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 96ZZZX5724Bar Assy · crackedPILOT REPORTS EXCESSIVE RT RUDDER APPLICATION WITH LITTLE CONTROL. CLOSE INSPECTION REVEALED RUDDER CONTROL BAR ASSY WAS CRACKED AT LEFT WELD AREA OF CROSS-OVER BAR. SUSPECT CAUSE OF FAILURE MAY HAVE BEEN THE RESULT OF OVER TOW-LIMITS DURING GROUND HANDLING SDR 96ZZZX5730Hyd Solenoid · contaminatedRUDDER PCU INVESTIGATION, FLUID FOUND IN SOLENOID COIL CAUSING FAILURE.SDR REXA96061Trim Indicator · driftingREQUIRES FULL RIGHT RUDDER TRIM AT SLOW AIRSPEEDS, 3 UNITS AT CRUISE AT SLOW AIRSPEEDS, A/C REQ'S FULL RIGHT RUDDER TRIM TO CENTER THE BALL AT CRUISE SPEEDS. THE TRIM IND STILL SHOWS 3 UNITS RIGHT WHEN YAW DAMPER IS ENGAGED, YELLOW RUDDER FLAG IS ANNUNCIATED SDR GLBA96211Yaw Sensor · malfunctionedRDU - TWO HARD UNCOMMANDED RUDDER TURNS WITH AUTOPILOT ENGAGED. TURNED OFF RUDDER BOOST. MAINTENANCE SECURED CANNON PLUG AT YAW RATE SENSOR. (M)SDR CA970113001Bushing · missing(CAN) THIS REPORT FROM CAA INDICATING THAT EXCESSIVE PLAY WAS NOTED IN THE LOWER PORTION OF BOTH THE TOP AND BOTTOM TRAIL-TO-FORE RUDDER HINGE POINTS. IT WAS FOUND THAT A BUSHING WAS MISSING. THE HINGE POINTS HAD BEEN PREVIOUSLY REPAIRED USING OVERSIZED BUSHESSDR 96ZZZX5293Crank · chafingWHILE PERFORMING AN ANNUAL INSPECTION, NOTICED LT RUDDER BAR CRANK WAS CHAFING ON RUDDER BAR WHEN BRAKE WAS APPLIED. SUSPECT RUDDER BAR CRANK WAS IMPROPERLY INSTALLED IN PRODUCTION. SLINGSBY IPC CHAPTER 19, PAGES 19, 20, ITEMS 5 AND 2.SDR 96ZZZX5234Tube Assy · elongated holesAIRCRAFT TOTAL TIME: 470.2 HOURS, 1995 SENECA IV. FOUND DURING ANNUAL INSPECTION, RUDDER HAD 3 TO 4 DEGREE MOVEMENT WITHIN THE MOUNT FITTING, PN 96319-802. FURTHER INSPECTION (RUDDER REMOVED) TORQUE TUBE ASSY HAD WORN, ELONGATED BOLT HOLES (4). CAUSE - VIBSDR CALA9601322Solenoid Valve · malfunctionedTHE AIRCRAFT BECAME HARD TO CONTROL ABOUT THE VERTICAL AXIS WHILE ON FINAL APPROACH. THE AIRCRAFT WANTED TO DUTCH ROLL AND YAW EXCESSIVELY AND DIDN'T RESPOND EFFECTIVELY TO PILOT CONTROLLED INPUTS ON RUDDER. THE AIRCRAFT HANDLED THE SAME WITH AND WITHOUT YAWSDR 96ZZZX5260Bolt · wrong partDURING PHASE 5 INSPECTION, FOUND INCORRECT BOLT AND NUTS INSTALLED IN RUDDER TORQUE TUBE WHERE IT ATTACHED TO BELLCRANK. THREE DIFFERENT TYPES OF LOCKING NUTS USED IN PLACE OF CASTLE NUTS THAT ARE REQUIRED. MOST LIKELY INSTALLED BY PAINT SHOP WHEN AIRCRAFT WSDR MALA965125Torque Tube · chafedMSP - DURING A SCHEDULED INSPECTION, MAINTENANCE FOUND RUDDER TORQUE TUBE CHAFED AT PRESSURE SEAL MOUNT AREA. REMOVED RUDDER TORQUE TUBE, PN 27-42051-037, AND INSTALLED NEW TORQUE TUBE IAW FAIRCHILD MM 27-20-20, PAGES 201-202. (X)SDR 96ZZZX5417Line · pin holeUPON LANDING, THE FLT CREW NOTICED HYD FLUID IN THE AREA OF THE VERT STAB. INVEST REVEALED THE RUD SERVO HYD RETURN LINE HAD BEEN CHAFED BY THE BRAIDED STEEL RUD SERVO LINE PN 000AE90-4-0232 WHERE A PIN HOLE HAD DEVELOPED. LINE WAS REPLACED AND PROTECTED WITHSDR CA970114013Rudder Bar · broken(CAN) WHILE TAXIING THE RUDDER BAR BROKE AT THE OUTBOARD PEDAL ATTACH REINFORCEMENT. SE 72-36 MOD. FOUND AND INCORPORATED.SDR CA961007012Rudder Bar · broken(CAN) WHILE WATER TAXIING, RUDDER BAR BROKE AT OUTBOARD PEDAL ATTACH AT REINFORCEMENT. REFERENCE AD CF-73-05. THIS UNIT HAS WELDED TAB WHICH BROKE THROUGH ALSO.SDR CALA9601263Transfer Valve · malfunctionedTHE FIRST OFFICER REPORTED, LEFT ROLL OF 5 TO 10 DEGREES BANK DURING TAKEOFF, 30 SECONDS LATER THE AIRCRAFT ROLLED RIGHT ABOUT 5 TO 10 DEGREES. YAW DAMPER RESPONSE WAS EXCESSIVE AND CAUSING FISH TAILING OF AIRCRAFT DURING CLIMB AND CRUISE. THE YAW DAMPER WASSDR 96UAL900666Pcu · inoperativeHAD VERY ABRUPT YAW DAMPER INPUT TO THE LEFT AT FLIGHT LEVEL 290. DISENGAGED YAW DAMPER AND COMPLETED EMERGENCY CHECKLIST. CONTINUED TO ORD, LANDING WAS DIFFICULT DUE TO SLUGGISH YAW ACTION BECAUSE YAW DAMPER TURNED OFF, JUST AS DESCRIBED IN THE FLIGHT MANUASDR CA961002005Control Cable · damaged(CAN) DURING INSPECTION IT WAS NOTED THAT THE RUDDER CONTROL CABLES WERE BLENDED AT THE FAIRLEADS WHERE THE CABLES EXIT THE FUSELAGE IN THE TAIL SECTION. SUBMITTER STATES THAT AIR TRACTOR SERVICE LETTER #77 ADDRESSES THIS ISSUE AND ADDS THE BLENDING IS WITHIN SDR 96ZZZX4762Bracket · failedPILOT REPORTED LOSS OF RUDDER CONTROL IN-FLIGHT. THE AIRCRAFT WAS LANDED SAFELY AND DELIVERED TO MAINTENANCE. INSPECTION REVEALED THE RUDDER PULLEY BRACKET L OCATED AT STA 1.67 HAD PULLED FREE FROM THE FORWARD BULKHEAD. THIS ALLOWED MISALIGNMENT OF THE CABLSDR ABXA9600612Rudder Pump · leakingONE HOUR INTO FLIGHT NOTICED HYDRAULIC QUANTITY SLOWLY DECREASING. MARKED GAUGE AND CONTINUED TO DECREASE VERY SLOWLY. APPROXIMATELY ONE NEEDLE WIDTH ABOVE STANDPIPE PERFORMED HYDRAULIC FLUID LOSS CHECKLIST. ONCE HYDRAULICS DEPRESSURIZED AND ISOLATED, QUANTSDR AWXA960398Rt Cam Roller · failedPHX - FLT 2294 - AIRCRAFT ARRIVED WITH FLIGHT CREW COMPLAINING OF STIFF RUDDER PEDALS. WE CONFIRMED A TIGHT RATCHETY FEEL WHEN OPERATING PEDALS, ESPECIALLY WHEN LEFT PEDAL WAS PUSHED. RUDDER TRIM STICKS AND IS NOT RESPONSIVE TO PILOT INPUTS. FOUND THE SEAL SDR 9618142276Rudder · oscillationSHORTLY AFTER TAKEOFF, NOTICEABLE RUDDER OSCILLATION. RETURNED TO MEM AND LANDED WITHOUT INCIDENT. PERFORMED RUDDER AND YAW DAMPER CHECK, SYSTEM OPERATIONAL CHECK OK.SDR ARWA9608004O-Ring · damagedINFLIGHT AT FL 350, HYDRAULIC QUANTITY SUDDENLY STARTED DESCENDING AND CONTINUED DESCENDING. ISOLATED HYDRAULIC SYSTEM. RETURNED TO MIAMI AND FOUND RUDDER SELECTOR VALVE PLUG LEAKING. REPLACED O-RING, NO LEAKS NOTED IAW DC-8 MM 29-00-00.SDR 96ZZZX5019Control Cable · brokenPILOT'S LEFT OUTBOARD RUDDER CABLE BROKE AT NICO PRESSURE FITTING. WITH RUDDER PEDALS ADJUSTED FULL FORWARD POSITION, S-TUBE MAKES CONTACT WITH NICO-PRESSURE FITTING. S-TUBE WORE THROUGH THE CABLE. AIRCRAFT WAS ON THE GROUND.SDR 96ZZZX4324Control Cable · brokenPILOT'S LEFT OUTBOARD RUDDER CABLE BROKE AT NICOPRESS FITTING. WITH RUDDER PEDALS ADJUSTSED FULL FORWARD POSITION, S-TUBE MAKES CONTACT WITH NICOPRESS FITTING. S-TUBE WORE THROUGH THE CABLE. AIRCRAFT WAS ON THE GROUND.SDR 96ZZZX5151Actuator · malfunctionedHKG/TPE - FLT CI-618 - AUGUST 7, 1996, RUDDER TRAVEL SYSTEMS 1 AND 2 FAULT. RUDDER TRAVEL ACTUATOR CHANGED. ARTF FEEL LIMITING COMPUTER CHANGE. 309CY1 AND 309CY2 RELAY CHANGE. FUNCTIONAL TEST OK PER A300-600R AMM 27-23-00.SDR 96UAL900598Bearing · crackedON TAKEOFF AT 60 KNOTS, AIRCRAFT JERKED TO THE RIGHT AND A KICK TO THE RIGHT IN THE RUDDER PEDALS WAS FELT. ABORTED TAKEOFF. STEERING WAS OK ON TAXI IN. *S/D* DURING SHOP OVERHAUL OF THE PCU THE PRIMARY SUMMING LEVER WAS REPLACED. AN ALTERNATE CONFIGURATISDR 96ZZZX4177Bracket · crackedWHILE COMPLETING 200-HOUR FACTORY INSPECTION OF NOSE AREA, FOUND BOTH PULLEY BRACKETS CRACKED AT BEND RADIUS. PULLEY IS FOR RUDDER CABLE AND IS SUPPORTED BY THESE TWO BRACKETS. REPLACED CRACKED BRACKETS WITH SUPERCEDING PART NUMBERS FROM MANUFACTURER. SUBMISDR 96ZZZX4176Bracket · crackedWHILE COMPLETING 200-HOUR FACTORY INSPECTION OF NOSE AREA, FOUND BOTH PULLEY BRACKETS CRACKED AT BEND RADIUS. PULLEY IS FOR RUDDER CABLE AND IS SUPPORTED BY THESE TWO BRACKETS. REPLACED CRACKED BRACKETS WITH SUPERCEDING PART NUMBERS FROM MANUFACTURER. SUBMISDR 96ZZZX3909Transducer · failedRUDDER BOOST INOPERABLE. LEFT SIDE, NO SIGNAL, HARD RIGHT PEDAL ALL THE TIME. REPLACED RUDDER BOOST TRANSDUCER, SYSTEM FUNCTIONAL TESTED NORMALLY.SDR 96ZZZX3908Transducer · failedON DEPARTURE, PILOT REPORTED RUDDER BOOST APPLIED RIGHT RUDDER. HAD TO USE DISCONNECT BUTTON TO DISCONNECT RUDDER BOOST SYSTEM AND RETURNED AND LANDED. TROUBLESHOOTING REVEALED TRANSDUCER GIVING FALSE SIGNAL. REPLACED TRANSDUCER AND FUNCTIONAL TESTS WERE NOSDR 96ZZZX3865Torque Tube · not safetiedWHILE PERFORMING CANADAIR ALERT SERVICE BULLETIN A604-27-002, FOUND RUDDER CONTROL TORQUE TUBE LOWER ROD END ATTACH HARDWARE (SAFETY COTTER PIN) NOT INSTALLED AND THE NUT BACKED OFF ALLOWING THE BOLT TO PARTIALLY BACK OUT. THE NUT WAS TORQUED AND COTTER PIN ISDR CA960729013Tube · cracked(CAN) RUDDER TORQUE TUBE CRACKED WHERE LOWER FLANGE IS WELDED TO TUBE. CRACK EXTENDS APPROXIMATELY 20 PERCENT OF THE CIRCUMFERENCE. AT REMOVAL IT WAS DISCOVERED THAT A GROOVE WAS WORN BY THE PHENOLIC TORQUE TUBE SEAL OF UP TO 30 PERCENT OF THE TUBE WALL THICKNSDR AU961037Bellcrank · failed(AUS) COPILOTS RUDDER BELLCRANK BROKEN IN THE VICINITY OF THE CROSSOVER PUSHROD ATTACHMENT HORN - FURTHER INVESTIGATION FOUND THAT THE FAILURE WAS CAUSED BY THE INCORRECT REMOVAL OF THE RUDDER STOP BAR AND EMBRITTLEMENT OF THE BARSDR CALA9600906Pcu · inoperativeTHE AIRCRAFT HAD AN UNCOMMANDED ROLL TO THE RIGHT ON TAKEOFF. FIFTEEN TO TWENTY DEGREES OF LEFT AILERON WAS REQUIRED TO MAINTAIN LEVEL FLIGHT. ALL OTHER INDICATIONS WERE NORMAL. THE AIRCRAFT CONTINUED TO CLE WHERE IT LANDED WITHOUT FURTHER PROBLEM. THE YAWSDR CA960703008Indicator · malfunction(CAN) ON DESCENT WITH RUDDER TRIM AT ZERO IT WAS NOTED THAT THE TRIM INDICATOR HAD DRIFTED TO 10 DEGREES RIGHT. A FEW MINUTES LATER INDICATION RETURNED TO ZERO WITH NO EFFECT TO FLIGHT CONTROL IN EITHER INSTANCE. INDICATOR REPLACED.SDR AU960912Arm · cracked(AUS) PILOTS RUDDER PEDAL ARMS BOTH CRACKED IN UPPER AREA OF THE 'I' SECTION - FOUND DURING INSPECTION IAW AD/BEECH55/69 AMDT2SDR 96ZZZX3675Control Horn · crackedDURING ANNUAL INSPECTION, CRACK FOUND COMING OUT OF BOLT HOLE WHERE HORN MOUNTS TO RUDDERVATOR. REPLACED WITH NEW PART.SDR COMA9610179Servo · defectiveWHEN AUTOPILOT DISENGAGED DURING APPROACH PHASE OF FLIGHT, THE RUDDER CONTROLS JAMMED AND EXCESSIVE FORCE WAS REQUIRED TO MOVE RUDDER CONTROLS. REPLACED DEFECTIVE RUDDER SERVO.SDR 96ZZZX3445Rudder Bar · brokenLEFT RUDDER PEDAL ATTACHMENT LINK ON RUDDER BAR IS BROKEN.SDR AU960816Pedal · malfunction(AUS) INTERMITTENT KNOCKING NOISE COMING FROM COPILOTS RUDDER PEDAL AREA - INVESTIGATION COULD FIND NO FAULTSSDR 96ZZZX3547Stop · brokenEXAMINATION OF THE RUDDER SECTION DISCLOSED THE CASTELLATED NUTS ON THE RUDDER TOP COUNTERWEIGHT WAS STRIKING VERTICAL SKIN ON THE LEFT SIDE OF THE VERTICAL FIN CREATING SMALL PUNCTURE HOLES IN THE SKIN. THIS WAS CAUSED BY THE PHENOLIC STOPS BEING BROKEN DUE SDR UPS96220437Centering Crank · crackedINSPECTION TYPE SI, RUDDER AFT CONTROL CENTERING CRANK ASSM HOUSING IS CRACKED AT LEFT SPRING MOUNT FLANGE. REMOVED AND REPLACED RUDDER CENTERING MECHANISM IAW MM 27-20-91.SDR CA960722009Control Cable · frayed(CAN) ON 100 HOUR INSPECTION BOTH RELATIVELY NEW RUDDER CABLES WERE FOUND FRAYED AT FIRST PULLEY AFT OF RUDDER PEDAL CONNECTIONS. THE CABLES WERE STAINLESS AND ARE SUPPOSED TO BE GOOD FOR 1000 HOURS PLUS.SDR 96ZZZX4381Torque Tube · bearing detachedSPARKS AROUND THE PILOT'S FEET WHEN HE WAS USING THE RUDDER PEDALS TO TURN THE ACFT FOR BACK-TRACKING DOWN THE RUNWAY TO EXIT POINT. REMOVED PILOT'S SEAT AND CARPET, FOUND RUDDER TORQUE TUBE BEARING ADRIFT FROM THE FLOOR LETTING THE RUDDER BAR ASSEMBLY LIFT ASDR AU960747Torque Tube · broken(AUS) RH RUDDER TORQUE TUBE FAILED IN AREA OF WELD ATTACHING THE MAIN TUBE TO THE SHORT VERTICAL STUB - VERTICAL STUB IS BOLTED TO THE RH RUDDER PEDALSDR MALA964994Pin · looseFLT NR 3311 - AFTER TAKEOFF FROM DTW, THE RUD PRESS AND RUD FULL PRESS CAUTION LIGHTS ILLUMINATED ABOVE 140 KTS. THE AIRCRAFT RETURN DTW. MAINTENANCE RESET A LOOSE PIN AT TERMINAL BLOCK 2721-FB1. ALL SYSTEMS OPERATED SATISFACTORILY. (M)SDR CAL960615Pwr Contl Unit · inoperativeTHE AIRCRAFT EXPERIENCED AN UNCOMMANDED ROLL AFTER TAKEOFF. RIGHT RUDDER INPUT WAS USED TO COUNTER ACT THE MOVEMENT. THE YAW DAMPER SWITCH WAS CONFIRMED ON. THE FLIGHT WAS CONTINUED TO BOS WHERE IT LANDED WITHOUT FURTHER EVENT. MAINTENANCE REMOVED AND REPLSDR CA960626004Control Cable · corroded(CAN) RUDDER CONTROL CABLES RUNNING UNDER FLOOR IN LOWER RIGHT HAND SECTION FOUND BADLY CORRODED (INCLUDES P/N C3CF197-5) AT STA. 310, AND AFT OF REAR BAGGAGE COMPARTMENT BULKHEAD. THIS AREA ALSO BELOW AND AFT OF BATTERY RACK. AIRCRAFT HAD BEEN OPERATED IN SALSDR 96ZZZX3202Bellcrank · holes elongatedDURING ANNUAL INSPECTION, HORIZONTAL STABILIZER WAS FOUND TO HAVE LOOSE MOTION. A DOUBLER KIT FROM CESSNA WAS INSTALLED TO CORRECT THIS PROBLEM. HOWEVER, DURING REPAIR, IT WAS NOTED THE RUDDER BELLCRANK HAD ELONGATED HOLES WHERE THE CABLES ATTACHED AND THE TSDR 9609846719Ratio Changer · failedDURING CLIMB, THE RUDDER RATIO LIGHT ILLUMINATED AFTER RETRACTING THE FLAPS. RESET CIRCUIT BREAKER AND LIGHT REMAINED ILLUMINATED. AIRCRAFT RETURNED TO MSP AND LANDED WITHOUT INCIDENT. REPLACED THE UPPER RUDDER RATIO CHANGER. FLAP OPERATIONAL CHECK GOOD.SDR SIMA961241Rudder Console · corrosionLAW - DURING MAINTENANCE, 'EM-5' CHECK, FOUND THE LEFT/RT RUDDER CONSOLES CORRODED AT THE CASING FLOOR ATTACH POINTS. THE LT/RT CONSOLES P/N 7227200-641 WERE REPLACED IAW SAAB AMM 27-21-05. AIRCRAFT WAS RETURNED TO SERVICE. (M)
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