Robinson Helicopter R44
Service difficulty reports · 447
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 aircraft_model_key = 'R44' 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 aircraft_model_key = 'R44' 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 AU010230Hub · corroded(AUS) TAIL ROTOR HUB CONTAINED STRESS CORROSION AND CRACKING FROM THE TEETER BEARING RACES.SDR AU010057Key · broken(AUS) NR 5 CYLINDER EXHAUST VALVE KEY BROKEN WITH DAMAGE TO TAPPET AND SOCKET. SUSPECT TAPPET DAMAGED AT MANUFACTURE CAUSING INCORRECT VALVE CLEARANCE.SDR CA010103002Hub · worn(CAN) AFTER NOTICING A RAPID INCREASE IN VIBRATION WE TRIED TO DYNAMICALLY BALANCE THE MAIN ROTOR. SINCE WE WERE UNABLE TO BE WITHIN RECEPTACLE LIMITS, WE REMOVED THE MAIN ROTOR HEAD AND ROTOR BLADES FOR FURTHER INSPECTION. WE FOUND THE HUB HOLE ENLARGED, THE SDR CA001201019Oil Filter · contaminated(CAN) DURING 100 HOUR INSPECTION, NON MAGNETIC MATERIAL WAS FOUND IN OIL FILTER.AN ACID TEST WAS CARRIED OUT ON THE MATERIAL FOUND IN OIL FILTER AND WAS FOUND TO BE SHINNY, NON ALUMIUM AND NON FERROUS. 2000-12-07 TC: EXPECT FOLLOW-UP FROM SUBMITTER WHEN IT BECSDR 20001106SH083Bushing · damagedENGINE DISASSEMBLED FOR INSPECTION AFTER ROTOR STRIKE AT 400.2 HOURS, TOTAL TIME SINCE NEW. INSPECTION OF COUNTERWEIGHT BLADE BUSHING ID (PN 73810) REVEALED TWO BUSHINGS WITH ID .0008 INCH AND .0011 INCH OUT-OF-ROUND AS INSTALLED, WERE BEYOND .0007 INCH LIMITSDR 20001106SH082Crankshaft · making metalENGINE WAS DISASSEMBLED FOR INSPECTION AFTER ROTOR STRIKE AT 18.2 HOURS, TOTAL TIME SINCE NEW. LOOSE CHIPS WERE FOUND AT ENDS OF 68484 OIL TUBE INSTALLED IN FRONT MAIN OF CRANKSHAFT.SDR AU000802Bearing · faulty(AUS) MAGNETO ADAPTER BEAR FAULTY. BEARING HAD NO CAGE FITTED. FOUND WHEN MAGNETO WAS REMOVED DUE TO BROKEN DRIVE CUSHIONS P/N LW-13641. (X)SDR 2000ZZZX372Shaft · shearedDURING ROUTINE MAINTENANCE, METAL WAS FOUND IN SCREEN AND FILTER AND SENT TO LYCOMING. ENGINE TAKEN OUT RIGHT AWAY, AND SHAFT P/N 21668 THAT HOLDS GEAR P/N 71652 HAD FLANGE SHEARED OFF AT BOLT AND STUD AND SPACER. CAUSED MAJOR DAMAGE TO ALL GEARS, CRANKCASE, SDR CA991112031Hub · scored(CAN) THE HUB OF THE BLOWER WAS FOUND CRACKED AND SEVERELY DAMAGED DUE TO POSSIBLE MOVEMENT OF THE BLOWER ALONG THE SHAFTS SURFACE. THE TWO TOUCHING PIECES HAVE SCORES AND TRANSPOSED METAL. PIECES SENT TO MFG FOR INVESTIGATION (MATERIAL OR OTHERWISE). PARTSSDR CA990907014Fuel Cell · contaminated(CAN) WRONG FUEL ADDED FROM FUEL CACHES.SDR CA990812007Bearing · failed(CAN) MAGNETO BEARING DESINTEGRATION. SEE ALSO OPERATOR CONTROL NR 981109044.SDR CA990812001Engine · failed(CAN) POWER LOSS EXPERIENCED WITH PART CARBURETOR HEAT APPLIED. A DECAY OF ROTOR RPM WAS EXPERIENCED RESULTING IN THE EMERGENCY LANDING. LYCOMING REP FOUND NO DISCREPANCIES AT INVESTIGATION. SUBMITTER STATED CARBURETOR ICING IS BELIEVED TO BE THE FAULT.SDR CA990728031Engine · failed(CAN) AFTER LIFT OFF, THE HELICOPTER YAWED SLIGHTLY AFTER A LOUD NOISE WAS HEARD. PILOT RETURNED TO PAD AND SHUT DOWN ENGINE.SDR CA990728030Engine · failed(CAN) ENGINE FAILURE LOSS OF POWER. AIRCRAFT CRASH LANDED. TSB INVESTIGATING INTO CARBURETOR HEAT CLUTCH ASSY AS CAUSE. CARBURETOR HEAT MECHANISM (SUBMITTER STATED THIS HAS NOT BEEN SUBSTANTIATED BY TSB).SDR CA990531010Points · broken(CAN) DURING GROUND RUN, MAGNETO CHECK WAS PERFORMED A PER ENGINE RUN-UP LIST. WHEN THE RIGHT MAG WAS SELECTED, THE RIGHT ENGINED DIED. INVESTIGATION REVEALED THAT THE MAIN POINT CAM FOLLOWER WAS BROKEN OFF AND MISSING. MAGNETO WAS REPLACED.SDR 99ZZZX2016Bearing · wornC106-5 AND C106-6 JOURNALS WORE INTO THE MAIN ROTOR HUB. THE HUB WAS SCRAP. SEVERE SHIP VIBRATIONS NOTICED WHEN LIGHT WEIGHT AND LOW COLLECTIVE INPUT. SUBMITTER STATED POSSIBLE CAUSE AS CORROSION ON JOURNALS WORE THE C648-1 BEARING MATERIAL AWAY UNTIL IT WOSDR 99ZZZX2015Bearing · wornC106-5 AND C106-6 JOURNALS WORE INTO AND THROUGH THE C648-1 BEARING MATERIAL MAKING METAL-TO-METAL CONTACT. HEAVY SHIP LOW FREQUENCY VIBRATION WAS NOTICED WHILE IN HOVER AND LOW COLLECTIVE INPUT. SUBMITTER STATED POSSIBLE CAUSE IS CORROSION ON JOURNALS, WORNSDR CA990513002Float · worn(CAN) THE CARBURETOR FLOAT PIVOT POINT WAS WORN AND THE FLOAT BRACKET (P/N 136-62) WAS BENT. THESE TWO PROBLEMS CAUSED THE FLOAT PONTOON TO RUB AGAINST THE CARBURETOR BOWL ASSEBLY. THERE WAS MINIMAL EVIDENCE OF THIS ON THE FLOAT PONTOON. THIS MAY HAVE CAUSED SDR CA990430007Engine · failed(CAN) THE ENGINE STARTED TO SURGE AND VIBRATE IN CLIMB. THE PILOT ATTEMPTED TO RETURN TO BASE, WHEN THE ENGINE QUIT. THE AIRCRAFT AUTOROTATED TO THE GROUND. FURTHER REPORT TO FOLLOW.SDR 99ZZZX1892T-Bar · looseT-BAR ON CYCLIC CONTROL IS RETAINED WITH A NUT AND COTTER PIN. THE NUT, WASHER AND COTTER PIN WERE NEVER INSTALLED AT THE FACTORY. THE THREADED PORTION STILL HAD MASKING TAPE ON THE THREADS. THE T-BAR PULLED OUT OF THE CYCLIC IN-FLIGHT AND COULD VERY EASILYSDR CA990223009Seat Belt · deteriorated(CAN) UPON TRYING TO FASTEN THE AFT LEFT SEAT BELT, THE WEB STITCHING BECAME UNDONE ALLOWING THE WEBBING TO SEPARATE FROM THE LOWER ATTACH POINT. INVESTIGATION INDICATES EITHER IMPROPER STITCHING OR THREAD DETERIORATION. TOTAL CALENDAR TIME IN SERVICE IS APPSDR CA990111006Bearing · misinstalled(CAN) DURING MAIN ROTOR REPLACEMENT, A LARGE AMOUNT OF ROTATIONAL PLAY, APPROXIMATELY 2 INCHES DISCOVERED, MAX SHOULD BE 0.060 INCH. UPPER YOKE ASSY BEARINGS IMPROPERLY INSTALLED, NOT PRESSED IN DEEP ENOUGH AND AT AN ANGLE, SCORING THE YOKE. INBOARD ARM ATTASDR CA981109044Bearing · failed(CAN) THE ENGINE DID NOT START NORMALLY. THE LEFT MAGNETO WAS REMOVED FOR INSPECTION AND THE GEAR BALL BEARINGS FELL INTO THE OIL SUMP. THE SUMP WAS OPENED AND THE BALL BEARING CASE WAS FOUND SHREDDED, POSSIBLY BY THE GEAR. IT WAS CONCLUDED THAT THE BEARING SDR CA981027012Pitch Link · wrong part(CAN) RECEIVED O/H TAIL ROTOR GEARBOX AND T/R PITCH CONTROL ASSY HAD R22 T/R PITCH LINKS P/N B345-1 INSTALLED INSTEAD OF R44 P/N B345-2. THIS UNIT HAD BEEN O/H AT THE MANUFACTURER.SDR 99ZZZX748Wire · chafedCIRCUIT BREAKER 'POPPED' AND WOULD NOT RESET. FOUND DIRECTIONAL GYRO WIRING CHAFED ON THE UPPER CONSOLE ASSEMBLY. REPAIRED WIRING AND RE-TIED BUNDLE TO CLEAR THE STRUCTURE.SDR AU980499Switch · faulty(AUS) MAIN ROTOR GEARBOX TEMPERATURE SWITCH FAULTY.SDR AU980498Bolt · separated(AUS) BOLT HEAD SEPARATED FROM THE SHANK. DOWEL PIN SHEARED.SDR 98ZZZX1164Spring Assy · failedWHILE PERFORMING INSPECTION FOR AD 98-06-12, FOUND LATERAL TRIM SPRING ASSY PULLED COMPLETELY OUT OF MOUNTING BLOCK AND DANGLING AGAINST BELLY SKIN. TRIM MOTOR ARM P/N C581-1 FROZEN ON SPRING SHAFT. SUBMITTER STATED HAD THIS UNIT FAILED IN-FLIGHT, LOSS OF COSDR CA980317089Pushrod · cracked(CAN) WHILE CARRYING OUT LYCOMING SB 527C (RECALL OF PISTON PINS). THE NR 4 CYLINDER EXHAUST PUSH ROD WAS FOUND CRACKED AT THE TAPPET END. THE CRACK WAS APPROXIMATELY 12 MM LONG.SDR 98ZZZX1115Shaft · wornROTORCRAFT EXPERIENCED A PARTIAL CYCLIC CONTROL FAILURE WHILE LANDING. PILOT WAS UNABLE TO ROLL LEFT USING CYCLIC INPUT. INVESTIGATION REVEALED THAT LATERAL TRIM ACTUATOR ASSEMBLY SHAFT, PN C585-1, HAD A STEP WORN IN IT WHICH ALLOWED THE TRIM ACTUATOR TO JAMSDR CA971221016Spring · failed(CAN) REF: RSB 21 AND FAA AD 97-16-02 SPRING ASSY, WOULD NOT TRIP THE STOPPING OF THE ACTUATOR ON THE LEFT SIDE. SWITCH V3-1001 WAS OK AND HAD BEEN DONE AT 497 HOURS AND WAS OK.SDR 97ZZZX4811Drain Tube · leaksDRAIN TUBE OPENING IS LOCATED INSIDE AIRFRAME IN TRANSMISSION AREA. WHEN SUMP DRAIN VALVE LEAKS, FUEL DRAINS INTO AND ACCUMULATES AT JUNCTION OF FIREWALLS CREATING EXTREME FIRE HAZARD. SUBMITTER RECOMMENDS REVISING THE SUMP DRAIN PLUMBING ALA R22 SYSTEM TO PSDR CA970624001Fanwheel · cracked(CAN) BEFORE FIRST FLIGHT OF DAY, AIRCRAFT IN HOVER. CLUTCH LIGHT FLICKERING AND PILOT HEARS GROWLING AND FEELS VIBRATION. INSPECTION FOUND CENTER HUB IN THE FAN HAD CRACKED COMPLETELY AROUND CAUSING THE CENTER HUB BOLTS TO LOOSEN OFF. THERE WAS ALSO A LOT SDR AU970504Bearing · rough(AUS) ENGINE TO TRANSMISSION CLUTCH UPPER SHEAVE BEARING NOISY AND ROUGH IN OPERATION - NO EVIDENCE OF LUBRICATION - TELETEMP INDICATOR HAD NOT ACTIVATEDSDR CA970422025Bearing Assy · fretted(CAN) FANWHEEL REMOVED FOR OTHER MAINTENANCE. FRETTING AND METAL TRANSFER WERE NOTED BETWEEN FANSHAFT AND FANWHEEL.SDR CA970507011Switch · failed(CAN) PILOT HEARD HUMMING NOISE AND LIGHT VIBRATION. CARRIED OUT AN EMERGENCY LANDING, 30 FEET OFF GROUND HEARD LOUD BANG AND LOST DIRECTIONAL CONTROL. AFTER INVESTIGATING, FOUND CLUTCH SHAFT FAILURE DUE TO SWITCH FAILURE ALLOWING BELT TENSION ACTUATOR TO OVSDR CA970422024Clutch · broken(CAN) GROWLING NOISE ON SHUTDOWN, CLUTCH SHAFT WAS REMOVED AND DIS- ASSEMBLED. BROKEN EAR ON SPRAG CLUTCH.SDR 97ZZZX3211Switch · failedTEMPERATURE SWITCH MALFUNCTIONED FOR NO OBVIOUS REASON. CAUSED INTERMITTENT OVERTEMP LIGHT OF M/R GEARBOX.SDR 97ZZZX3210Spring Assy · wornARM C581-1 WAS BINDING AND WEARING INTO SHAFT. THIS CAUSED THE LATERAL SPRING ASSEMBLY TO LOCK MOMENTARILY. EXCESSIVE WEAR ON THE SPRING SHAFT COULD AFFECT THE FLIGHT CONTROLS AND AIRCRAFT CONTROL ABILITY.SDR 97ZZZX3321Bearing · wornENG/TRANSMISSION COUPLING, LOWER BEARING OF ACTUATOR WHICH IS CONNECTED TO LOWER SHAFT AND BEARING ASSEMBLY WORE OUT. THIS CAUSED THE ACTUATOR ASSEMBLY TO VIBRATE AND, THEREFORE, ONE BELT TENSION SWITCH TO BREAK. BEARING TOO WEAK TO HOLD UP TO THE PRESSURE ASDR 97ZZZX3320Switch · brokeENGINE/TRANSMISSION COUPLING, VIBRATION OF ACTUATOR CAUSED ACTUATOR SPRINGS TO VIBRATE ON BOTH SWITCHES AND, THEREFORE, ONE BELT TENSION SWITCH TO BREAK. SWITCH BROKE IN CLOSED POSITION. SPRINGS TOO WEAK TO WITHSTAND VIBRATION.SDR CA970212001Hose · loose(CAN) PILOT FELT AN OBSTRUCTION WHEN MOVING THE TAIL ROTOR DURING LANDING. INSPECTION FOUND THAT THE HEATER HOSE WAS RUBBING ON THE LOWER FORWARD BELLCRANK (P/N C317-2). THE HOSE LAYS ALONGSIDE THE BELLCRANK AND CAME IN CONTACT WITH A CONTROL TUBE BOLT.SDR CA961112003Fan Wheel · misalignment(CAN) WITNESS MARKS MISALIGNED ON COOLING FAN.SDR AU961090Firewall · damaged(AUS) VERTICAL FIREWALL LOWER DIAGONAL CENTRAL TUBE AND ATTACHING DOUBLERS SEPARATED FROM FIREWALL DURING HARD LANDINGSDR CA970422023Fanshaft · fretting(CAN) FANWHEEL REMOVED FOR OTHER MAINTENANCE. FRETTING AND METAL TRANSFER NOTICED BETWEEN THE FANSHAFT AND FANWHEEL.SDR CA960123013Clamp · cracked(CAN)TAIL PIPE ATTACHMENT CLAMP P/N C169-17 WAS FOUND CRACKED ACROSS BOTH WELDS AND CLAMP.SDR CA950912019Bearing · cracked(CAN)DURING FACTORY ACCEPTANCE THE PILOT/OWNER REPORTED THAT THE FORCE REQUIRED FOR FLAPPING THE TAIL ROTOR WAS EXCESSIVE. COMPANY FLIGHT TEST RESPONDED THAT THIS WAS NORMAL FOR A NEW AIRCRAFT. DURING THE IMPORT INSPECTION THE FLAPPING BEARING INNER RACE WAS
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