JASC 2730
Service difficulty reports · 2,649
Reports filed under 2730 · Elevator 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 = '2730' 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 = '2730' 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 UALA2011050502216Actuator · faultyELAC 2 PITCH FAULT DISPLAYED ON UPPER ECAM SCREEN - F-CTL. CREW COMMENTS: HAPPENED AFTER TAKEOFF. REPLACED ELAC 2. ACP'D LAND TEST. ALL GND TESTS GOOD, A-C IN CAT III STATUS. FAULT RECURRED. ELAC PREVIOUSLY REPLACED. REPLACED PITCH TRIM ACTUATOR. LEAKSDR UALA2011050202155Pca · faultyP ELEV PCU STATUS MSG. TEST OK PER MEL. FOUND RIGHT CENTER SYSTEM ELEVATOR PCA FAULTING, REPLACED PCA PER MM.SDR UALA2011042902106Servo · leakingLEFT SIDE SERVO ELEVATOR GREEN SYSTEM LEAK FROM BODY. REPLACED LT SIDE SERVO ELEVATOR ACTUATOR GREEN SYSTEM 34CE1 PER AMM, NO LEAKS AND ALL TESTS OKAY.SDR UALA2011042501974Yaw Damper · leakingFLUID DRIPPING FROM ELEV CTRL ACCESS DOOR AND BOTH SIDES OF TAIL CONE. FOUND LEFT YAW DAMPER LEAKING AT 5-10 DROPS PER MINUTE, WITHIN LINE MAXIMUM DISPATCH LIMITS, CARRY FORWARD LEAKAGE LIMITS PERMIT CONTINUED AIRCRAFT OPERATION FOR A MAXIMUM OF 75 FLT HOURS,SDR DJFA2011015Actuator · shearedAFTER ENGINE START, THE CREW REPORTED PITCH AND ROLL CONTROL FELT AS THOUGH IT WAS BINDING. MX FOUND THE PITCH FEEL ACTUATOR TO BE SHEARD AT THE ROD END. THE PTICH FEEL ACTUATOR WAS REPLACED.SDR UALA2011042501981Elevator · vibrationPILOT REPORTS FUSELAGE SHUDDERS DURING CONTROL COLUMN CHECK WHEN YOKE IS PULLED BACK FULLY AND THEN RETURNED TO NEUTRAL POSITION. ACCOMPLISHED FIM TASK 27- 31 TASK 904, 'NOISE & VIBRATION DURING ON-GRD ELEVATOR CONTROL SURFACE MOVEMENT NO VIBRATION NOTED WHENSDR 2011FA0000254Nut · backed outINSPECTION AFTER ACFT RECEIVED FROM PAINT SHOP FOUND LT ELEVATOR ACTUATING ROD NUT UNPINNED AND BACKED OFF ALMOST COMPLETELY AND BOLT BACKING OUT. LT AILERON OTBD HINGE NOT ATTACHED. HINGE PLATE PINCHED BETWEEN SKIN. AILERON BINDING. THIS ACFT HAS BEEN FLOWSDR UALA2011041801882Rod End · faultyAIRFRAME TAIL VIBRATION DURING CLIMB. GROSS WT LASTED UNTIL FL 300. MAINT TEXT: CREW REPORTS THERE WAS NO YAW DURING VIBRATION. NO VISIBLE ANOMALY OBSERVED ON HORIZONTAL STAB. ACCOMPLISHED MT-005 REV G VIBRATION TROUBESHOOTING. ELEVATOR SERVO CONTROL FREESDR YENA20110417234Computer · failedFLT 817 JFK-SDQ, CREW DECLARED EMERGENCY AND AIRCRAFT DIVERTED TO MCO DUE TO DURING CRUISE AT FLT FL350 RECEIVED ECAM "F/CTL ALTN LAW" (PROT LOST). T/S CFDS POST FLIGHT, FOUND ELAC NR 1 FAULTED. REMOVED AND REPLACED ELAC NR 1 PER AMM 27-93-34-04. OPS CHECK SDR 2011FA0000279Control Cable · failedDURING TOUCH AND GO`S, AFTER COMPLETING THE SECOND TOUCH AND GO, AND WITH FULL POWER IN A CLIMB AT AN ALTITUDE OF APPROX 15 FEET, THE NOSE OF THE ACFT PITCHED DOWN ABRUPTLY. THE ACFT NOSE GEAR CONTACTED THE RUNWAY VERY HARD, FOLLOWED IMMEDIATELY BY THE MAIN SDR UALA2011032501417Servo · faultyFLIGHT ATTENDANT REPORTS VIBRATION IN BACK OF ACFT STRONG. CLIMBING BETWEEN 24000 & 36000 FT, SPEED 300 KTS PITCH SET AT 4 DEG NOSE UP, VIB FELT IN FWD & AFT, LOWERING NOSE TO 3 DEG PITCH UP DECREASED VIB. REPLACED LEFT BLUE AND GREEN ELEV SERVO CONTROL EYE SDR UALA2011032401409Computer · faultyAT SHUTDOWN ECAM F-CTL SIDESTICK PRIORITY. REPLACED NR 1 ELAC PER MM. ACCOMPLISHED ELAC TEST, REF MM AND AFS TEST, REF MM AND LAND CAT III TEST, REF MM. ALL TESTS PASS.SDR DXTA2011032104518Elevator System · frozenAFTER LEAVING CRUISE FLIGHT AT FL400 WITH AUTOPILOT ENGAGED IN VS MODE, AIRPLANE STARTED TO OSCILLATE IN PITCH WHILE DESCENDING THROUGH FL 300 AS INDICATED AIRSPEED INCREASED. AUTOPILOT WAS DISCONNECTED AND ATTEMPTED TO USE ELECTRIC TRIM WITH NO RESULTS. ATTEMSDR 2011FA0000184Torque Tube · corrodedELEVATOR TORQUE TUBE HAS INTERNAL CORROSION INSIDE TORQUE TUBE WITH RUST CONCENTRATION AROUND WELDED AREAS. AMM CHAP 27-30-00, PAGE 3 ITEM 2(C)(3) STATES TO INSPECT EVERY 200 HRS OR ANNUAL FOR INTEGRITY, EXCESSIVE WEAR, AND CRACKS. INSPECT WELD FOR CRACKS. TSDR F3LA2011032100616Servo · slowON ROTATION ACFT ROLLS RT REGARDLESS OF WIND. PERFORMED FLT CONTROL MOVEMENT CHECKS FOUNFD LT ELEVATOR SERVO SLOW TO REACT. REF LP 596444, ITEM 1, R & R SERVO CONTROL ELEVATOR LT GREEN HYD REF AMM 27-34-51-400-001 AND 27-34-51-0000.001, OPS CHECK NORMAL.SDR UALA2011031501232Actuator · leakingLT ELEVATOR L ACTUATOR LEAKING. REPLACED ELEVATOR PCA PER MM, OPS NORMAL. CONFIRMED INSTALLATION OF LEFT CENTER SYSTEM ELEVATOR PCA PER MM. LINES SECURE AND ALL BOLTS TORQUED. NO LEAKS NOTED.SDR NX4R00006AControl Cable · wornDURING A 100 HR INSP, THE "UP" ELEVATOR CABLE WAS FOUND WORN AT FS-65.33. THE CABLE HAD MANY STRANDS WORN GREATER THAN 50 PERCENT THROUGH.SDR UALA2011031101184Computer · faultedCREW REPORTED ELEVATOR FORCES ABNORMALLY HEAVY. RT SYSTEM ELEV PCA AT LT ELEVATOR (OTBD) IS LEAKING AT ROD END. OPERATED AILERONS. NO LEAKS NOTED. SUSPECT COLD SOAK LEAK. UNABLE TO DETERMINE IF LEAK IS FROM LT INBD OR LT OTBD PCA DUE TO RESIDUAL HYD FLUISDR 2011FA0000167Bellcrank · brokenDURING ANNUAL INSP, FOUND ELEVATOR BELLCRANK PN 0411258 WITH A BEARING THAT CAME LOOSE FROM IT'S SWAGED MOUNTING. THE ONLY THING THAT KEPT IT FROM FALLING OUT COMPLETELY WAS THE FORK ROD THAT CONNECTS TO THE CONTROL COLUMN. ONCE THIS ROD WAS REMOVED THE BEARSDR A6WA201140171Elevator System · stiffABNORMALLY HEAVY FLIGHT CONTROL FEEL WHEN DOING ELEVATOR CHECKS ( FLAPS AT -0- DEGREES OR 20 DEGREES. PERFORMED OPS TEST AND FREEDOM OF MOVEMENT OF ELEVATORS REF AMM 27-31-00. OPS CHECKED GOOD. PERFORMED FUNCTIONAL TEST OF PITCH SIMUALTOR UNITS IAW AMM 27-3SDR UALA2011030401076Rod End · wornLT ELEVATOR OTBD SERVO FAILS EXCESSIVE PLAY CHECK PER MM. REPLACED OTBD SERVO EYE-END. COMPLETED INSTALLATION UP TO PARAGRAPH A(6) OF MM.SDR DXTA2011030304488Bungee · bindingJAMMED ELEVATOR CONTROL IN FLIGHT. REQUIRED FLIGHT CONTROLS TO BE SPLIT IN FLIGHT. R & R THE VARIABLE FEEL BUNGEE ON RT ELEVATOR IAW THE MM CH 27-33-00. OPS CHECK IS GOOD. R & R ELEVATOR PITCH MODULE NK122 IAW MM CH 24-53-00 OPS CHECKS ARE GOOD.SDR 2011FA0000154Control Cable · brokenAFTER TAKEOFF PILOT HEARD A "SNAP". ACFT PITCHED UP. PILOT REALIZED HE HAD LOST DOWN ELEVATOR CONTROL. PILOT REGAINED CONTROL BY USE OF TRIM CONTROL AND POWER REDUCTION. ACFT RETURNED FOR A SUCCESSFUL LANDING. NOTE: THE TOTAL TIME ON THE CABLE IS UNKNOWSDR UALA2011021500789Rod End · faultyMODERATE TAIL VIBRATION, RTFL. VIBRATION CHECKLIST FILLED OUT BY CREW, SHOWS VERTICAL BOUNCE. FOUND PLAY AT ELEVATOR SERVO CONTROL ROD ENDS, REPLACED ELEV SERVO CONTROLS 34CE4 AND 34CE3 IAW AMM AND ROD ENDS OF SERVO CONTROLS 34CE1 AND 34CE2 IAW AMM, TESTS OKSDR CA110209029Control Cable · frozenPILOT REPORTED THAT AS THE ACFT FLARED FOR LANDING THE PITCH CONTROL FELT LIKE IT WAS IN MANUAL REVERSION, REALLY STIFF. ONCE IN THE FLARE WITH MAIN WHEELS ON THE GROUND THE CREW PULLED EVEN HARDER TO STOP THE NOSEWHEEL FROM SLAMMING DOWN AND SUDDENLY THE PITSDR UALA2011020100554Pcu · no testACE MONITOR TEST FAILED MSG27-13004. FOUND ACTIVE MESSAGE 27-10116. LT INBD ELEVATOR PCU PRESSURE REDUCER SOLENOID OPERATED VALVE IS NOT IN COMMANDED POSITION. TRIED NEW ACE- NO HELP. VERIFIED 28 VDC AT PCU CONNECTOR IAW FIM. IAW FIM WIRE CHECKS OK FROM ASDR ASOA201100273Transducer · failedSTALL FAIL CAUTION MESSAGE IN FLIGHT AT FL280, STAYED ON REMAINDER OF FLIGHT. COMPLIED WITH QRH. (EMERGENCY DECLARED) R & R RT TRANSDUCER IAW AMM 27-35-05. PERFORMED OPS TEST OF TRANSDUCER IAW AMM 27-35-05-710-801 AND AIR DATA SENSOR HEATER CONTROLLERS IAW SDR CA110131001Pcu · broken(CAN) WHILE PERFORMING TASK CARD 000-27-220-010 (OPERATIONAL CHECK OF EACH ELEVATOR PCU) ON HYDRAULIC SYSTEM #1 THE R/H ELEVATOR AFTER BEING PUSHED TO THE NOSE UP POSITON IT WOULD NOT RETURN TO THE NEUTRAL POSITION. AFTER REMOVING ACCESS PANEL TO INSPECT ELEVASDR DXTA2011010704402Warning Message · illuminatedAFTER TAKEOFF "PITCH FEEL FAIL" CAS MESSAGE ILLUMINATED. COMPLETED CHECKLIST AND RETURNED TO LAND. PERFORMED PITCH FEEL SYS FUNCTIONAL CHECK IAW MM 27-30-00. ALL DMU VALUES WITHIN LIMITS AT THIS TIME AND PITCH FEEL SYS, OPS CHECKED GOOD.SDR ANCF2011010500073Computer · malfunctionedAIR TURNBACK. PILOT REPORT: AFTER TAKEOFF AIL SERVO FAULT FCTL ALT LAW PROTECTION LOST. IAW AMM TASK 27-93-34-000-001 / 27-93-34-400-001 ELAC N° 2 WAS REMOVED AND REPLACED. OPERATIONAL TEST OF ELAC WAS PERFORMED AMM TASK 27-93-00-710-001.SDR YENA20110103190Servo · failedFLT 735 JFK-BQN, AIR RETURN TO JFK DURING CLIMBOUT APPROX 17,000 FEET FELT MODERATE VIBRATION THROUGHOUT ENTIRE AIRCRAFT. TURNED OFF AUTOPILOT APPLIED LIGHT PRESSURE TO RIGHT RUDDER. PERFORMED BACKLASH CHECK AND REPLACED RUDDER SERVO CONTROL 1025GM, 2025GM, SDR YENA20110103189Servo · failedFLT 735 JFK-BQN, AIR RETURN TO JFK DURING CLIMBOUT APPROX 17,000 FEET FELT MODERATE VIBRATION THROUGHOUT ENTIRE AIRCRAFT. TURNED OFF AUTOPILOT APPLIED LIGHT PRESSURE TO RIGHT RUDDER. PERFORMED BACKLASH CHECK AND REPLACED RUDDER SERVO CONTROL 1025GM, 2025GM, SDR YENA20110103188Servo · failedFLT 735 JFK-BQN, AIR RETURN TO JFK DURING CLIMBOUT APPROX 17,000 FEET FELT MODERATE VIBRATION THROUGHOUT ENTIRE AIRCRAFT. TURNED OFF AUTOPILOT APPLIED LIGHT PRESSURE TO RIGHT RUDDER. PERFORMED BACKLASH CHECK AND REPLACED RUDDER SERVO CONTROL 1025GM, 2025GM, SDR UALA2010123004781Actuator · faultyHEAVY ELEVATOR CONTROL FORCES NEEDED. IAW THE FLIGHT CREW ELEVATOR NEEDED MORE PRESSURE THEN NORMAL TO MOVE. REPLACED ELEV FEEL ACTUATOR IAW MM, LEAK CHECK AND TEST GOOD.SDR REXA201000336Bushing · wornCREW REPORTS A INFLIGHT AIRFRAME VIBRATION. UPON INSPECTION, MAINTENANCE FOUND THE RT ELEVATOR PCU LINGAGE BUSHINGS WORN P/N: 600-10300-563. MAINTENANCE REPLACED ALL BUSHINGS AND BOTH ELEVATORS PASSED BACKLASH.SDR UALA2010122704710Actuator · faultyELEVATOR ASYMMETRY STATUS MESSAGE ON TAXI IN. REPEAT WU. RT STAB TRIM MODULE SHOWS LIMIT ASYMMETRY ACTUATOR. SAM BOX PREVIOUSLY REPLACED. REPLACED ELEVATOR ASYMMETRY ACTUATOR. OPS NORMAL.SDR REXA201000333Elevator · wornAIRCRAFT EXPERIENCED MODERATE TO LOW VIBRATION IN CRUISE AT 280-300 KNOTS. NO ABNORMAL INDICATIONS. MAINTENANCE FOUND RT ELEVATOR BOLTS AND BUSHINGS WORN TOO LIMITS (P/N HTS22-DU5-22 AND NAS538B7P13).SDR YENA20101220170Servo Control · out of limitsFLT 1797 FLL-SDQ, AIR RETURN TO FLL - DURING CLIMBOUT OF 27,000 FEET EXPERIENCED EXTREME AIRFRAME VIBRATION. AUTO PILOT WAS DISCONNECTED AND AIRCRAFT WAS LEVELED OUT. VIBRATION STOPPED MOMENTARILY, THEN RESUMED WHEN CLIMB INITIATED. PERFORMED CHECK OF ELEVASDR UALA2010122004636Module · faultySTATUS MESSAGE: "ELEV ASYM" REPLACED STAB TRIM-AIR LOCK-ASYM-MODULE PER MM, GROUND CHECK NORMAL.SDR CALA2010121600622Pca · leakingC HYD QTY LIGHT CAME ON IN FLIGHT FOUND LT ELEV INBOARD PCA LEAKING. R&R LT ELEV INBRD PCA. PER A/C M/M 27-31-05 UP TO AND INCLUDING STEP 15 OF PG 413, SEE N/R 4457919 FOR COMPLETION OF INSTALLATION AND OPS & LEAK CHECK. ROTABLE PARTS CHANGE WAS INDICATED - SDR CA101130013Support · distortedDURING ANNUAL INSPECTION, IT WAS DISCOVERED THAT THE ELEVATOR DOWN STOP BRACKET WAS NOT FULLY INSTALLED FROM THE FACTORY. EIGHT RIVETS ON THE LOWER SUPPORT ASSEMBLY WERE NOT INSTALLED. THIS ALLOWED THE SUPPORT BRACKET TO BEND OUT OF PLACE AND AFFECTED TRAVELSDR CA101125004Bellcrank · misinstalledBELL-CRANK FOUND INSTALLED UPSIDE DOWN. JOGGLE CAUSES INTERFERENCE WHEN INSTALLED UPSIDE DOWN. LOWER CLEVIS RUBS AFT BULKHEAD CLEARANCE OPENING. PARTS CATALOGUE DOES NOT SHOW ORIENTATION OF JOGGLE ON THE BELL-CRANK.SDR UALA2010112404340Control Column · stiffSTICK FORCES VERY HEAVY. PITCH CONTROL ON GROUND TEST AND DURING LANDING FLARE OUT VERY HEAVY. ACCOMPLISHED ELEVATOR FEEL SYSTEM FORCES TEST PER MM. CHECKED WITHIN LIMITS.SDR USAA20101122BB078Roller · defectiveCLT FLT 1794 EN ROUTE LAS TO CLT. REPORTED AS: "THE CAPTAIN'S AND FIRST OFFICER'S CONTROL COLUMN'S "STICK" WHEN MOVING THROUGH NEUTRAL POSITION TOWARD UP OR DOWN. MOST NOTICEABLE ON TAKEOFF, APPROACH, AND LANDING. CAUSED ABRUPT AIRCRAFT "BUMP" WHEN BREAKSDR HALA2010111400535Actuator · defectiveETOPS SIGNIFICANT SYSTEM - BTB - BTB ELEVATOR CONTROL IS BINDING. NOTICED FROM BOTH CAPT AND F/O YOKES. OPS CHECK RT ELEVATOR LT, CT, RT PCA NO LEAKS NOTED. NO TEMPTURES DIFFERENCE. 5897. PERFORMED FIM TASK 27-31-00 FIG 105 SH1 STEP2. 8088. FOUND ELEVATORSDR CA101112005Torque Tube · cracked(CAN) ELEVATORS WERE REMOVED TO CARRY OUT MANDATORY SERVICE BULLETIN 2145 INSPECTION/REPLACEMENT OF ELEVATOR TORQUE TUBE. NDT COMPANY CARRIED OUT FLUORESCENT LIQUID PENETRANT INSPECTION ON LEFT AND RIGHT TORQUE TUBE ASSYS P/N 115-610010-325. THEY FOUNDED A CSDR HALA2010110700526Cable · brokenFOUND FLAP BUS TO ELEVATOR SERVO FORCE LIMITER CABLE BROKEN IN RT WHEEL WELL. FOUND TO BE FLAP INPUT TO ELEVATOR SERVO LIMITER CABLE, REMOVED & FABRICATED NEW CABLE IAW AMM 91-10-02 INSTALLED CABLE. RIG & OPS PEND IAW AMM 20-00-02. RIGGED & OPS CHECK GOOD ISDR DXTA2010110804294Elevator · unknownJUST PRIOR TO ROTATION AFTER V1 ELEV TRIM LIGHT CAME ON, ACFT FELT NOSE HEAVY, TRIM WAS SET IN THE PROPER LOCATION. ADJUSTED LEFT ELEVATOR TO NEUTRAL POSITION & ELEVATOR TRIM TABS TO NEUTRAL POSITION. CHECKED ELEVATOR AND ELEVATOR TRIM, TRAVEL OK. ADJUSTED SDR DXTA2010110304287Push-Pull Rod · looseDURING FLT VIBRATION FELT IN ACFT AIRFRAME. VIBRATION INCREASED WITH ACFT AIRSPEED & NOT ENGINE SPEED. VIBRATION WORSE TOWARD REAR OF ACFT. VIBRATION WAS NOT FELT BELOW 190 KTS, BUT INCREASED PROGRESSIVELY AS SPEED INCREASED. CHANGING ACFT ATTITUDE DID NOT CSDR CA101102004Torque Tube · corroded(CAN) DURING A ROUTINE PHASE INSPECTION, A BLACK OXIDE AROUND THE FASTENERS WAS DISCOVERED ON THE RT HORN OF THE RT ELEVATOR TORQUE TUBE INDICATING WEAR. UPON FURTHER INSPECTION MOVEMENT BETWEEN THE HORN AND THE ELEVATOR TORQUE TUBE WAS APPARENT. THE MANUFAC
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