JASC 2720
Service difficulty reports · 3,131
Reports filed under 2720 · Rudder 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 = '2720' 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 = '2720' 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 DALA2018011100215Control Cable · abnormalRUDDER CONTROL CABLES NR 1 AND 2 WERE FOUND UN-SAFETIES. RIGGING WAS VERIFIED.SDR GLBA2018011100699Rudder Pedal · shearedPILOTS REPORTED THAT WHILE TAXING OFF THE RUNWAY, WHEN RIGHT RUDDER PRESSURE WAS APPLIED, THE CAPTAIN'S RIGHT RUDDER PEDAL ASSEMBLY SHEARED OFF, FLOPS LOOSE ON THE ASSEMBLY. R & R THE CAPTAIN'S RT RUDDER PEDAL AND ARM ASSEMBLY IAW MM 27-20-03-201. OPS CHECKSDR DALA2018011100190Control Quadrant · crackedDURING REMOVAL OF CAPT'S RUDDER PEDAL BRACKET, FOUND RUDDER PEDAL ADJUSTMENT QUADRANT CRACKED. RMVD AND REPL CAPT'S RUDDER PEDAL ADJUSTMENT QUADRANT PER AMM 27-20(134146). C/W RII INSTALL OF RUDDER PEDAL ADJ QUADRANT PER AMM 27-20.SDR DALA2018011100189Bracket · crackedWHILE PERFORMING HFEC INSPECTION OF CAPTAINS RUDDER PEDAL BRACKET PER EM2720-01088-0901, FOUND CRACK IN AFT OUTBOARD WEB RADIUS. MARKED. CAPTAINS RUDDER PEDAL BRACKET REPLACED IAW AMDS W/C 2720-01088-0701.SDR FDEA201712243442Cable · frozenENROUTE, RUDDER PEDALS AND TRIM WHEEL BECAME FROZEN/LOCKED. UNUSABLE UNTIL TAT REACHED 10 DEGREES. OPENED PANEL 364AR AND REMOVED ABOUT 1 INCH OF POOLED WATER INSIDE COMPARTMENT. CLEANED AND LUBRICATED BOTH TRIM AND RUDDER CABLES INSIDE COMPARTMENT IAW AMM SDR HYIA20171227001Torque Tube · crackedDURING A SCHEDULED INSPECTION, THE RT RUDDER PEDAL TORQUE TUBE WAS CRACKED AND FAILED AT THE WELD INTERSECTION OF THE RT PEDAL 'POST'. THIS FINDING IS A RESULT OF A RECENTLY IMPLEMENTED MAGNIFIED VISUAL INSPECTION OF THESE WELDS AT EACH 180 FLIGHT HOURS OF OPSDR 2017FA0000652Torque Tube · looseCOPILOT RUDDER PEDAL TORQUE TUBE BASE SHOWS MOVEMENT WHEN FORCE IS APPLIED TO THE RUDDER PEDALS ON THE COPILOT SIDE. AN ABNORMAL SOUND IS HEARD AND THE MOUNTING HARDWARE APPEARS TO BE LOOSE.SDR A6WA201745460Rudder · unknown9898 UNCOMMANDED YAW IN CLIMB RUDDER TRIMMED RIGHT MANUALLY CENTERED THEN RUDDER TRIMMED LEFT MANUALLY RE-CENTERED THEN RUDDER WAS UNCONTROLLABLE C/W QRH DISCONNECTED RUDDER A/P OFF ABLE TO CONTROL A/C. NUMEROUS ERRORS ON FCC 1 IN FCC DIAGNOSTICS, R/R FCCSDR AALA201711269012Pcu · failedAIRCRAFT WAS GROUNDED. ON FINAL APPROACH AT APPROX. 500 THE RUDDER KICKED TO THE RIGHT CAUSING NOSE OF AIRCRAFT TO SWING RAPIDLY WITHOUT PILOT RUDDER PEDAL INPUT. YAW DAMPER THEN DISENGAGED WITH AN AMBER CAUTION LIGHT. REMOVED AND REPLACED PRIMARY RUDDER POWSDR HYIA20171117001Torque Tube · failedWHILE IN CRUISE, THE RT RUDDER PEDAL WENT TO THE FLOOR, FULL FORWARD. THE PILOT DID NOT HAVE ANY RUDDER AUTHORITY, BUT THE AIRCRAFT REMAINED IN STRAIGHT AND LEVEL FLIGHT. DIVERTED AND LANDED SAFELY WITH NO ISSUES. THE AIRCRAFT WAS UNABLE TO TAXI FROM THE RUSDR B4VR2017110800001Bracket · brokenRUDDER TRIM CONTROL BRACKET ATTACHED TO RUDDER PEDALS HAD ARM BROKEN OFF OF IT. WAS REPORTED BY FLIGHT CREW THAT THE RUDDER TRIM HAD NO EFFECT ON THE CONTROL SYSTEM. VISUAL INSPECTION FOUND THAT THE ARM WAS BROKEN OFF. IT APPEARS TO HAVE A SMALL AREA THAT HSDR 2PL6D005GNQ3Unknown · unknownDURING LEVEL FLIGHT AT 10,000 FEET, AND SPEED OF APPROXIMATELY 180 KIAS, THE "CONTROL LOCK ON" CAS MESSAGE
ILLUMINATED ON THE PFD'S. THE CONTROL LOCK LEVER WAS CHECKED TO BE IN THE UNLOCKED DETENT . AFTER MOVING THE
LEVER SLIGHTLY, AND FIRMLY RETURNING IT TOSDR HALA2017101700253Warning Message · false activationRUDDER RATIO EICAS AND OVERHEAD DISCRETE ANNUNCIATOR ILLUMINATED DURING TAKE OFF. NO OTHER INDICATIONS NOTED. PERFORMED A BITE IAW FIM 27-09/814, NO FAULTS NOTED, OK FOR CONTINUED SERVICE.SDR MASA2017091312625Not Reported · malfunctionedUNCOMMANDED RUDDER INPUT (EMER DECLARED). MX IS TROUBLESHOOTING.SDR CALA2017090102975Fitting · debondedRIGHT LOWER AFT HOIST POINT DISBONDED AND LOOSE. REPAIRED THE RUDDER IAW TD 80340786/005 A AND SRM 51-77-11.SDR CA190515011Pulley · worn(CAN) DURING THE FIRST 100HR/ANNUAL INSPECTION OF THE AIRCRAFT WE DISCOVERED THAT THE REAR RUDDER PULLEYS ARE SHOWING ABNORMAL SIGNS OF WEAR. THE LH AND RH PULLEYS (P/N: MS24566-3B) MOUNTED ON THE REAR BULKHEAD (PART OF ASSEMBLIES D67-2725-11(12)-00 FOR THE RUSDR HALA2017072100203Actuator · inoperativeRUDDER TRIM WILL NOT MOVE. REMOVED & REPLACED RUDDER TRIM ACTUATOR IAW AMM 27-21-11. OPS & SECURITY CHECKED GOOD.SDR MASA2017070912452Dampener · malfunctionedUNCOMMANDED RIGHT RUDDER DEFLECTION. R & R THE YAW DAMPENER CONTROL PANELSDR QXEA2017071000459Pcu · malfunctionedNR 1 RUDDER HYD CAUTION ILLUMINATED DURING CRUISE, PUSH OFF LIGHT DID NOT ILLUMINATE. NO OTHER ABNORMALITIES. REMOVED FROM SERVICE. REPLACEMENT OF LOWER RUDDER PCU. OPS CHECKED GOOD. AIRCRAFT RETURNED TO SERVICE.SDR DALA2017062004876Motor · wornUPPER AND LOWER PULLEY FOR RUDDER BELOW YAW DAMPENER MOTOR WORN.SDR SCNA20170616090Shaft · crackedFORWARD NOSE AREA, FO'S SIDE, RUDDER JACK SHAFT, CROSS ROD, UPPER FLANGE CRACKED. REPLACED JACKSHAFT ASSEMBLY. ADJUSTMENT AND FUNCTIONAL TESTED GOOD.SDR DALA2017061204652Crank Assy · corrodedCORROSIN ON RUDDER THROUGH LIMITER CRANK BS 1485 11 HRS POSITION IN THE AFT ACCESSORY COMPARTMENT. RUDDER THROUGH LIMITER CRANK WAS REPLACED.SDR S9BA201706050002Actuator · bindingON CLIMB GUST LOCK LIGHT CAME ON, AFTER REACHING CRUISE THE CREW BECAME AWARE THAT THERE WAS NO RESPONSE TO THE RUDDER INPUT.SDR DALA2017052104053Shutoff Valve · leakingDURING FLIGHT, CREW REPORTED RIGHT HYDRAULIC FLUID QUANTITY LOSS AND ACCOMPLISHED QRH PROCEDURE SECURING RIGHT HYDRAULIC SYSTEM PUMPS. ON APPROACH, ATTEMPTED TO RE-PRESSURIZE RIGHT HYDRAULIC SYSTEM PER QRH AND THE SYSTEM FAILED TO PRESSURIZE. ACCOMPLISHED ALTESDR AALA201706029034Bearing · wornEXCESSIVE PLAY ON RUDDER HINGE ARM NR 4 BEARING. REPLACED HINGE ARM IAW AMM 55-36-41, AND SRM 51-44-11.SDR AALA201706029026Bearing · wornAEXCESSIVE PLAY ON VERTICAL STABILIZER HINGE ARM NR 2 BEARING. REPLACED HINGE ARM IAW SRM 51-40-00.SDR O2GA2017050285701Trim System · frozenRUDDER TRIM FROZE DURING INITIAL CLIMB OUT. AT LOWER ALTITUDES RUDDER TRIM FUNCTIONED NORMAL. MAINTENANCE PERFORMED THE REQUIREMENTS OF NTO 940-2017-00253 & 940-2017-00250. A SUCCESSFUL OPERATIONAL CHECK FLIGHT WAS PERFORMED. AIRCRAFT WAS RETURNED TO SERVICE.SDR O2GA2017050286901Rudder · frozenRUDDER TRIM FROZE IN FLIGHT AND FREED UP ON DESCENT TO WARMER AIR. MAINTENANCE PERFORMED THE REQUIREMENTS OF NTO LETTER FOR RUDDER AND PITCH TRIM ACTUATORS. A SUCCESSFUL OPERATIONAL CHECK FLIGHT WAS PERFORMED. AIRCRAFT WAS RETURNED TO SERVICE.SDR EPUA20170424001Bolt · strippedPILOT RIGHT RUDDER PEDAL SOFT. MAINTENANCE INSPECTED AIRCRAFT AND DETERMINED THAT THE AFT BOLT CAPTURING THE INBOARD RUDDER BAR BEARING BLOCK HAD BACKED OUT ALLOWING THE BEARING BLOCK TO SPREAD OPEN WHEN PRESSURE WAS APPLIED. THE BOLT WAS INSPECTED AND THE TSDR CVGA20170427001Torque Tube · crackedRUDDER TORQUE TUBE IS CRACKED AROUND THE WELD POINT OF THE BOTTOM RIB.SDR A8ZR20170414001Bearing · migratedDURING PRE-FLIGHT CHECK, THE RUDDER TRAVEL DID NOT TOUCH FULL CONTROL BOX ON LOWER ECAM PAGE AND THE LAST 1/10 OF PEDAL TRAVEL WAS HARD. TROUBLESHOOTING AND INSPECTION FOUND THE LOWER RUDDER BELLCRANK BEARING MIGRATED FROM THE LEFT HAND LUG.SDR QXEA2017040300209Unknown · malfunctionedABNORMAL RESISTANCE FELT WITH RUDDER PEDAL INPUT TO RIGHT SIDE REQUIRING MORE FORCE THAN NORMAL. WAS ABLE TO OVERCOME RESISTANCE. RUDDER CONTROL WAS AVAILABLE FOR LANDING. SIGNIFICANTLY GREATER PRESSURE ON CLIMB OUT THAN ON APPROACH. NEGLIGIBLE DIFFERENCE ON SDR DALA2017040302704Rod End · corrodedDURING SEVERE TURBULENCE INSPECTION FOUND RUDDER CONTROL POSITION ROD ENDS CORRODED / DAMAGE. REPLACED BUS ROD ASSY PER AMM 27-21 - VERIFIED INSTALLATION RII COMPLETE.SDR SIMA20170329001Pressure Switch · failedRUDDER SYSTEM 1 -2 INOP MSG ON EICAS AUTOPILOT AND YAW DAMPER KICKED OFF ABOUT THE SAME TIME. PERFORMED FIM TASK, 27-22-00-810-804-A AND REMOVED AND REPLACED THE RUDDER SYSTEM NR 2 PRESSURE SWITCH, IAW AMM 27-23-04, OPS CHECK GOOD. PERFORMED FUNCTIONAL TEST OSDR EBVR20170327001Torque Tube · corrodedRUDDER TORQUE TUBE AREA IS RUSTED, REMOVED THE RUDDER TORQUE TUBE AND INSTALLED NEW TORQUE TUBE. CORROSION WAS FOUND ON THE LOWER RUDDER RIB WHILE REPLACING THE TORQUE TUBE. REPAIRED THE LOWER RUDDER TORQUE TUBE RIB IAW ERO-889729, REV IR.SDR O2GA2017033186201Trim System · frozenRUDDER TRIM FROZE IN FLIGHT "0" POSITION. UNABLE TO USE RUDDER TRIM. ONCE DESCENDED TO LOWER ALTITUDE THE RUDDER TRIM WORKED FINE. AIRCRAFT IS CURRENTLY STILL IN SCHEDULED MAINTENANCE AT THE SERVICE CENTER. SDR SUPPLEMENT TO FOLLOW.SDR DALA2017032702435Mechanism · corrodedAFT ACCESSORY COMPARTMENT, CORROSION ON BELLCRANK AT RUDDER THROW-LIMITER MECHANISM. BELLCRANK AT RUDDER THROW-LIMITER MECHANISM WAS REPLACED AND INSTALLED PER RII AMDS 2720-2325 STEP NR 6 AND MUST BE ADJUSTED PER RII AMDS 2720-2325 STEP NR 7.SDR 29GA2017032300001Rudder · bindingON LANDING, RUDDER JAMMED ON CAPTAIN SIDE. I HAD NO MOVEMENT ON THE RUDDER PEDDLES LEFT OR RIGHT , THE COPIOT WAS ABEL TO ASSIST & THE ACFT SAFTLEY STOPPED TAI IS NORMAL WITH EXCEPTION OF HAVING TO PUSH REALLY HARD ON THE BRAKES TO STOP ACFT. PERFORMED INSPSDR O2GA2017032486501Rudder · bindingON REACHING CRUISING ALTITUDE OF 18,000 FT. ATTEMPTED TO ADJUST THE RUDDER TRIM AND NOTICED IT WAS STIFF BUT OPERATIONAL. ON THE GROUND TRIM OPERATED NORMAL. MAINTENANCE COMPLIED WITH RUDDER TRIM NTO 940-2016-01658. NO DEFECTS NOTED. OPERATIONAL CHECK FLIGHT PSDR UIEA2017030800310Cover · crackedON FLIGHT CONTROL CHECK PRIOR TO TAXI, EXPERIENCED STICKING, SNAPPING, INAPPROPRIATE RIGHT RUDDER RETURN. CONDITION SEEMED TO AMELIORATE WITH REPETITION BUT DID NOT CORRECT ITSELF. INITIAL INSPECTION FOUND THE RUDDER PEDAL COVER ASSEMBLY WAS CRACKED, THIS CAUSSDR UOIA20170803Rudder · inoperativeDURING FLIGHT RUDDERS STOPPED RESPONDING.SDR QXEA2017022700076Rudder · bindingAFTER ENGINE START, ATTEMPTED RUDDER CONTROL CHECK, AND FOUND RUDDER PEDALS/CONTROL JAMMED ON BOTH SIDES. NO MESSAGES OR CAUTIONS NOTED. RUDDER DEFLECTION ON PFD SHOWS 3/4 DEFLECTION. HYD QUANTITIES INDICATE NORMAL. PERFORMED OPS TEST OF RUD CONT SYSTEM PER AMSDR 2017F00051Bracket · corrodedRUDDER TORQUE TUBE BRACKET CORRODED.SDR HALA2017021300032Charger · no testRUDDER RATIO EICAS CAUTION MESSAGE AT TOUCHDOWN. PERFORMED RUDDER RATIO CHANGER SYSTEM TEST IAW AMM 27-21-00-715-001-001. LVDT & TEST FAIL FAULT BALLS PRESENT ON RIGHT RRCM. IAW FIM 27-09-00 FAULT TREE 814, BLOCKS 1, 51, 51A. REPLACED THE RRCM LVDT IAW SDR ASOA201702123007Control Unit · malfunctionedTHE CREW REPORTED A RUDDER OVERBOOST MESSAGE AFTER TAKEOFF. THE AIRCRAFT RETURNED AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE INSPECTED AND REPLACED THE RUDDER POWER CONTROL UNIT. OPERATIONAL CHECKS WERE GOOD.SDR 2017FA0000056Attach Fitting · brokenWHEN RUDDER PEDAL WAS DEPRESSED PILOT NOTED IT DID NOT FEEL RIGHT. UPON INVESTIGATION DISCOVERED THAT THE OUTBOARD, RIGHT RUDDER PEDAL ATTACHMENT TAB HAD BROKEN OFF OF THE FUSELAGE. FURTHER INVESTIGATION REVEALED NO PENETRATION OF THE WELD IN THE BASE METAL OFSDR EVGR201701170001Torque Tube · brokenACFT HAS A HISTORY OF TAIL WHEEL SHIMMY. TROUBLESHOOTING INSPECTION FOUNR THE PILOT'S PEDALS WERE STAGGERED AND THE PILOT’S LT PEDAL HAD SLIGHT FORE AND AFT MOVEMENT WITH THE RT PEDAL HELD STATIONARY. THE TWO BOLTS THAT CONNECT THE PILOT’S RUDDER TORQUE TUBE TSDR VNAA2017011500019Transmitter · faultyRUDDER INDICATION NOT SHOWING CENTERED. REMOVED AND REPLACED RUDDER POSITION TRANSMITTER.SDR 5TTY201611280001Actuator · vibrationDURING CLIMB, VIBRATION WAS FELT FROM THE AIRCRAFT REAR AREA AT SPEED BETWEEN 250KTS TO 300KTS CONSEQUENTLY, RETURNED DEPARTURE. AFTER AN UNEVENTFUL LANDING, A FAULT ANALYSIS WAS PERFORMED PER TSM 05-50-00-810-801-A AND FOUND THE RUDDER GREEN HYD SYSTEM SERVSDR QMLA2016112616135Fastener · missingPILOT BEGAN EXPLAINING THE PROBLEM HE ENCOUNTERED. REMOVING THE PANELS FOR FURTHER INSPECTION OF THE PEDAL ASSEMBLIES. THE PILOT AND MYSELF NOTICED THE CLEAR CIRCUIT BREAKER COVER WASN'T SECURED IN PLACE AND WAS INTERFERING WITH THE PEDAL TRAVEL. IT WAS DETERM
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