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 USAA2011091300014Unknown · malfunctionedON LANDING ROLLOUT, AT APPROXIMATELY 120 KTS, AIRCRAFT VEERED TO THE RIGHT. WITH FULL LEFT RUDDER, THE AIRCRAFT CONTINUED RIGHT WITH BOTH PILOTS APPLYING FULL LEFT RUDDER AND BRAKES, PROBLEM CONTINUED. BELOW 100KTS, THE TILLER WAS APPLIED SUCCESSFULLY. MAINTSDR AALA20110909MIA01Module · faultyMIA - CREW REPORTED DURING TAKEOFF EXCESSIVE RIGHT RUDDER TRIM AND EICAS MESSAGE LEFT FUEL LOW PRESSURE LIGHT ILLUMINATED. FLIGHT RETURNED MIA LANDED WITHOUT INCIDENT. AIRCRAFT REMOVED FROM SERVICE. REPLACED LEFT AND RIGHT RUDDER RATIO MODULES. SYSTEM GROUSDR NOCA08411Link Assy · defectiveAIRCRAFT FAILED RUDDER FREEPLAY CHECK AS PER EO 757-27-027 AD 2006-07-23. FOUND LOWER PCA ACTATOR LINK. REMOVED AND REPLACED LINK ASSY AND BUSHING AS PER MM 27-21-20 RIGGING AND OPS CHECK AS PER MM 27-21-00.SDR C2XA11CL202Unknown · malfunctionedORD FLT 6159 THE CREW REPORTED A RUDDER II INOP MESSAGE IN FLIGHT AND THE RUDDER I C/B WAS POPPED. THE AIRCRAFT RETURNED TO ORD AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED AND PERFORMED OPERATIONAL CHECKS AND COULD NOT DUPLICATE THE PROBLEM. THE WIRISDR C2XA11CL198Pressure Switch · faultyCLE FLT 2866 THE CREW REPORTED A RUDDER SYSTEM 1 INOP MESSAGE DURING TAXI. THE AIRCRAFT RETURNED TO THE GATE. MAINTENANCE REPLACED THE RUDDER 1 PRESSURE SWITCH. OPERATIONAL CHECKS WERE GOOD.SDR 2011FA0000570Bearing · tornDURING EVENT 1 INSPECTION RUDDER PEDAL TORQUE TUBE SUPPORT BEARING, PN 80859-002 WAS FOUND TO BE TORN FREE FROM THE FUSELAGE STRUCTURE WHERE IT ATTACHES BELOW THE CENTER INSTRUMENT PANEL.SDR FDEA201109013622Fitting · wornRUDDER LOWER SERVO CONTROL ACTUATOR ATTACHMENT LUG UPPER SURFACE HAS WEAR MARKS CAUSED BY THE ANTI ROTATION WASHER. FITTING REMOVED FROM RUDDER DUE TO WEAR OUT OF LIMITS. FITTING REPLACED IAW 51-72-10/51-40-21. DUE TO MISLIGNMENT OF FITTING, ITEM REPAIRED ISDR UALA2011082904634Pin · wornMOVEMENT OF F-O'S RUDDER PEDALS CAUSES F-O'S RUDDER PEDAL ADJUSTMENT KNOB TO MOVE CCW DIR. REPLACED THE PEDAL ADJUSTMENT CRANK HANDLE, PIN WAS WORN DOWN.SDR JIKA20110826001Control Cable · brokenON PREFLIGHT INSPECTION, THE PILOT NOTICED THERE WAS NO RESISTANCE IN THE RUDDER PEDALS WHEN MOVED FROM LT TO RT, THIS WAS CONFIRMED WHEN THE PILOT MOVED THE RUDDER PEDALS AND ANOTHER PILOT CONFIRMED THERE WAS NO RUDDER MOVEMENT. MX INSPECTED THE RUDDER CONTRSDR SIMA201123802Pcu · malfunctionedON FLIGHT 2734 THE CREW REPORTED THAT DURING CLIMBOUT RECEIVED A RUDDER OVER BOOST MESSAGE ON EICAS. THE CREW COMPILED WITH THE CHECKLIST AND NO FURTHER PROBLEMS WERE NOTED. THE CREW DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT. THE AIRCRAFT WAS REMOVESDR DXTA2011082604711Rudder Pedal · bindingWHEN AIRPLANE IS TURNED TO THE LEFT IN FLIGHT THE RUDDER SEEMS TO GET STUCK. PROBLEM HAPPENS WITH AUTOPILOT ENGAGED AND DISENGAGED. DIDN'T MATTER WHAT ALTITUDE/AIRSPEED. HAPPENED MULTIPLE TIMES. CYCLED RUDDER SEVERAL TIMES. OPS CHECKED GOOD. CHECKED PCU BSDR DXTA2011082404708Bungee · failedDURING DESCENT WITH FGC CHANNEL [A] CONTROLLING, UNCOMMANDED RUDDER INPUTS LT AND RT OCCURRED. SHORTLY AFTER, AMBER CAS "FLIGHT CONTROL FAULT" AND "RUDDER" FLIGHT CONTROL SHUTOFF LIGHT ILLUMINATED INTERMITTENTLY ABOUT 12 TIMES. AMBER CAS DID NOT REMAIN ON. SDR UALA2011082204498Rudder Pedal · lack of lubeINITIALLY CAPTAIN'S RUDDER PEDALS STUCK IN FULL DOWN POSITION. NOW DOES NOT AUTO EXTEND WITH LEVER ON SPRINGS. LUBED PER AMM, OPS CHECK'S GOOD.SDR C8GA2011000018Relief Valve · leakingWHILE EN-ROUTE, THE CREW NOTED THAT THE B-SYSTEM HYD QUANTITY WAS DECREASING AND THE LOW LIGHT ILLUMINATED. ACFT DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT. POST FLIGHT INSPECTION WAS PERFORMED, NOTING THAT THE UPPER RUDDER LOAD LIMIT RELIEF VALUE WASSDR CA110819004Cable · frayed(CAN) THE RT RUDDER CABLE WORN.SDR UALA2011081804396Servo Valve · failedCENTER RUDDER SERVO CMD FAULT NEED TO REPLACE CENTER RUDDER DAS VALVE DUE TO FAILED. REPLACED DAS CENTER SERVO VALVE.SDR 2011FA0000519Control Arm · brokenTHE PILOT REPORTED THAT THE RUDDER TRIM WAS WEAK. INVESTIGATION LED TO FINDING THE ARM ATTACH POINT ON THE RUDDER CONTROL ARM ASSY (63457-003) HAD BROKEN OFF. THE RUDDER PEDAL ASSY WAS REMOVED FROM THE ACFT AND SUBSEQUENT INSPECTION FOUND THAT THE CENTER SUPSDR UALA2011080304057Pedal · faultyF/O RUDDER PEDAL ADJUSTMENT HAVE NO TENSION. CHECKED BELOW RUDDER PEDALS. PNEU BUFFER "PUSHROD" HAS NO INTERNAL PRESSURE. REPLACED F/O RUDDER PEDAL. ADJ BUFFER ASSY.SDR UALA2011080304025Rudder · contaminatedWHILE OPERATING RUDDER OBSERVED HYD FLUID DRIPS FROM BASE OF RUDDER. OPENED VERTICAL STAB ACCESS PANEL AND CHECKED ALL THREE RUDDER ACTUATORS. FOUND SOME EVIDENCE OF SEEPAGE BUT NO ACTIVE LEAKS. CLEANED ACTUATOR COMPARTMENT AND AREA BELOW RUDDER OF SKYDROL.SDR 9JLA20110801002Unknown · malfunctionedCREW REPORTED THAT THE "RUDDER WAS STIFF AFTER COLD SOAK" TROUBLSHOOTING REALLY COULDN'T DUPLICATE DISCREPANCY, BUT THE RUDDER AFU WAS LUBED DURING A RECENT C CHECK. REMOVED THE RUDDER AFU P/N 105043-07 S/N 1156. INSTALLED A REPAIRED AFU S/N 1138. CREW REPOSDR F3LA2011080400663Feel Unit · bindingREFERENCE PILOT REPORT LOG PAGE 615630 ITEM 1, UPON TOUCHDOWN PILOT NEEDED RIGHT RUDDER TO STRAIGHTEN NOSE BUT RUDDER FELT LOCKED IN CENTERED POSITION. AFTER APPLYING MORE PRESSURE PEDAL UNLOCKED AND APPEARED TO WORK NORMALLY. REMOVED AND REPLACED ARTIFICIAL FSDR UALA2011072703831Rod End · looseON LANDING RUDDER FAILED TO RESPOND TO RUDDER PEDAL INPUTS-UNABLE TO EVEN TEST RUDDER. FOUND BOLT MISSING AT ROD END FOR MECHANICAL INPUT. INSTALLED NEW BOLT NUT WASHER PIN REF MM. RUDDER OPS CHECK OKAY. ALSO ALL MISSING HARDWARE HAS BEEN ACCOUNTED FOR.SDR UALA2011071903678Unknown · vibrationPER CREW - VIBRATION NOTICED ON TAKEOFF AND CLIMB, PASSENGERS REPORTED THE NOISE AND FIRST OFFICER FELT THE VIBRATION IN RUDDER PEDALS. NOISE DID ABATE ONCE ACFT SPEED AND ALTITUDE INCREASED. NO EICAS MESSAGES OR SYSTEM FAULTS NOTED AND NO HISTORY OF VIBRATISDR UALA2011071303532Pcu · leakingCENTER RUDDER PCU LEAKING HYD FLUID BEYOND MM LIMITS. RUDDER PCU LEAKING HYD FLUID. NEW ONE PLANESIDE, REMOVING. DDK 0835. AS A RESULT OF ACT LOCK INSTALLED, RUDDER DEFLECTED ON PCU LOCK AND DAMAGED SEAL. CENTER PCU. REMOVED CENTER PCU, ACCOMPLISHED DETSDR UALA2011070603354Lever · damagedEXCESSIVE RUDDER TRIM NEEDED (4 UNITS) TO CNTR YOKE. SUSPECT RUDDER RATIO CHANGER. RUDDER IS OUT OF RIG. FOUND YAW DAMP SUMMING LEVER WITH SHEARED RIVETS. REPLACED YAW DAMPNER LEVER.SDR 2011FA0000439Control Cable · frayedRUDDER CABLES FRAYED AT 471.8 TIS. SHOULD LAST 1000 HRS IAW MFG.SDR 2011FA0000464Torque Tube · brokenRUDDER TORQUE TUBE ASSY BROKE AT POINT WHERE BELCRANK IS ATTACHED TO TORQUE TUBE CAUSING LOSS OF STEERING CONTROL.SDR FDEA201106212355Solenoid Valve · crackedSYSTEM A QTY DECREASED DURING CLIMBOUT AT 10,000 FT. ON LOWER RUDDER POWER UNIT CONTROL, HYD SOLENOID VALVE LEAKING. REPLACED VALVE ASSY AND SEALS IAW MM 27-20-142-4. SYS "A" HYD SYS FILTERS REPLACED IAW MM 29-11-062-3, NO METAL FOUND IN SYS. R & R SYS A SDR CWQR20110617001Control Cable · wornDURING AN INSP, THE RUDDER CABLE ASSY WAS FOUND TO HAVE BEEN SAWING INTO THE RUDDER SERVO BRACKET CABLE GUARD. THIS HAS BEEN DOING THIS SINCE THE ACFT WAS MANUFACTURED. THE WORN CABLE ASSY WAS REPLACED AND THE RUDDER SERVO CABLE GUARD WAS RECLOCKED TO PROVIDESDR 2011FA0000396Shaft · wornFOUND GROOVES WORN INTO SHAFT OF THE 2 SCREWS THAT ENTER INTO THE RUDDER ACTUATOR ASSEMBLY. ACFT IS SET FOR CRUISE CONFIGURATION: DURING FLIGHT, TAIL VIBRATES CAUSING GROOVES TO WEAR INTO SHAFT OF SCREWS AT POINT WHERE SCREWS ENTER INTO ACTUATOR.SDR CA110613016Control Cable · brokenDURING INSPECTION OF CONTROL CABLES, FOUND RT RUDDER RETURN CABLE BROKEN AT SWAGED BALL TERMINAL.SDR SIMA201116001Unknown · malfunctionedON FLIGHT 2761 THE CREW REPORTED, ABORTED THE TAKEOFF ROLL DUE TO NO RUDDER CONTROL. THE FIRST OFFICER PRESSED THE QUICK DISCONNECT BUTTON AND CONTROL WAS REGAINED. THE AIRCRAFT WAS REMOVED FROM SERVICE. NO MESSAGE ON THE CENTRAL MAINTENANCE COMPUTER, THE ASDR DXTA2011060704608Actuator · leakingWITH HIGH POWER SETTING, BOTH PEDALS ARE VERY DIFFICULT TO MOVE FROM BOTH COPILOT AND PILOT SIDE. SUSPECT RUDDER BIAS IS PRESSURIZING BOTH SIDES SIMULTANEOUSLY. RUDDER BIAS CHECKED OK ON GROUND. REMOVED RUDDER BIAS ACTUATOR AND ACTUATOR MOUNT. INSTALLED ACTUSDR AALA20110606JFK01Module · faultedJFK - CREW REPORTED EICAS MESSAGE FOR RUDDER RATIO WITH LIGHT AND AILERON LOCKOUT MESSAGE WITH LIGHT. EMERGENCY DECLARED FLIGHT RETURNED JFK LANDED WITHOUT INCIDENT. AIRCRAFT REMOVED FROM SERVICE. REPLACED BOTH SAMS M525 AND M524. ALSO REPLACED LEFT AIR DASDR MASA2011060602946Warning System · false activationRUDDER LIM FAULT ON DESCENT. RESET SPOST.SDR UALA2011060202695Ace · malfunctionedFLIGHT CONTROL SYS ANY CONDITION OF THE FLIGHT CONTROL SYSTEM OR IT'S SYSTEM INTERFACES WHICH WOULD PREVENT DISPATCH. FLIGHT CONTROLS SYSTEM BELOW MINIMUM DISPATCH REQUIREMENTS, STATUS MSG-2710302 LATCHED TA MODE. REPLACED ACE L2 PER MM. ACE TEST OK. PFC SSDR UALA2011053102669Servo · vibrationAIRFRAME VIBRATION BEGAN FL220 A-P DISC SET TRIM MANUALLY VIBRATION STOPPED. REQUESTED FLT CREW TO COMPLETE VIBRATION SURVEY. PLEASE TROUBLESHOOT ACFT USING TSM05-50-00-201. POSITIVE FIX REQUIRED BEFORE NEXT FLIGHT. REPLACED ALL RUDDER SERVO ROD ENDS.SDR AALA20110531MIA01Solenoid · defectiveMIA - CREW REPORTED RUDDER RATION AND EICAS MESSAGE. EMERGENCY DECLARED FLIGHT RETURNED MIA LANDED WITHOUT INCIDENT. AIRCRAFT REMOVED FROM SERVICE. REPLACED RUDDER RATIO SOLENOID. SYSTEM GROUND CHECK NORMAL OPERATION.SDR CA110531005Tube · wornPRIOR TO START-UP THE PILOT NOTICED THAT HE WASN`T ABLE TO ADJUST THE RUDDER PEDALS, AFTER A VISUAL INSPECTION THE AME NOTICED THAT THE LT PILOT SIDE RUDDER PEDALS "S" TUBE HAD THE RUDDER CABLE PROTRUDING FROM ONE OF THE BEND. BOTH PILOT SIDE RUDDER PEDALS WESDR UALA2011052702584Rudder · warning lightRUDDER RATIO LIGHT ILLUMINATED, FLIGHT DIVERTED. EICAS MESSAGE RUDDER RATIO DISPLAYED. LIGHT EICAS CAME ON IMMEDIATELY AFTER TAKEOFF. RE-ALIGNED ALL IRU'S. BITE CHECKED YAW DAMP MODULES OK. RUDDER RATIO CHARGE MODULES IN NORM. PERFORMED FIM 27-21-709-004 SDR FDEA201105261995Actuator · malfunctionedAIRFRAME SHAKES AT HIGHER SPEEDS UNLESS PRESSURE APPLIED TO RUDDER, APPLYING A CONSTANT LOAD TO IT. IN 5 PREVIOUS OBSERVATIONS OF IDENTICAL SYMPTOMS, THE ISSUE IN EACH CASE TURNED OUT TO BE WORN RUDDER ACTUATORS. INSTALLED LOWER RUDDER ACTUATOR. TORQUED ANSDR C2XA11TY064Pressure Switch · bypassingTYS - A/C EN ROUTE FROM EWR TO TYS WHEN CREW GOT A MESSAGE OF RUDDER SYSTEM 1 AND 2 INOP IN FLIGHT. A/C LANDED SAFELY AND MAINTENANCE REMOVED AND REPLACED SYSTEM 1 AND SYSTEM 2 PRESSURE SWITCHES IAW AMM 27-23-001 AND OPS CHECKED GOOD. A/C WAS RELEASED TO SESDR HALA2011052500228Yaw Damper · inoperativeETOPS SIGNIFICANT SYS - AFTER LANDING, EICAS MSG L YAW DAMPER, L YAW DAMPER INOPERATIVE ON OVERHEAD. RERACKED LT YAW DAMPER MODULE. GROUND OPS CHECKED OK IAW AMM 22-21-00.SDR SIMA201113803Yaw Damper · failedFLT 4612, CREW REPORTED DURING CRUISE, EXPERIENCED UNCOMMANDED RUDDER MOVEMENTS MULTIPLE TIMES, ALL PHASES OF FLT. DISPLACED INCLINOMETER HALF TRAVEL AT 310 KTS. HAPPENED DURING ALL ALTITUDES WITH AUTO PILOT ON OR OFF. ACFT LANDED WITHOUT INCIDENT. WAS RSDR HALA2011051500195Warning Light · false activationETOPS SIGNIFICANT SYS - RUDDER RATIO LIGHT CAME ON IN FLT EICAS MSG RUDDER RATIO DISPLAYED ON DOWNWIND FOR LANDING APPROX 6000' AND 190KTS. PERFORMED AMM 27-21-715-001-001. OPS TEST RUDDER AND RUDDER TRIM CONTROL TEST OK. NO FAULT NOTED.SDR DXTA2011051604582Rudder · bindingRUDDER PEDALS ARE BINDING ON TAKEOFF FROM RT SEAT AND BINDING FROM LT SEAT ON LANDING AFTER PASSING THROUGH NEUTRAL POSITION ON CROSSWIND LANDING. ALL RUDDER BIAS TESTS WERE GOOD PRIOR TO TAKEOFF. VISUALLY INSPECTED RUDDER CABLE RUNS. CHECKED PRIMARY, SECOSDR UALA2011051202359Seal Plate · damagedHYDRAULIC LEAK AT RUDDER. FOUND RUDDER RATIO CHANGER SERVO VALVE SEAL PLATE DAMAGED. REPLACED REF MM. ACP LEAK CHECK.SDR UALA2011050902274Indicator · faultyEXCESSIVE RUDDER TRIM. ACCOMPLISHED UP TO BLOCK 7 RUDDER RIG HIGH AND LOW SPEED GOOD. NEED TO CONTINUE BLOCK 8 PG 116 CHECK THERMAL COMPENSATION. BOTTOM CLEARANCE .080 TOP CLEARANCE .100. WILL NEED TO BE ADJUSTED TO PROPER CLEARANCES. THERMAL COMP LINKAGESDR NX4R20110503001Rudder Pedal · crackedDURING PREFLIGHT, THE FLIGHT CREW NOTICED THAT THE RUDDER PEDALS WERE NO LONGER SYMMETRICAL COMPARED TO EACH OTHER. A MX TECH INSPECTED THE PILOT'S RT PEDAL (PN-DA4-2723-36-00) AND NOTICED THAT THE VERTICAL WEB THAT CONNECTS THE PEDAL TO THE BRAKE MASTER CYLISDR UALA2011050202117Rudder · bindingCREW REPORTED BOTH RUDDER PEDAL HEAVY AND BINDING. FOUND NO BINDING WITH HYD PRESS ON AND OFF. ACCOMPLISHED RUDDER PEDAL FORCE CHECK PER MM. FOUND ALL FORCES WITHIN LIMITS. AIRCRAFT TO BE TEST FLOWN FOR FURTHER EVALUATION.
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