JASC 2710

Service difficulty reports · 2,967

Reports filed under 2710 · Aileron 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 = '2710'
  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.

SDR 2003FA0000558Bearing · 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 ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING.May 12, 2003 · N863AF · Grob G120ASDR 2003FA0000557Bearing · failedDURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.May 12, 2003 · N862AF · Grob G120ASDR 2003FA0000555Bearing · failedDURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.May 12, 2003 · N865AF · Grob G120ASDR 2003FA0000554Bearing · failedDURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.May 12, 2003 · N867AF · Grob G120ASDR 2003FA0000553Bearing · failedDURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.May 12, 2003 · N867AF · Grob G120ASDR 2003FA0000552Bearing · failedDURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAINING CLIP AND SEAL WERE BEING FORCED OUR OF BEARING.May 12, 2003 · N865AF · Grob G120ASDR 2003FA0000548Bearing · failedDURING INSPECTION FO 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 ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. REMay 12, 2003 · N867AF · Grob G120ASDR 2003FA0000546Bearing · 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 ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. REMay 12, 2003 · N862AF · Grob G120ASDR 2003FA0000544Bearing · 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 ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. REMay 12, 2003 · N864AF · Grob G120ASDR 2003FA0000543Bearing · 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 ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. REMay 12, 2003 · N864AF · Grob G120ASDR 2003FA0000542Bearing · 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 CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. RECOMMMay 12, 2003 · N861AF · Grob G120ASDR 2003FA0000541Bearing · 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 ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. REMay 12, 2003 · N867AF · Grob G120ASDR 2003FA0000540Bearing · 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 ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. RECMay 12, 2003 · N865AF · Grob G120ASDR 2003FA0000538Bearing · 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 ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. REMay 12, 2003 · N861AF · Grob G120ASDR 2003FA0000536Bearing · 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 ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING.May 12, 2003 · N863AF · Grob G120ASDR 2003FA0000535Bearing · 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 ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF BEARING. RECOMMMay 12, 2003 · N862AF · Grob G120ASDR 2003FA0000534Bearing · 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 ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. RECOMMEND DESIGN CHANGE OR REPLACEMay 12, 2003 · N861AF · Grob G120ASDR SWAA031071Bearing · wornDURING SCHEDULED SERVICE CHECK, FOUND AILERON CONTROL WHEEL SLOW WHEN RETURNING FROM LEFT TURN. REMOVED AND REPLACED AILERON CONTROL UPPER SHAFT BEARING PER MM.May 10, 2003 · N721WN · Boeing 7372T4SDR CA030514002Link · worn(CAN) AFTER T/O AT APPROX 4,000 FT CREW COMPLAINED ABOUT AN AIRFRAME HARMONIC VIBRATION. NO EICAS MSGS WERE POSTED & ENGINE VIBRATIONS AND PARAMETERS WERE NORMAL .AT 16,000 FT A/P DISCONNECTED, APPROX 10-20 SECONDS LATER A/C ROLLED TO THE RT, F/O BROUGHT THE May 8, 2003 · Cndair CL6002B19SDR QXEA0300547Aileron · out of adjustLWS-ON FLIGHT NUMBER 2710, CREW NOTICED CONTROLS WERE HEAVY. ADJUSTED AILERON CABLE TENSION AND SPOILER SYSTEM. OPERATIONAL CHECK GOOD. NO PARTS REPLACED. AIRCRAFT RETURNED TO SERVICE.May 8, 2003 · N357PH · Dhav DHC8202SDR COMA0360221Pulley · frozenFOUND AILERON CABLE PULLEY FROZEN IN RIGHT WING NEAR THE INBOARD AILERON HINGE POINT. W.S. 282.0 DURING E.O. 27-081A. REMOVED DEFECTIVE PULLEY AND INSTALLED A SERVICEABLE PULLEY.May 2, 2003 · N971CA · Cndair CL6002B19SDR A6WA200360025Warning Light · illuminatedMWS RUDDER VALVE LIGHT IS ILLUMINATED IN FLIGHT AFTER DEPARTURE. AIR RETURN TO ORD. RESET ABD, TESTED IAW.May 1, 2003 · N292UE · Bac 146200ASDR AUS20030500Control Cable · frayed(AUS) AILERON CABLES PNO C6CW1031-1 (2OFF) AND PNO C6CW1032-1 CONTAINED BROKEN STRANDS IN AREA OF WING ROOT FAIRLEADS.Apr 24, 2003 · Dhav DHC6200SDR CA030424001Lever · fractured(CAN) DEPARTING THE CREW FOUND ABNORMAL CONTROL INPUT WAS REQUIRED TO MAINTAIN THE AIRCRAFT LEVEL. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WHERE MAINTENACE FOUND A BROKEN LT AILERON CONTROL LEVER. THE MOUNTING FOOT ONTHE FORWARDOUTBOARD CORNER WAS FRACTUREApr 18, 2003 · Braero HS7482ASDR CA030417011Pcu · inoperative(CAN) AFTER PUSHBACK AND START, FLAP 2 SELECTED AND HYDRAULIC SYSTEM A LOW PRESSURE ILLUMINATED AND HYD QTY GUAGE DECREASED TO ZERO. MAINTENANCE FOUND THE A SYSTEM AILERON POWER CONTROL UNIT (PCU) FILTER BOWL HAD FRACTURED RESULTING IN LOSS OF HYD PRESS/FLUID.Apr 15, 2003 · Boeing 7372T5SDR 2003FA0000520Linkage · out of adjustDURING ANNUAL INSPECTION, FOUND THE AILERON TRIM TAB LINKAGE RUBBING ON LEADING EDGE OF AILERON. UPON INVESTIGATION AND CONVERSING WITH MFG TECH, FOUND THE TRIM TAB LINKAGE ARM (PN 451350393) WAS INSTALLED 180 DEGREES OUT, WITH THE SHORT END HOOKED TO THE ACTApr 9, 2003 · N1066H · Beech 58SDR CA030409014Bellcrank · cracked(CAN) FOUND BRACKET CRACKED FOR A LENGTH OF ABOUT 2 CENTIMETERS JUST BELOW FORWARD BOLT HOLE. DEFECT CAN ONLY BE SEEN WITH INSPECTION MIRROR FROM OUTBOARD INSPECTION HOLE.Apr 8, 2003 · Piper PA28160SDR 2003FA0000392Bearing · failedDURING PROGRESSIVE INSPECTION OF THE AIRCRAFT THERE WAS A STRANGE SOUND FROM THE AILERON SYSTEM. FURTHER INVESTIGATION REVEALED THAT THE BEARING FROM THE LT AILERON ASSEMBLY WAS COMING APART. PROBABLE CAUSE IS DESIGN OF AILERON LEVER ASSEMBLY. THE ANGLE ANDApr 7, 2003 · N865AF · Grob G120ASDR 03FDEA00381Brush Holder · detachedN 517 RT WING ALL SPEED AILERON LWR BRUSH ASSY HAS BECOME DETACHED FROM STRUCTURE. REMOVED AND REPLACED BRUSH ASSY. IAW/SRM 51-40-21 PG.7 UNDER W/O NO. 13350 FEDEX 04/04/2003.Apr 3, 2003 · N443FE · Airbus A310SDR PCAA0304065Servo · failedACFT HAD DEAD SPOT LT AILERON ROLL. PITCH TRIM STIFF & OVER RESPONSIVE TO UP. MX OP CHECKED ROLL SPOILERS & CHECKED RIGGING OF AILERON CABLE CIRCUIT. CABLE TENSION ADJ FROM CONTROL WHEEL TO SPLITTER QUADRANT. TRIM CABLES, TRAVELS & RIGGING CHECKED. AILEROApr 2, 2003 · N804EX · Dhav DHC8102SDR 2003UALA00359Aileron · malfunctionedFLT EXPERIENCED AILERON PROBLEMS PRIOR TO LANDING. AUTOPILOT WARNING RECEIVED. DISCONNECTED AUTO PILOT. AIRPLANE COULD NOT TURN LEFT (RIGHT TURNS OK).Apr 1, 2003 · N175UA · Boeing 747422SDR AUS20030383Pin · missing(AUS) LT AILERON CHAIN CLEVIS BOLT SPLIT PINS MISSING AND TOP NUT LOOSE. THE AIRCRAFT HAD ONLY FLOWN FOR TWO HOURS SINCE THE LAST ANNUAL INSPECTION.Mar 27, 2003 · Cessna 172NSDR CA030330002Pulley · seized(CAN) FLT CREW REPORTED A/P TRIM CAUTION MSG ACCOMPANIED WITH FLASHING 'A' ON THE PFD WHILE CLIMBING THROUGH 25,000 FT (OAT -25C). AFTER A/P WAS DISENGAGED, THE AILERONS WERE NOTABLY STIFF. AN EMERGENCY WAS DECLARED AND THE CREW ELECTED TO DIVERT.UPON REACHINMar 25, 2003 · Cndair CL6002B19SDR 021081FControl Rod · corrodedRT AILERON PUSH PULL TUBE CORRODED SEVERELY. HOLE WORE THROUGH. LOCATED BEHIND ENGINE. RECOMMEND SPECIAL ATTENTION BE PAID TO THIS AREA DURING INSPECTIONS.Mar 25, 2003 · N6902 · Piper PA60602PSDR CA030327002Servo · failed(CAN) ON CLIMB AT 15,000 SIGNIFICANT CYCLIC VIBRATION FELT AT 315 KTS.PROBLEM REDUCED AT SLOWER SPEED AND WORSE WHEN TURNING. RT AILERON SERVO ACTUATOR REPLACED AS PER AMM.Mar 24, 2003 · Airbus A320211SDR 2003FA0000377Motor · damagedSHAFTED IN ROLL, TRIM MOTOR ASSEMBLY SHEARED IN FLIGHT, DURING LANDING APPROACH. THE PILOT RETAINED CONTROL AND A SAFE LANDING WAS ACCOMPLISHED. NO FURTHER DAMAGE WAS FOUND DURING INSPECTION OF THE TRIM SYSTEM, AILERON AND LEFT WING. THE CAUSE OF THIS FAILUMar 21, 2003 · N508JS · Cirrus SR20SDR VNAA0303028Aileron · bindingTHE CREW REPORTED THE AILERONS BIND AT THE NEUTRAL POSITION. MAINTENANCE INSPECTED AILERONS AND CABLES NO DEFECTS NOTED. MAINTENANCE REMOVED AND REPLACED CAPTAIN'S YOKE COVER IN ACCORDANCE WITH DORNIER MAINTENANCE MANUAL 27-31-01. PERFORMED OPERATIONAL CHECMar 21, 2003 · N429JS · Dorner DO328100SDR COMA0360159BellcrankAILERON CONTROLS PARTIALLY JAMMED IN FLIGHT WITH AP TRIM LWD CAUTION.COULD NOT DUPLICATE - DISCREPANCEY ON GROUND - CLEANED AND LUBED AILERON BELLCRANKS AND ADJUSTED WHEEL BIN SPLASH GUARDS I/A/W COMAIR E.O. 27-069 RB.Mar 20, 2003 · N915CA · Cndair CL6002B19SDR CA030327003Bearing · failed(CAN) DURING CLIMB IN MANUAL FLIGHT , BEOND 5 DEG. LT WHEEL DEFLECTION AILERONS FELT VERY HEAVY 9 AS IF IN MANUAL REVERSION ) AT THIS POINT IN TIME RUDDER TRIM 0 UNITS AND ADI BALL CENTERED. AILERON TRIM 1/2 UNIT LT IN STABLE CRUISE. AILERON TOWER SHAFT UPPER Mar 12, 2003 · Boeing 7372T7SDR 2003UALA00259Actuator · leakingCENTER HYDRAULIC SYSTEM QUANTITY EICAS MESSAGE. SYSTEM SECURED AT .23. EXCESSIVE HYDRAULIC LEAKAGE FROM LEFT AILERON POWER CONTROL ACTUATOR (PCA). REPLACED SUBJECT ACTUATOR WITH SERVICEABLE UNIT.Mar 10, 2003 · N548UA · Boeing 757222SDR QXEA0300319Actuator · inoperativeSEA ON FLIGHT 2516- ABORTED TAKEOFF DUE TO TAKEOFF ROLL CONFIG/AILERON WARNING AND AURAL WARNING. TAKEOFF CONFIG OKAY. ADVISORY MESSAGE WAS PRESENT. REMOVED AND REPLACED AILERON TRIM ACTUATOR. OPERATIONAL CHECKS GOOD. AIRCRAFT RETURNED TO SERVICE.Mar 4, 2003 · N614QX · Cndair CL6002C10SDR QXEA0300312Actuator · failedPDX - FLIGHT 2083 - ON CLIMBOUT, MORE PRESSURE THAN NORMAL WAS REQUIRED TO ROLL THE AIRCRAFT TO THE LEFT. AIRCRAFT RETURNED TO FIELD. MAINTENANCE INSPECTED THE AIRCRAFT AND REPLACED THE LEFT INBOARD ROLL SPOILER ACTUATOR. OPERATIONAL CHECKS WERE GOOD AND THE AMar 1, 2003 · N357PH · Dhav DHC8202SDR 2003UALA00238Fitting · crackedCRACKED AILERON FITTINGS ON A/C. LEFT AILERON INBOARD FITTING - CRACKED HORIZONTAL FLANGE INBOARD AND OUTBOARD SIDES. RIGHT AILERON INBOARD FITTING - CRACKED HORIZONTAL FLANGE INBOARD SIDE. SUPPLEMENTAL DATA UPDATE CRACKED FITTING DISCOVERED DURING NDT INSPECTFeb 26, 2003 · N768UA · Boeing 777222SDR CA030220008Control Cable · frayed(CAN) AILERON DIRECT CABLE FRAYED AT NYLON PULLEYS IN CABIN ROOF AREAFeb 20, 2003 · Cessna A185ESDR COMA0360110Trim SwitchFLIGHT 9458 AILERON MASTER CAUTION, T/O ABORTED.FOUND AILERON TRIM OUT OF THE TAKE OFF RANGE.Feb 20, 2003 · N986CA · Cndair CL6002B19SDR UPS03240272Hinge · corrodedINSPECTION TYPE: C+SI, LT WING O/B AILERON BEARING HINGES (4 OFF) CORRODED. LEFT O/B AILERON REPLACED IAW MM 27-10-14.Feb 18, 2003 · N936UP · Boeing 727108CSDR UPS03240262Aileron · corrodedINSPECTION TYPE:C&SI CORROSION ON O/B R/H AILERON HINGES 2, 3 & 4 ON INVESTIGATION OF HINGE ASSYS, HINGES FOUND TO BE CORRODED BEYOND ALLOWABLE LIMITS IAW SRM 57-50-11. INSTALLED REPLACEMENT AILERON IAW MM 27-10-14. REF. NRC 632179 FOR AILERON RIGGING & Feb 18, 2003 · N936UP · Boeing 727108CSDR AUS20030227Control Cable · misrigged(AUS) FLIGHT CONTROL PROBLEMS. SUSPECT CAUSED BY AILERON CONTROL SYSTEM RIGGING. PROBLEM WAS FOUND TO BE AN INHERENT CHARACTERISTIC OF THIS SERIES AIRCRAFT.Feb 17, 2003 · Dhav DHC8202SDR CA030312008Control Cable · failed(CAN) AILERON CONTROL JAM. ACTION QRH ESTABLISHED THAT PILOT SIDE WAS OPERATING CHANNEL. CONTROL ON CO-PILOT AILERON, FULL CONTROL FOR AILERON UP. AILERON MOTION FROM APPROX NEUTRAL AND DOWN NON EXISTENT. CONTROL ON CAPTAIN SIDE WAS FULL AND FREE. FOUND RT AFeb 14, 2003 · Cndair CL6002B19SDR WRNA200300005SwitchFlight control servo control lever lock circuit breaker tripsCorrective Action: Removed and replaced low speed aileron green system actuator micr-switch assy. ops checked good.Feb 14, 2003 · N820SC · Airbus A300B4203
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