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 CA030613004Mount · cracked(CAN) DURING TAKE OFF RUDDER PEDAL MOUNT ASSY PN C2CF1777A CRACKED AT BASE OF OPERATING LEVER WELD ALLOWING THE RT RUDDER PEDAL TO DROP TO THE FLOOR, RUDDER CONTROL WAS LOST AND THE TAKE OFF ABORTED. UPON EXAMINATION OF THE AFFECTED PARTS IT WAS NOTED THAT THESDR S2YA03020Relay · failedBEFORE TAKEOFF OF FLIGHT 1226, THE RUDDER BOOST ACTIVATED. THE CREW ABORTED THE TAKEOFF. THE SYSTEM WAS PUT ON MEL AND THE FLIGHT CONTINUED. ON 6/16 THE MECHANIC CLEARED THE MEL BY REPLACING A RELAY AND REPAIRING SOME CHAFED WIRES TO THAT RELAY. THE AIRCRASDR 2003FA0000608Control Cable · looseWHEN RUDDER IS DEFLECTED TO THE FAR RIGHT, THE RIGHT RUDDER CABLE GOES SLACK AND HANGS UP UNDER THE NUT FOR THE ELEVATOR PULLEY CLUSTER LOCATED BY THE FUSELAGE RIGHT SIDE ACCESS PANEL. TO PREVENT THIS, INSTALLED A SECOND NUT ON THE BOLT AND INSTALLED AN AN4-1SDR 2003FA0000680Turnbuckle · unsafetiedDURING THE FIRST ONE HUNDRED HOUR INSPECTION OF THIS AIRCRAFT THE AFT TURNBUCKLE FOR THE RUDDER SYSTEM, AS VIEWED THROUGH ACCESS DOOR 311, HAD FIVE THREADS EXPOSED ON LOWER END AND FOUR THREADS EXPOSED ON UPPER END. BOTH ENDS WERE SAFETIED WITH CLIPS. CLOSE SDR SWIA200312034Actuator · malfunctionedRIGHT RUDDER LIMITED TO APPROXIMATELY 1/3 OF FULL TRAVEL DURING INITIAL CLIMB. RUDDER WORKS CORRECTLY WITH BLUE SYSTEM SWITCH TURNED OFF. REMOVED AND REPLACED BLUE SYSTEM RUDDER ACTUATOR IAW EMB 120 MM 27-22-02. OPS CHECK GOOD IAW EMB MM 27-20-00. NO DEFECSDR 2003F00359Limiter · failedDURING PILOT'S PREFLIGHT, WITH APU RUNNING, THE 'RUDDER LIMIT FAIL' RED CAS MESSAGE ANNUNCIATED. ANOTHER AIRCRAT WAS UTILIZED FOR THE TRIP. THE RUDDER LIMITER FAILED TO ACTUATE DUE TO A FAULT IN THE ELECTRICAL COMPONENTS OF THE SYSTEM. AIRCRAFT WAS DE-POWERSDR CA030517002Rudder · binding(CAN) INCORPORATION OF AD 2000-20R1 (CESSNA S/B SEB01-1) RESULTS IN BINDING BETWEEN NEW STOP BOLTS AND RUDDER STRUCTURE DUE TO THE INCREASED SIZE OF THE STOP BOLTS. BINDING WAS NOT APPARENT UNLESS PRESSURE WAS APPLIED TO BOTH RUDDER PEDALS.SDR QXEA0300578Warning Light · illuminatedSEA-ON FLIGHT NUMBER 2008, ON CLIMBOUT THROUGH 8,000 FEET, RUDDER PRESSURE AND RUDDER PRESSURE CAUTION LIGHTS ILLUMINATED. REMOVED AND REPLACED DUAL LEVEL PRESSURE REGULATOR. PERFORMED OPERATIONAL CHECK OF DUAL PRESSURE REGULATOR VALVE. OPERATIONAL/LEAK CHESDR CA030726002Spring · damaged(CAN) SPRING PEDAL ATTACH REPLACE.SDR SWAA031098Bearing · wornDURING SCHEDULED A2 CHECK, FOUND AILERONS DIFFICULT TO MOVE OUT OF CENTER DETENT. REMOVED AND REPLACED 4 EA BEARINGS ON AILERON CONTROL DRUM PER MM.SDR 2003FA0000551Bearing · failedDURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING. PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL SYSTEM WHICH ALLOWS HE CONTROL ROD DEFLECTION TO EXCEED THE DSDR 2003FA0000550Bearing · failedDURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.SDR 2003FA0000549Bearing · failedDURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAIN CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.SDR 050601Transducer · failedFROM FARMINGTON NEW MEXICO TO ALBURQUERQUE NEW MEXICO ON FLIGHT 704, DURING TAKEOFF THE RUDDER FELT CROOKED AND STIFF ACCORDING TO THE CREW. ABORTED TAKEOFF AND RETURNED TO THE GATE WITH NO FURTHER INCIDENT. MAINTENANCE CHANGED THE LEFT HAND ENGINE RUDDER BOSDR CA030515003Bellcrank · cracked(CAN) DURING INVESTIGATION THE RUDDER BELLCRANK WAS FOUND CRACKED.SDR CA030604009Rudder Pedal · worn(CAN) AFTER FINDING A BROKEN RUDDER PEDAL, AN INSPECTION WAS CARRIED OUT ON THE OTHER A/C. ON ONE OF THE AIRCRAFT, THE ATTACHMENT POINT FOR THE RUDDER PEDAL WAS FOUND EXCESSIVELY WORN IN THE SAME LOCATION AS THE BROKEN PEDAL FOUND ON THE OTHER AIRCRAFT. INSPSDR MEX2003155Actuator · inoperativeAIRCRAFT RETURN TO PLATFORM DUE TO RUDDER PCA EICAS MESSAGE. THE RUDDER MODULE WAS VERIFIED AND THE ALARM WAS FOUND IN RIGHT RUDDER RATIO. IN HANGER THE FIM 27-21-00 PROCEDURE WAS ACCOMPLISHED. BEING ALL CORRECT.SDR MWEA030181Rib · corrodedLOWER END OF RUDDER HAS RIB ASSEMBLY THAT HAS CORROSION AT FLANGE. REMOVED DAMAGE AND INSTALLED NEW RIB.SDR ASAA0380358Link · corrodedOAK - FOUND DURING 15K CHECK, RUDDER THROW LIMITER LINK IS CORRODED. REPLACED LINK PER MM 27-20-06. (M)SDR ASAA0380357Crank Assy · corrodedOAK - FOUND DURING 15K CHECK, RUDDER THROW LIMITER CRANK ASSY IS CORRODED. REPLACED CRANK ASSY PER MM 27-20-06. (M)SDR 2003FA0000498Spring · failedDURING TAXI TO POSITION FOR TAKEOFF, THE RIGHT RUDDER RETURN SPRING FAILED AT THE ATTACHMENT HOOK TO THE CABLE BELLCRACK. THE PILOT HEARD A NOISE BUT DID NOT REALIZE THE SPRING HAD FAILED UNTIL LATE IN THE ROLLOUT. THE FLIGHT CYCLE WAS COMPLETED WITHOUT EVENSDR SWIA200311890Actuator · failedAFTER TAKEOFF, DISCOVERED WE HAD VERY LIMITED RIGHT RUDDER AUTHORITY. RIGHT RUDDER PEDAL WOULD ONLY DEPRESS ABOUT 1 1/2 INCHES. LEFT PEDAL TRAVEL NORMAL AND ALL COCKPIT INDICATIONS NORMAL. INSPECTED RUDDER FOR FREEDOM OF MOVEMENT, CHECKED GOOD. BLUE SYSTEMSDR 2003FA0000408Control Cable · jammedWHEN THE RUDDER IS DEFLECTED TO THE FAR RIGHT , THE RIGHT RUDDER CABLE GOES SLACK AND HANGS UP UNDER THE NUT FOR THE ELEVATOR PULLEY CLUSTER LOCATED BY THE FUSELAGE RIGHT SIDE ACCESS PANEL. TO PREVENT THIS A GUARD WAS SUGGESTED TO PREVENT THE CABLE FROM SLIPPSDR 2003FA0000389Control Cable · out of rigWHEN THE RUDDER IS DEFLECTED TO THE FAR RIGHT, THE RIGHT RUDDER CABLE GOES SLACK AND HANGS UP UNDER THE NUT FOR THE ELEVATOR PULLEY CLUSTER LOCATED BY THE FUSELAGE RIGHT SIDE ACCESS PANEL. TO PREVENT THIS A GUARD WAS SUGGESTED TO PREVENT THE CABLE FROM SLIPPISDR RAIA00304110Pressure Switch · failedPIT- RUDDER NR 2 FAIL WARNING. MAINTENANCE REMOVED AND REPLACED NR 2 RUDDER PRESSURE SWITCH, OPS CK GOOD.SDR CA030411006Control Cable · failed(CAN) WHILE INVESTIGATING A PREVIOUS RUDDER CABLE FAILURE IT WAS DISCOVERED THAT THE OVAL SLEEVE ON THE LT OUTBOARD RUDDER CABLE, AT THE RUDDER PEDAL END, WAS IMPROPERLY SWAGED. NONE OF THE THREE COMPRESSIONS WERE SUFFICIENT. MAINTENANCE RECORDS DID NOT INDISDR P5CA0300805Pedal · displacedWITH RUDDER SURFACES NEUTRAL RUDDER PEDALS WERE DISPLACED 1-8 UNITS (RIGHT). OPERATIONAL CHECKED PER AMM 27-21-00. OPS CHECK NORMAL. SUSPECT LARGE LATERAL IMBALANCE AS INDICATED ON W/B FORMS.SDR 2003F00272Actuator · malfunctionedUNUSUAL NOISE COMING FROM RUDDER ACTUATOR DURING MANUAL OPERATION. RUDDER QUADRANT BELLCRANK RUBBING ON CABLE GUIDE. SUPPORT MOUNT HOLE TOO BIG FOR PIVOT BUSHING. GULFSTREAM RESEARCHING REASON FOR DEFECT. (M)SDR CA030404010Sleeve · inoperative(CAN) WHEN RIGHT RUDDER WAS APPLIED TO RECOVER FROM A LEFT HAND SPIN A BANG WAS HEARD. THE PILOT FLYINGS (FROM THE RIGHT SEAT) RIGHT RUDDER PEDAL FOLDED TO THE FLOOR. SUBSTANTIAL SLACK WAS NOTED IN THE RIGHT HAND RUDDER CABLE WHERE IT MEETS THE PEDAL. THE PISDR CA030408002Spring · broken(CAN) PILOT REPORTED NOSE STEERING SEEMED SLOPPY ON TAXI AND RUDDER STIFF AFTER 70 KIAS ON TAKEOFF. REMOVED TAILCONE AND FOUND BOTH RUDDER RETURN SPRINGS BROKEN WITH THE LEFT HAND SPRING BINDING ON THE ELEVATOR SUPPORT ARM. REPLACED SPRINGS AND OPERATION NORSDR CA030507007Pedal · broken(CAN) DURING AN OPERATIONAL CHECK OF CONTROLS DURING MAINTENANCE, LT RUDDER PEDAL FRACTURED AT ITS ATTACHMENT POINT FROM WEAR. OBLONG WEAR WAS NOTED IN ATTACHMENT AREA. WEAR WAS NOT READILY NOTICED DUE TO ATTACHEMENT DESIGN AND ATTACHMENT TO BRAKE MASTER CYLISDR MEX2003109Gearbox · inoperativeAIRCRAFT ARRIVED WITH REPORT PRIMARY HORIZONTAL STABILIZER WITHOUT MOVEMENT, IT WAS NECESSARY TO COMPENSATE WITH ELEVATOR DURING FINAL APPROACH. THE GEARBOX ASSEMBLY TRIM AND ALTERNATE ENGINE WERE REPLACED IAW MM AND RELAY LONGITUDINAL TRIM WAS REPLACED IAW MSDR MEX2003107Gearbox · stuckDURING FINAL APPROACH LONG TRIM WAS STUCKED, THE NOSE COMPENSATION UP WAS NOT POSSIBLE. THE PRIMARY ACTUATOR ENGINE WAS REPLACE. THE GEAR BOX ASSY TRIM AND ALTRENATE ENGINE WERE REPLACED IAW MM AND RELAY LONGITUDINAL TRIM WAS REPLACED IAW, TESTS CORRECT.SDR AUS20030385Control Cable · worn(AUS) RT RUDDER CONTROL CABLE WORN BEYOND LIMITS.SDR RAIA00303085Pressure Switch · inoperativePIT- RUDDER HARD OVER FAULT AND SPOILER FAULT INDICATION. MAINTENANCE REMOVED AND REPLACED NUMBER 2 RUDDER PRESSURE SWITCH. LEAK AND OPS CHECK OK. PERFORMED OPS CHECK ON SPOILER SYSTEM, OPS CHECK OK. COULD NOT DUPLICATE.SDR QXEA0300393Hinge · wornPDX - FORE RUDDER UPPER MAIN HINGE WORN EXCESSIVELY OR MISSING PARTS. REPAIRED IAW DHC-8 400 SRM 51-22-40-340-801 AND HORIZON AIR EA 6-55-26.SDR QXEA0300389Bushing · missingPDX - FORE RUDDER LOWER MAIN HINGE POINT MISSING BUSHING. REPAIRED IAW HORIZON AIR EA 6-55-26.SDR QXEA0300386Hinge Bracket · wornPDX - FORE RUDDER AFT LOWER HINGE BRACKET UPPER SURFACE WORN AROUND ATTACH HOLE. REPAIRED IAW HORIZON AIR EA 6-55-25.SDR COMA0360145Trim Switch · malfunctionedFLIGHT 5219 RUDDER TRIM STUCK AT 1/4 RIGHT. REPLACED THE RUDDER TRIM PANEL.SDR 03X03038751Arm · crackedDURING A SCHEDULED INSPECTION THE RUDDER QUADRANT DRIVE ASSEMBLY WAS FOUND CRACKED AT THE RUDDER FEEL SPRING ATTACH ARM. THE FEEL SPRING ATTACH ARM IS ATTACHED IN TWO SECTIONS TO THE RUDDER QUADRANT, ONE SECTION WAS CRACKED ALL THE WAY THROUGH. IF THE ATTACHSDR HNAA0300014Rudder · crackedTop forward rudder skin has a crack. Repaired rudder skin.SDR AWXA200300237Coupler · damagedON SHORT FINAL, FIRST OFFICER COULDN`T MOVE RUDDER PEDALS IN EITHER DIRECTION; AFTER LANDING, WITH NOSE WHEEL DOWN AND AT LOWER SPEED, BOTH CAPTAIN AND FIRST OFFICER HAD FULL RUDDER MOVEMENT. MAINTENANCE PERFORMED A VISUAL INSPECTION OF RUDDER PEDAL HARDWARE, SDR 2003FA0000329Horn · looseON ANNUAL INSPECTION FOUND ELEVATOR HORN LOOSE. HORN IS BOLTED TO TWO INBOARD SOLID RIBS OF ELEVATOR. IT IS NOW BROKEN LOOSE FROM THESE TWO RIBS. THIS IS A VERY SERIOUS CONDITION, NEEDS TO BE CHECKED. THIS AIRCRAFT IS STORED OUTSIDE.SDR 2003FA0000230Ring · missingONE TIME FLEET INSPECTION REVEALED SAFETY CLIP MISSING. THIS CLIP HOLDS THE SHAFT THAT ATTACHES THE RUDDER PEDAL TO THE FUSELAGE FITTING.ONE TIME INSPECTION INITIATED DUE TO ANOTHER AIRCRAFT IN FLEET HAVING PEDAL VERTICAL STABILTY DETERIORATE.SDR 2003FA0000229Ring · missingONE TIME FLEET INSPECTION REVEALED SAFETY RING MISSING.ONE OF THREE AIRCRAFT BELIEVED TO HAVE NOT HAD INSTALLED AT FACTORY.INSPECTION OF AIRCRAFT DID NOT PRODUCE MISSING PART.SDR 2003FA0000228Ring · missingRUDDER PEDAL LOST VERTICAL STABILTY AND THE INSTRUCTOR PILOT REPORTED THE PROBLEM TO MAINTENANCE. MAINTENANCE INSPECTED THE AREA AND FOUND THE SAFETY RING,WHICH HOLDS THE RUDDER PEDAL ATTACH SHAFT TO THE FUSELAGE FITTING, MISSING. AN INSPECTION WAS MADE TO FINSDR CA030218008Control Cable · corroded(CAN) 2 CABLES FOUND CORRODED AND FRAYED AT FUSELAGE STA. 20.5. BOTTOM OF FORWARD LANDING GEAR BULKHEAD. DEFECT WAS FOUND ON CABLES BECAUSE THEY HAD TO BE REMOVED FOR MAJOR STRUCTURAL REPAIRS. THOSE CABLES RUN ON PULLIES ATTACHED TO THE BULKHEAD AT THE VERY BOSDR S03J27006Control Cable · out of rigRUDDER DOES NOT FULL DEFLECT TO RT . RUDDER & RUDDER TRIM SYSTEM RIG CHECK FOUND CONTROL CABLE TENSION WAS OUT OF LIMIT. PERFORM RUDDER AND RUDDER TRIM CONTROL SYS ADJ IAW 27-21-00. PERFORM RUDDER TRIM SYS TEST NML. EON 744-27-632292-0017 R1 IS ISSUED SDR CA030410001Rod · damaged(CAN) RUDDER POSITION FEED BACK ROD ASSEMBLY DAMAGED FROM SKYDROL ROD IS MADE FROM A KEVLAR MATERIAL THAT IF A PRE-EXISTING CONDITION ALLOWS SKYDROL TO CONTAMINATE THE STRUCTURE OF THE ROD IT WILL DETERIORATE.SDR WVE2003F00003Sensor · inoperativeDURING POWER UP BY FLIGHT CREW; THE FLIGHT CREW REPORTED RIGHT RUDDER FORCE EXISTS WITH AMBER LIGHT (RUDDER BOOST) ILLUMINATED, PEDAL FORCE STOPS WHEN LEFT RUDDER FORCE IS APPLIED.
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