# Service difficulty reports: N864AF A list on [N864AF](https://openairdocs.org/aircraft/N864AF.md). Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first. - [SDR 2015FA0000653](https://openairdocs.org/sdr/2015FA0000653.md): Ignition Switch · failed · Dec 16, 2015 · N864AF · Grob G120A · Ignition Switching > PILOT REPORTED SMOKE OUT OF IGNITION SWITCH DURING START UP. INVESTIGATION FOUND THE STARTER SWITCH HAD INTERNALLY ARCED ACROSS THE CONTACTS. - [SDR 2007FA0000003](https://openairdocs.org/sdr/2007FA0000003.md): Pump · out of limits · Nov 10, 2006 · N864AF · Grob G120A · Pneumatic System > PILOT REPORTED SUCTION INDICATOR WAS BELOW LIMITS, AC RETURNE TO BASE. UPON TROUBLESHOOTING, THE MECHANIC REMOVED THE AIR PUMP AND NOTICED THE SHAFT WAS VERY EASY TO ROTATE, HAD NO RESISTANCE TO IT. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME. (K) - [SDR 2007FA0000004](https://openairdocs.org/sdr/2007FA0000004.md): Pump · weak · Oct 26, 2006 · N864AF · Grob G120A · Vacuum Distribution System > IN 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. OP - [SDR 2005FA0000602](https://openairdocs.org/sdr/2005FA0000602.md): Volt Regulator · inoperative · Apr 13, 2005 · N864AF · Grob G120A · DC Regulator > AFTER 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. - [SDR 2005FA0000151](https://openairdocs.org/sdr/2005FA0000151.md): Swivel · cracked · Nov 24, 2004 · N864AF · Grob G120A · Nose/Tail Landing Gear > INSPECTION OF NOSE GEAR UPPER TRUNNION BOLTS FOUND CRACKS AROUND WELDS AND ON THE EARS FOR THE SWIVEL TUBE. PROBABLE CAUSE EXCESSIVE STRESSES IN THIS AREA. AT THIS TIME NO RECOMMENDATION UNTIL MFG MAKES DETERMINATION OF CAUSES. (K) - [SDR 2005FA0001122](https://openairdocs.org/sdr/2005FA0001122.md): Bearing · failed · Nov 4, 2004 · N864AF · Grob G120A · Main Landing Gear > DURING INSPECTION OF MAIN LANDING GEAR, DISCOVERED EXCESSIVE FORE AND AFT PLAY IN RT MLG LEG. RT MAIN LEG COULD MOVE FORE AND AFT 4MM OR MORE. GEAR LEG WAS REMOVED. INSPECTION OF THE AFT TRUNION ASSY REVEALED THAT THE BEARING HAD FAILED AND HAD EXCESSIVE PL - [SDR 2004FA0000720](https://openairdocs.org/sdr/2004FA0000720.md): Starter · intermittent · Jul 27, 2004 · N864AF · Grob G120A · Engine Starter > PILOT REPORTED STARTER WOULD NOT ENGAGE, PROBABLE CAUSE AT THIS TIME UNKNOWN. - [SDR 2004FA0000717](https://openairdocs.org/sdr/2004FA0000717.md): Ignition Switch · intermittent · Jul 27, 2004 · N864AF · Grob G120A · Ignition Switching > AFTER INSTALLING IGNITION SWITCH, THE MECHANIC NOTICE THE SWITCH WAS HARD TO PUSH IN AND INTERMITTENT AT THE START POSITION. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME. - [SDR 2003FA0001016](https://openairdocs.org/sdr/2003FA0001016.md): Motor · failed · Sep 25, 2003 · N864AF · Grob G120A · Hydraulic Pump (Electric/Engine), Main > DURING 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 CAPA - [SDR 2003FA0000549](https://openairdocs.org/sdr/2003FA0000549.md): Bearing · failed · May 12, 2003 · N864AF · Grob G120A · Rudder Control System > DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAIN CLIP AND SEAL WERE BEING FORCED OUT OF BEARING. - [SDR 2003FA0000544](https://openairdocs.org/sdr/2003FA0000544.md): Bearing · failed · May 12, 2003 · N864AF · Grob G120A · Aileron Control System > DURING 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. RE - [SDR 2003FA0000543](https://openairdocs.org/sdr/2003FA0000543.md): Bearing · failed · May 12, 2003 · N864AF · Grob G120A · Aileron Control System > DURING 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. RE - [SDR 2003FA0000537](https://openairdocs.org/sdr/2003FA0000537.md): Bearing · failed · May 12, 2003 · N864AF · Grob G120A · Flight Control System > DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAING 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. RECO - [SDR 2003FA0000497](https://openairdocs.org/sdr/2003FA0000497.md): Valve · inoperative · May 3, 2003 · N864AF · Grob G120A · Landing Gear Retraction/Extension System > PILOT REPORTED GEAR WAS SLOWLY TO EXTEND, OVER 1 MINUTE. AFTER PULLING 3 G`S AT 150 KNOTS GEAR FINALLY EXTENDED DOWN AND LOCKED. ON FURTHER INVESTIGATION WE FOUND NO PROBABLE CAUSE OR RECOMMENDATIONS TO PREVENT THIS FROM RECURRING. - [SDR 2003FA0000387](https://openairdocs.org/sdr/2003FA0000387.md): Alternator · failed · Mar 31, 2003 · N864AF · Grob G120A · DC Generator-Alternator > ALTERNATOR FAILED TO PROVIDE ANY OUTPUT WHILE IN USE. SUSPECT INTERNAL FAILURE. - [SDR VJ32003F00023](https://openairdocs.org/sdr/VJ32003F00023.md): Line · worn · Mar 3, 2003 · N864AF · Grob G120A · Hydraulic System, Main > HYDRAULIC 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 THE - [SDR 2003FA0000343](https://openairdocs.org/sdr/2003FA0000343.md): Pump · failed · Feb 20, 2003 · N864AF · Grob G120A · Engine Fuel Pump > DURING GROUND RUN FUEL PRESSURE READINGS WERE HIGH AND UNABLE TO ADJUST PRESSURES. - [SDR 2003FA0000168](https://openairdocs.org/sdr/2003FA0000168.md): Manifold · inoperative · Jan 28, 2003 · N864AF · Grob G120A · Landing Gear Retraction/Extension System > DURING FLIGHT THE FLIGHT CREW REPORTED THAT THE LEFT GEAR WAS SLOW TO EXTEND. MAINTENANCE TROUBLESHOT SYSTEM AND FOUND LEFT EXTENSION VALVE BAD. PARTICLES INSIDE OF VALVE WHICH PREVENTED FLUID TO FLOW UNRESTRICTED. - [SDR VJ32003F00009](https://openairdocs.org/sdr/VJ32003F00009.md): Relay · shorted · Dec 9, 2002 · N864AF · Grob G120A · Hydraulic System, Main > DURING PROGRESSIVE INSPECTION AND CYCLE OF THE LANDING GEAR, WE HAD A FAILURE OCCUR. FOUND A BAD HYD. CONTROL RELAY THAT SHORTED. BECAUSE OF THAT SHORT, IT ALLOWED TOO MUCH CURRENT TO FLOW TO PC BOARD AND SHORT OUT BOARD BETWEEN RELAY K-13 PIN 13 AND 16 TO B - [SDR VJ32002F00084](https://openairdocs.org/sdr/VJ32002F00084.md): Terminal Block · loose · Oct 4, 2002 · N864AF · Grob G120A · Engine Starting System Wiring > DURING PROGRESSIVE INSPECTION OF ENGINE FOUND TERMINAL STUD ON STARTER SOLENOID LOOSE. - [SDR VJ32002F00082](https://openairdocs.org/sdr/VJ32002F00082.md): Valve · failed · Oct 4, 2002 · N864AF · Grob G120A · Engine Fuel Distribution > DURING FLIGHT THE CHT IS CONSISTENTLY HIGH DURING ALL LEVELS OF FLIGHT. PROBABLE CAUSE IS INTERNAL FAILURE OF MANIFOLD VALVE NOT ALLOWING FUEL FLOW PROPERLY. - [SDR VJ32002F00081](https://openairdocs.org/sdr/VJ32002F00081.md): Manifold · inoperative · Sep 25, 2002 · N864AF · Grob G120A · Engine Fuel Distribution > ENGINE WILL NOT SHUT DOWN IN IDLE CUT OFF. RPM JUMPS FROM 250 RPM TO 400 RPM. BELIEVE DIAPHRAM DOES NOT SEAT TO CUT OFF FUEL FLOW. - [SDR VJ32002F00079](https://openairdocs.org/sdr/VJ32002F00079.md): Uplock Sensor · failed · Sep 25, 2002 · N864AF · Grob G120A · Landing Gear Position and Warning > DURING LANDING GEAR INSPECTION GEAR ON LT MAIN WOULD NOT RELEASE FROM UP POSITION UNLESS USING EMERGENCY SYSTEM. TROUBLE SHOOTING THE GEAR SYSTEM FOUND THE LEFT UPLOCK SWITCH WAS NOT RELEASING WHEN GEAR SELECTED TO DOWN POSITION. PROBABLE CAUE COULD BE THE W - [SDR VJ32002F00068](https://openairdocs.org/sdr/VJ32002F00068.md): Sensor · broken · Sep 6, 2002 · N864AF · Grob G120A · Magneto/Distributor > RPM INDICATION SENSOR RING FOUND BROKEN DURING ROUTINE INSPECTION. THIS SENSOR RING FITS UNDER THE VENT OF THE RIGHT MAGNETO AND PROVIDES ENGINE RPM INDICATIONS. APPEARS TO BE BROKEN DUE TO FLEXING/FATIGUE. PERHAPS A DIFFERENT SENSOR OR OTHER MORE SECURE MO - [SDR VJ32002F00067](https://openairdocs.org/sdr/VJ32002F00067.md): Strap · broken · Sep 6, 2002 · N864AF · Grob G120A · Engine Oil Cooler > TERMINAL END OF OIL COOLER STRAP FOUND BROKEN DURING ROUTINE INSPECTION. APPEARS TO BE CAUSED BY FLEXING AND FATIGUE. RECOMMEND OTHER METHOD OF MOUNTING OIL COOLER. PERHAPS A RIGID MOUNT WOULD BE BETTER. - [SDR VJ32002F00066](https://openairdocs.org/sdr/VJ32002F00066.md): Handle · failed · Sep 6, 2002 · N864AF · Grob G120A · Landing Gear Position and Warning > GEAR HANDLE EXPERIENCED INTERNAL FAILURE CAUSING MALFUNCTION OF THE HYDRAULIC GEAR PUMP. WHEN THE PUSH TO TEST BUTTON WAS PRESSED FOR THE ANNUNCIATOR PANEL, THE PUMP WOULD OPERATE. - [SDR VJ32002F00065](https://openairdocs.org/sdr/VJ32002F00065.md): Downlock Switch · failed · Sep 6, 2002 · N864AF · Grob G120A · Landing Gear Position and Warning > DOWN SWITCH FAILED CAUSING NO DOWN INDICATION OF NOSE GEAR IN THE DOWN POSITION. - [SDR VJ32002F00061](https://openairdocs.org/sdr/VJ32002F00061.md): Baffle · cracked · Aug 5, 2002 · N864AF · Grob G120A · Reciprocating Engine Cylinder Section > ENGINE BAFFLE CRACKED ON NUMBER 4 CYLINDER FROM NORMAL ENGINE VIBRATION. - [SDR VJ32002F00060](https://openairdocs.org/sdr/VJ32002F00060.md): Baffle · cracked · Aug 5, 2002 · N864AF · Grob G120A · Reciprocating Engine Cylinder Section > ENGINE BAFFLE CRACKED ON NUMBER 1 CYLINDER FORM NORMAL ENGINE VIBRATION. RECOMMEND FOR FACTORY TO REINVESTIGATE ENGINEERING DRAWING TO COME UP WITH A STRONGER PIECE OF BAFFLING TO INSTALL. - [SDR 2002FA0000768](https://openairdocs.org/sdr/2002FA0000768.md): Bracket · cracked · Jun 11, 2002 · N864AF · Grob G120A · DC Generator-Alternator > ALTERNATOR BRACKET CRACKED, THIS BRACKET IS USED TO ADJUST THE BELT TENSION. REMOVED BRACKET AND INSTALLED NEW BRACKET. ADJUSTED BELT TENSION IAW MM. - [SDR VJ32002F00045](https://openairdocs.org/sdr/VJ32002F00045.md): Pump · failed · May 21, 2002 · N864AF · Grob G120A · Pneumatic System > IN FLIGHT THE INSTRUMENT VACUUM SYSTEM FAIL. THE AIRCRAFT RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTEM FOUNDED THAT THE ROTOR HAD FROZEN UP AND THE SHAFT HAD SHEARED. PUMP WAS REMOVED AND A NEW PUMP INSTALLED. OPERATIONAL CHECK OF THE SYSTEM CHE - [SDR VJ32002F00044](https://openairdocs.org/sdr/VJ32002F00044.md): Baffle · cracked · May 21, 2002 · N864AF · Grob G120A · Reciprocating Engine Cylinder Section > ENGINE BAFFLE CRACKED ON NUMBER 1 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED. - [SDR 2002FA0000713](https://openairdocs.org/sdr/2002FA0000713.md): Support Bracket · cracked · May 4, 2002 · N864AF · Grob G120A · DC Generator-Alternator > ALTERNATOR SUPPORT BRACKET CRACKED. PART REMOVED AND A NEW SUPPORT BRACKET INSTALLED. ## The whole list in SQL Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS: ```sql 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 n_number = 'N864AF' AND registry_match = 'registration' ORDER BY difficulty_date DESC ``` This list as a web page: https://openairdocs.org/aircraft/N864AF/reports --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.