JASC 6700
Service difficulty reports · 317
Reports filed under 6700 · Rotorcraft Flight Control, newest first.
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 jasc_code = '6700' 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 jasc_code = '6700' 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 CA120227004Cyclic Control · malfunctioned(CAN) WHILE PERFORMING A FLIGHT CONTROL CHECK IT WAS FOUND THAT WITH FULL FORWARD CYCLIC INPUT THE COLLECTIVE COULD ONLY BE LIFTED 70 PERCENT OF THE WAY UP. WHEN THE COLLECTIVE WAS FORCED HIGHER UP IN TRAVEL IT WOULD IN TURN FORCE THE CYCLIC AFT. SO WITH FULLSDR CA111201007Bracket · broken(CAN) BRACKET ASSY CAP WHICH IS A MATCHING PART WAS INSTALLED WITHOUT THE NECESSARY SHIMMING IN PLACE. SO INCORRECT ASSY AND THE POSSIBILITY OF THE COLLECTIVE POLE BEING SNAPPED UP WITH NO BLADES INSTALLED OVER ITS LIFE MAY HAVE LED TO THE BREAKING OF THE BEASDR CA061023003Control Tube · scratched(CAN) CONTROL TUBE, PN 222-001-021-145 WAS INSTALLED ON WRONG SIDE OF PILOT CYCLIC STICK LOWER LEVER CAUSING A FOULING CONDITION WITH THE ACFT STRUCTURE IN THE MOST LT CYCLIC TRAVEL.SDR RMXA110308224142Potentiometer · wornON THE SECOND LEG OF A MISSION, AT 16 MINUTES FROM DESTINATION (FOR REFUEL), A YELLOW "GOV" LIGHT ILLUMINATED AND REMAINED ON UNTIL SHUTDOWN. ON RESTART, THE LIGHT DID NOT ILLUMINATE, AND DID NOT ILLUMINATE DURING THE REPOSITION TO OUR PAD, (A 6 MINUTE FLIGHTSDR RMXA308852Potentiometer · intermittentACFT INDICATED AN AMBER GOV LIGHT IN FLIGHT, WITH NO ENGINE, MAIN ROTOR, OR TAIL ROTOR FLUCTUATIONS IN FLIGHT. TECH RETRIEVED AN INTERMITTENT FAILURE CODE 122 FOR THE COLLECTIVE POTENTIOMETER. WHEN THE ACFT WAS POWERED BACK UP AFTER LANDING THE AMBER GOV LIGHSDR RMXA363942Potentiometer · malfunctionedACFT INDICATED AN AMBER GOV LIGHT IN FLIGHT, WITH NO ENGINE, MAIN ROTOR, OR TAIL ROTOR FLUCTUATIONS IN FLIGHT. TECH RETRIEVED AN INTERMITTENT FAILURE CODE 122 FOR THE COLLECTIVE POTENTIOMETER. WHEN THE ACFT WAS POWERED BACK UP AFTER LANDING THE AMBER GOV LIGHTSDR CA110209013Bushing · stiffPILOT REPORTED STIFF IN LATERAL CYCLIC CONTROL. MIXING UNIT LEVER BUSHING FOUND TOO TIGHT AND BIND WHEN ROTATED.SDR EVCA00008Clevis Bolt · damagedPILOT REPORTED VIBRATION TO MECHANIC. MECHANIC INVESTIGATED AND FOUND PLAY IN RED LOWER PITCH CHANGE LINK CLEVIS. UPON DISASSY, MECHANIC FOUND BOLT AND CLEVIS SEVERLY DAMAGED. MECHANIC R & R BOLT AND CLEVIS.SDR CA100812016Control Tube · noisyINTERNAL NOISE (RATTLING) INSIDE OF CONTROL TUBE ASSY ON MAIN ROTOR SHUTDOWN.SDR CA100813007Rod End · corrodedNOTED THE LT AND RT CYCLIC MOVEMENTS WERE GETTING STIFFER AS TIME WENT ON. UPON INVESTIGATION THE LATERAL CYCLIC CONTROL ROD END PN 101-126TMG WAS FOUND SEVERALLY CORRODED CAUSING IT TO BIND. THE PART WAS REPLACED DURING A RECENT 12 YEAR INSP THAT WAS COMPLETSDR CA091106001Jackshaft · cracked(CAN) DURING FLIGHT, PILOT FOUND THE CONTROLS TO BECOME UNRESPONSIVE (LOSS OF FULL SENSE OF OPERATION). FAR MORE FWD CYCLIC WAS REQUIRED AND HIGHER COLLECTIVE PITCH THEN NORMAL. PILOT LANDED THE ACFT WITHOUT INCIDENT. ANOTHER ACFT WITH AN AME WAS SENT TO THIS SDR HEEA126111Control Tube · crackedCORROSION AND CRACKS ON CONTROL TUBE, NEXT TO END AT FIXED CLEVIS. SCRAPPED CONTROL TUBE. NOTE: PREVIOUSLY SUBMITTED ON 10/6/09.SDR MJ01709002Trunnion · bindingDURING THE "FLIGHT CONTROLS TRAVEL AND FLIGHT BOOST SYS CHECK" AS PART OF THE PRE-FLIGHT CK, COMPANY PILOTS NOTICED ABNORMAL RESISTANCE OF LONGITUDINAL CYCLIC CONTROL MOVEMENT. AT THIS POINT THE ACFT WAS GROUNDED AND TURNED OVER TO MX. UPON FURTHER INVESTIGASDR CHIAMJ017/09/002Actuator · restrictedDURING (FLIGHT CONTROLS TRAVEL AND FLIGHT BOOST SYS CK) AS PART OF PRE-FLIGHT CHECKS (DESCRIBED IN FLIGHT MANUAL PART 1, SECTION 2 PAGE 2-11 ITEM 29 (A)) PILOTS NOTICED ABNORMAL RESISTANCE OF LONGITUDINAL CYCLIC CONTROL MOVEMENT. AT THIS POINT ACFT WAS GROUNDSDR EVCA2009/01/09001Lever · wrong partDURING AUDIT OF ELECTRONIC MX RECORDS AN UNRECOGNIZED PN WAS DISCOVERED. INVESTIGATION OF MFG ELECTRONIC TECH PUBS REVEALED (4) PN LISTED FOR THE COLLECTIVE LEVER. (3) OF THE PN WERE LISTED AS NON PROCUREABLE/SUPERCEDED. THE ONE PN SHOWN AS PROCURABLE WAS ISSSDR CA081117004Bearing Race · cracked(CAN) A 12 YEAR INSP WAS BEING CARRIED OUT ON THE HELICOPTER. 2 CRACKS WERE FOUND ON THE INNER RACE OF A BALL BEARING ASSY. THE CRACKS ORIGNALLY STARTED FROM THE RIVET HOLES. THE BEARING ASSY/SUPPORT ATTACH THE INNER RACE OF BEARING BY 4 RIVETS TO THE PILOT`SSDR QML2008F00015Pcu · failedON TAKEOFF, PEDAL STOP FAILED TO ENGAGE AND PEDAL STOP CAUTION 1 LIGHT ILLUMINATED. ACFT WAS APPROX 4 NM FROM AIRPORT. PERFORMED EMERGENCY PROCEDURES AND DECIDED TO FLY ACFT TO AIRPORT. NORMAL LANDING WAS MADE AND MECHANIC WAS NOTIFIED. THE PEDAL RESTRICTOSDR M7KA0817084022Potentiometer · failedAMBER GOVERNOR LIGHT ILLUMINATED IN FLIGHT AND SUBSEQUENT TO FAILURE REPORT GENERATION THE COLLECTIVE POTENTIOMETER WAS INDICATED TO BE DEFECTIVE. A NEW PART WAS INSTALLED AND NO FURTHER DEFECT NOTED. (K)SDR M7K2008F00132Potentiometer · defectiveA FAULT CODE WAS GENERATED ON SHUTDOWN INDICATING A DEFECTIVE COLLECTIVE POTENTIOMETER. A NEW PART WAS INSTALLED AND NO FURTHER FAULT WAS DETECTED. THIS IS A RECURRING FAULT FOR THIS PART WHICH HAS EFFECTED THE DISPATCH RELIABILITY FOR THIS MODEL AC. SUGGESSDR M7K2008F00107Potentiometer · defectiveUPON AC SHUTDOWN A FAILURE CODE WAS GENERATED INDICATING THE COLLECTIVE POTENTIOMETER WAS DEFECTIVE. A NEW PART WAS INSTALLED WITH NOT FURTHER DEFECT REPORTED. THIS IS A REOCCURRING PROBLEM FOR THIS PART THAT HAS EFFECTED THE DISPATCH RELIABILITY FOR THIS MODSDR M7K2008F00101Potentiometer · defectivePILOT REPORTS HAVING AN AMBER GOVERNOR LIGHT IN FLIGHT. UPON AC SHUTDOWN, A FAILURE CODE WAS GENERATED INDICATING THE COLLECTIVE POTENTIOMETER WAS DEFECTIVE. A NEW PART WAS INSTALLED WITH NO FURTHER DEFECT REPORTED. THIS IS A RECURRING PROBLEM FOR THIS PARTSDR M7K2008F00102Potentiometer · defectivePILOT REPORTS HAVING AN AMBER GOVERNOR LIGHT IN FLIGHT. UPON AC SHUTDOWN, A FAILURE CODE WAS GENERATED INDICATING THE COLLECTIVE POTENTIOMETER WAS DEFECTIVE. A NEW PART WAS INSTALLED WITH NO FURTHER DEFECT REPORTED. THIS IS A RECURRING PROBLEM FOR THIS PARTSDR M7K2008F00111Potentiometer · defectiveFAILURE CODE AT SHUTDOWN INDICATED A FAULT WITH THE COLLECTIVE POTENTIOMETER. INSTALLED NEW POTENTIOMETER AND NO FURTHER PROBLEM NOTED. THIS IS A VERY COMMON FAULT FOR THIS PART THAT EFFECTS THE DISPATCH RELIABILITY FOR THIS MODEL AIRCRAFT. (K)SDR M7K2008F00110Potentiometer · defectiveFAILURE CODE AT SHUTDOWN INDICATED A FAULT WITH THE COLLECTIVE POTENTIOMETER. INSTALLED NEW POTENTIOMETER AND NO FURTHER PROBLEM NOTED. THIS IS A VERY COMMON FAULT FOR THIS PART THAT EFFECTS THE DISPATCH RELIABILITY FOR THIS MODEL AIRCRAFT. (K)SDR M7K2008F00108Potentiometer · defectivePILOT REPORTED THAT WHEN ADJUSTING POWER FOR CRUISE FLIGHT THE ENGINE HAD FLUCTUATIONS WHEN PASSING THROUGH A CERTAIN COLLECTIVE POSITION THAT WERE REPEATABLE IF SELECTING THE POSITION IN QUESTION. UPON SHUTDOWN A FAULT CODE WAS GENERATED INDICATING THE COLLESDR M7K2008F00075Potentiometer · defectivePILOT REPORTS AMBER GOVERNOR LIGHT ILLUMINATED DURING FLIGHT. A FAULT CODE WAS GENERATED INDICATING THE POTENTIOMETER AS THE LIKELY DEFECTIVE UNIT. A NEW PART WAS INSTALLED AND NO FURTHER DEFECTS WERE NOTED. THIS IS A RECURRING PROBLEM FOR THIS PART THAT HASSDR CA080411003Rod End · damaged(CAN) ROD END HAS TEFLON MISSING WITH METAL TO METAL CONTACT (TC NR 20080411003)SDR CA080411001Actuator · failed(CAN) ACTUATOR FAILED, (WOULD NOT RETRACT) ON PRESTART TEST. FAILED IN THE EXTEN POSITION (CYCLIC FULL FWD) (TC NR 20080411001)SDR M7K2008F00109Potentiometer · defectiveAC HAD SOME SUDDEN YAWING WHEN PASSING THROUGH A SPECIFIC COLLECTIVE POWER SETTING THAT WAS REPEATABLE AND INDICATED A SUDDEN CHANGE OF ENGINE TORQUE SUCH AS ONE MAY EXPERIENCE WITH COMPRESSOR STALLS. NO FAULT CODES WERE GENERATED AD THE ENGINE HAD NO OBSERVASDR M7K2008F00106Potentiometer · crackedAMBER GOVERNOR LIGHT ILLUMINATED IN FLIGHT AND A FAULT CODE GENERATED INDICATING FAULT WITH COLLECTIVE LEVER VALUES BEING PROVIDED BY THE POTENTIOMETER. NEW POTENTIOMETER INSTALLED WITH NO FURTHER DEFECT NOTED. SUGGEST DIFFERENT MFG OR DESIGN BE CONSIDERED ASDR M7K2008F00105Potentiometer · defectiveAMBER GOVERNOR LIGHT ILLUMINATED IN FLIGHT AND A FAULT CODE GENERATED INDICATING FAULT WITH COLLECTIVE LEVER VALUES BEING PROVIDED BY THE POTENTIOMETER. NEW POTENTIOMETER INSTALLED WITH NO FURTHER DEFECT NOTED. SUGGEST DIFFERENT MFG OR DESIGN BE CONSIDERED ASDR M7K2008F00140Potentiometer · failedA FAULT CODE WAS GENERATED AT ENGINE SHUTDOWN INDICATING A DEFECT WITH THE COLLECTIVE POTENTIOMETER. A NEW POTENTIOMETER WAS INSTALLED. THIS HAS BECOME A VERY COMMON PROBLEM WITH THE LATEST REPLACEMENT PART THAT THEY LAST MUCH LESS THAN THE 2000 HOUR SERVICESDR M7K2008F00115Potentiometer · intermittentTHIS PART IS THE POSITION INDICATOR FOR BOTH COLLECTIVE AND TAIL ROTOR FADEC CONTROL ACTIONS. IT ALMOST NEVER FAILS TOTALLY BUT GENERATES A FAILURE CODE THAT REQUIRES THEY BE REPLACED. THESE PARTS CAN LAST THOUSANDS OF HOURS OR LESS THAN FIFTY. ONLY RECENTLSDR M7K2008F00114Potentiometer · intermittentTHIS PART IS THE POSITION INDICATOR FOR BOTH COLLECTIVE AND TAIL ROTOR FADEC CONTROL ACTIONS. IT ALMOST NEVER FAILS TOTALLY BUT GENERATES A FAILURE CODE THAT REQUIRES THEY BE REPLACED. THESE PARTS CAN LAST THOUSANDS OF HOURS OR LESS THAN FIFTY. ONLY RECENTLSDR M7K2008F00113Potentiometer · intermittentTHIS PART IS THE POSITION INDICATOR FOR BOTH COLLECTIVE AND TAIL ROTOR FADEC CONTROL ACTIONS. IT ALMOST NEVER FAILS TOTALLY BUT GENERATES A FAILURE CODE THAT REQUIRES THEY BE REPLACED. THESE PARTS CAN LAST THOUSANDS OF HOURS OR LESS THAN FIFTY. ONLY RECENTLSDR M7K2008F00112Potentiometer · intermittentTHIS PART IS THE POSITION INDICATOR FOR BOTH COLLECTIVE AND TAIL ROTOR FADEC CONTROL ACTIONS. IT ALMOST NEVER FAILS TOTALLY BUT GENERATES A FAILURE CODE THAT REQUIRES THEY BE REPLACED. THESE PARTS CAN LAST THOUSANDS OF HOURS OR LESS THAN FIFTY. ONLY RECENTLSDR PG9A115818Potentiometer · malfunctionedFAIL CODE 122 DISPLAYED ON VEMD AFTER FLIGHT. REPLACED COLLECTIVE PITCH POTENTIOMETER.SDR PG9A115817Potentiometer · malfunctionedFAIL CODE 122 DISPLAYED ON VEMD AFTER FLIGHT. REPLACED COLLECTIVE PITCH POTENTIOMETER.SDR KBM2006F00235Servo · leakingSERVO LEAKING FROM WEEP HOLE. REMOVED AND REPLACED. (K)SDR EOP2006F00000Servo · malfunctionedAC HAD A STRANGE VIBRATION AND A SQUEALING SOUND. AFTER TROUBLESHOOTING WHERE THIS VIBRATION AND SOUND WAS COMING FROM, THE MECHANIC NOTICED ONE OF THE SERVO’S VIBRATING A LITTLE BIT AND PUT HIS HAND ON IT AND THE SOUND STOPPED. SERVO WAS CHANGED AND THE SYSSDR CA060424009Yoke · obstructedWITH THE COLLECTIVE IN THE MID TO FULL DOWN POSITION AND THE CYCLIC FULL FORWARD AND LEFT THE RT CONTROL YOKE CONTACTS THE WINDSCREEN DEFROST HEATER PIPE.SDR CA060224002Cyclic Control · obstructedCYCLIC STICK FWD MOVEMENT RESTRICTED BY T/R PEDAL STOP MECHANISM CABLE. T/R PEDAL STOP MECHANISM CABLE BRACKET 427-001-296-103 FOUND MISLOCATED.SDR CA060112004Push-Pull Rod · wornWHILE REMOVING A HYDRAULIC SERVO, IT WAS NOTED THAT THE PUSH PULL TUBE FROM THE SERVO TO THE SWASHPLATE WAS WEARING WHERE IT PASSED THROUGH THE MIDDLE RIB OF THE MAST FAIRING. THE CHAFING WAS MINOR, AND HAD ONLY GONE THOUGH THE TOP LAYER OF PAINT, AND STARTEDSDR KNK2006F00001Servo · leakingSERVO LEAKING FROM LOWER POSTON SEAL. (K)SDR 2005FA0001628Sleeve · crackedCRACK INDICATION REVEALED AT WELD TO TUBE SLEEVE. INSPECTION METHOD: FLUORESCENT MAGNETIC PARTICLE. (K)SDR ALG2005F00094Actuator · inoperativeON TAKEOFF AND LANDING CYCLIC CONTROL MOVEMENT FEELS LIMITED IN FORE AND AFT TRAVEL. UPON LANDING THE MECHANIC REMOVED PITCH ACTUATOR ARTIFICIAL FEEL SN 10006, AND INSTALLED SERVICEABLE PITCH ACTUATOR SN 71054 AND HE COMPLIED WITH CONTINUITY CHECK OF CONTROLSSDR B65A106213Control Unit · unserviceableCONTROL UNIT IS CAUSING AN UNCONTROLLABLE LATERAL INPUT.SDR 2005FA0001337Motor · inoperativeON APPROACH TO LANDING THE LONG TRIM MOTOR QUIT WORKING. REPLACED UNIT. (K)SDR 2005FA0000224Bolt · misinstalledFOUND THAT MAX POS OF THROT (POWER LEVER ANGLE) COULD NOT BE OBTAINED USING NML ADJ PROC. FOUND COPILOT THROTTLE LINKAGE WAS FOULING ON COLLECT ELBOW (PN 206-001-203-101). LINKAGE IS ATTACHED TO COL THROTTLE LEVER WITH (NAS6603-9D) BOLT INSTALLED W/HEAD FACSDR 2005FA0000247Trim System · failedDURING DESCENT TO LANDING THE CYCLIC STICK JAMMED SO AS TO NOT ALLOW ANY LATERAL MOVEMENT TO THE RT BEYOND NEUTRAL POSITION. THIS WAS CAUSED BY THE SPRING TUBE COMING OUT OF THE TRIM HOUSING AND LOCKING THE TRIM ARM AT A .7500 EXTENDED POSITION. THE SPRING T
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