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 DXTA2009051103643Valve · failedDURING STATIC T/O POWER APPLICATION AT APPROX 90 PERCENT N1, RT RUDDER MOVED FWD UNCOMMANDED, THEN RUDDER BIAS LIGHT ILLUMINATED. INSPECTED RUDDER BIAS PLUMBING IN TAILCONE, NO DEFECTS NOTED. INSPECTED RUDDER BIAS ACTUATOR. NO DEFECTS NOTED. C/W GROUND RUN, CSDR RAIA2009050800004Warning System · malfunctionedPIT - CREW ABORTED TAKEOFF AT 60 KIAS DUE TO RUDDER SYSTEM NR 1 INOP MESSAGE ON THE EICAS. MAINTENANCE RESET THE RUDDER SYSTEM AND PERFORMED AN OPERATIONAL CHECK OF THE SYSTEM IAW AMM PROCEDURES. NO DEFECTS NOTED.SDR NOCA02709Pca · failedRUDDERS LOCKED ON LANDING. TILLER NOSE WHEEL STEERING OK. ACCOMPLISHED ON PL 765-0905-03, PERFORMED FIM TASK 27-21-00 FIG 107. REMOVED ACCESS PANEL 324BL, 324EL, 324GL, 324JL, 324LL, PERFORMED VISUAL INSPECTION OF FEEL CENTERING AND TRIM MECHANISM, ALSO ALL SDR CA090601007Control Cable · frayed(CAN) CABLE FRAYED AT PULLEY STA 26.SDR CA090601006Control Cable · frayed(CAN) RUDDER CABLE FRAYED AT PULLEY STA 76.SDR 2009F00034Torque Tube · corrodedWHILE COMPLYING WITH AD 2003-24-07, INSPECTION OF RUDDER TORQUE TUBE, FOUND EXTENSIVE CORROSION INSIDE OF TUBE. NEW MFG KIT TO REPAIR TUBE WAS ORDERED. RUDDER RIBS WHERE NOT AFFECTED.SDR CA090506013Pin · sheared(CAN) DURING ROUTINE INSP IT WAS NOTED THAT THE RUDDER GUST LOCK WAS INOPERATIVE. THE GUST LOCK PIN WAS FOUND SHEARED.SDR DXTA2009043003626Motor · malfunctionedAUTOPILOT ENGAGED THE TRIM CLACKER BEGAN TO RUN AND DID NOT STOP. WITH AUTOPILOT OFF, PRIMARY TRIM FAILED WITH NO CAS MESSAGE. CLACKER RUNS CONTINOUS IN FGC A OR B. REMOVED PRIMARY TRIM MOTOR ASSEMBLY AND INSTALLED A NEW MOTOR ASSEMBLY. OPERATIONAL CHECKED GOSDR P5CA200904290195Grommet · loosePRE TAXI RUDDER CHECK UNSATISFACTORY. FOUND CABLE GROMMET LOOSE AND STICKING ON PULLEY. GROMMET RESECURED AND OP'S CHECKED OK IAW AMM 27-55-00 AND AMM 20-11-07-074-016.SDR CA090601008Control Cable · frayed(CAN) CABLE FRAYED AT PULLEY STA 76.SDR DXTA2009042703619Switch · malfunctionedIN FLIGHT AT FL430 AMBER "RUD STBY SYS FAIL" ILLUMINATED. RESET WAS UNSUCCESSFUL. REMOVED AND REPLACED RUDDER STANDBY SWITCH IAW MM 29-20-05. SYSTEM OPS CHECK GOOD.SDR CA090416001Switch · seized(CAN) ON DESCENT, THE ACFT FELT AS THOUGH IT WERE SLIDING SIDEWAYS. CREW CONFIRMED NO RUDDER TRIM. MANUAL TRIM WAS USED. ACFT LANDED AT DESTINATION AIRPORT UNEVENTFULLY. MX INVESTIGATION DETERMINED THE RUDDER TRIM SWITCH WAS JAMMED IN THE FULL LT POSITION. SDR CA090402008Control Cable · frayed(CAN) CABLE FRAYED AT PULLEY LOCATED AT STN 49.SDR DXTA2009040303577Rudder · jammedRUDDER JAMMED AS WE TOOK THE RUNWAY FOR DEPARTURE. ROLL AND PITCH AXIS WERE FREE. ACCOMP RUDDER BIAS, OPS CHECKS IAW AFM 3-175 & OPS MANUAL 2-49, OPS CHECKS GOOD. VERIFIED YAW DAMPER OPS BY ACCOMP AUTOPILOT SERVO DRIVE ADJ/TEST FOR YAW DAMPER ONLY IAW AMM 22-SDR UALA2009032700906Control Cable · out of rigFOUND RUDDER CABLES OUT OF RIG. WITH RUDDER TRIM ZERO AND RIG PINS IN AFT CABLE QUADRANT AND MIXER OF FEEL AND CENTERING UNIT FREE FIT CANNOT INSERT RIG PIN IN FWD CABLE QUADRANT-CABLE TENSION REGULATOR. STARTED CABLE ADJUSTMENT. CABLE THAT NEEDS TO BE SHORSDR DXTA2009032703565Angle · bentON TAKEOFF ROLL, THE RUDDER PEDALS FELT VERY STIFF. AFTER TAKEOFF WITH THE YAW DAMPER OFF, IT WAS VERY DIFFICULT TO DEPRESS THE RT RUDDER. ON FINAL APPROACH WITH THE YAW DAMPER OFF, THE RUDDER PEDALS FELT LIKE THEY WERE RUBBING SOMETHING WHEN DEPRESSED. FOUNDSDR QXEA2009032500204Trim System · malfunctionedSJC - DURING TAKEOFF FROM SJC, RUDDER TRIM WENT FROM NEUTRAL TO FULL RIGHT. RUDDER TRIM COULD BE OVER POWERED WITH TRIM KNOB, BUT WOULD RETURN TO FULL RIGHT INDICATION WHEN TRIM KNOB WAS RELEASED. RE-SET RUDDER TRIM CIRCUIT BREAKERS & C/W OPERATIONAL TEST OSDR A6WA200940156Control Panel · malfunctionedON CLIMBOUT, AFTER INITIAL LT TURN, RUDDER (TRIM) RAN FULL LEFT DEFLECTION UNCOMMANDED. ABLE TO OVER POWER WITH USE OF RUDDER PEDAL. AUTO-PILOT WAS NOT ENGAGED. DECLARED EMERGENCY LANDING IN IAD. REMOVED AND REPLACED TRIM CONTROL PANEL AND RUDDER TRIM ACTUSDR CA090305004Limiter · faulty(CAN) MX CREW HAD AN ISSUE WITH THE RUDDER LIMITER UNIT. THEY FOUND THE UNIT TO HAVE 3 BURNED TRANSISTORS ON THE CIRCUIT BOARD. P/N OF THE RUDDER LIMITER UNIT IS (9121836-10-4). THE FAULTY UNIT HAD A STICKER STAMPED WITH THE DATE,1988 ON IT. THE ACTUAL TIME INSDR 2009FA0000131Torque Tube · corrodedPREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN THE SUPPLEMENTAL INSP DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. FOUND RUDDER TORQUE TUBE RUSTED DURING INSPECTION OF SUPPLEMENTAL INSPECTION 27-20-04. REPLACED TORQUE TUBE PN 5833011-9.SDR 2009FA0000130Torque Tube · corrodedPREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN THE SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. FOUND RUDDER TORQUE TUBE RUSTED DURING INSPECTION OF SUPPLEMENTAL INSPECTION 27-20-04. REPLACED TORQUE TUBE PN 583301SDR 2009FA0000129Torque Tube · corrodedPREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN THE SUPPLEMENTAL INSP DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. FOUND RUDDER TORQUE TUBE RUSTED DURING INSP OF SUPPLEMENTAL INSP 27-20-04. REPLACED TORQUE TUBE PN 5833011-9.SDR 2009FA0000127Torque Tube · corrodedPREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN THE SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. FOUND RUDDER TORQUE TUBE RUSTED DURING INSPECTION OF SUPPLEMENTAL INSPECTION 27-20-04. REPLACED TORQUE TUBE PN 583301SDR 2009FA0000126Torque Tube · corrodedPREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN THE SUPPLEMENTAL INSP DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. FOUND RUDDER TORQUE TUBE RUSTED DURING INSP OF SUPPLEMENTAL INSP 27-20-04. REPLACED TORQUE TUBE PN 5833011-9.SDR 2009FA0000125Torque Tube · corrodedPREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN THE SUPPLEMENTAL INSP DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. FOUND RUDDER TORQUE TUBE RUSTED DURING INSPECTION OF SUPPLEMENTAL INSPECTION 27-20-04. REPLACED TORQUE TUBE PN 5833011-9.SDR DXTA2009022003517Yaw Damper · failedYAW DAMPER FAIL UPPER A-B ANNUNCIATOR ILLUMINATED IN FLIGHT, UPPER RUDDER IS HARD LEFT.SDR CA090219011Bellcrank · cracked(CAN) MX INS PHASE 5, VISUAL INSP OF RUDDER, FOUND PROBLEM WITH RUDDER BELLCRANK. NOTICED PAINT THAT WAS ROUGH LOOKING AND AROUND THE WELD OF THE LOWER WELDED ON PLATE. THE PAINT WAS CRACKED, CORROSION WAS EVIDENT THROUGH THE PAINT. NDT WAS REQUESTED TO CHESDR CA090312001Spring · disconnected(CAN) ON FEB 13/2009 AT 14927.1 TAT, ACFT WAS REPORTED BY FLIGHT CREW TO HAVE AN EXCEPTIONALLY LOOSE RUDDER RETURN SPRING (LT SIDE). MX INVESTIGATION FOUND THE SPRING HAD BECOME DISCONNECTED. A NEW SPRING WAS INSTALLED AND RUDDER CONTROL SYS WAS FOUND TO BE SESDR QXEA2009021700126Feel Unit · malfunctionedRNO - WHEN PULLING POWER TOWARDS IDLE ON DESCENT AND ADDING THE REQUIRED LEFT RUDDER AT ABOUT 1-1 1/2 INCH TRAVEL THERE IS AN INCREASE IN PEDAL RESISTANCE FOR APPROXIMATELY THE SAME DISTANCE AND THEN AN ABRUPT RELEASE IN PRESSURE REQUIRED FOLLOWED BY NORMAL TRSDR 2009FA0000124Torque Tube · corrodedPREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN THE SUPPLEMENTAL INSP DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. FOUND RUDDER TORQUE TUBE RUSTED DURING INSPECTION OF SUPPLEMENTAL INSP 27-20-04. REPLACED TORQUE TUBE PN 5833011-9.SDR CA090309003Bolt · wrong part(CAN) ACFT WAS DELIEVERED WITH NAS6204 (MATL ALLOY STEEL, CADIUM PLATED) INSTEAD OF NAS6304 BOLTS (A286 CRES).SDR CA090129006Tube · wornINSPECTION OF THE RUDDER PEDAL ASSEMBLY REVEALED EXCESSIVE WEAR ON THE S TUBE CAUSED BY WEAR FROM THE RUDDER CABLE. THE WEAR WAS DETECTED BY VISUALLY CHECKING THE OUTER SURFACE OF THE S TUBE FOR MATERIAL DEFORMATION IN THE AREA(S) WHERE THE CABLE CAUSES THE MSDR FDEA200901290390Servo · malfunctionedECAM WARNING OF JAMMED GREEN SERVO RECEIVED ON TAKEOFF ROLL AT 83 KNOTS. REJECTED TAKEOFF, ALL CHECKLIST AND ECAM DIRECTIVES COMPLIED WITH. T/S GREEN SERVO JAM PER TSM 27-14-00, FIG 103, BLOCK 2. FOUND PIN B TO C OPEN ON 27CB GREEN SERVO JAM SWITCH. NEEDSDR CA090203006Rudder Pedal · wornDURING THE AIRCRAFT PREFLIGHT INSPECTION, THE PILOT REPORTED THAT THE PILOTS SIDE RUDDER PEDAL CABLE WAS STUCK IN THE FULL FORWARD POSITION. CLOSER INSPECTION BY MAINTENANCE REVEALED THAT THE PILOTS SIDE LT RUDDER CABLE HAD WORN THROUGH THE S TUBE THAT FORMS SDR CA090113006Arm · broken(CAN) PILOT NOTICED THAT THE PEDAL WAS LOOSE IN FLIGHT, SO HE LOOKED DOWN AND COULD SEE IT NOT ATTACHED TO THE TOP OF RT PEDAL. (TC NR 20090113006)SDR DXTA2008122403435Rudder Control · malfunctionedRUDDER PEDALS HAVE GRINDING FEELING DURING TAKEOFF ROLL AND IN-FLIGHT.SDR DXTA20081223034Arm · wornRUDDER PEDALS GRINDING DURING TAKEOFF ROLL AND IN-FLIGHT. GRINDING IS FELT W/POWER ON OR IDLE, & W/ AUTO-PILOT AND YAW DAMP ON OR OFF. GRINDING IS NOT FELT DURING STATIC CHECKS OR LOW SPEED TAXI REGARDLESS OF POWER SETTINGS. FOR BINDING AND DEFECTS. NONE NOTESDR HNAA2008122200358Regulator · failedRUDDER PRESSURE AND RUDDER FULL PRESSURE CAUTION LIGHT'S ILLUMINATED AFTER TAKEOFF. QUANTITY’S AND PRESSURE WERE NORMAL. RUDDER PRESSURE WENT OUT BELOW 140 KNOTS, RUDDER FULL PRESSURE WENT OUT AT 120 KNOTS. REMOVED AND REPLACED RUDDER DUAL PRESSURE REGULATOSDR 2009FA0000123Torque Tube · corrodedPREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN THE SUPPLEMENTAL INSP DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. FOUND RUDDER TORQUE TUBE RUSTED DURING INSP OF SUPPLEMENTAL INSPECTION 27-20-04. REPLACED TORQUE TUBE PN 5833011-9.SDR QXEA2008121701248Rudder Pedal · stuckSTS - AT TOP OF DESCENT CREW ATTEMPTED TO APPLY A SLIGHT AMOUNT OF RUDDER PRESSURE TO THE RIGHT RUDDER PEDAL AND ENCOUNTERED WHAT FELT LIKE A JAMMED RUDDER. A/P WAS ON AND AIRSPEED WAS 275 KIAS. BOTH DIRECTIONS AND PILOTS SAME FEEL AND RESULT. AFTER PUSHINGSDR QXEA2008121501240Feel Unit · malfunctionedPDX - CAPTAINS AND FO'S RIGHT RUDDER PEDAL'S STICKY. REMOVED AND INSTALLED SERVICEABLE RUDDER FEEL SUMMING UNIT IAW AMM TASK 27-22-06-000-801 AND 27-22-06-400-801. PERFORMED RUDDER CONTROL SYS RIG CK IAW Q400 AMM TASK 27-21-00-830-810/ 27-21-00-830-811/ 27-2SDR CA081201007Rudder Bar · chafed(CAN) SCREWS ATTACHING CENTER CONTROL CONSOLE COVER PN 0413463-5 WERE TOO LONG AND CHAFING IN TO THE RT SIDE OF THE RUDDER PEDAL TORQUE TUBE.SDR QXEA2008120301213Rudder Pedal · lack of lubePDX - RUDDER PEDALS NOTICEABLE HARDER TO PUSH TO THE RIGHT SIDE. IT BINDS-UP AND THERE IS A SLIGHT RATCHETING, THEN IT PUSHES THROUGH AND FREES UP. INSPECTED UNDER COCKPIT BEHIND PANELS 121BL AND 122BR FOR ANY SIGNS OF BINDING OR FOREIGN OBJECT DEBRIS, NONE SDR CA081126001Control Unit · failed(CAN) WHILE PERFORMING TASK 27-21-28-710-801 OPS TEST OF THE RUDDER SHUT-OFF VALVES, NR1 RUDDER SHUT-OFF VALVE FAILED TO CLOSE WHEN SELECTED OFF. THE FLIGHT CONTROL ELECTRONIC CONTROL UNIT (FCECU) WAS REPLACED. THE TASK WAS PERFORMED AND PASSED THE TEST. THE SDR CA081121006Tube · worn(CAN) DURING THE ACFT PRE-FLIGHT THE PILOT REPORTED THAT THE RUDDER PEDAL ASSY ON THE RT SIDE WAS DIFFICULT TO ADJUST ALONG THE SLIDE TUBE ASSY. CLOSER INSPECTION BY MAINT REVEALED THAT THE RT OTBD FWD RUDDER CABLE HAD WORN THROUGH THE S-TUBE THAT IS WELDED TOSDR FDEA200811184905Control Unit · bindingSECOND REJECTED T/O DUE TO BLUE RUDDER SERVO CONTROL JAM, ECAM WARNING CAME ON AT 40-50 PERCENT N1. NO FAULT FOUND ON 1ST RTO. RAN ENGINE & CHECKED ALL FLT CONTROL OPERATIONS (WRI 27-20/2731). REPLACED JAMMING DETECTION CONTROL UNIT IAW AMM 27-14-17-4 PRECSDR 08FDEA04905Control Unit · inoperative2ND REJECTED TAKEOFF DUE TO BLUE RUDDER SERVO CTL JAM, ECAM WARNING CAME ON AT 40-50 PERCENT N1. NO FAULT FOUND ON 1ST RTO, RAN ENG AND CHECKED ALL FLT CONTROL OPERATION (WRI 27-20/2731). REPLACED JAMMING DETECTION CONTROL UNIT PER AMM 27-14-17-4 PRE CAUTIONSDR CA081118005Tube · worn(CAN) INSP OF THE RUDDER PEDAL ASSY REVEALED EXCESSIVE WEAR ON THE S TUBE CAUSED BY WEAR FROM THE RUBBER CABLE. THE WEAR WAS DETECTED BY VISUALLY CHECKING THE OUTSIDE OF THE S TUBE FOR MATERIAL DEFORMATION IN THE AREA WHERE THE CABLE CAUSES THE MOST FRICTION OSDR CA081114003Pedal · cracked(CAN) DURING ROUTINE INSP THE RUDDER PEDAL WAS FOUND CRACKED.SDR 08FDEA04869Bellcrank · corrodedNR 1 RUDDER SERVO ACTUATOR BELLCRANK AT RIB 12 HAS CORROSION.
Back to JASC 2720