WHICH IS AN AIRFRAME PART SUPPLIED BY MFG. WE INSTALLED THE FIRST NEW TRANSMITTER IT LASTED 39.7 HRS, THE SECOND TRASDR CA130423001Servo · stiff(CAN) DURING ENGINE START THE PILOT IN COMMAND & MECHANIC OBSERVE THE TAIL ROTOR LT PEDAL MOVING TO FULL DEFLECTION WITHOUT INPUT. THE PIC DID RESTRICTED THE UNCOMMANDED MOVEMENT OF THE LT PEDAL BY APPLYING FORCE. THE PIC DID MENTIONED TO THE MECHANIC THAT TSDR CA130321008Skin · deformed(CAN) FOUND A 2.5CM X 5CM SMOOTH DEFORMATION AT BS91 CM AT TOP LT OF TAILBOOM. SUSPECT HEAT DEFORMATION FROM ENGINE EXHAUST.SDR CA130306004Fuel Control · disconnected(CAN) FUEL LEVER WAS DISCONNECTED AT LINKAGE. LEVER POSITIONED IN OPEN POSITION DURING RIGGING REQUIREMENTS. LINKAGE RECONNECTED. AT NO TIME WAS THE FUEL SYSTEM FUEL LINES OPENED. THE NEXT ENGINE START ATTEMPT RESULTED IN FAILED START ATTEMPT. THE SYSTEM WASDR CA130213001Mount · cracked(CAN) DURING A 12 YEARS AIFRAME INSPECTION, THE HYDRAULIC PUMP MOUNT WAS FOUND CRACKED TO ONE OF THE MOUNTING BOLT HOLE. PART WAS MFG IN 03/04.SDR CA130208006Servo · seized(CAN) DURING START SEQUENCE THE TAIL ROTOR PEDAL MOVED AND SEIZED IN FULL LT CONFIGURATION. THE PILOT ACTUATED THE HYDRAULIC TEST SWITCH AND THE TAIL ROTOR PEDAL DID RETURN TO NEUTRAL POSITION. A MECHANIC WAS DISPACTH TO THE ACFT AND WITH THE HELP OF A REMOSDR CA130208003Hose · unserviceable(CAN) HYD FLUID LOSS WAS DISCOVERED ON DAILY INSPECTION. HYD FLUID WAS NOTICED COMING FROM THE HYD PRESSURE LINE, LT SERVO TO EPICYCLIC JUNCTION, WHERE THE BRAIDED PORTION OF THE LINE IS CRIMPED TO THE FITTING. FLUID LEAKING OBSERVED AT BOTH ENDS OF THE CRIM
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