# Service difficulty reports: N865AF

A list on [N865AF](https://openairdocs.org/aircraft/N865AF.md).

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.

- [SDR 2007FA0000007](https://openairdocs.org/sdr/2007FA0000007.md): Pump · worn · Oct 30, 2006 · N865AF · Grob G120A · Vacuum Distribution System
  > DURING FLIGHT SUCTION PRESSURE READING DROPPED TO ZERO, DURING FURTHER TROUBLESHOOTING, TECH FOUND THE ENGINE DRIVEN AIR PUMP WAS NOT PRODUCTING ENOUGH SUCTION. PROBABLE CAUSE COULD BE FROM PISTION WEARING INSIDE OF PUMP. RECOMMENDATION AT THIS TIME IS FOR T
- [SDR 2007FA0000006](https://openairdocs.org/sdr/2007FA0000006.md): Shaft · broken · Sep 26, 2006 · N865AF · Grob G120A · Vacuum System
  > DURING ENGINE START, SUCTION PRESSURE WAS READING ZERO, DURING FURTHER TROUBLESHOOTING, TECH FOUND THE ENGINE DRIVEN DRIVEN DRY AIR PUMP HAD A BROKEN SHAFT. PROBABLE CAUSE COULD BE FROM VIBRATION OR HARD START. NO RECOMMENDATION AT THIS TIME. (K)
- [SDR 2006FA0000225](https://openairdocs.org/sdr/2006FA0000225.md): Blower Motor · worn · Feb 27, 2006 · N865AF · Grob G120A · Air Distribution Fan
  > PILOT 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)
- [SDR 2005FA0000925](https://openairdocs.org/sdr/2005FA0000925.md): Servo · malfunctioned · Jun 14, 2005 · N865AF · Grob G120A · Fuel Controlling System
  > PILOT 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 INVESTIGA
- [SDR 2005FA0000112](https://openairdocs.org/sdr/2005FA0000112.md): Ignition Switch · inoperative · Jan 18, 2005 · N865AF · Grob G120A · Ignition Switching
  > PILOT REPORTED STARTER WOULD NOT ENGAGE, AFTER FURTHER INVESTIGATION FOUND IGNITION SWITCH WAS BAD. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME. (K)
- [SDR 2003FA0001012](https://openairdocs.org/sdr/2003FA0001012.md): Lever · binding · Sep 29, 2003 · N865AF · Grob G120A · Aileron Control System
  > DURING 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.
- [SDR 2003FA0000850](https://openairdocs.org/sdr/2003FA0000850.md): Bearing · bulged · Aug 11, 2003 · N865AF · Grob G120A · Aileron Control System
  > DURING 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.
- [SDR 2003FA0000718](https://openairdocs.org/sdr/2003FA0000718.md): Relay · shorted · Jun 8, 2003 · N865AF · Grob G120A · Hydraulic System, Main
  > WHILE PERFORMING GEAR CHECK, THE HYDRAULIC PRESSURE WOULD NOT BUILD UP. FOUND RELAY SHORTED OUT. RECOMMEND INSTALLING AN INLINE FUSE IN THE SYSTEM. WHEN THIS RELAY FAILS, THE RELAY AND DIODES BOARD ALSO FAILS.
- [SDR 2003FA0000730](https://openairdocs.org/sdr/2003FA0000730.md): Shaft · sheared · Jun 4, 2003 · N865AF · Grob G120A · Pneumatic Distribution System
  > DURING 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
- [SDR 2003FA0000555](https://openairdocs.org/sdr/2003FA0000555.md): Bearing · failed · May 12, 2003 · N865AF · Grob G120A · Aileron Control System
  > DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.
- [SDR 2003FA0000552](https://openairdocs.org/sdr/2003FA0000552.md): Bearing · failed · May 12, 2003 · N865AF · Grob G120A · Aileron Control System
  > DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAINING CLIP AND SEAL WERE BEING FORCED OUR OF BEARING.
- [SDR 2003FA0000551](https://openairdocs.org/sdr/2003FA0000551.md): Bearing · failed · May 12, 2003 · N865AF · Grob G120A · Rudder 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 SYSTEM WHICH ALLOWS HE CONTROL ROD DEFLECTION TO EXCEED THE D
- [SDR 2003FA0000550](https://openairdocs.org/sdr/2003FA0000550.md): Bearing · failed · May 12, 2003 · N865AF · Grob G120A · Rudder Control System
  > DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.
- [SDR 2003FA0000540](https://openairdocs.org/sdr/2003FA0000540.md): Bearing · failed · May 12, 2003 · N865AF · 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. REC
- [SDR 2003FA0000392](https://openairdocs.org/sdr/2003FA0000392.md): Bearing · failed · Apr 7, 2003 · N865AF · Grob G120A · Aileron Control System
  > DURING 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 AND
- [SDR 2003FA0000346](https://openairdocs.org/sdr/2003FA0000346.md): Uplock · inoperative · Mar 17, 2003 · N865AF · Grob G120A · Landing Gear Position and Warning
  > DURING 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
- [SDR VJ32003F00024](https://openairdocs.org/sdr/VJ32003F00024.md): Shock Mount · cracked · Mar 3, 2003 · N865AF · Grob G120A · Engine Mount Section
  > DURING 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.
- [SDR VJ32003F00012](https://openairdocs.org/sdr/VJ32003F00012.md): Relay · shorted · Dec 9, 2002 · N865AF · Grob G120A · Hydraulic System, Main
  > DURING PROGRESSIVE INSPECTION FOUND BAD RELAY THAT CAUSED THE LANDING GEAR SYSTEM TO FAIL. BELIEVE THE CAUSE IS BECAUSE THE HYDRAULIC CONTROL RELAY SHORTED INTERNALLY. STILL TROUBLESHOOTING THE SYSTEM TO FIND WHAT CAUSE THE RELAY TO SHORT.
- [SDR VJ32003F00007](https://openairdocs.org/sdr/VJ32003F00007.md): Motor · inoperative · Dec 9, 2002 · N865AF · Grob G120A · Hydraulic Pump (Electric/Engine), Main
  > DURING PROGRESSIVE INSPECTION AND CYCLING THE GEAR THE HYDRAULIC PUMP RCCB CIRCUIT BREAKER WOULD POP. THE HYDRAULIC MOTOR ON THE HYDRAULIC PUMP UNIT WAS PUTTING OUT OVER 75 AMPS.
- [SDR VJ32003F00004](https://openairdocs.org/sdr/VJ32003F00004.md): Handle · shorted · Dec 9, 2002 · N865AF · Grob G120A · Landing Gear Selector
  > LANDING GEAR HANDLE COULD NOT BE SELECTED TO THE UP POSITION AFTER PROGRESSIVE INSPECTION WAS PERFORMED ON AIRCRAFT BY MAINTENANCE. BELIEVE THAT HANDLE HAS A SHORT INTERNALLY CAUSED BY THE SHORTING OUT THE HYDRAULIC CONTROL RELAY AND THE RELAY AND DIODES BOA
- [SDR VJ32002F00094](https://openairdocs.org/sdr/VJ32002F00094.md): Armature · burned out · Nov 21, 2002 · N865AF · Grob G120A · Engine Starter
  > DURING GROUND START OF AIRCRAFT ENGINE WOULD NOT START. MAINTENANCE PERSONNEL INSPECTED AND FOUND STARTER HAD BECOME INOPERATIVE. THE STARTER HAS AN ORDER OF BURNED OUT ARMATURE. NO RECOMMENDATION, PART SENT BACK FOR WARRANTY.
- [SDR VJ32002F00075](https://openairdocs.org/sdr/VJ32002F00075.md): Meter · fluctuates · Sep 13, 2002 · N865AF · Grob G120A · Aircraft Fuel Distribution System
  > DURING FLIGHT THE FLIGHT CREW NOTICED THE FUEL FLOW FLUCTUATING. BELIEVED CAUSED FROM HEAT IN ENGINE BAY CAUSING FUEL TO VAPORIZE AS IS PASSES THROUGH FUEL FLOW METER. RECOMMENDATION IS MOUNT THE FUEL FLOW METER HORIZONTALLY AND WRAP IN HEAT SHIELDING.
- [SDR VJ32002F00063](https://openairdocs.org/sdr/VJ32002F00063.md): Knob · damaged · Sep 9, 2002 · N865AF · Grob G120A · Engine Air Intake System
  > ALT. AIR KNOB BECOMES LOOSE AND INOPERATIVE WITH USE. KNOB IS PLASTIC WITH A HELI-COIL INSERT, SCREWED ONTO THREADED END OF CABLE. KNOB MUST BE ROTATED TO OPERATE ALTERNATE AIR AND THIS CAUSES KNOB TO WEAR AND LOOSEN ON CABLE END. A MORE SECURE METHOD OF AT
- [SDR VJ32002F00056](https://openairdocs.org/sdr/VJ32002F00056.md): Pump · failed · Jun 19, 2002 · N865AF · Grob G120A · Pneumatic Distribution System
  > IN FLIGHT THE INSTRUMENT VACUUM SYSTEM FAIL. THE AIRCRAFT RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTEM FOUNDED THAT THE ROTOR SHAFT HAD SHEARED. PUMP WAS REMOVED AND A NEW PUMP INSTALLED. OPERATIONAL CHECK OF THE SYSTEM CHECKED NORMAL. PART SENT
- [SDR 2002FA0000763](https://openairdocs.org/sdr/2002FA0000763.md): Transducer · failed · Jun 15, 2002 · N865AF · Grob G120A · Fuel Flow Sensor
  > FUEL PRESSURE INDICATION WAS 75 PSI WITH THE ENGINE SHUT DOWN AND THE FUEL BOOST PUMP SHUT OFF. REMOVED TRANSDUCER AND INSTALLED NEW FUEL PRESSURE TRANSDUCER. GROUND OPERATION OF FUEL SYSTEM CHECKED NORMAL.
- [SDR 2002FA0000752](https://openairdocs.org/sdr/2002FA0000752.md): Transducer · failed · Jun 15, 2002 · N865AF · Grob G120A · Fuel Flow Sensor
  > AFTER START UP OF THE ENGINE THE FUEL FLOW INDICATION WENT TO ZERO. AIRCRAFT WAS TAKEN TO MAINTENANCE AND FOUND THAT IF YOU TAPPED ON THE UNIT IT WILL WORK. FUEL FLOW TRANSDUCER WAS REMOVED AND AN NEW FUEL FLOW TRANSDUCER WAS INSTALLED. GROUND RUN OF THE E
- [SDR 2002FA0000766](https://openairdocs.org/sdr/2002FA0000766.md): Transducer · leaking · Jun 12, 2002 · N865AF · Grob G120A · Fuel Flow Sensor
  > FUEL FLOW INTERMITTENT WENT TO ZERO IN FLIGHT. ENGINE FUEL FLOW SYSTEM WAS INSPECTED AND FOUND THAT FUEL FLOW TRANSDUCER WAS LEAKING FUEL. REMOVED TRANSDUCER AND INSTALLED NEW TRANSDUCER. OPERATIONAL CHECK OF THE ENGINE ON THE GROUND CHECKED NORMAL.
- [SDR 2002FA0000767](https://openairdocs.org/sdr/2002FA0000767.md): Shock Mount · broken · Jun 11, 2002 · N865AF · Grob G120A · Instrument Panel
  > INSTRUMENT SHOCK MOUNT BROKEN, IT SUPPORTS THE UPPER RIGHT HAND SIDE. REMOVED BROKEN SHOCK MOUNT AND INSTALLED NEW SHOCK MOUNT.
- [SDR VJ32002F00043](https://openairdocs.org/sdr/VJ32002F00043.md): Baffle · cracked · May 16, 2002 · N865AF · Grob G120A · Reciprocating Engine Cylinder Section
  > ENGINE BAFFLE CRACKED ON NUMBER 1 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED.
- [SDR VJ32002F00038](https://openairdocs.org/sdr/VJ32002F00038.md): Pump · failed · May 16, 2002 · N865AF · Grob G120A · Pneumatic System
  > IN FLIGHT, THE INSTRUMENT VACUUM SYSTEM FAILED. 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 C
- [SDR VJ32002F00036](https://openairdocs.org/sdr/VJ32002F00036.md): Pump · failed · May 10, 2002 · N865AF · Grob G120A · Hydraulic Pump (Electric/Engine), Main
  > IN FLIGHT, THE LANDING GEAR HYDRAULIC PUMP CIRCUIT BREAKER POPPED WITH THE GEAR UP, THE GEAR WAS LOWERED AND A SAFE LANDING WAS MADE. AIRCRAFT WAS PLACED ON JACKS AND THE GEAR SYSTEM WAS OPERATIONAL CHECKED. WITH THE GEAR UP AND LOCKED THE HYDRAULIC PUMP WOU
- [SDR 2002FA0000515](https://openairdocs.org/sdr/2002FA0000515.md): Pump · failed · Apr 15, 2002 · N865AF · Grob G102ASTIR · Hydraulic Pump (Electric/Engine), Main
  > THE LANDING GEAR WAS SWLECTED IN FLIGHT TO THE DOWN POSITION; THE RIGHT MAIN GEAR LIGHT FAILED TO COME ON IN THE DOWN AND LOCKED POSITION. THE AIRCRAFT WAS YAWED AND THE DOWN AND LOCK GEAR LIGHT CAME ON. A SAFE LANDING WAS MADE. AIRCRAFT WAS TAKEN TO MAINTE
- [SDR 2002FA0000474](https://openairdocs.org/sdr/2002FA0000474.md): Switch · failed · Apr 2, 2002 · N865AF · Grob G102ASTIR · Magneto/Distributor
  > MAGNETO SWITCH FAILED TO START ENGINE, FOUND BAD SWITCH. NEW SWITCH INSTALLED, OPERATIONAL CHECKED NORMAL. PART SENT IN FOR WARRANTY.

## 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 = 'N865AF' AND registry_match = 'registration'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/aircraft/N865AF/reports

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