JASC 6720
Service difficulty reports · 852
Reports filed under 6720 · Tail Rotor Control System, 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 = '6720' 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 = '6720' 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 QR9R2026073000002Actuator · faultyDURING RUN-UP, YAW SAS AND BACKUP SAS CAUTIONS WOULD NOT GO OUT. DURING TROUBLESHOOTING, SHOT RESISTANCE BETWEEN PINS B AND C OF YAW SEMA AND FOUND THAT IT WAS BAD. ON AFCS BANNER UPON POWERING UP AP1 AND AP2, YAWEMA INVALID WAS PRESENT. REMOVED AND REPLACED SSDR 8LFA202506170003Bearing · failedTAIL ROTOR BLADE CONTROL PITCH LINK BEARING FAILED, THE INNER RACE SEPARATED FROM THE OUTER RACE, WHICH ALLOWED THE PITCH LINK ROD END TO MOVE AXIALLY ALONG THE ATTACHMENT HARDWARE WITHIN THE FORK OF THE TAIL ROTOR BLADE PITCH CONTROL FITTING.SDR 2025FA0000426Pitch Link · wornRAPID WEAR OF TAIL ROTOR PITCH LINKSDR QR9R2025051400001Cable · damagedAFTER RECEIVING PART FROM SUPPLY, MAINTENANCE DETECTED THE TAIL ROTOR FLEXBALL CABLE THREADS WERE DAMAGED ON FWD END AT JAM NUT. REPLACED CABLE IAW AMM 67-20-00, 4-7.SDR H11A2025062500425Bearing · wornRAPID WEAR OF TAIL ROTOR PITCH LINK BEARINGSDR 2NVA202408210020Control Rod · deformedDURING ATTEMPTED ROTOR ENGAGEMENT FOLLOWING ENGINE START, TAIL ROTOR PEDALS DEFLECTED FULL LEFT. ENGINE WAS IMMEDIATELY SHUT DOWN AFTER LESS THAN 45 DEGREES OF ROTOR MOVEMENT. INSPECTION REVEALED CONTACT BETWEEN AFT FLEX PLATE AND TAIL ROTOR CONTROL ROD. FURTHSDR HEEA202310230001Retaining Ring · dislodgedDURING CRUISE FLIGHT, WASHERS AND RETENTION RING WERE SEEN ON THE COPILOT FLOOR. DISCOVERED THE RIGHT TAIL ROTOR PEDAL WAS SLIPPING OFF. RETURNED TO BASE WITH NO FURTHER INCIDENT.SDR 2023FA0000282Pin · malfunctionedDURING AN AVIONIC TEST FLIGHT THE TAIL ROTOR PEDAL LOCKOUT EXPANDABLE PIN FELL APART FROM THE PIN HANDLE. THERE ARE NO INSTRUCTION TO IDENTIFY THIS ISSUE IN THE INSTALLATION INSTRUCTION. (IIN-D119-827). THIS COULD HAVE BEEN A CATASTROPHIC.SDR QR9R2023020700001Actuator · oscillatesIN STRAIGHT AND LEVEL FLIGHT, AIRCRAFT OSCILLATES IN YAW AXES. WHEN SAS CUT IS ACTIVATED, OSCILLATIONS STOP. REMOVED AND REPLACED SEMA ACTUATOR IAW 67-20-00, 4-14, 4-8. TEST FLIGHT SUCCESSFULLY COMPLETED IAW AMM 05-60-00, 6-1.SDR QMLA2022120400484Pedal · bindingSHORTLY AFTER TAKE OFF, LEFT PEDAL WAS APPLIED WITH A BINDING IN THE PEDAL CONTROLS. AN UNUSUAL SOUND WAS COMING WHEN PEDAL INPUT WAS APPLIED. MAINTENANCE PULLED MULTIPLE FAILURE CODES RELATED TO THE YAW ANTICIPATOR STORED IN THE VEMD. INSPECTED ENTIRE TAIL RSDR QR9R20220715002Actuator · failed#1 AP ACTUATOR FAILED 3 TIMES ON PREFLIGHT. REMOVED AND REPLACED SEMA ACTUATOR IAW AMM 67-20-00, 4-8. T/F SUCCESSFULLY COMPLETED.SDR QR9R20220629003Actuator · warning messageDURING FLIGHT, AP1 FAIL AND ACTUATOR CAUTIONS ILLUMINATED. CONDUCTED EMERGENCY PROCEDURE BUT ACTUATOR CAUTION REMAINED ON. DURING TEST FLIGHT EVAL: AP 1&2, YAW SAS, ACTUATOR, BACKUP SAS CAUTIONS PRESENT WITH AMBER Y ON PFD. REPLACED YAW SEMA IAW AMM 67-20-00,SDR 2022FA0000212Actuator · wrong partIN ACCORDANCE WITH SB MBB-BK117 C-2-67-013, IF THE TAIL ROTOR ACTUATOR (P/N B673M40A1001 [TYPE 1]) IS REPLACED, IT WILL BE REPLACED WITH THE IMPROVED VERSION (P/N B673M40A1002 [TYPE 2]) OF THE TAIL ROTOR ACTUATOR. THE TYPE 1 T/R ACTUATOR WAS REPLACED ON MARCH SDR 2VKA2022030720221Pitch Link · crackedDURING THE PREFLIGHT INSPECTION ONE OF THE BEARINGS ON THE TAIL ROTOR PITCH CHANGE LINK WAS FOUND WORN. THE BEARING STARTED TO WEAR THROUGH THE OUTER RACE AND THE PITCH CHANGE LINK WAS CRACKED.SDR QR9R20211022003Actuator · warning lightACTUATOR LIGHT CAME ON IN FLIGHT WITH STIFFNESS IN THE CYCLIC, AUTO PILOT FAILED TEST AFTERWARDS AND THE YAW CODE CAME UP AFTER MULTIPLE TESTS WITH POWER ON. MTF EVAL: ACTUATOR LIGHT ILLUMINATED WITH CORRESPONDING YAW ADVISORY, DURING COORDINATED TURN. MAINTENSDR 2021F00282Lever · wornON MANY EC135 SERIES AIRFRAMES, EXCESSIVE WEAR HAS BEEN NOTED ON A PRIMARY FLIGHT CONTROL LEVER. SPECIFICALLY THE TAIL ROTOR HYDRAULIC ACTUATOR INPUT LEVER. DIRECT CONTACT OF THIS LEVER WITH A STATIONARY COMPONENT CAUSES ABRASION AND WILL EVENTUALLY LEAD TO FASDR QR9R20210721001Trim Motor · unreliableDURING FUNCTIONAL CHECK FLIGHT FOR TAIL ROTOR BALANCE AND SLEEVE REPLACEMENT YAW ACTUATOR FAILED. ATTEMPTED SEVERAL RESETS AND AUTO PILOT CHECKS BUT YAW CHANEL WOULD NOT PASS.SDR Z1RA76110232020Servo · leakingTAIL ROTOR SERVO LEAKING AT SHAFT SEAL.SDR YV3R2020110900377Pitch Control · noisyCUSTOMER REPORTED PITCH CONTROL ASSEMBLY P/N: A031-1 HAD BEARING NOISE.SDR YV3R2020091700346Pitch Control · defectiveCUSTOMER REPORTED TAIL ROTOR PITCH CONTROL P/N: C031-1 HAD AN UNUSUAL BEARING NOISE AFTER ENGINE SHUT DOWN, WHILE DRIVE TRAIN STILL RUNNING.SDR YV3R2020082900335Push-Pull Rod · wornCORRECTED (UNIQUE CONTROL #): CUSTOMER REPORTED PUSH-PULL TUBE P/N: C121-17 WAS WORN AT FORWARD GUIDE POSITION.SDR YV3R2020082800335Push-Pull Rod · wornCUSTOMER REPORTED PUSH-PULL TUBE P/N: C121-17 WAS WORN AT FORWARD GUIDE POSITION.SDR 2A6R2019121655001Flex Coupling · separatedDURING HEAVY MAINTENANCE, FOUND THE TAIL ROTOR FLEXBALL CABLE OUTER SHEATH AT THE AFT END TO BE BROKEN AND SEPARATED FROM THE CRIMPING SLEEVE APPROXIMATELY 1/4". IF LEFT UNDISCOVERED FOR MUCH LONGER THERE WAS A RISK OF MECHANICAL BINDING OR INTRODUCTION OF FOSDR HDNA201911189494Actuator · faultyPILOT REPORTED AN ACTUATOR WARNING LIGHT ILLUMINATED ON THE CENTRAL PANEL DISPLAY SYSTEM WITH NO SECONDARY INDICATIONS OR SUBSEQUENT DEGRADATION OF CONTROL-ABILITY. SYSTEM WAS DEFERRED I/A/W WITH THE APPROVED MEL AND RETURNED TO SERVICE. DURING THE REPAIR PHASSDR YV3R2019012320203Bearing · roughCUSTOMER REPORTED TAIL ROTOR PITCH CONTROL P/N: C031-1 HAS ROUGH BEARINGS.SDR 11RR20190820767Cable · brokenON TAKEOFF PILOT REALIZED HE HAD NO ANTI-TORQUE INPUT WITH LEFT PEDAL INPUT. THE PILOT LOWERED THE COLLECTIVE IMMEDIATELY BUT THE AIRCRAFT ROTATED 180 DEGREES BEFORE COMING TO REST. UPON INSPECTION IT WAS FOUND THE RH THRUSTER CABLE WAS BROKEN APPROXIMATELY ATSDR HDNA2019071800001Bearing Race · crackedTHE TAIL ROTOR CONTROL ROD PN 350A27-1910-0401 AFT BEARING RACE CRACKED.SDR CA190626014Bearing · failed(CAN) DURING LAST SHUT DOWN OF THE DAY THE PILOT NOTED THAT ON WHINED DOWN THERE WAS A SQUEAL COMING FROM THE BACK OF THE AIRCRAFT. IT WAS DETERMINED THAT THE TAIL ROTOR PITCH CONTROLLER BEARINGS WERE MAKING THE NOISE. AFTER A BRIEF INQUIRY WITH ROBINSON TECHNSDR 2019FA0000124Control Cable · bindingA/C EXPERIENCED STUCK RIGHT PEDAL IN FLIGHT RESULTING IN EMERGENCY LANDING. UPON INSPECTION OF ANTI-TORQUE SYSTEM, FOUND FORWARD AND AFT THRUSTER CONTROL CABLE ASSEMBLIES BOUND UP AT THE TAIL BOOM CONNECT/DISCONNECT POINT. THIS LOCATION IS WHERE THE FORWARD ANSDR 2018FA0000380Rocker · looseDURING A WALK AROUND INSPECTION THE TECHNICIAN NOTICED THAT THE ROCKER ARM ASSEMBLY ON THE TAIL ROTOR HUB ASSEMBLY WAS VERY LOOSE. FURTHER INVESTIGATION REVILED THAT THE BEARING HAD BECOME LOOSE IN THE ROCKER ARM ASSEMBLY. IN THIS APPLICATION THE BEARING IS ROSDR 2018FA0000193Quill · disconnectedAIRCRAFT EXPERIENCED A LOSS OF TAIL ROTOR CONTROL DURING FLIGHT REQUIRING THE PILOT TO CONDUCT A HOVERING AUTOROTATION THAT DAMAGED THE LANDING GEAR AND BELLY OF THE AIRCRAFT. POST INCIDENT SHOWED TAIL ROTOR CONTROLLABILITY AND CONTINUITY FROM THE PEDDLES TO SDR 2A6R20171121005Control Tube · crackedA CRACK WAS DISCOVERED PROPAGATING FROM THE FORWARD END OF THE TUBE PART OF THE CONTROL ROD, WHERE THE END IS RIVETED ON.SDR JYDR20170811215Servo · lockedTAIL ROTOR GEAR BOX & SERVO ASSY RECEIVED WITH A WRITE-UP OF UNABLE TO CHANGE PITCH OF BLADES BY HAND DURING INSPECTION.. UPON RECEIPT IN SHOP PITCH CHANGE SHAFT MOVED FREELY BY HAND. T/R G/B WAS DISASSEMBLED AND FOUND OK. T/R G/B SERVO WAS CHECKED AND FOUND BSDR M3XA2017071301Pedal · out of alignmentEXPERIENCED A PEDAL PROBLEM WHILE ON APPROACH TO LANDING. PILOT NOTICED THAT THE PEDALS SEEMED MISALIGNED FROM THEIR NORMAL POSITION. HE ELECTED TO LAND AT THE AIRPORT KROA. HE NOTED WHEN HE LOWERED THE COLLECTIVE THE NOSE MOVED TO THE RIGHT BUT IT WAS NOT SDR AC2R2017031001Rod End · damagedFOUND TAIL ROTOR PITCH CHANGE SHAFT (PCS)- INPUT CONTROL TUBE ROD END BEARING OUTER RING WAS NO LONGER SECURE IN THE ROD END. ONCE THE ROD END WAS REMOVED FROM THE PCS, THE BEARING DID NOT HAVE ANY RESISTANCE TO KEEP IT INSTALLED INTO RODEND. THE ROD END WAS SDR CA160215013Support · broken(CAN) DURING INSPECTION OF FRONT PEDAL SUPPORT IT WAS NOTED THAT BOTH UPPER TANGS OF THE LEFT PEDAL SUPPORT WERE BROKEN OFF. THERE MAY BE SOME INDICATIONS THAT A TANG CRACKED AND THEN SNAPPED ALSO BREAKING THE OTHER UPPER TANG. THE LOWER TANGS OF THE PEDAL SUPSDR QMLA2016010216001Accumulator · low pressureTHE PILOT & MEDICAL CREW WERE ENROUTE TO AN ACCIDENT SCENE WHEN THE PILOT FELT SOME FEEDBACK IN THE TAIL ROTOR PEDALS. ABORTED THE FLIGHT & PROCEEDED TO THE NEAREST AIRPORT FOR A PRECAUTIONARY LANDING. MADE AN APPROACH TO A RUNWAY TO ENSURE CONTROLLABILITY, SDR EVCA201601125Bellcrank · damagedTAIL ROTOR CONTROL BELLCRANK LOCATED UNDER TAIL ROTOR GEARBOX HAS MECHANICAL DAMAGE WHERE THE LONG TAIL ROTOR CONTROL TUBE MATES WITH THE BELLCRANK. DAMAGE EXCEEDS ALLOWABLE LIMIT OF .010".SDR CA150914004Bearing · debonded(CAN) Y9-Y10 BELLCRANK, BEARING FOUND DISBONDED FROM HOUSING DURING ROUTINE INSPECTION.SDR QMLA2015090415082Bearing · crackedDURING A0521 NT, 100 HR TAIL ROTOR INSPECTION, WAS REMOVING THE TAIL ROTOR CROSS HEAD ASSEMBLY & FOUND THE BLADE END PC LINK BEARING CRACKED WITH A CHUNK MISSING FROM THE FLANGE AREA OF THE BEARING, THE SPHERICAL SURFACE WAS INTACT. R & R PC LINK. EXCESSIVE SDR CA150824009Link · broken(CAN) DURING FLIGHT THE PILOT NOTED A BUMP AND THEN AN IMMEDIATE VIBRATION. AUTOPILOT WAS TURNED OFF AND THE ACFT WAS SLOWED DOWN BUT THE VIBRATION LEVEL DID NOT CHANGE. AS THE ACFT WAS SETTLING TO THE GROUND TO LAND THE PILOT FELT THE ACFT YAW TO THE RIGHT SDR CA150615023Spider · seized(CAN) PERFORMING 100HR INSPECTION ON ACFT. REMOVED T/R PITCH LINKS & SPIDER LINK. CHECKED SPIDER ASSEMBLY FOR FREEDOM OF MOVEMENT & PLAY ON THE TAIL ROTOR GEARBOX OUTPUT SHAFT. FOUND T/R SPIDER ASSEMBLY TO BE EXCESSIVELY TIGHT ON THE OUTPUT SHAFT. GROUNDED SDR 3UWR201503160001Pitch Link · out of toleranceTAIL ROTOR PITCH LINK HAS LESS THEN 300 HOURS TIME IN SERVICE AND THE ROLL STAKE BEARING HAS APPROX. 1/8 INCH OF PLAY. I DO NOT KNOW IF THIS IS A ON GOING PROBLEM BUT IT IS A DANGEROUS ONE.SDR CA150313012Grease · frozen(CAN) TAIL ROTOR PEDALS INCLEASINGLY STIFF DURING FLIGHT, NO MECHANICAL OBSTRUCTION FOUND. PEDAL BEARING BLOCK GREASE FREEZING DUE TO LOW OAT. POSSIBLE IMPROPER GREASE INSTALL. BLOCKS REMOVED, CLEANED, INSPECTED AND REGREASED WITH A257-1 GENERAL PURPOSE GREASDR CA150224032Bushing · damaged(CAN) TAIL ROTOR ASSY, WAS REMOVED TO FACILITATE REPLACEMENT OF PITCH HORN ASSY, PN 355A12-5102-00 X 2. UPON REMOVAL, THE ANTI-ROTATION BUSHING WAS FOUND DEFORMED AT THE TIP, PREVENTING ITS REMOVAL FROM THE PITCH HORN. A REQUEST HAS BEEN SUBMITTED WITH MFG HELSDR CA141008013Flt Controls · malfunctioned(CAN) IN PREPARATION FOR CONTINUED PRODUCTION FLIGHT TESTING, ALL WAS NORMAL. DURING FLIGHT TESTING IN THE MORNING OF THE 6TH AND DURING INITIAL FLIGHT ON THE 3RD, AND DURING THE START OF ENGINE NR 2 (THE FIRST ENGINE BEING STARTED), AN UNCOMMANDED LT PEDAL FSDR CA140903012Bearing · rough(CAN) AFTER LANDING AND DURING ENGINE WIND DOWN, A LOUD SQUEAL WAS HEARD COMING FROM THE AFT OF THE HELICOPTER. IT WAS DETERMINED THAT THE NOISE WAS EMANATING FROM THE TAIL ROTOR PITCH CONTROL BEARINGS. THE TAIL ROTOR PITCH CONTROL LINKS WERE DISCONNECTED ANSDR CA140723001Pedal · stiff(CAN) TAIL ROTOR CONTROL PEDALS STIFF IN FLIGHT, ABNORMAL FORCE REQUIRED.SDR CA140715009Solenoid · inoperative(CAN) WATER ENTRAPMENT CAUSED THE PEDAL STOP SOLENOID TO BECOME INOPERATIVE. WHEN THE LOWER WSPS PANEL WAS OPEN, WATER WAS TRAPPED IN THE AREA JUST BELOW THE PEDAL STOP SOLENOID DUE TO THE DRAIN HOLE BEING PAINTED OVER & OBSTRUCTED BY PAINT.SDR HLXR2014FA0000369Drum · crackedFOUND CRACKS ON DRUM ASSEMBLY DURING TWO YEAR INSPECTION ON FLIGHT CONTROLS. TWO POSTS HAD ONE CRACK EACH, RUNNING HALF THE MOUNT POST CIRCUMFERENCE. CRACKS MAY BE CAUSED BY THE AIRFLOW OF THE FAN PUSHING AGAINST THE ROTATING CONE ASSEMBLY WHICH IS HELD ON A
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