Aero Commander 690B
Service difficulty reports · 73
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 = '690B' 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 aircraft_model_key = '690B' 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 2025F00176Drag Brace · brokenLEFT MAIN LANDING GEAR DRAG BRACE ASSEMBLY P/N EA1570-501 WAS FOUND CRACKED IN THE UPPER PORTION OF THE DRAG BRACE. CRACK WAS FOUND DURING A PRE FLIGHT INSPECTION. THE CRACK IS IN AN AERA THAT TWIN COMMANDER SL 376 ADDRESSES FOR NDT INSPECTION. CRACKED DRAG BRSDR 2024F00109Wire · chafedDURING TRAINING FLIGHT AROUND THE PATTERN ABOVE KFMM PILOT NOTICED FIRE WARNING LIGHT INTERMITTENTLY ILLUMINATED. PILOT REPORTED REDUCING POWER AND LIGHT WOULD NOT ILLUMINATE AGAIN. LANDED AIRCRAFT AND REPORTED TO MAINTENANCE THE CONDITION. UPON TROUBLESHOOTINSDR 2022FA0000295None · noneTHE WHEEL AND BRAKES ON THE LH MAIN LANDING GEAR CAUGHT FIRE DURING A LONG TAXI FOR A DEPARTURE. THE INITIAL PICTURES SHOWED ALL COMPONENTS INTACT. THE AIRCRAFT WAS THEN TOWED ON A DOLLY TO THE FBO.SDR 2019FA0000185Brace · damagedWHILE PERFORMING SERVICE LETTER NO. 355, FUSELAGE STATION 386.82 SCREW TORQUE INSPECTION, FOUND BOTH BOLTS ATTACHING BRACES 310024-15 AND 310024-16 TO BRACE 310024-53 LOOSE AND THE BOLT HOLES ELONGATED. SERVICE LETTER 355 IS A ONE TIME INSPECTION INTENDED TO SDR LAMA20190624531Tire · flatON LANDING ROLL OUT, THE PIC NOTED A NOISE AND THE AIRCRAFT TENDED TO PULL TO THE LEFT. A VISUAL CONFIRMATION OF A FLAT TIRE ON THE LT MAIN GEAR WAS NOTED. THE AIRCRAFT EXITED THE RUNWAY AND STOPPED ON THE TAXI WAY FOR FURTHER EVALUATION AND REPAIR. THE LT WHESDR EHSA2019F00173Attach Bolt · looseCRACKS WERE FOUND DURING ROUTINE INSPECTION AT STATION 386.82. THIS SECTION IS LOCATED AT THE FORWARD SECTION OF THE ATTACH POINT FOR THE VERTICAL TAIL. UPON FURTHER INSPECTION OF THE REMAINING 8 AIRCRAFT 2 ADDITIONAL AIRCRAFT WERE FOUND TO HAVE MINOR CRACKISDR 7PTA201808040001Engine · power lossAFTER TAKE OFF, DURING CLIMB PASSING THROUGH 4000 AGL, THE RIGHT ENGINE LOST POWER. PILOT SHUT THE ENGINE DOWN, FEATHERED THE PROP AND RETURNED TO DEPARTURE. OPEN.SDR 2018FA0000138Control Cable · looseDURING REQUIRED NEGATIVE TORQUE SYSTEM CHECK FLIGHT, THE RT ENGINE WAS SHUTDOWN AND FAILED TO RE-LIGHT. THE ENGINE WOULD NOT RE-LIGHT DUE TO A FAILURE OF THE AIRFRAME EMERGENCY FUEL SHUTOFF CONTROL ASSEMBLY (CABLE PN 57-7741-2075). AN IN-FLIGHT EMERGENCY WAS DSDR 7PTA2018012500001Hydraulic Line · backed outLEFT ENGINE HYDRAULIC LINE BETWEEN ENGINE HYD PUMP AND FIREWALL. FITTING AT THE FIREWALL LOOSENED UP AND LEAKED HYD FLUID TO THE POINT THE PILOT GOT A HYP PRESS LOW LIGHT. PILOT DECLARED AND EMERGENCY AND LANDED WITHOUT INCIDENT.SDR L50R2015FA0000478Shaft · brokenTHE AIRCRAFT EXPERIENCED AN INFLIGHT, UNCOMMANDED NOSE GEAR EXTENSION INTO THE DOWN & LOCKED POSITION. TROUBLESHOOTING IN A MAINTENANCE FACILITY REVEALED THAT THE ACTUATING SHAFT OF THE HYDRAULIC NOSE GEAR RETRACT CYLINDER HAD FRACTURED AND FAILED. BY DESIGNSDR 2015F00046Engine · fireAFTER LANDING, PILOT WAS TAXING AND THE LEFT ENGINE FIRE LIGHT CAME ON, THE ENGINE LOST ALL POWER AND FIRE AND SPARKS WERE COMING OUT OF THE TAIL PIPE. VISUAL INSPECTION SHOWED NR 3 TURBINE WHEEL BLADES MELTED. AFTER REMOVAL AND DISASSEMBLY OF THE ENGINE, ALSDR 2013FA0000060Engine · failedIN NORMAL CRUISE AT 3,000 FT MSL, THE LT ENGINE LOST COMPLETE POWER AND SUBSEQUENTLY BEGAN TO NTS (NEGATIVE THRUST SENSING). THE ENGINE WAS INDENTIFIED, VERIFIED AND FEATHERED IAW EMERGENCY CHECKLIST PROCEDURES.SDR O9IA2012012400012Blower Motor · burnedDURING CLIMBOUT, PILOT SELECTED WINDSHIELD DEFOG. ELECTRIC ODOR IN COCKPIT AND SMOKE SEEN FROM AREA BEHIND INSTRUMENT PANEL. PILOT NOTICED THAT DEFOG BLOWER WAS NOT FUNCTIONAL. CABIN PRESSURE WAS DUMPED AND ACFT RETURNED TO STATION. INVESTIGATION REVEALED SDR CA120130011Line · misinstalled(CAN) UPON DISCONNECTING COMPONENTS TO REMOVE THE CENTER SECTION BLADDERS, SOME COMPONENTS WERE FOUND TO BE CONNECTED INCORRECTLY. UPON CONSULTING MM TO VERIFY WIRING, FOUND THE FOLLOWING: THE RT ENGINE FUEL LINE WAS CONNECTED TO THE LT FUEL SHUTOFF AND THE RSDR 2011FA0000699Strut · crackedLEFT MAIN GEAR STRUT WAS FLAT, TRIED TO SERVICE, WHEN WE APPLIED NITROGEN PRESSURE HYDRAULIC FLUID CAME OUT OF A 3 INCH LONG CRACK IN THE STRUT BODY AND BEARING ASSY. AFTER TALKING WITH MFG THEY HAVE NEVER SEEN THIS TYPE OF FAILURE BEFORE.SDR 2011FA0000320Skin · misrepairedFOUND SB 237 IAW AD 2009-25-2 UPPER WING SKIN, STRAP INSP AND MODIFICATION DONE INCORRECTLY. HARDWARE AND FASTENERS WERE NOT CORRECTLY PLACED AND WERE SUBSTITUTED INCORRECTLY IAW SB 237. MFG WAS NOTIFIED AND AN ENGINEERING REPAIR AND AMOC WAS COMPLETED. ALTSDR 2010FA0001101Pulley · chafedFLAP PULLEY CHAFES FLAP BRACKET - PREVIOUSLY ADDRESSED IN AD98-07-17 AND SB226.SDR 2010FA0001100Pulley · chafedFLAP PULLEY AND CLIP CHAFE FLAP BRACKET - ADDRESSED PREVIOUSLY IN BOTH AD98-07-17 AND SB226.SDR 2010F00211Control Head · burnedDME HEAD SHORTED INSIDE CAUSING SMOKE TO BE PULLED INTO AVIONICS VENTILATION SYS AND CIRCULATED TO THE ACFT CABIN.SDR NYS2009F00000Drag Brace · crackedDURING PHASE INSP, FOUND UPPER WEB OF DRAG BRACE CRACKED THRU UPLOCK BRACKET ATTACH HOLE.SDR PAI52007S4751Line · rupturedHYDRAULIC PRESSURE FLEX LINE AT RT ENGINE DRIVEN HYDRAULIC PUMP RUPTURED IN FLIGHT CAUSING LOSS OF HYDRAULIC FLUID.SDR 2007FA0000092Turbine Wheel · damagedINSPECTION OF ENGINE REVEALED DAMAGE TO 3RD STAGE TURBINE ROTOR VISIBLE THROUGH ENGINE TAILPIPE. ENGINE WAS REMOVED FROM AIRCRAFT AND THE TURBINE SECTION MODULE REMOVED TO INVESTIGATE FOR CAUSE OF DAMAGE. UPON INSPECTION 4 EA PINS WERE FOUND MISSING FROM 2NDSDR 2006FA0000083Skin · corrodedCORROSION BEYOND 10 PERCENT LIMITS IN LEADING EDGE SKIN UNDER BALANCE WEIGHTS. FOUND DURING SB238. (K)SDR FTU2004F00003Spar · crackedWHILE COMPLYING WITH SB 236. AILERON SPAR IB HINGE INSPECTION AND REINFORECMENT DATED MARCH 9, 2004 PART 1, BOTH AILERON IB SPAR WEBS AT IB HINGE AREA WERE FOUND CRACKED, THE AFT AND FORWARD END RIBS ALSO SHOWED CRACKS. WHILE COMPLYING WITH THE NEEDED REPAIRSDR LDI2004F00000Trunnion Pin · seizedNOSE GEAR WOULD NOT RETRACT. TRUNNION PINS HAD FROZEN UP. TRUNNION PINS DO NOT HAVE ANY LUBRICATION GREASE ZERTS WHICH COULD HAVE PREVENTED THE NOSE GEAR TRUNNION FROM FREEZING UP.SDR W1J2004F00000Retaining Ring · out of positionON 2/6/04 A NORMAL ENGINE RUN AND TAXI WAS BEING PERFORMED. AS WE ATTEMPTED TO TAXI OUT THE LT SIDE SEEMED TO HAVE NO THRUST OR MOVEMENT. WE HEARD A LOUD THUMP OR POP ON THE LT SIDE OF THE AIRCRAFT. AT THAT TIME WE ABORTED THE TAXI AND SHUT DOWN BOTH ENGINESDR FTU2003F00004Exciter · failedEXCITER BOX HAD INTERMITTENT FAILURE AFTER ONLY BEING IN SERVICE FOR 11.3 HOURS. THIS UNIT WAS ORIGINALLY A MFG BLUE LABELED REMANUFACTURED PART. INSTALLED ANOTHER OVERHAULED UNIT, OPS CHECKED SYSTEM, NO PROBLEMS FOUND. THIS UNIT RETURNED TO VENDOR FOR POSSSDR FTU2003F00002Pump · mismanufacturedWHEN PUMP WAS INSTALLED, IT WAS DISCOVERED THAT THE THREADS ON THE IN AND OUT PORTS WERE STRAIGHT THREAD. THE FITTINGS THAT ARE CALLED OUT IN THE IPC ARE PIPE THREAD, BECAUSE OF THE LIMITED SPACE AT THE PUMP MOUNTED POSITION. OVERHAUL PUMP WAS CHANGED AND THSDR 2003FA0000516Cap · separatedSHORTLY AFTER LEVELING OFF AT A CRUISE ALTITUDE OF 16,000 FT, THE AIRCRAFT MADE A HARD UNCOMMANDED TURN TO THE LEFT AND LOST APPROX 1000 FT ALTITUDE BEFORE THE PILOT WAS ABLE TO REGAIN CONTROL. POST FLIGHT INSPECTION REVEALED THAT THE TOP PORTION OF THE RUDDESDR 2002FA0001222Indicator · defectiveNON-LINEAR ERROR GAGE READS COOLER THAN INPUT 5 DEGREE AT 400, 6 DEGREE C 500, 7 DEGREES C 600 AS HIGH AS 10 DEGREE AT TIMES ZERO ERROR AT 200 DEGREE. DEFECT FOUND DURING CALIBRATION OF EGT DUE TO TEMP SPLITS.SDR 2002FA0000924Relay · failedNR 2 BATTERY MAIN RELAY FAILED CLOSED. THE FAILURE CREATED HEAT DISTRESS AND MELTED THE CONTACTORS WITHIN THE RELAY.SDR O9I2002F00002Rib · crackedDURING A ROUTINE PERIODIC INSPECTION A CRACK WAS FOUND IN VERTICAL STABILIZER BOTTOM RIB (PN 410008197) . THE CRACK RADIATED FROM THE SIDE FLANGE (LEFT) FORWARD RIVET AND EXTENDED TO THE EDGE OF THE RIB. THE TOTAL CRACK LENGTH IS .375 INCH. THE LOWER RIB OSDR MV52002F00001Monitor · failedFUEL QUANTITY INDICATION -0- AT ALL TIMES. REPLACEMENT OF FUEL QUANTITY CONTROL MONITOR CORRECTED INDICATION PROBLEM.SDR MV52002F00000Tube · crackedFORWARD CABIN DOOR STEP TUBE CRACKED AT ROLL PIN (PN MS9048-047) ATTACHMENT. CRACK EXTENDED ONE INCH AFT FROM THE ROLL PIN.SDR MV52001F00001Skin · crackedUPPER FUSELAGE SKIN CRACKED AT COMM ANTENNA MOUNTING BASE LOCATED AT STATION 210, FIVE INCHES LEFT OF AIRCRAFT CENTERLINE. ANTENNA INSTALLATION WAS ORIGINAL FROM AIRCRAFT MANUFACTURE. CRACK ATTRIBUTED TO INSUFFICIENT METAL THICKNESS TO BOTH OUTER SKIN OF .02SDR MV52001F00000Angle · crackedANGLE LOCATED AT LEFT MAIN LANDING GEAR TO WING ATTACH AREA CRACKED AT INBOARD SIDE. CRACK EXTENDED ONE INCH FROM AFT PORTION OF WING AREA FORWARD.SDR 20001207SH017Drag Brace · crackedUPPER PORTION OF DRAG BRACE CRACKED. CRACK EXTENDED APPROXIMATELY .50 INCH. (X)SDR 20001130SH003Seat Track · corrodedPILOT INBOARD SEAT RAIL LOCATED AT THE FLOOR ATTACHMENT HAD EVIDENCE OF CORROSION AT THE AFT ATTACHMENT SCREWS. (X)SDR 20001109SH009Aileron · crackedDURING INSPECTION, 3 EACH .25 INCH LONG CRACKS WERE FOUND ON THE LEADING EDGE AT THE FASTENERS USED TO SECURE THE AILERON BALANCE WEIGHT. AFTER THE LEADING EDGE WAS REMOVED FROM THE AILERON AS PART OF THE REPAIR, A .75 INCH LONG CRACK WAS FOUND IN THE LOWER ISDR 20001026SH008Arm · crackedARM ASSY CRACKED AT LANDING GEAR DOOR ATTACH AREA. (X)SDR 20000622SH031Control Cable · frayedRIGHT RUDDER CABLES FRAYED. (X)SDR 20000524SH014Control Cable · frayedLEFT AND RIGHT FORWARD RUDDER CABLES HAD BROKEN WIRE STRANDS AT LEFT AND RIGHT PULLEY AT BS 99.00. FOUND DURING 100-HOUR INSPECTION. ROTATED CABLES 10 DEGREES FROM PULLEY TO SEE BROKEN WIRE STRANDS. CAUSE, DETERIORATION DUE TO TIME. AIRCRAFT TT: 5,313 HOUSDR 20000524SH013Control Cable · brokenLEFT AND RIGHT FORWARD RUDDER CABLES HAD BROKEN WIRE STRANDS AT LEFT AND RIGHT PULLEY AT BS 99.00. FOUND DURING 100-HOUR INSPECTION. ROTATED CABLES 10 DEGREES FROM PULLEY TO SEE BROKEN WIRE STRANDS. CAUSE, DETERIORATION DUE TO TIME. AIRCRAFT TT: 5,313 HOUSDR 20000516SH002Channel · crackedAFTER REMOVAL OF BOTH RT AND LT AILERON INBOARD HINGE ASSEMBLIES, FOUND BOTH AILERON ''U'' CHANNELS HAD CRACKS IN THE WEB AROUND THE LOWER HINGE ATTACH BOLTS. SUBMITTER RECOMMENDED INSTALLING A REINFORCING PLATE ON AFT SIDE OF WEB IAW AC 43.131B PAR 4-58, 4-5SDR 20000516SH001Channel · crackedAFTER REMOVAL OF BOTH RT AND LT AILERON INBOARD HINGE ASSEMBLIES, FOUND BOTH AILERON ''U'' CHANNELS HAD CRACKS IN THE WEB AROUND THE LOWER HINGE ATTACH BOLTS. SUBMITTER RECOMMENDED INSTALLING A REINFORCING PLATE ON AFT SIDE OF WEB IAW AC 43.131B PAR 4-58, 4-5SDR 20000522SH002Line · brokenRIGHT ENGINE WOULD NOT START. FOUND PY LINE BROKEN JUST AFT OF LINE FITTING. REPLACED LINE. (X)SDR 99ZZZX4242Control Cable · frayedCABLE FOR TRIM CONTROL AT THE COLLINS AUTOPILOT ELEVATOR TRIM SERVO WAS FOUND FRAYED APPROXIMATELY 90 PERCENT THROUGH.SDR 99ZZZX14Autopilot · misinstalledAUTOPILOT WOULD NOT CAPTURE NAV OR SLOW TO CAPTURE. AUTOPILOT WOULD DRIFT FROM PROPER COURSE WHEN CAPTURED. THIS WAS DUE TO INCORRECT HSI MODE RELAY INTERFACE WIRING FOR GPS. WIRING WAS INTERRUPTED AT AUTOPILOT FLIGHT DIRECTOR FD 112V AND SHOULD HAVE BEEN ISDR 99ZZZX948Tire · leakingTIRES WERE REPLACED BECAUSE THEY WOULD NOT HOLD AIR. INSPECTION REVEALED DILATING HOLES ALLOWING AIR LOSS TO CONTINUE AFTER SEVERAL DAYS. LEAKAGE BECAME WORSE TO THE POINT RE-INFLATION WAS NEEDED AFTER EACH FLIGHT. HIGH RISK OF LANDING WITH FLAT TIRE ON TRISDR 99ZZZX947Tire · leakingTIRES WERE REPLACED BECAUSE THEY WOULD NOT HOLD AIR. INSPECTION REVEALED DILATING HOLES ALLOWING AIR LOSS TO CONTINUE AFTER SEVERAL DAYS. LEAKAGE BECAME WORSE TO THE POINT RE-INFLATION WAS NEEDED AFTER EACH FLIGHT. HIGH RISK OF LANDING WITH FLAT TIRE ON TRI
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