JASC 6710
Service difficulty reports · 1,151
Reports filed under 6710 · Main Rotor 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 = '6710' 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 = '6710' 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 QMLA2016032416029Rod End · wornPILOT REPORTED, HOPPING VIBRATION, IN-FLIGHT WHILE EN-ROUTE TO HOSPITAL. DURING POST FLIGHT CHECK, DISCOVERED THE RED MAIN ROTOR BLADE PITCH LINK UPPER ROD END TO HAVE LATERAL PLAY.SDR E3MA20160202001Actuator · abnormalDURING POST MX FLIGHT CHECKS, THE PILOT SAID SMALL INPUTS TO THE COLLECTIVE RESULTED IN LARGE MOVEMENTS TO THE ACFT. THE ENG TORQUES WERE ALSO DIFFICULT TO STABILIZE. AFTER LANDING, SHUTDOWN & INSPECTION BY MX, A LAG OF COLLECTIVE INPUT TO THE MOVEMENT OF THSDR QMLA2015110215102Bushing · bindingAFTER INSTALLING DUAL CONTROLS & READY TO DEPART TO RETURN TO BASE FOR PILOT TRAINING, THE ACFT WAS STARTED & BROUGHT TO GND IDLE IAW EC130B4, NORMAL PROCEDURES CHECKLIST. FLIGHT CONTROLS CHECKED GOOD & FREE OF MAJOR BINDING, EXCEPT FOR SLIGHT ADDED FRICTION SDR QMLA2015070815054Bracket · crackedWHEN MECHANIC ON DUTY WAS PERFORMING AN AIRWORTHINESS CHECK ON THE ACFT, A CRACK WAS FOUND IN THE BRACKET THAT SECURES THE MR, CHINA HAT, TO THE MR HEAD. LEAD MECHANIC WAS NOTIFIED ALONG WITH PICTURES.SDR CA150706012Jam-Nut · loose(CAN) DURING ARRIVAL INSPECTION, ONE OF THE MR PITCH CHANGE LINKS WAS FOUND TO HAVE BOTH THE UPPER & LOWER JAM NUTS LOOSE. THE UPPER NUT HAD THE REQUIRED SAFETY BUT NO TORQUE ON EITHER END OF THE LINK.SDR CA150429012Bearing · damaged(CAN) PILOT REPORTED INTERMITTENT COLLECTIVE CONTROL RESTRICTIONS AT VARIOUS POWER SETTINGS THROUGHOUT THE COLLECTIVE CONTROL RANGE. ENGINEER REPORTED THE PROBLEM WAS BEING CAUSED BY MOISTURE INGRESS AND THEREBY LOSS OF LUBRICATION TO THE BEARINGS, PN MS2764SDR E3MA20150204001Clamp · missingDURING A PREFLIGHT INSPECTION, DAMAGE WAS DISCOVERED ON THE MAIN ROTOR DRIVE LINK. IT WAS DETERMINED THAT THE DAMAGE WAS MOST LIKELY CAUSED BY THE LOWER SWASH PLATE HOSE CLAMP, DUE TO THE FACT THAT THE CLAMP WAS MISSING.SDR CA141124001Pushrod · chafed(CAN) DURING 36 MONTH INSPECTION, COLLECTIVE PUSH ROD FOUND CHAFED. CHAFING WAS CAUSED BY BLIND RIVETS INSTALLED DURING POST MFG OF ACFT. PUSH ROD REMOVED, AND RIVETS ARE TO BE REPLACED WITH SOLID RIVETS TO ALLOW FOR ADDITIONAL CLEARANCE.SDR ALGA2014082433384Bearing · wornUPON PICKUP TO A HOVER BINDING WAS FELT IN THE CYCLIC FLIGHT CONTROL SYS. ACFT WAS LANDED & THE BINDING CONDITION WAS CONFIRMED BY THE COPILOT. ACFT WAS GND TAXIED TO PARKING. IDLER LINK IN FLIGHT CONTROL SYS WAS FOUND TO HAVE WORN BEARING. IDLER LINK WAS SDR Q2HA2014092500001Actuator · malfunctionedINCREASED COLLECTIVE FORCES WERE REQUIRED TO CONTROL AIRCRAFT. AN INSPECTION OF THE ENTIRE FLIGHT CONTROL SYS WAS PERFORMED WITH NO ANOMALIES. IT WASN`T UNTIL THE COLLECTIVE SERVO ACTUATOR WAS REPLACED THAT THE DISCREPANCY CLEARED. THIS SERVO WAS INSTALLED SDR Q2HA2014090500001Actuator · malfunctionedINCREASED COLLECTIVE FORCES WERE REQUIRED TO CONTROL AIRCRAFT. AN INSPECTION OF THE ENTIRE FLIGHT CONTROL SYSTEM WAS PERFORMED WITH NO ANOMALIES. IT WASN`T UNTIL THE ENTIRE FLIGHT CONTROL SYSTEM WAS PERFORMED WITH NO ANOMALIES. IT WASN`T UNTIL THE COLLECTIVSDR 2014FA0000037Friction Cup · misinstalledPILOT REPORTED HARD POINTS IN THE CYCLIC CONTROL SYS DURING GROUND OPERATION AND IN FLIGHT. CYCLIC CONTROL FOUND TO HAVE ABNORMAL WEAR BETWEEN CYCLIC FRICTION BOX AND THE FRICTION CUP, THIS WAS DUE TO DIRT AND DUST ACCUMULATION. FRICTION CUP AND FRICTION BOXSDR 2014FA0000036Friction Cup · wornPILOT REPORTED HARD POINTS IN THE CYCLIC CONTROL SYS DURING GROUND OPERATION AND IN FLIGHT. THE CYCLIC CONTROL WAS FOUND TO HAVE ABNORMAL WEAR BETWEEN THE CYCLIC FRICTION BOX AND THE FRICTION CUP, THIS WAS DUE TO 2 FACTORS. DIRT AND DUST ACCUMULATION. THE FSDR CA131210007Transducer · fouled(CAN) DURING GROUND RUN, FADEC FAULT/DEGRADE LIGHT ILLUMINATED. PILOT ATTEMPTED TO SWITCH OFF ENGINE BUT COULD NOT, THEN SUCCESSFULLY SELECTED TO SWITCH OFF MANUALLY. INVESTIGATION INITIATED BY MRO, WHICH REVEALED THE COLLECTIVE PITCH (CP) TRANSDUCER FAILED. SDR CA131114003Bellcrank · frozen(CAN) THE PILOT REPORTED THAT DURING FINAL APPROACH TO A LANDING, THE COLLECTIVE FROZE AT APPROX 30 PERCENT WHEN POWER WAS REDUCED. A SIGNIFICANT AMOUNT OF FORCE WAS REQUIRED TO PUSH THROUGH THE BINDING TO CONTINUE WITH THE APPROACH. ONCE POWER WAS RE-APPLISDR AC2A201311060001Collective Stick · bindingDURING FINAL APPROACH, COLLECTIVE CONTROL BOUND OR FROZE AT APPROXIMATELY 30 PERCENT POWER WHEN POWER WAS REDUCED. A SIGNIFICANT AMOUNT OF FORCE WAS REQUIRED TO PUSH THROUGH THE CONTROL BINDING TO CONTINUE WITH THE APPROACH. ONCE POWER WAS REAPPLIED TO ARRESDR CA131010011Bearing · loose(CAN) ON THE ACFT, THE DUAL CYCLIC CONTROL WAS MAKING NOISE WHILE MOVING IT LATERALLY, A CLICKING SOUND. AFTER INVESTIGATION, IT WAS FOUND THAT THE LOWER BEARING OF THE PIVOT ASSY WAS SLIGHTLY MOVING AXIALLY INSIDE OF ITS HOUSING. IT APPEARS THAT THE BEARINGSDR 3GMA2013F00167Cyclic Control · obstructedDURING A NORMAL CHECK OF THE FLIGHT CONTROLS DURING MX, FOUND THE CO-PILOTS CYCLIC MISINSTALLED, CYCLIC CAN CONTACT GLARESHIELD AND POSSIBLY WEDGE UNDER IT. GLARESHIELD AND INSTRUMENT PANEL ARE NOT OEM INSTALLED PARTS. MODIFIED UNDER STC SR00650DE-D. ISSUE SDR 2013FA0000329Bracket · brokenCOLLECTIVE BUNGIE BRACKET BROKE IN FLIGHT. PILOT MADE A RUN ON LANDING WITH MINIMAL COLLECTIVE CONTROL.SDR 2A6R20130430298Control Rod · crackedDURING AAIP INSPECTION, LONGITUDINAL CONTROL ROD TO HYDRAULIC PACK WAS FOUND TO BE CRACKED.SDR QMLA2013022813031Bearing · roughON APPROACH TO LANDING PILOT REPORTED BINDING IN CYCLIC CONTROL IN THE AFT QUADRANT. MX INVESTIGATION REVEALED 2 BEARINGS IN CYCLIC CONTROL SYS WITH ROUGH SPOTS. REPLACED 1 EA PN ASNA0136-35E2 BEARING AND 1 EA ASNA0137-35E2 BEARING IN CYCLIC CONTROL TORQUE SSDR 2A6R201212103121Collective Stick · failed144 MONTH INSPECTION IAW AMM 05-24-00. A HARDNESS TEST WAS PERFORMED; THE COLLECTIVE FLIGHT CONTROL FAILED THE HARDNESS TEST AND THE COLLECTIVE FLIGHT CONTROL IS DEEMED AS "NOT AIRWORTHY".SDR ALGA2012102329050Actuator · malfunctionedAFTER RUNUP COMPLETE AND HESS TEST FLIGHT, ADVANCED THROTTLES TO FLY POSITION AND COLLECTIVE ROSE. PUT COLLECTIVE BACK DOWN AND ACFT TURNED RIGHT. SHUTDOWN ACFT. REMOVED COLLECTIVE ACTUATOR WITH NEW SERVICEABLE ACTUATOR.SDR E3MA201210180001Bolt · wornDURING FLIGHT, THE PILOTS WERE COMPLAINING OF A VIBRATION IN THE MAIN ROTOR. THE MAIN ROTOR TRACK AND BALANCE WAS CHECKED AND NECESSARY ADJUSTMENTS WERE MADE TO BRING IT WITHIN ACCEPTABLE LIMITS. THE VIBRATION REMAINED DURING FLIGHT. AFTER FURTHER INSPECTIOSDR QMLA2012071212115Cyclic Control · bindingDURING MX TEST FLIGHT, AFTER COMPLETION OF 3600 HR INSPECTION, COMPLETED GROUND RUN AND HOVER CHECKS. PROCEEDED TO TAKEOFF, AT APPROX 100 FT AGL SLOWLY ACCELERATED ACFT THROUGH ETL, CYCLIC CONTROL LOCKED UP IN THE PITCH AXIS. NOSE OF ACFT CONTINUED TO PITCHSDR CA120425003Piston · worn(CAN) PLASMA COATING HAS DETACHED FROM APPROXIMATELY 80 PERCENT OF THE UPPER RING OF THE PISTON HEAD.SDR CA120328007Piston · damaged(CAN) PLASMA COATING HAS DETACHED FROM APPROXIMATELY 15 PERCENT OF THE UPPER RING OF THE HEAD OF THE PISTON HEAD.SDR QMLA2012030812053Cyclic Stick · loosePLAY IS FELT IN THE CYCLIC STICK - FORE AND AFT AXIS: DISCOVERED THE CYCLIC PITCH STICK STAND WAS SLIDING BACK AND FORTH ON THE BUSHING THAT WAS SUPPOSE TO BE PRESS FITTED TO THE CYCLIC PITCH STICK STAND.SDR CA120213007Trim Switch · intermittent(CAN) PILOT REPORTED, ATT MODE-ERRATIC PITCH. DISCUSSION WITH THE PILOT REVEALED THAT THE PROBLEM OCCURED IN THE DECENT AND IN ATT MODE. THE PILOT STATED THAT HE ELECTED NOT TO USE THE VERTICAL MODE AND REPORTED THE FAULT UPON LANDING. THE CO-PILOT CYCLIC SSDR ALGA2012011611712Tube · corrodedTUBE HAS CORROSION BEYOND REPAIRABLE LIMITS.SDR ALGA1012421121Tube · corrodedREPLACED TUBE DUE TO CORROSION BEYOND LIMITS.SDR ALGA1311611212Rod End · wornROD END WORN BEYOND REPAIRABLE LIMITS.SDR 2012FA0000117Torque Tube · mismanufacturedDURING A 600 HR A/F INSPECTION, NOTICED 8 RIVETS SHOWING EVIDENCE OF LOOSENESS. THE AFFECTED RIVETS ARE LOCATED ON THE RT SIDE OF THE TORQUE TUBE AND GO AROUND. THE CIRCUMFERENCE OF THE COLLECTIVE TORQUE TUBE ASSY. AFTER MOVING THE PILOTS COLLECTIVE CONTROSDR HCMA2011F00000Potentiometer · malfunctionedDURING A TOUR FLIGHT WITH 6 PASSENGERS AND THE PILOT ON BOARD, THE ACFT LEFT THE HELIPAD AND 10 MINUTES INTO FLIGHT, THE AMBER "GOV" LIGHT ILLUMINATED ON THE CAUTION PANEL. THE PILOT RETURNED TO THE HELIPORT WITHOUT INCIDENT. THE ACFT WAS SHUTDOWN NORMALLY. SDR CA110720007Governor · malfunctioned(CAN) ROTOR RPM DROOPING TO 94 PERCENT. GOVENOR REPLACED.SDR CA110217002Actuator · faultedCSAS PITCH LIGHT WOULD NOT EXTINGUISH DURING GROUND TEST. PITCH ACTUATOR WAS DETERMINED AT FAULT - WITH CSAS SYS POWERED UP IT WAS POSSIBLE TO MANUALLY EXTEND AND RETRACT THE ACTUATOR FROM STOP TO STOP WHEN IT SHOULD HAVE BEEN INTERNALLY BRAKED. REPLACEMENT OSDR 2011FA0000042Control Unit · misalignedFOUND MIXER UNIT MISALIGNED CAUSING THE CYCLIC STICK TO RISE UNCOMMANDED DURING GROUND CHECKS AND ALSO CAUSED THE STRESS OF OTHER FLIGHT CONTROL COMPONENTS IN THE SYS CAUSING RIVETS TO WORK WHEN THE ACFT WAS SHUTDOWN AND THE CYCLIC IN THE LOCKED POSTION.SDR CA101209009Bushing · damaged(CAN) STIFF THROTTLE REPORTED. WHEN TAKEN APART WE HAVE FOUND DAMAGE TO THE BEARING SURFACE OF THE FLEX COUPLINGS FROM SAND. ALSO DAMAGE TO COLLECTIVE ELBOW BUSHING FROM SPAWLING METAL OF THE FLEX SHAFT ON THE #2 THROTTLE. THERE IS NO PROTECTION IN THIS AREA FSDR CA101019019Bolt · brokenDURING NORMAL OPERATIONS A "SNAP" IN THE CYCLIC WAS NOTICED BY THE PIC. AS POWER WAS APPLIED THE PIC NOTED ABNORMAL BEHAVIOR IN THE ACFT THAT REQUIRED A FULL RT AND FWD CYCLIC INPUT TO MAINTAIN STRAIGHT AND LEVEL ATTITUDE. ACFT WAS STABILIZED AND LANDED IMMESDR CA101018004Potentiometer · erratic(CAN) A FAILURE CODE ON THE VEMD INDICATED A COLLECTIVE POTENTIOMETER MALFUNCTION ON ONE FLIGHT, ALSO THE PILOT REPORTED THAT DURING CRUISE THE COLLECTIVE INPUT TO THE ENGINE DID NOT RESPOND IMMEDIATELY AND CAUSED THE A/C TO TWITCH.SDR HEEA129640Transducer · warning lightIN CRUISE FLIGHT ENGINE OUT LIGHT MOMENTARY ILLUMINATED WITH AUDIO WARNING. MOMENTARY YAW TO LEFT. COLLECTIVE TRANSDUCER FAULT CHANNEL 1. REPLACED TRANSDUCER.SDR ALGA2010F00206Control Cable · bindingON APPROCH, THE COLLECTIVE STUCK AT APPROX 50 PERCENT TORQUE. PILOT WAS ABLE TO FORCE COLLECTIVE TO BREAK IT FREE. PROBLEM WAS CAUSED BT A N2 CONTROL CABLE SEIZEING UP CAUSING THE SHEAR RIVET TO SHEAR.SDR YTRA1019601Bolt · missingTHE PILOT WAS UNABLE TO MAKE ANY COLLECTIVE CONTROL SYS INPUTS. ON INSP IT WAS DISCOVERED THAT BOLT PN 20-057-5-20D HAD BECOME DISCONNECTED FROM LINK ASSY PN 206-001-558-103 AND SWASHPLATE LEVER ASSY PN 206-010-447-109.SDR 2010FA0000401Collective Stick · crackedFOUND A CRACK IN THE PILOT'S COLLECTIVE STICK. THE CRACK RADIATES.SDR QMLA2010032210009Potentiometer · unsecurePILOT REPORTED THAT, IN CRUISE FLIGHT, WHEN SLOWLY INCREASING POWER FROM 93 PERCENT NG, PILOT PERCEIVED THAT ACFT EXPERIENCED A YAW/TORQUE KICK. DURING OCCURRENCE, NO GOV LIGHTS ILLUMINATED, NOR WERE ANY GOV LIGHTS ILLUMINATED DURING SHUTDOWN, DURING NORMAL LSDR EVCA731DASupport · crackedDURING A ROUTINE INSP, MECHANIC FOUND RT (PILOT) SUPPORT ASSY CRACKED. SUPPORT ASSY REMOVED AND REPLACED.SDR 2010F00063Support · crackedDURING A ROUTINE INSP, MECHANIC FOUND RT (PILOT) SUPPORT ASSY CRACKED. SUPPORT ASSY R & R.SDR QMLA2010030110005Rod · bentTHE PILOTS FELT STIFFNESS IN THE FWD QUADRANT OF THE CYCLIC DURING TAKEOFF. TAKEOFF WAS ABORTED LEFT ACFT RUNNING, CHECK FOR BINDING OF THE SERVOS, NONE FOUND. ACFT SHUTDOWN, BELLY PANEL REMOVED FLIGHT CONTROLS WERE INSP AND FOUND BENT PUSH PULL TUBE. NO OTHESDR CA090928004Spring · broken(CAN) DURING INSPECTION FOUND SPRING BROKEN. (TC# 20090928004)SDR CA090730004Bearing · wornTHE LINEAR ACTUATOR ADJUSTMENT SCREW STICKS AND DOES NOT POP BACK OUT, THE SHAFT BEARING HAS PLAY IN IT.
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