N861AF, cancelled Apr 14, 2026
Service difficulty reports · 21
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. 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 n_number = 'N861AF' AND deregistration_id = 'N861AF-2026-04-14' 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 n_number = 'N861AF' AND deregistration_id = 'N861AF-2026-04-14' 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 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 HRSSDR 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 RECOMMENDATISDR 2005FA0000799Plate · debondedDURING ROUTINE INSPECTION OF AIRCRAFT, TECH FOUND EXCESSIVE MOVEMENT BETWEEN RUDDER AND RUDDER LEVER ASSY. FURTHER INSPECTION SHOWED DISBONDING BETWEEN THE RUDDER SPAR AND THE RUDDER LEVER ASSY SPACER PLATE. PROBABLE CAUSE APPEARS TO BE EXCESSIVE FLEXING OF SDR 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 ADJSDR 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 SSDR 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.SDR 2003FA0000715Hinge · failedDURING 50 HR INSPECTION THE TECH FOUND THE RETAINING CLIP COMING OUT OF BEARING.SDR 2003FA0000542Bearing · failedDURING 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 CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. RECOMMSDR 2003FA0000538Bearing · failedDURING 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. RESDR 2003FA0000534Bearing · failedDURING 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 ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. RECOMMEND DESIGN CHANGE OR REPLACESDR 2003FA0000347Selector Valve · failedDURING A PROGRESSIVE INSPECTION, TECH FOUND THE FUEL SELECTOR VALVE LOOSE AND HARD TO TURN. PROBABLE CAUSE IS INTERNAL FAILURE.SDR VJ32003F00008Motor · failedDURING PROGRESSIVE INSPECTION AFTER BLOWING GEAR DOWN AND CYCLING GEAR MOTOR WINDING SMELLED AS BURNED OUT. GEAR WOULD NOT CYCLED AFTER THAT, AND WOULD POP CIRCUIT BREAKER TO THE HYD PUMP RCCB. MOTOR ACTED AS IF THE LOAD WAS TOO HEAVY FOR THE MOTOR TO PRODUCSDR VJ32003F00005Shock Mount · damagedDURING PROGRESSIVE INSPECTION OF ENGINE BAY FOUND LOWER LT MOUNT DAMAGED FROM HEAT OF EXHAUST SYSTEM. SUGGEST INSTALLING SOME TYPE OF HEAT SHIELDING OR CHANGING MOUNT TO A MORE HEAT RESISTANT STYLE.SDR VJ32002F00062Clamp · crackedDURING PROGRESSIVE INSPECTION FOUND CLAMP CRACKED AND ROLL RIVET SHEARED OFF. PROBABLE CAUSE IS ENGINE VIBRATION.SDR VJ32002F00059Baffle · crackedENGINE BAFFLE CRACKED ON NUMBER 3 CYLINDER FROM NORMAL ENGINE VIBRATION.SDR 2002FA0000718Muffler · crackedTAIL PIPE SUPPORT BRACKET CRACKED AT WELD. REMOVED MUFFLER AND INSTALLED NEW MUFFLER ASSEMBLY. PART SENT IN FOR WARRANTY.SDR 2002FA0000714Baffle · crackedENGINE BAFFLE CRACKED ON NUMBER 3 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED. PART SENT IN FOR WARRANTY.SDR 2002FA0000712Baffle · crackedENGINE BAFFLE CRACKED ON NUMBER 1 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED.SDR VJ32002F00042Pump · burned outLANDING GEAR FAILED, WHEN THE GEAR WAS SELECTED TO THE UP POSITION AFTER TAKE OFF. THE GEAR WAS LOWER AND A SAFE LANDING WAS MADE. INSPECTION OF THE GEAR SYSTEM FOUND THAT THE MOTOR ON THE HYDRAULIC PUMP BURNED OUT. PUMP ASSEMBLY WAS REMOVED AND A NEW PUMP SDR 2002FA0000478Pump · damagedMETAL SHAFT SHEARED IN PUMP. REMOVED AND INSTALLED NEW PUMP, SYSTEM OPERATIONAL CHECKED NORMAL. PUMP SENT IN FOR WARRANTY.SDR 2002FA0000477Pin · brokenLEFT HAND STOP PIN BROKEN OFF, REMOVED AND INSTALLED NEW CLOCK. PART SENT IN FOR WARRANTY.
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