Aero Commander 690A
Service difficulty reports · 121
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 = '690A' 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 = '690A' 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 CA080205008Power Cable · frozen(CAN) DURING A TEST FLIGHT, THE LT POWER LEVER CABLE FROZE AND WOULD NOT RESPOND TO INPUTS. THE OAT AT THE TIME WAS -28 DEG C. THE POWER SETTING WAS AT MAX ITT FOR TEST PURPOSES. SINCE THE PILOT COULD NOT REDUCE POWER, THE ENGINE WAS SHUTDOWN AND THE PROPELLESDR CA071109006Indicator · unserviceable(CAN) DURING CRUISE THE NR2 ENGINE ITT INDICATION BECAME ERRATIC, THEN CLIMBED THROUGH THE RED LINE. THE FLIGHT CREW SHUTDOWN THE ENGINE AND FEATHERED THE PROP. THE AIRCRAFT RETURNED TO AIRPORT. MAINTENANCE TESTED THE ITT SYSTEM AND FOUND THE INDICATOR TO BE ASDR 03200701Engine · shutdownWHILE ON SHORT FINAL (APPROX .2500 MILE), PILOT REPORTED THE RT ENGINE SHUTDOWN. AS HE WAS ON SHORT FINAL HE DID NOT NOTICE IF THERE WAS A CORRESPONDING INITIATION OF THE NTS SYSTEM OR IF THE ENGINE/PROP BEGAN TO FEATHER. WHEN THE PROBLEM WAS NOTICED THE PILSDR CA061027002Spar · cracked(CAN) DURING ANNUAL X-RAY INSPECTION OF THE VERTICAL STABILIZER, A CRACK WAS DETECTED ON THE LEFT HAND SIDE OF THE VERTICAL STABILIZER CENTRE SPAR AT THE 4TH FASTENER ABOVE THE DOUBLER. THE CRACK APPEARS TO RUN INTO THE RADIUS OF THE CENTRE SPAR. THE AIRCRAFT SDR O9I2006F00000Support Bracket · crackedAFTER LANDING AND WHILE ROLLING OUT, THE NOSE LANDING GEAR COLLAPSED. THE AIRCRAFT CAME TO REST ON THE NOSE GEAR AND NOSE GEAR DOORS (AND MLG). THE BELLY WAS NOT DAMAGED. AFTER INSPECTING THE NOSE LANDING GEAR IT WAS DISCOVERED THAT THE DRAG BRACE SUPPORT HSDR 690100305DGRestraint · brokenSCHEDULED MX, BOTH ENG`S STARTED FOR A ROUTINE OPS CHK. ABOUT 4 MINS INTO RUN-UP, WITH PROP BLADES LT IN FLAT PITCH, NR 2 ENG FIRE WARN LIGHT ILLUMINATED. PILOT PERFORMED A CAUTIONARY SHUTDOWN OF BOTH ENG`S. AN INITIAL INSPECT OF NR 2 ENG FOR CAUSE OF FIRE SDR CA050421002Selector Valve · malfunctioned(CAN) DURING ACCOMPLISHMENT OF THE FLIGHT IDLE CHARACTERISTIC CHECK ON THE AIRCRAFT, THE CREW WAS UNABLE TO MOVE THE LANDING GEAR SELECTOR TO THE DOWN POSITION. AFTER SEVERAL UNSUCCESSFUL ATTEMPTS TO MOVE THE SELECTOR THE SIDE PEDESTAL COVER WAS REMOVED TO ACSDR CA041209006Strap · corroded(CAN) DURING REPLACEMENT OF LOWER SPAR CAP, WE WERE ADVISED THAT AN NEW AD IS PENDING AND WILL BE ISSUED IN JANUARY 2005 TO ADDRESS A CORROSION PROBLEM WITH THE PART NUMBERS. THE STRAPS WERE REMOVED AND EXTENSIVE CORROSION WAS FOUND UNDER THE STEEL STRAPS ON TSDR CA041013011Arm · crackedDURING ACCOMPLISHEMENT OF TWIN COMMANDER SL376 INSPECTION OF MLG CLEVIS AND DRAGBRACE, 2 CRACKS WERE NOTED DURING COMPLETION OF EDDY CURRENT INSPECTION OF THE LEFT HAND MLG. THE CRACKS ARE LOCATED AT THE MOUNTING HOLE FOR THE EYE BOLT P/N 330085-43. ATTACHEDSDR MV52004F00001Pulley · fodWHILE IN FLIGHT, PILOT EXPERIENCED SEVERE AILERON BINDING. AN EMERGENCY WAS DECLARED AND THE AIRCRAFT LANDED WITHOUT INCIDENT. AFTER INSPECTION OF THE COMPLETE AILERON SYSTEM, IT IS SUSPECTED THAT FOD HAD COME IN CONTACT BETWEEN THE AFT AILERON PULLEY AND CASDR O9I2004F00000Fcu · failedTHE NR 2 ENGINE FCU FAILED TO PROPERLY LIMIT FUEL TO THE ENGINE. DURING THE FINAL DECENT, THE FLIGHT CREW BROUGHT BACK THE THROTTLES TO THE FLIGHT IDLE POSITION FOR LANDING. IT WAS NOTED AT THAT TIME THAT THE NR 2 ENGINE WAS STILL PRODUCING 250 HP, A LEVEL HSDR 121JWFirewall · crackedTHE LT AND RT ENGINE ALUMINUM FIREWALLS (P/N 660001-11 / -12 CHANNEL) HAVE DEVELOPED VERTICAL CRACK INDICATIONS AT THE LOWER SHEAR CLIP ATTACHMENT TAB. BOTH THE LT AND RT ENGINE IB LOWER TABS ARE COMPLETELY SHEARED AT THE FLANGE RADIUS.SDR MV5RO55NBellcrank · failedTHE BELLCRANK FOR THE LT NOSE GEAR AFT DOOR FAILED/ CRACKED AT THE ROD END UPPER ATTACH POINT AND FELL OVER IN THE WHEEL WELL WHILE THE GEAR WAS IN THE UP POSITION. WHEN THE DOWN POSITION WAS SELECTED THE GEAR COULD NOT EXTEND DUE TO THE ROD BEING IN THE WAY.SDR CA040429001Wire · failed(CAN) DURING CRUISE, THE RT ENGINE BETA LIGHT ILLUMINATED. ALL PROPELLER AND ENGINE PERFORMANCE WAS NORMAL. THE FLIGHT CREW SHUT DOWN THE AFFECTED ENGINE AND FEATHERED THE PROPELLER AS A PRECAUTION. THE AIRCRAFT RETURNED TO THE AIRPORT. UPON INVESTIGATION, MASDR 690A0220004MTPropeller · incorrectTHE NR 1 PROPELLER WAS REMOVED TO FACILITATE ENGINE MAINTENANCE. WHILE THE PROP WAS OFF IT WAS SENT TO A REPAIR STATION TO HAVE THE BLADES RETURNED TO FEATHER. THE PROP WAS THEN INSPECTED AND TESTED. PROPELLER INSPECTION FOUND THAT THE BLADE ANGEL SETTING FROMSDR 690A120903MTEngine · seizedAFTER SHUTDOWN THE PROPELLER WAS BEING TURNED THROUGH BY HAND WHICH IS STANDARD PROCEDURE FOR TPE331-5'S. THE PILOT NOTICED A RUBBING NOISE AND THE PROP BECAME HARDER TO TURN. LATER THE PROP COULD NOT BE TURNED.SDR CA031114009Spar · cracked(CAN) AS A FOLLOW UP INSPECTION ON THE REST OF OUR FLEET FOLLOWING THE DISCOVERY OF THE CRACKED AILERON SPAR ON OUR AIRCRAFT, THE LT AILERON SPAR WAS FOUND CRACKED ON THIS AIRCRAFT. THE CRACKS ARE ALL LOCATED IN THE SAME AREA AS PREVIOUSLY REPORTED AND ARE APSDR CA031106013Spar · cracked(CAN) DURING X-RAY INSPECTION OF THE VERTICAL STABILIZER, A CRACK WAS NOTED ON THE CENTER SPAR FLANGE LOCATED 2 FASTENERS UP FROM THE EXTERNAL DOUBLER APEX. THE CRACKIS APPROXIMATELY 5/8 - 3/4 INCH IN LENGTH AND RUNS 90 DEGREES TO THE FLANGE. A CRA CK APPROXIMSDR CA031106012Channel · cracked(CAN) WHILE COMPLETING A X-RAY INSPECTION ON THE VERTICAL STABILIZER, A CRACK WAS NOTED ON THE RT VERTICAL FLANGE OF THE CHANNEL. THE CRACK IS APPROXIMATELY .6250 INCH IN LENGTH. IT IS LOCATED IN THE AREA COVERED BY AD95-13-02. THE AIRCRAFT HAD BEEN MODIFIED SDR CA031106010Channel · cracked(CAN) DURING X-RAY INSPECTION OF THE VERTICAL STABILIZER A CRACK APPROXIMATELY .7500 INCH LONG WAS NOTED ON P/N 410008-85 CHANNEL LOCATED IN THE LOWER SECTION OF THE VERTICAL STABILIZER. THIS PART IS LOCATED IN THE AREA SUBJECT TO AD 95-13-02. THE CRACK IS RUNSDR 2003FA0000964Window · crackedOPERATOR COMPLAINED OF PRESSURIZATION PROBLEM. DURING CABIN PUMP UP, A LEAK WAS DISCOVERED AT THE RT PICTURE WINDOW. THE WINDOWS OUTER PANEL WAS FOUND TO BE CRACKED. THE CRACK LENGTH WAS DETERMINED TO BE 18 INCHES. THE CRACK WAS LOCATED AT THE UPPER FASTENSDR 2004F00362Windshield · crackedPILOT WINDSHIELD CRACKED VERTICALLY IN LEFT LOWER CORNER TO UPPER LEFT CORNER DURING FLIGHT, OUTER PANE ONLY. AIRCRAFT WAS DESCENDING ON FINAL FROM 13,000 FEET. AIRCRAFT DID NOT DEPRESSURIZE AND LANDED WITHOUT INCIDENT. (M)SDR CA021212004Skin · cracked(CAN) WHILE ACCOMPLISHING AN INSPECTION 2 CRACKS WERE NOTED EMANATING FROM A FASTENER HOLE IN THE VERTICAL STAB SKIN. THE CRACKS WERE 5/16 INCH AND 3/16 INCH IN LENGTH. THE CRACKS WERE LOCATED AT WL 25.1, 4 FASTENERS ABOVE THE SB 218 KIT DOUBLER (REF AD95-13-0SDR VH32002F00000Landing Gear · damagedUPON LANDING TOUCHDOWN, SEVERE SHIMMY. TAXIED CLEAR OF RUNWAY, SHUT DOWN AIRCRAFT. INSPECTED LEFT MAIN GEAR, FOUND DAMAGE.SDR CA020829007Windshield · cracked(CAN) PILOTS WINDSHIELD CRACKED AFTER TAKEOFF, CLIMBING THROUGH 2,000 FEET. AIRCRAFT FLOWN TO HOME BASE UNPRESSURIZED.SDR CA020604010Line · broken(CAN) DURING CLIMB THE AIRCRAFT WOULD NOT PRESSURIZE. THERE WAS A LOUD WHISTLING SOUND COMING FROM THE ENTRANCE DOOR AREA, INDICATING NO PRESSURIZATION. THE AIRCRAFT RETURNED TO BASE. UPON INVESTIGATION IT WAS NOTED THAT THE FLARE END OF ONE CONNECTION HAD PULSDR O9I2002F00000Housing · crackedDURING FLIGHT THE PILOT NOTICED THE RIGHT ENGINE OIL PRESSURE DROPPED ABOUT 30 PSI. THE AIRPLANE LANDED UNEVENTFULLY. THE ENGINE WAS DISASSEMBLED AND THE OIL PRESSURE PUMP HOUSING WAS FOUND CRACKED, RESULTING IN AN INTERNAL OIL LEAK REDUCING ENGINE OIL PRESSSDR CA011210017Skin · cracked(CAN) DURING INSPECTION OF THE AIRCRAFT, CRACKS WERE NOTED ON THE VERTICAL STABILIZER SKIN. THE CRACKS WERE LOCATED AT THE FIRST FASTENER ABOVE THE DOUBLER AT THE CENTRE SPAR. THE LONGEST CRACK MEASURED .75 INCHES IN LENGTH. A X-RAY INSPECTION WAS ACCOMPLISSDR CA020104003Chip Detector · cracked(CAN) UPON REINSTALLATION OF THE CHIP DETECTOR DRAIN VALVE BODY IN ENGINE NR 1 BEFORE TORQUE VALVE WAS OBTAINED (75 IN LB) , THE NUT PORTION WHICH INCLUDES A RECEPTICLE FOR THE CHIP DETECTOR SEVERED OFF. INSPECTION OF THE PART SHOWED PRESENCE OF PREVIOUS CRACSDR CA011116001Pushrod · bent(CAN) DURING CLIMBOUT THE AIRCRAFT PRESSURIZATION REDUCED FROM 4.8 PSI TO 3.5 PSI. UPON INVESTIGATION IT WAS NOTED THAT THE LOWER AFT ENTRANCE DOOR BAYONET WAS NOT EXTENDING INTO THE AIRFRAME. THE TWO PUSHRODS P/N'S 900009-49-7.22 AND 900009-49-9.70 WERE FOUNDSDR O9I2001F00000Control Arm · disconnectedTHE RIGHT ENGINE WAS SHUT DOWN AFTER DISCOVERING A NON-RESPONSIVE POWER LEVER DUE TO THE AIRCRAFT POWER LEVER CABLE BECOMING DISCONNECTED FROM THE RIGHT ENGINE PROPELLER PITCH CONTROL (PPC). THE AFFECTED POWER LEVER ARM THAT BECAME DISCONNECTED IS SPLINED TO SDR 2001F00324Control Cable · failedLEFT ENGINE CONTROL CABLE FAILED TO THE PORTION THAT CONTROLLED THE MANUAL FUEL SHUTOFF VALVE. FAILURE WAS LOCATED AT THE AREA THAT THE FUEL AND PROPELLER MANUAL STOP AND FEATHER CABLE ARE COMBINED INTO ONE CONTROL. (M)SDR 20010604CW015Clamp · corrodedCORROSION IN CLAMPS AND BEARING RACES, REJECTED ALL 3 CLAMPS AND 1 RACE.SDR MV5R055NAngle · crackedRIGHT MAIN LANDING GEAR INBOARD GEAR MOUNT SIDE BRACE TO WING ATTACHMENT ANGLE CRACKED. CRACK LOCATED AT THE AFT PORTION OF THE ANGLE EXTENDING ONE INCH FORWARD.SDR E27R7302Gear · failedBULL GEAR FOUND TO HAVE SHED APPROX 6 IN OF TEETH IN 2 SEGMENTS CAUSING EXTENSIVE DAMAGE TO GEAR BOX COMPONENTS AND CASE. WHICH RESULTED IN AN IN FLIGHT SHUTDOWN.SDR E27R730Channel · failedDURING PRESSURIZATION LEAK CHECKS, THE CABIN WAS FOUND TO HAVE TWO LARGE LEAKS IN THE LEFT AND RIGHT WING ROOT AREA. ON EXAMINATION OF THE SUSPECT AREAS IT WAS FOUND THAT THE LEFT AND RIGHT SUPPORT CHANNELS PN 3107041 & 3107042 HAD FAILED FROM FS 144 WL TO FSSDR 20010206CW007Fuel Control · malfunctionedWHILE DOING OVERSPEED GOVERNOR CHECK, ENGINE RPM STAYS ABOVE TAKEOFF, PROP GOVERNOR HIGH, AND WILL NOT REDUCE WHEN POWER LEVER AND CONDITION LEVER ARE RETARDED. THIS CONDITION ALSO PREVENTS THE PROP FROM COMING OFF THE LOCKS. TROUBLE SHOOTING HAS DETERMINED SDR E27R1730Channel · crackedDURING PRESSURAZATION LEAK CHECKS, THE CABIN WAS FOUND TO HVE TWO LARGE LEAKS IN LT AND RT WING ROOT AREA. ON EXAM OF THE SUSPECT AREAS IT WAS FOUND THAT THE LT AND RT SUPPORT CHANNELS PN310704-1 AND 310704-2 HAD FAILED FROM FS 144 WL10 TO FS 175 WL 14. THE SDR 20001120SH059Skin · corrodedDURING 100-HOUR INSPECTION, AIRCRAFT NACELLE AREA FOUND THE UPPER ENGINE MOUNT ATTACH STRUCTURE STEEL STRAPS HEAVILY CORRODED. UPON REMOVAL OF THE UPPER NACELLES ON THE LEFT AND RIGHT SIDES OF THE AIRCRAFT, FOUND HEAVY PITTING AND WIDE SPREAD CORROSION OVER TSDR 20001109SH033Fuel Control · fluctuatesDURING THE RUN AND ADJUSTMENT AFTER THE INSTALLATION OF THE FUEL CONTROL, WHEN THE POWER LEVER WAS ADVANCED ABOVE THE FLIGHT IDLE GATE WITH THE CONDITION LEVER IN THE HIGH POSITION, THE ENGINE GOES TO FULL POWER WITHIN A .50 INCH ABOVE THE FLIGHT GATE. WHEN TSDR 20001013SH007Link · crackedLINK ARM ASSY LOCATED ON RIGHT MAIN GEAR TO DOOR LINK FOUND CRACKED AT LINK TO ARM ATTACH AREA. (X)SDR 20000913SH027Plenum · crackedINLET PORTION OF PLENUM ASSEMBLY CRACKED AT WELD AREA. (X)SDR 20000803SH014Bracket · crackedAFT ENGINE MOUNT SUPPORT BRACKET TO LEFT ENGINE CRACKED AT INBOARD WEB. (X)SDR CA000218023Bearing · making metal(CAN) COMPRESSOR BEARING FOUND MAKING NOISE AND OIL CONTAMINATED WITH METAL FRAGMENTS. REPLACED.SDR 20001205SH011Starter Gen · failedSTARTER/GENERATOR FAILED AFTER 207 HOURS OF OPERATION. FAILED FIRST TIME AFTER 14 HOURS. FAILURE OCCURRED INTERNALLY. (X)SDR 99ZZZX3649Line · leakingA BLEED AIR LEAK AT STA 234 DAMAGED A NEARBY WIRING BUNDLE CAUSING VARIOUS ANNUNCIATOR INDICATIONS RESULTING IN THE REQUEST FOR AN EMERGENCY LANDING. BLEED AIR LEAK WAS CAUSED BY FLARE DEFORMING ALLOWING TUBING TO PULL OUT OF THE FITTING. ESCAPING BLEED AIR SDR 99ZZZX13Autopilot · 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 DETECTOR INDICATOR FD 112V AND SHOULD HSDR 98ZZZX4192Acm · failedAIR CYCLE MACHINE (ACM) WOULD NOT COOL AIRCRAFT. REPLACED WITH EXCHANGE UNIT DUE TO BEARING FAILURE.SDR CA980804033Windscreen · cracked(CAN) 30 TO 40 SECONDS AFTER WINDSHIELD HEAT WAS TURNED ON TO LOW POSITION WITH AIRCRAFT CLIMBING THROUGH 18,000 FEET, THE WINDSHIELD DEVELOPED SEVERAL CRACKS ALL COMING FROM THE AREA OF THE HEAT STRIP ON LOWER SECTION OF SCREEN. WINDSHIELD INSTALLED IN MARCHSDR AU980890Regulator · failed(AUS) LEFT VOLTAGE REGULATOR FAILED. HIGH VOLTAGE OUTPUT CAUSED BATTERIES TO BOIL WITH CONSEQUENT ACID SPILLAGE.
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