Lycoming AEIO-540-D4D5

Service difficulty reports · 129

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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 engine_model_key = 'AEIO540D4D5'
  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 CA101015004Brake Pads · mismarkedACFT WAS IN FOR 100 HR CHECK. THE BRAKE LININGS WERE BEING REPLACED. MX RECEIVED NEW LININGS. AFTER INSTALLATION THE WHEEL WOULD NOT TURN. BRAKE LININGS WERE REMOVED AND IT WAS NOTED THAT 1 LINING WAS OF A DIFFERENT SIZE THAN THE OTHERS, BUT WAS STAMPED WIOct 13, 2010 · Grob G120A · Landing Gear Brake SystemSDR 2010FA0000851Control Cable · brokenPILOT REPORTED DURING GROUND OPERATION HE EXPERIENCED A TOTAL LOSS OF MIXTURE CONTROL. INVESTIGATION MIXTURE CONTROL CABLE HAD BROKEN AT THE CONTROL IN THE CABIN. PROBABLE CAUSE UNKNOWN. RECOMMEND ENGINE CONTROL CABLES BE REPLACED AT ENGINE CHANGE (1800 HRSAug 20, 2010 · N861AF · Grob G120A · Mixture ControlSDR CA100729001Valve · failedPILOTS NOTED STRONG SMOKE/ODOR. CANOPY WAS OPENED IN FLIGHT TO VENT SMOKE/ODORS. RETURNED FOR LANDING. CO2 DETECTOR HAD TURNED DARK TO THE UNSAFE ZONE AND REMAINED DARK TILL SHORTLY AFTER LANDING. ACFT INSPECTED AND FOUND INDICATIONS OF EXHAUST STAINS AROUJul 26, 2010 · Grob G120A · Heating SystemSDR CA100716004Switch · failed(CAN) DURING A MISSION, THE PILOTS SELECTED THE MUTE SWITCH ON THE AUDIO SYSTEM TO TALK AMONGST THEMSELVES. UPON SELECTING THE MUTE SWITCH TO TRANSMIT, THEY FOUND THAT THEY COULD NOT COMMUNICATE WITH TOWER OR OTHER AIRCRAFT. THE PILOT SELECTED THE APPROPRIATJul 15, 2010 · Grob G120A · Audio Integrating SystemSDR CA101008004Control Cable · chafed(CAN) ON A PRE START CHECK, THE PILOT NOTED THE PROP LEVER NOT FUNCTIONING PROPERLY. THE CABLES ARE KNOWN BY MX TO START CHAFING AND BINDING INTERNALLY JUST FWD OF THE PROP CONTROL LEVER CABLE HSG ATTACH POINT TO THE ACFT STRUCTURE. SOME CABLE HSG ARE SECUREJul 9, 2010 · Grob G120A · Propeller Controlling SystemSDR CA091207001Nozzle · leaking(CAN) AFTER ROLLING UPRIGHT FROM INVERTED FLIGHT ON A TRAINING MISSION, THE ACFT BACKFIRED FOLLOWED BY A STRONG FUEL SMELL IN THE COCKPIT. EMERGENCY CHECKS WERE COMPLETED AND WHILE ACFT WAS INBOUND TO DEPARTURE AIRPORT THERE WAS A SECOND OCCURENCE OF STRONG FDec 4, 2009 · Grob G120A · Fuel Injector NozzleSDR 2010FA0000028Throttle Cable · brokenPILOT REPORTED DURING LANDING, THROTTLE WAS NOT GOING FULLY TO IDLE THEN SUDDENLY SOMETHING BROKE AND ENGINE WENT TO FULL POWER. AFTER FURTHER INVESTIGATION FOUND THROTTLE CABLE BROKEN WHERE IT COMES THRU THE FIREWALL. PROBABLE CAUSE UNKNOWN, NO RECOMMENDATIDec 3, 2009 · N861AF · Grob G120A · Power LeverSDR CA091127003Engine · power loss(CAN) THE INSTRUCTOR AND STUDENT WERE DEPARTING ON A LOCAL TRAINING FLIGHT AND EXPERIENCED A ROUGH RUNNING ENGINE WHEN THEY REDUCED POWER AFTER T/O. THE INSTRUCTOR ACTIONED THE `ROUGH ENGINE` TASKS OF THE APPROVED CHECKLIST, CONTACTED ATC TO DECLARE AN EMERGENNov 23, 2009 · Grob G120A · Reciprocating Engine Power SectionSDR CA091123004Injector · failed(CAN) INSTRUCTOR AND STUDENT WERE ABOUT 15-20MIN INTO A LOCAL TRAINING FLIGHT WHEN SLIGHT ENG VIBRATIONS WERE NOTED DURING PWR CHANGES MADE AROUND 2300 RPM. INSTRUCTOR FOLLOWED ROUGH RUNNING CHECKLIST STEPS IN APPROVED CHECKLIST AND DETERMINED THAT ENG RAN RONov 20, 2009 · Grob G120A · Fuel Injector NozzleSDR CA091103007Unknown · odor(CAN) PREPARING FOR A LOCAL TRAINING FLIGHT, THE STUDENT AND INSTRUCTOR RECEIVED TAXI CLEARANCE FOR A RUN-UP FROM GROUND CONTROL. DURING THESE `BEFORE TAKE-OFF` CHECKS THE STUDENT BELIEVED THAT HE DETECTED A BURNING ODOR. THE INSTRUCTOR COULD NOT DETECT THE ODNov 3, 2009 · Grob G120A · Air Distribution SystemSDR CA091105004Spark Plug · fouled(CAN) THE STUDENT AND INSTRUCTOR DEPARTED FOR A LOCAL TRAINING FLIGHT AND NOTICED A SMALL AMOUNT OF ENGINE VIBRATION DURING THE T/O. THE VIBRATION WAS NOTED AGAIN LATER WHEN THEY RETURNED TO THE AIRPORT FOR CIRCUIT PRACTICE. A PRACTICE MISSED APPROACH WAS CONDNov 3, 2009 · Grob G120A · Spark Plug/IgniterSDR CA091022006Skin · dented(CAN) THE STUDENT PILOT WAS CARRYING OUT THE PREFLIGHT INSPECTION OF THE ACFT & NOTED SEVERAL INDENTATIONS ON UPPER SKIN ON THE RT WING. FURTHER INSPECTION BY MX BY "TAP TESTING" REVEALED THE EXTENT OF THE DELAMINATION. OUTBOARD EDGE OF OUTBOARD DELAMINATION Oct 21, 2009 · Grob G120A · Wing, Plate/SkinSDR CA090909006Ignition Switch · shorted(CAN) A STUDENT PILOT WAS CARRYING OUT PRE-FLIGHT INSPECTION OF AIRCRAFT IN PREPARATION FOR A LOCAL TRAINING FLIGHT. WHEN THE BATTERY MASTER WAS SELECTED "ON", THE ENGINE BEGAN TO CRANK. THE MASTER WAS IMMEDIATELY SELECTED OFF AND CRANKING CEASED. THE STUDENT Sep 9, 2009 · Grob G120A · Ignition SwitchingSDR CA090902005Terminal · damagedACFT WAS ENGAGED IN A LOCAL TRAINING FLIGHT WITH STUDENT PILOT FLYING ON FINAL APPROACH WHEN "ALT OFF" ANNUNCIATOR ILLUMINATED AND AMMETER SHOWED DISCHARGE. INSTRUCTOR COMMANDED THE OVERSHOOT AND TOOK CONTROL OF THE ACFT. AN EMERGENCY WAS DECLARED AND THE INAug 31, 2009 · Grob G120A · Electrical Power System WiringSDR CA090819005Unknown · odor(CAN) PREPARING FOR A LOCAL TRAINING FLIGHT, AIRCREW NOTED A "BURNING ODOR" DURING THE PRE-TAKE-OFF RUN-UP. AIRCREW ADVISED ATC OF THE PROBLEM AND THAT THEY WERE SHUTTING DOWN IN POSITION. THEY THEN CARRIED OUT THE PUBLISHED "SMOKE IN THE COCKPIT" CHECKLIST.Aug 19, 2009 · Grob G120A · Air Distribution SystemSDR CA090819004Wire Harness · chafedON A LOCAL TRAINING FLIGHT THE AIRCREW NOTED A "SMOKY ODOR" ON CLIMBOUT FROM A `TOUCH AND GO` LANDING. THE AIRCREW ADVISED ATC OF THE PROBLEM AND THAT THEY WERE RETURNING TO THE AIRPORT. THEY THEN CARRIED OUT THE PUBLISHED "SMOKE IN THE COCKPIT" CHECKLIST. Aug 13, 2009 · Grob G120A · Light System WiringSDR CA090205010Actuator · damagedAIRCRAFT ON LOCAL FLIGHT TRAINING MISSION. INSTRUCTOR NOTED FLAPS CIRCUIT BREAKER POPPED WHEN FLAPS SELECTED UP. C/B RESET AS PER CHECKLIST, POPPED WHEN SELECTED UP A SECOND TIME. INSTRUCTOR ADVISED ATC OF FLAP DIFFICULTY AND RETURNED TO LAND WITH FLAPS IN Jan 23, 2009 · Grob G120A · Trailing Edge Flap ActuatorSDR CA080829005Magneto · failed(CAN) ACFT FLOWN ON LOCAL FLIGHT TRAINING SORTIE WITH INSTRUCTOR AND STUDENT ON BOARD. INSTRUCTOR REPORTED NO NOTICEABLE ENGINE ROUGHNESS OR PWR LOSS DURING FLIGHT. AFTER TAXI TO PARKING POSITION, INSTRUCTOR EGRESSED A/C AND ADVISED STUDENT TO CARRY-OUT SHUTDAug 29, 2008 · Grob G120A · Magneto/DistributorSDR CA071029008Frame · damaged(CAN) FLIGHT DEPARTED AT 1344 FOR AT TRAINING FLIGHT TO THE WEST PRACTICE AREA. APPROXIMATELY 5 MINUTES OUT WHILE CRUISING AT 4000 FT AND 120 KTS THE INSTRUCTOR OBSERVED (ALT OFF) ANNUNCIATION. A SCAN OF INTEGRATED ENGINE DISPLAY REVEALED (AMPS) TO BE READING Oct 26, 2007 · Grob G120A · Fuselage Miscellaneous StructureSDR CA070813005Indicator · unreliable(CAN) MFG INSTALLED MICROTECHNA ELECTRIC ATTITUDE INDICATORS IN A FLEET OF 9 AIRCRAFT USED FOR FLIGHT TRAINING. AFTER 18 MONTHS, ONE ORIGINAL ATTITUDE INDICATOR IS STILL FUNCTIONING AFTER 500 HOURS (9) INSTRUMENTS AVERAGED 225 HOURS BEFORE FAILING THE FIRST TIAug 3, 2007 · Grob G120A · Attitude and Direction Data SystemSDR CA070227006Handle · failed(CAN) LANDING GEAR HANDLE FAILED TO GIVE GEAR POSITION LIGHT AND IN-TRANSIT LIGHT INDICATIONS DURING A TRAINING MISSION. THE PILOT ELECTED TO FLY BY THE TOWER FOR ALL GEAR IN EXTENDED POSITION CONFIRMATION BEFORE AN UNEVENTFUL LANDING. AFTER SHUTDOWN, THE LANFeb 22, 2007 · Grob G120A · Landing Gear SelectorSDR CA070209022Flap System · frozen(CAN) THE COLD WEATHER HAS AFFECTED SEVERAL AIRCRAFT IN THE FLEET OF 9. IN -25 C OR COLDER TEMPERATURES, THE CIRCUIT BREAKERS POP AFTER LANDING WHEN THE FLAPS ARE SELECTED (TC NR 20070209022)Feb 9, 2007 · Grob G120A · Trailing Edge Flap Control SystemSDR 2007FA0000004Pump · weakIN FLIGHT, THE INSTRUMENT VACUUM SYSTEM WOULD NOT PUT OUT PROPER SUCTION AND CAUSED THE ATTITUDE INDICATOR TO TUMBLE. THE AC RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTEM FOUND THAT THE PUMP WAS WEAK. PUMP WAS REMOVED AND A NEW PUMP INSTALLED. OPOct 26, 2006 · N864AF · Grob G120A · Vacuum Distribution SystemSDR 2006FA0000911Pump · leakingPILOT REPORTED A STRANGE ODOR AFTER THEY PUT THE GEAR UP, WHILE TROUBLESHOOTING MECHANIC FOUND ENGINE FUEL PUMP LEAKING FROM PRESSURE ADJUSTMENT SCREW. NO PROPABLE CAUSE OR RECOMMENDATIONS AT THIS TIME. (K)Aug 28, 2006 · N862AF · Grob G120A · Engine Fuel PumpSDR 2006FA0000225Blower Motor · wornPILOT REPORTED EXCESSIVE VIBRATION WITH AIR CONDITION ON. WHILE TECH WAS TROUBLESHOOTING SYSTEM FOUND THAT BLOWER MOTOR HAD TOO MUCH END PLAY ON BLOWER FAN SHAFT MAKING IT VIBRATE. NO RECOMMENDATIONS AT THIS TIME. (K)Feb 27, 2006 · N865AF · Grob G120A · Air Distribution FanSDR 2005FA0000925Servo · malfunctionedPILOT REPORTED ENGINE QUIT AFTER LANDING WITH BOOST PUMP ON. ON GROUND RUN PERFORMING MIXTURE IDLE CHECK, WE FOUND WITH BOOST PUMP OFF, WE HAD .5 INCH MANIFOLD PRESSURE DROP AND WITH BOOST PUMP ON. WE HAD 1.5 INCH MANIFOLD PRESURE DROP. ON FURTHER INVESTIGAJun 14, 2005 · N865AF · Grob G120A · Fuel Controlling SystemSDR 2005FA0000603Pump · malfunctionedPILOT REPORTED THAT IDLE RPM WAS TOO HIGH, 850 RPM. WHILE TECH WAS TRYING TO ADJUST IDLE, FOUND THAT THE FUEL PRESSURE WAS LOW - 16 PSI AND UNABLE TO ADJUST. REPLACEMENT OF ENGINE DRIVEN FUEL PUMP WAS REQUIRED. RECOM TO ADD A METHOD PLUS DATA FOR MAKING ADJApr 14, 2005 · N861AF · Grob G120A · Engine Fuel PumpSDR 2005FA0000602Volt Regulator · inoperativeAFTER 20 MINUTES INTO ENGINE, START CHARGING SYSTEM STILL SHOWING 7 AMPS OF CHARGING. MAINT TECH FOUND VLOTAGE REGULATOR WAS NOT WORKING. VOLTAGE REGULATOR WAS REPLACED AND OPERATIONAL CHECK OF CHARGING SYSTEM CHECK, GOOD. NO RECOMMENDATIONS AT THIS TIME.Apr 13, 2005 · N864AF · Grob G120A · DC RegulatorSDR 2005FA0000691Uplock · intermittentDURING FLIGHT, GEAR SELECTED TO DOWN AND LT MAIN GEAR EXTENSION WAS DELAYED. AFTER ABOUT 25 SECONDS LT MAIN GEAR EXTENDED. MAINTENANCE TECHNICIAN FOUND LT LANDING GEAR UP LOCK ASSY WAS INTERMITTENT. REPLACED ASSY. NO RECOMMENDATION AT THIS TIME. (K)Jan 12, 2005 · N862AF · Grob G120A · Landing Gear Position and WarningSDR 2005FA0000111Pump · shearedDURING RUN-UP OF AIRCRAFT PILOT REPORTED LOST OF INSTRUMENT VACUUM SUCTION. MAINTENANCE TECHNICIAN FOUND VACUUM PUMP HAD A BROKEN SHAFT. UPON REPLACEMENT OF VACUUM PUMP INSTRUMENT SUCTION WAS FOUND TO BE OK. RECOMMEND FINDING A REPLACEMENT THAT IS MORE DURANov 17, 2004 · N862AF · Grob G120A · Vacuum Distribution SystemSDR 2005FA0001123Servo · inoperativePILOT REPORTED LOW FUEL FLOW ON TAKEOFF, UPON FURTHER INVESTIGATION THE MECHANIC FOUND THE FUEL FLOW WAS AT 149 PPH UNTIL THE ENGINE GOT HOT THEN THE FUEL FLOW DROPPED DOWN TO 142-144 PPH. NO RECOMMENDATION AT THIS TIME. (K)Nov 8, 2004 · N863AF · Grob G120A · Fuel Controlling SystemSDR 2003FA0001111Relay · failedFOLLOWING AN EMERGENCY GEAR EXTENSION, PERFORMED DURING A ROUTINE INSPECTION, SYSTEM WOULD NOT OPERATE. FAULT DETERMINED TO BE FAILED RELAY FOR HYDRAULIC CONTROL. PROBABLE CAUSE, TO MUCH LOAD FOR RELAY. MANUFACTURER CONTACTED AND MANUFACTURER STATED THAT A Oct 15, 2003 · N863AF · Grob G120A · Landing Gear Retraction/Extension SystemSDR 2003FA0001012Lever · bindingDURING PRE-FLIGHT INSPECTION, FLIGHT CREW FELT BINDING ON THE AILERON SYSTEM UPON FURTHER INSPECTION FOUND BEARINGS IN AILERON LEVER 2 ASSY. TO BE DAMAGED AND BINDING. DAMAGE APPEARS TO BE CAUSED BY THE BUSHING PN 120A4435.02 IN THE FORK ENDS PN 120A4435.01.Sep 29, 2003 · N865AF · Grob G120A · Aileron Control SystemSDR 2003FA0001013Lever · bindingDURING FLEET WIDE INSPECTION, FOUND BEARINGS IN AILERON LEVER 2 ASSY. PN 120A4242 TO BE DAMAGED AND BINDING. DAMAGE APPEARS TO BE CAUSED BY THE BUSHING PN 120A4435.02 IN THE FORK ENDS PN 120A4435.01. IT APPEARS THAT DESIGN LIMITATIONS OF THE BEARINGS ALLOWISep 29, 2003 · N867AF · Grob G120A · Aileron Control SystemSDR 2003FA0001014Lever · bindingDURING FLEET WIDE INSPECTION, FOUND BEARINGS IN AILERON LEVER 2 ASSY. PN 120A-4242 TO BE DAMAGED AND BINDING. DAMAGE APPEARS TO BE CAUSED BY THE BUSHING PN 120A-4435..02 IN THE FORK ENDS PN 120A4435.01. IT APPEARS THAT DESIGN LIMITATIONS OF THE FLIGHT CONTRSep 29, 2003 · N863AF · Grob G120A · Aileron Control SystemSDR 2003FA0001015Lever · bindingDURING FLEET WIDE INSPECTION, FOUND BEARING IN AILERON LEVER 2 ASSY. PN 120A-4242 TO BE DAMAGED AND BINDING. DAMAGE APPEARS TO BE CAUSED BY THE BUSHING PN 120A-4435.02 IN THE FORK ENDS PN 120A4435.01. IT APPEARS THAT DESIGN LIMITATIONS OF THE FLIGHT CONTROLSep 29, 2003 · N862AF · Grob G120A · Aileron Control SystemSDR 2003FA0001036Lever · bindingDURING FLEET WIDE INSPECTION, FOUND BEARINGS IN AILERON LEVER 2 ASSY. PN 120A4242 TO BE DAMAGED AND BINDING. DAMAGE APPEARS TO BE CAUSED BY THE BUSHING PN 120A4435.02 IN THE FORK ENDS PN 120A4435.01. IT APPEARS THAT DESIGN LIMITATIONS OF THE FLIGHT CONTROL SSep 29, 2003 · N861AF · Grob G120A · Aileron Control SystemSDR 2003FA0001016Motor · failedDURING FLIGHT TRAINING, GEAR FAILED TO RETRACT. MAINTENANCE TECHNICIAN FOUND THAT THE HYDRAULIC PUMP MOTOR OF THE RETRACT SYSTEM HAD FAILED. PROBABLE CAUSE IS OVERHEATING OF THE HYDRAULIC PUMP MOTOR. RECOMMENDATION IS TO MANUFACTURE TO INSTALL A HIGHER CAPASep 25, 2003 · N864AF · Grob G120A · Hydraulic Pump (Electric/Engine), MainSDR 2003FA0000872Bearing · failedDURING PRE-FLIGHT INSPECTION, FLIGHT CREW REPORTED A NOISE FROM THE RUDDER. INSPECTION OF THE RUDDER SYSTEM REVEALED A FAILED BEARING IN THE BEARING SUPPORT OF THE LOWER RUDDER HINGE. THE OUTER CASE OF THE BEARING HAD TWO PIECES BROKEN OFF AND MISSING. BEARAug 14, 2003 · N862AF · Grob G120A · Rudder StructureSDR 2003FA0000850Bearing · bulgedDURING SPECIAL INSPECTION OF THE AIRCRAFT REVEALED THAT THE BEARING ON THE LT AILERON LEVER ASSY IS SHOWING SIGNS OF BULGING . PROBABLE CAUSE IS DESIGN OF LEVER ASSY. THE AMOUNT OF USE OF THIS SYSTEM. REDESIGN OR REPLACE BEARING OF A HIGHER QUALITY.Aug 11, 2003 · N865AF · Grob G120A · Aileron Control SystemSDR VJ32003F00028Bracket · crackedDURING ROUTINE INSPECTION, FOUND THE ALTERNATOR MAOUNTING BRACKET CRACKED. SUSPECT VIBRATION CAUSED CRACK. RECOMMEND GUSSETS BE WELDED INTO RADIUS OF BRACKET OR CHANGE IN MATERIAL/MANUFACTURING PROCESS.Jul 30, 2003 · N861AF · Grob G120A · DC Generator-AlternatorSDR 2003FA0000730Shaft · shearedDURING FLIGHT, THE INSTRUMENT VACUUM SYSTEM FAILED. THE AIRCRAFT RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTEM REVEALED THAT THE ROTOR SHAFT HAD SHEARED. PROBABLE CAUSE MAY BE THE ENGINE MOUNTS USED ARE TOO SOFT AND ALLOW THE ENGINE TO VIBRATE TOO Jun 4, 2003 · N865AF · Grob G120A · Pneumatic Distribution SystemSDR 2003FA0000750Actuator · failedDURING FLIGHT, TRIM WOULD NOT STOP AND CONTINUED TO MOVE TO THE LEFT. PROBABLE CAUSE IS INTERNAL COMPONENT FAILURE IN THE AILERON TRIM ACTUATOR UNIT.May 13, 2003 · N867AF · Grob G120A · Aileron Tab Control SystemSDR 2003FA0000492Seal · leakingFLIGHT CREW NOTICED ODOR OF FUEL DURING GROUND RUN. TECHNICIAN TROUBLESHOOT FUEL SYSTEM AND NOTICED FUEL STAINS ON FUEL PUMP. SO REPLACED FUEL PUMP. ONCE PUMP REMOVED NOTICED GEAR SPLINE WAS WORN DASTRICALLY.Apr 28, 2003 · N863AF · Grob G120A · Engine Fuel PumpSDR 2003FA0000387Alternator · failedALTERNATOR FAILED TO PROVIDE ANY OUTPUT WHILE IN USE. SUSPECT INTERNAL FAILURE.Mar 31, 2003 · N864AF · Grob G120A · DC Generator-AlternatorSDR 2003FA0000348Pump · overheatedTHE HYDRAULIC PUMP CIRCUIT BREAKER KEEPS POPPING WHILE PUMP BUILDS UP PRESSURE. NO WARNING LIGHT COMES ON TO INDICATE PUMP IS GETTING HOT. HOWEVER WHEN YOU TOUCH THE PUMP WITH YOUR HAND IT IS HOT.Mar 20, 2003 · N867AF · Grob G120A · Hydraulic Pump (Electric/Engine), MainSDR 2003FA0000342Shaft · damagedDURING FLIGHT AIR PRESSURE INDICATED ZERO OUTPUT. MAINTENANCE TECH FOUND BROKEN SHAFT ON DRY AIR PUMP. PROBABLE CAUSE: VIBRATION FROM ENGINE. C/A: MFG TO INVESTIGATE PUTTING STIFFER LORD MOUNTS ON ENGINE FRAME TO REDUCE ENGINE VIBRATION TO OTHER COMPONENTSMar 19, 2003 · N862AF · Grob G120A · Pneumatic Distribution SystemSDR 2003FA0000346Uplock · inoperativeDURING FLIGHT GEAR ON LT SIDE WOULD NOT RELEASE. FLIGHT CREW HAD TO PREFORM EMERGENCY EXTENSION AND PULL G`S TO RELEASE GEAR. TROUBLE SHOOT SYSTEM AND FOUND LEFT GEAR UPLOCK WOULD NOT RELEASE GEAR. REPLACED UPLOCK ASSY. RIGGING WAS OUT OF LIMIT. PROBABLE Mar 17, 2003 · N865AF · Grob G120A · Landing Gear Position and WarningSDR VJ32003F00023Line · wornHYDRAULIC LINE WAS FOUND TO HAVE A HOLE WORN IN IT, DURING REGULAR INSPECTION EVENT. THE CAUSE OF THE WEAR AND HOLE WAS FOUND TO BE A BOLT ON THE LANDING GEAR WEARING ON IT DURING EACH EXTENSION/ RETRACTION CYCLE. THIS LINE SUPPLIED HYDRAULIC PRESSURE TO THEMar 3, 2003 · N864AF · Grob G120A · Hydraulic System, MainSDR VJ32003F00024Shock Mount · crackedDURING THE REQUIRD 100 HOUR INSPECTION, MOUNT FOUND TO BE CRACKED FROM EXHAUST HEAT. PART WAS REPLACED WITH NEW AND CRACKED MOUNT RETURNED. SUGGEST ALTERNATE MOUNT AND/OR APPLICATION OF HEAT SHIELD TO PROTECT MOUNT.Mar 3, 2003 · N865AF · Grob G120A · Engine Mount Section
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