Grob-Werke G 120A

Service difficulty reports · 225

Newest first. General aviation reporting is voluntary.

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 aircraft_model_key = 'G120A'
  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 CA190611008Inertia Reel · inoperative(CAN) SHOULDER HARNESS LOCK FAILED. INERTIA LOCK IS STILL FUNCTIONAL BUT THE MANUAL LOCK (FOR AEROBATIC FLIGHT) IS NOT WORKING. HARNESS ASSEMBLY REPLACED. (TC# 20190611008)Jun 11, 2019 · Grob G120A · Emergency EquipmentSDR CA190208015Buckle · broken(CAN) DURING A 200 HR INSPECTION THE AME NOTICED THE SEAT BUCKLE PAD WAS SEPARATED FROM THE BUCKLE AFTER DISASSEMBLY IT WAS NOTICED THAT TWO OF THE 4 ATTACH SCREW HOLES HAD BEEN BROKEN FROM THE BACK OF THE BUCKLE A THIRD SCREW HOLE HAD NUMEROUS CRACKS THE SEATFeb 8, 2019 · Grob G120A · Emergency EquipmentSDR 2018FA0000047Handle · brokenCO-PILOTS CONTROL STICK SHELL BROKEN DURING AIRCRAFT CLIMB.Jan 25, 2018 · N193TP · Grob G120A · Control Column SectionSDR 2017FA0000500Control Stick · crackedCO-PILOT CONTROL STICK HANDLE CRACKED AND SEPARATED.Sep 20, 2017 · N195TP · Grob G120A · Control Column SectionSDR CA160304010Tension Spring · stiff(CAN) PILOT REPORTED CONTROL STICK APPEARS EXCESSIVLY STIFF. THIS WAS DETECTED UPON ENTRY IN THE AIRCRAFT PRIOR TO FLIGHT. INSPECTION FOUND THAT THE FWD RUDDER AILERON COUPLING SPRING WAS BROKEN. BOTH SPRINGS REPLACED IAW MM 27-12 AND MSB 1121-074. NO DETECTMar 3, 2016 · Grob G120A · Rudder Control SystemSDR 2015FA0000653Ignition Switch · failedPILOT REPORTED SMOKE OUT OF IGNITION SWITCH DURING START UP. INVESTIGATION FOUND THE STARTER SWITCH HAD INTERNALLY ARCED ACROSS THE CONTACTS.Dec 16, 2015 · N864AF · Grob G120A · Ignition SwitchingSDR CA151028005Wire · shorted(CAN) ON FINAL APPROACH , THE ALT OFF RED ANNUNCIATOR ILLUMINATED. 5 SECONDS LATER THE Ï¿½VOLTÏ¿½ ANNUNCIATOR ILLUMINATED AS WELL. THE IP NOTED THAT THE BATTERY CURRENT DRAW WAS 63 AMPS. THE PILOT CONTINUED THE APPROACH WITH THE INTENTION TO LAND. THE CREW NOOct 27, 2015 · Grob G120A · AC Generator-AlternatorSDR CA150527003Spacer · defective(CAN) AS ACFT STARTED TO TAXI, RUBBING NOISES HEARD FROM COCKPIT & TAXI WAS ABORTED. FOUND THE NOSE WHEEL TILTED OVER, RUBBING ON THE FORK ASSEMBLY. WHEEL & FORK ASSEMBLY WERE REPLACED. ENG & GEAR MOUNT INSPECTED, NO FURTHER DEFECTS FOUND. ACFT RETURNED TOMay 26, 2015 · Grob G120A · Wheel/Ski/FloatSDR CA150106003Relay · damaged(CAN) AVIONICS BUSS 1 AND 2 CONTROL RELAYS FOUND TO BE WIRED INCORRECTLY FROM MANUFACTURE. WIRES FOR CONNECTION 85 WERE ON CONNECTION 86 AND WIRES FROM 86 WERE FOUND ON CONNECTION 85. RELAY INTERNAL DIODES WERE DAMAGED. WIRING CORRECTED AND RELAYS REPLACED.Jan 2, 2015 · Grob G120A · DC Generating SystemSDR CA140521006Wire Harness · broken(CAN) WIRE FOUND BROKEN DURING FLEET CAMPAIGN TO CHECK FOR BROKEN WIRES. FLAP OPERATED NORMALLY.May 21, 2014 · Grob G120A · Flight Control System WiringSDR CA140505011Wire · broken(CAN) FLAP STUCK AT FULL FLAP. WOULD NOT MOVE UP OR DOWN. NO INDICATION IN COCKPIT. FOUND WIRE AT SYMMETRY SWITCH BROKEN. THE SYMMETRY UNIT MOVES WITH EACH CYCLE OF THE SYSTEM. THE WIRE GETS BENT EACH TIME EVENTUALLY CAUSING FAILURE AT THE TERMINAL END.Apr 29, 2014 · Grob G120A · Flight Control System WiringSDR CA130122003Drive Assy · malfunctioned(CAN) FLAP C/B POPPED OUT WHEN FLAPS SELECTED DOWN ON FINAL. C/B PUSHED BACK IN ON THE GROUND AND FLAPS WERE SELECTED DOWN, THEN UP AND C/B POPPED OUT AGAIN. WEATHER WAS -25C WHEN INCIDENT OCCURED. ACFT WAS ON FIRST FLIGHT AFTER MULTIPLE HOURS OF COLD-SOAKIJan 21, 2013 · Grob G120A · Trailing Edge Flap Control SystemSDR CA130117012Drive Assy · malfunctioned(CAN) FLAP SYS VERY SLOW TO OPERATE IN COLD WEATHER, -20C. CURRENT INITIALLY READS 25 AMPS WHILE OPERATING, AFTER A COUPLE CYCLES IT STILL READS 18 AMPS AND SYS OPERATES AT ROUGHLY HALF SPEED. DISCONNECTED FLAP ACTUATORS AND FLEX SHAFTS IN SYS AND AMMETER STJan 17, 2013 · Grob G120A · Trailing Edge Flap Control SystemSDR CA120727003Ignition Switch · smoke(CAN) PILOT REPORTED SEEING SMOKE COMING FROM THE SWITCH ON START UP. ENGINE SHUTDOWN AND ACFT ROUTED TO MAINTENANCE. NO LOOSE WIRES OR CONNECTIONS FOUND AT SWITCH AREA. CAN SMELL BURNED ELECTRONICS INSIDE SWITCH. SWITCH REPLACED AND SYSTEM OPERATED NORMALJul 26, 2012 · Grob G120A · Ignition SwitchingSDR CA120607008Actuator · malfunctioned(CAN) RT MLG DOWN LOCK INDICATOR SHOWED RED WITH GEAR HANDLE SELECTED IN THE DOWN POSITION. GEAR WAS NOT DOWN AND LOCKED. LANDING OCCURED WITHOUT INCIDENT. ACFT WAS TOWED TO HANGAR FOR TROUBLESHOOTING. MAINTENANCE TROUBLESHOT THE SYS AND FOUND THE RT MLG AJun 7, 2012 · Grob G120A · Landing Gear ActuatorSDR CA120530005Pitot Tube · contaminated(CAN) PITOT HEAT CAUTION LIGHT AFTER 20 MINS OF USE. DUE TO HEAVY RAINS, THE PITOT STATIC TUBE ASSY, SUPPORT ASSY, FILLED UP WITH WATER. THE WATER CAUSED A SHORT AT THE CONNECTOR INSIDE THE TUBE. WIRES REPAIRED AND PITOT STATIC TUBE REPLACED. SUGGEST A DRAIMay 25, 2012 · Grob G120A · Pitot/Static SystemSDR CA120412003Switch · failed(CAN) FIRST ATTEMPT, FLAPS DIDNT RETRACT FROM TAKEOFF TO UP POSITION. SECOND ATTEMPT THEY WORKED FINE. 2ND OCCURANCE ON SAME FLIGHT, THE FLAPS DIDNT EXTEND TO TAKEOFF POSITION AND THE CIRCUIT BREAKER POPPED. REPLACED BOTH UP AND DOWN SWITCHES, ADJUSTED AND Apr 11, 2012 · Grob G120A · Trailing Edge Flap Control SystemSDR CA120322006Drive Unit · malfunctioned(CAN) FLAP C/B TRIPPED. FOUND FLAP DRIVE MOTOR CURRENT TO BE TOO HIGH WHEN CYCLING FLAPS, PARTICULARLY WHEN THE DRIVE MOTOR IS COOL OR COLD. MOTOR WAS ALSO MAKING GROANING SOUNDS WHEN OPERATING. FLAP DRIVE MOTOR SYSTEM FOUND TO BE PROBABLEMATIC IN COLD WEAMar 22, 2012 · Grob G120A · Trailing Edge Flap Control SystemSDR CA120302002Servo · malfunctioned(CAN) ELECTRIC TRIM KEPT RUNNING FOR 1-2 SECS AFTER RELEASING THE TRIM SWITCH AND KEPT RUNNING EVEN IF HOLDING THE TRIM DISCONNECT. FOUND ELEVATOR TRIM SERVO CLUTCH NOT DISENGAGING IMMEDIATELY ON ELEVATOR TRIM SERVO. REPLACED TRIM SERVO AND TESTED OPS.Feb 29, 2012 · Grob G120A · Elevator Tab Control SystemSDR CA120203012Switch · cracked(CAN) FLAP CIRCUIT BREAKER POPPED. WHEN FLAPS WERE SELECTED UP, THE FLAPS WORKED FINE. FLAPS WORKED INTERMITTENTLY IN THE DOWNWARDS DIRECTION. REPLACED THE FLAP SELECTION SWITCH, DOWNWARD DIRECTION, AND THE SYS TESTED PROPERLY. MICROSWITCH HOUSING WAS FOUNFeb 2, 2012 · Grob G120A · Trailing Edge Flap Control SystemSDR CA120131011Switch · malfunctioned(CAN) FLAPS STUCK UP, CIRCUIT BREAKER TRIPPED TWICE. ON GROUND, SELECTING DOWN AND PUTTING IN THE CIRCUIT BREAKER STILL CAUSED BREAKER TO POP. REPLACED UPWARDS MICROSWITCH AND SYS WORKS PROPERLY.Jan 30, 2012 · Grob G120A · Trailing Edge Flap Control SystemSDR CA120118002Drive Unit · failed(CAN) FLAP SYSTEM CIRCUIT BREAKER POPPED WHEN FLAPS OPERATED. TROUBLESHOOTING SHOWED SYS DREW 18 AMPS WHEN COLD SOAKED, OAT -20C. AFTER BEING HEATED IN HANGAR FOR 4 HOURS, THE FLAP SYSTEM DREW 6 AMPS. WHEN COLD SOAKED, FLAP DRIVE UNIT ALONE DREW 15 AMPS.Jan 17, 2012 · Grob G120A · Trailing Edge Flap Control SystemSDR CA120113006Tcas System · malfunctioned(CAN) TRAFFIC AVOIDANCE SYSTEM NOT GOING FROM GROUND MODE TO AIR MODE AFTER TAKE- OFF. AIRCRAFT SYSTEM TESTED SERVICEABLE DURING GROUND TESTS.Jan 11, 2012 · Grob G120A · Air Collision Avoidance SystemSDR CA111213001Wire · out of position(CAN) WIRING TOUCHED THE EXHAUST MANIFOLD. SYS WAS SHORTING & CAUSED THE TAXI LIGHT CB TO POP. THE ROUTING OF THE WIRING & THE LOCATION OF THE TAXI & LANDING LIGHT CONNECTORS, 826884-2 & 826883-2, INSIDE THE COWL BY THE LIGHTS LOCATES THE CONNECTORS & WIRES Dec 7, 2011 · Grob G120A · Light System WiringSDR CA111201006Ignition Switch · malfunctioned(CAN) WITH SWITCH IN "BOTH ON" POSITION, STARTER ENGAGES WHEN KEY IS TAPPED/BRUSHED. SWITCH REPLACED, NO FURTHER FAULTS FOUND. TOTAL STARTS ON SWITCH 87.Nov 30, 2011 · Grob G120A · Ignition SwitchingSDR CA111128005Control Rod · gouged(CAN) ELEVATOR TRIM ROD, 120A-4441, HAS TWO SPOTS WHERE BOLTS FROM THE ELEVATOR CONTROL ROD, 120A-4441, WERE GOUGING INTO THE ROD WHEN THE SYS WAS BEING OPERATED. IN ORDER TO RECTIFY, THE BOLTS AT THE QUADRANT FOR THE ELEVATOR CONTROL ROD, 120A-4441, THE AILENov 28, 2011 · Grob G120A · Elevator Tab Control SystemSDR CA111122005Clamp · out of position(CAN) THE UPPER AFT SCREW RETAINING PANEL 120A-2812 WAS FOUND TOUCHING A WIRING BUNDLE LOCATED BEHIND THE CENTER CONSOLE PANEL, 120A-2880. WE REPLACED AND REPOSITIONED THE CLAMP, RSGU 1.13/12-W5-SILICON, WITH CLAMP, RSGU-15/15-W6. THIS ALLOWED THE SCREW TO BNov 22, 2011 · Grob G120A · Electrical Power System WiringSDR CA111109008Clamp · out of position(CAN) THE UPPER AFT SCREW RETAINING PANEL 120A-2812 WAS FOUND TOUCHING A WIRING BUNDLE LOCATED BEHIND THE CENTER CONSOLE PANEL (120A-2880). REPLACED AND REPOSITIONED THE CLAMP (RSGU 1.13/12-W5-SILICON) WITH CLAMP (RSGU-15/15-W6). THIS ALLOWED THE SCREW TO BE Nov 9, 2011 · Grob G120A · Electrical Power System WiringSDR CA111110003Brake Pads · worn(CAN) BRAKE PAD WEAR IS UNEVEN. THE TOP OF THE PADS IS WEARING AT TWICE THE RATE OF THE LOWER PART OF THE PADS. THE PROBLEM APPEARS TO BE THAT THERE IS NOT ENOUGH ROOM FOR THE PAD PRESSURE PLATE TO SLIDE ALONG THE BRAKE CALIPER ANCHOR BOLTS WHEN THE BRAKE CALINov 8, 2011 · Grob G120A · BrakeSDR CA111028003Ignition Switch · inoperative(CAN) ACFT WOULD NOT START. REPLACED SWITCH AND ALL TESTED SERVICEABLE.Oct 28, 2011 · Grob G120A · Ignition SwitchingSDR CA111026009Brake Pads · misinstalled(CAN) BRAKE PAD WEAR IS UNEVEN. THE TOP OF THE PADS IS WEARING AT TWICE THE RATE OF THE LOWER PART OF THE PADS. THE PROBLEM APPEARS TO BE THAT THERE IS NOT ENOUGH ROOM FOR THE PAD PRESSURE PLATE TO SLIDE ALONG THE BRAKE CALIPER ANCHOR BOLTS WHEN THE BRAKE CALOct 26, 2011 · Grob G120A · BrakeSDR CA111026008Actuator · malfunctioned(CAN) WHEN FLAPS ARE SELECTED TO UP, LOUD SCREECHING AND HOWLING SOUNDS COMING FROM THE RT FLAP ACTUATOR. THIS HAPPENS ONLY AT THE LAST 4" OF TRAVEL IN THE UP DIRECTION.Oct 25, 2011 · Grob G120A · Trailing Edge Flap ActuatorSDR CA111003009Vent Line · loose(CAN) PILOTS REPORTED FUEL ODOR IN COCKPIT. CHANGED FUEL VENT DRAINS THEN DISCOVERED LT FUEL VENT LINE HAD BEEN LOOSENED OFF DURING MX AND HAD NOT BEEN RETIGHTENED. ONCE RETIGHTENED FUEL SMELL DID NOT RE-OCCUR.Sep 29, 2011 · Grob G120A · Aircraft Fuel Distribution SystemSDR CA110930005Ignition Switch · failed(CAN) DURING PRE-INSPECTION GROUND RUN, ENGINE WAS SHUTDOWN IAW CHECK, IGNITION KEY OFF AND MASTER OFF. WHEN POWER MASTER WAS RE-SELECTED ON, THE STARTER ENGAGED IMMEDIATELY WITH THE IGNITION KEY IN THE OFF POSITION. MASTER TURNED OFF AND CRANKING CEASED.Sep 27, 2011 · Grob G120A · Ignition SwitchingSDR CA110920010Hose · worn(CAN) DURING A LEAK TEST OF THE AIR CONDITIONING, IT WAS DISCOVERED THAT THE MAIN DELIVERY HOSE HAD A LEAK AND REQUIRED REPLACEMENT. THE AFFECTED HOSE IS LOCATED IN THE ENGINE COMPARTMENT AND IN CLOSE PROXIMITY TO THE EXHAUST MANIFOLD AND IS SUBJECT TO HIGH HSep 20, 2011 · Grob G120A · Air Distribution SystemSDR 2011FA0000535Control Cable · failedPILOT REPORTED DURING FLIGHT HE EXPERIENCED A TOTAL LOSS OF MIXTURE CONTROL. INVESTIGATION REVEALED THE MIXTURE CONTROL CABLE HAD BROKEN AT THE CONTROL IN THE CABIN. NO RECOMMENDATIONS AT THIS TIME.Aug 19, 2011 · N867AF · Grob G120A · Mixture ControlSDR CA110812005Pump · failedFUEL PUMP WAS INSTALLED TO REPLACE ANOTHER PUMP WITH LOW IDLE PRESSURE. ON STARTUP FOR GROUND TEST, IT WAS NOTICED THAT THE PUMP HAD ZERO OUTPUT. ON REMOVAL FOR REPLACEMENT, IT WAS NOTED THAT THE DRIVE SHAFT WAS SHEARED. IT WAS THEN NOTICED THAT THE FITTING Aug 12, 2011 · Grob G120A · Engine Fuel PumpSDR CA110811007Pump · malfunctionedFUEL PUMP WAS INSTALLED TO REPLACE ANOTHER PUMP WITH LOW IDLE PRESSURE. ON STARTUP FOR GROUND TEST, IT WAS NOTICED THAT THE PUMP HAD ZERO OUTPUT. ON REMOVAL FOR REPLACEMENT, IT WAS NOTED THAT THE DRIVE SHAFT WAS SHEARED. IT WAS THEN NOTICED THAT THE FITTING Aug 11, 2011 · Grob G120A · Engine Fuel PumpSDR 2011FA0000453Pump · failedPILOT REPORTED LOW FUEL PRESSURE AT 700 RPM, 10-12 PSI. INSTALLED ANOTHER PUMP RAN ACFT OPS CHECKED OK. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.Jul 9, 2011 · N862AF · Grob G120A · Engine Fuel PumpSDR CA110412009Wire · chafed(CAN) MULTIPLE WIRES ON GROUND BLOCK MODULE VN220 BEHIND THE RT INTRUMENT PANEL WERE FOUND WITH ABRASION DAMAGE CAUSED BY CHAFING ON THE ENGINE INSTRUMENT DISPLAY. SEVERAL WIRES WERE FOUND WITH THE INSULATION DAMAGED THROUGH TO THE CONDUCTOR.Apr 11, 2011 · Grob G120A · Instrument System WiringSDR CA110331027Buss · intermittent(CAN) BUSS MODULE HAD INTERMITTENT CONTACT CONNECTION. OCCURED ON TWO SEPARATE MODULES ON TWO DIFFERENT SYSTEMS. MODULE W21018 FOR ADF FLIGHT TIMER FAILED AT PIN "K". AIRTIME 13.2 HRS. MODULE W21040 FOR ELT FAILED. NO DETAILS. AIRTIME 24.8HRS. BOTH MODULEMar 30, 2011 · Grob G120A · Instrument System WiringSDR 2011FA0000149Pump · failedAFTER INSTALLING ENGINE DRIVEN FUEL PUMP ON THE ENG, MECHANIC WENT OUT TO PERFORM AN ENGINE OPS CHECK AND FOUND ENGINE WOULDN’T KEEP RUNNING UNLESS BOOST PUMP WAS IN THE ON POSITION. UPON TROUBLESHOOTING MECHANIC FOUND THE SHAFT WAS SHEARED ON THE FUEL PUMP. Mar 3, 2011 · N863AF · Grob G120A · Engine Fuel PumpSDR 2011FA0000148Pump · leakingMECHANIC PERFORMED A LEAK CHECK AFTER INSTALLING ENGINE DRIVEN FUEL PUMP ON THE ENGINE AND FOUND FUEL LEAKING FROM SHAFT DRIVE. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.Mar 3, 2011 · N863AF · Grob G120A · Engine Fuel PumpSDR 2011FA0000144Pump · leakingMECHANIC WAS PERFORMING A POST MAINTENANCE CHECK ON AIRCRAFT AND NOTICED FUEL STAINS ON THE DOG HOUSE, MECHANIC THEN PERFORMED A LEAK CHECK AND FOUND FUEL LEAKING FROM VENT ON ADJUSTMENT COVER ON ENGINE DRIVEN FUEL PUMP. NO PROBABLE CAUSE OR RECOMMENDATIONS ATMar 2, 2011 · N867AF · Grob G120A · Engine Fuel PumpSDR CA110225008Circuit Breaker · failed(CAN) PERFORMING AN AERO SEQUENCE, UPON INITIATING FINAL MANOUVER, SMOKE WAS DETECTED AND A SMALL AMOUNT SEEN BY PILOT, LT SEAT, COMING FROM THE CIRCUIT BREAKER PANEL AREA. THE ACFT RETURNED TO BASE WITHOUT INCIDENT. MAINTENANCE INVESTIGATION REVEALED THATFeb 23, 2011 · Grob G120A · Electrical Power System WiringSDR CA110225010Manifold · failed(CAN) DURING APPROACH, LANDING GEAR FAILED TO DEPLOY. EMERGENCY SYSTEM ACTIVIATED. ACFT LANDED WFI. MAINTENANCE INSPECTION FOUND THAT THE LANDING GEAR EXTENSION SOLENOID, MAGNETIC SELECTOR VALVE, PART OF MANIFOLD, ON THE HYD SUPPLY MANIFOLD WAS UNSERVICEABLFeb 22, 2011 · Grob G120A · Hydraulic System, MainSDR CA101021012Washer · missingDURING A 200 HR INSP ON 2 OTHER ACFT, MSB 1121-109/1 WAS BEING CARRIED OUT AS REQUIRED WHEN IT WAS NOTED THAT THE WASHERS WERE MISSING. THE MFG WAS CONTACTED AND DETERMINED THAT THIS WAS NON CONFORMANCE TO THE TYPE CERTIFICATE. IT WAS DECIDED THAT THE REMAINOct 20, 2010 · Grob G120A · Wing Miscellaneous StructureSDR CA101021011Washer · missingDURING A 200 HR INSP ON 2 OTHER ACFT, MSB 1121-109/1 WAS BEING CARRIED OUT AS REQUIRED WHEN IT WAS NOTED THAT THE WASHERS WERE MISSING. THE MFG WAS CONTACTED AND DETERMINED THAT THIS WAS A NON CONFORMANCE TO THE TYPE CERTIFICATE. IT WAS DECIDED THAT THE REMAOct 20, 2010 · Grob G120A · Wing Miscellaneous StructureSDR CA101021010Washer · missingDURING A 200 HR INSP ON 2 OTHER ACFT, MSB 1121-109/1 WAS BEING CARRIED OUT AS REQUIRED WHEN IT WAS NOTED THAT THE WASHERS WERE MISSING. THE MFG WAS CONTACTED AND DETERMINED THAT THIS WAS A NON CONFORMANCE TO THE TYPE CERTIFICATE. IT WAS DECIDED THAT THE REMAOct 20, 2010 · Grob G120A · Wing Miscellaneous StructureSDR CA101021009Washer · missingDURING A 200 HR INSP ON 2 OTHER ACFT, MSB 1121-109/1 WAS BEING CARRIED OUT AS REQUIRED WHEN IT WAS NOTED THAT THE WASHERS WERE MISSING. THE MFG WAS CONTACTED AND DETERMINED THAT THIS WAS A NON CONFORMANCE TO THE TYPE CERTIFICATE. IT WAS DECIDED THAT THE REMAOct 20, 2010 · Grob G120A · Wing Miscellaneous Structure
Back to Grob-Werke G 120A