Douglas DC-10-10CF
Service difficulty reports · 37
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 = 'DC1010CF' 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 = 'DC1010CF' 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 05FDEA00152Support · corrodedCOMPLY WITH EA 8-5750-55430 WINGS - FLAP VANE SUPPORT CORROSION REWORK RIGHT O/B FLAP. COMPLIED WITH EA 8-5750-55430.SDR 02FDEA00083Shutoff Valve · leakingAFTER T/O NR 3 ELEV SHUTOFF VALVE LEAKING FLUID WHEN PRESS. REMOVED AND REPLACED ELEV SHUT OFF VALVE PER MM 29-12-23-2.SDR 01FDEA01019Control Unit · failedON T/O ROLL, NR 1 BUS FAILED. REMOVED AND REPLACED GENERATOR RELAY 1, BUS CONTROL AND CIRCUIT BREAKER PER MM 24-00-00-2.SDR 01FDEA00793Hydraulic Line · leakingHYD NR 1 QUANTITY DECREASED TO ZERO & PRESS LESS THAN 1000. REMOVED AND REPLACED HYD LINES. LEAK CHECK OK.SDR 01FDEA00679Light · illuminatedNR 3 MANIFOLD FAIL LIGHT ILLUM. RED TABS ACCOMPLISHED.SDR 01FDEA00626Frame · corrodedBS 919 AFT SIDE OF FRAME BETWEEN LT AND RT LONGERON 49 AREAS OF LEVEL 1 CORRODED. *S/D* REMOVED AND REPLACED FRAME PER SRM 53-30-00, 51-21-01, 51-41-01 & 51-35-01.SDR 00FDEA00869Transmitter · damaged00-350 ON LD FLAP INDICATOR SHOW LEFT INBD FLAP LESS THAN SEL AT 35 DEGREES POSITION. R&R LEFT OUTBOARD TRANSMITTER PER IAW DC10-10 MM 27-54-03-2. OK FOR SERVICE.SDR 98FDEA00039Start Valve · failedDURING CLIMBOUT, ENGINE 1 START VALVE OPEN LIGHT ILLUMINATED. REMOVED PNEUMATIC SUPPLY FROM NR 1 MANIFOLD AND RETURNED TO OAK. ENGINE OPERATION APPEARED NORMAL. LIGHT REMAINED ON THROUGHOUT APPROACH AND LANDING. DUMPED FUEL TO LANDING WEIGHT OF 375,000. FSDR 98FDEA00038Start Valve · failedDURING CLIMBOUT, ENG NR 1 START VALVE OPEN LIGHT ILLUMINATED. REMOVED PNEUM SUPPLY FROM NR 1 MANIFOLD AND RETURNED TO OAK. ENGINE OPERATION APPEARED NORMAL. DUMPED FUEL TO LANDING WEIGHT OF 375.000 PRIOR TO LANDING. START VALVE LIGHT WENT OUT AFTER 3 TO 5 SDR 98FDEA00037Fire Detector · failedON PUSHBACK PRIOR TO STARTING NR 2 ENG, ENG NR 2 LOOP-A LIGHT ILLUMINATED. FOLLOWED ABNORMAL PROCEDURE P2-8-11. FIRE DETECTOR LOOP LIGHT ILLUMINATED WITHOUT FIRE WARNING. SHUT DOWN APU, FIRED BOTH ENGINE 2 FIRE BOTTLES (AFTER FIREBELL AND LIGHT IN FUEL LEVESDR 97FDEA00316Reservoir · leaking97-0098, HYD SYS 3 ELEVATOR OFF LT ILLUMINATED. HYD QTY DROPPED TO 1 GAL. ACCOMPLISHED RED TAB PROCEDURE. PRESSURE DROPPED ONLY AFTER PUMPS WERE SHUT OFF. HYD FLUID FOUND ON POST FLT IN RT WHEEL WELL. REMOVED AND REPLACED NR 3 RESERVOIR TO STEP B5, M/M 29SDR 97FDEA00251Retract Mech · malfunctionAFTER T/O FROM PHX AND FLAPS SELECTED UP, FLAPS STOP RED AT 100. FLAPS SELECTED TO 150 AND AFTER ABOUT TWO MINUTES, THE FLAPS WENT DOWN TO 150. FUEL WAS DUMPED TO LANDING WEIGHT AND A 500 FLAP LANDING WAS MADE AT PHX. FLAPS OPERATED NORMALLY TO 300 AFTER 15SDR 97FDEA00066Transmitter · leakingTHIRTY MIN AFTER T/O IN LEVEL FLT, HYD SYS 3 ELEVATOR OFF LIGHT ILLUMINATED. RAN RED TAB AND PROBLEM WAS NR 3 SYSTEM. RAN NR 3 SYSTEM FAILURE CHECKLIST. LANDED 35 DEGREE FLAPS AND 3.3 GAL REMAIN IN SYSTEM. FOUND HYDRAULIC SYSTEM 3 TRANSMITTER FAILED. REPLASDR 96FDEA01575Window · shatteredAT 1100Z F/O'S WINDSCREEN OUTER PANEL SHATTERED, FL350, TAT - 48, COMPLIED WITH RED TABS. REMOVED AND REPLACED WINDOW AND WINDOW HEAT CONTROLLER PRECAUTIONARY PER MAINTENANCE MANUAL.SDR 96FDEA01434Cargo Compt · fireAIRCRAFT DIVERTED TO SWF DUE TO MAIN DECK SMOKE DETECTORS NR 7, 8 AND 9 ILLUMINATING. EMERGENCY WAS DECLARED AND AIRCRAFT LANDED. *S/D* R1 SLIDE DEPLOYED NORMALLY UNDER EMERGENCY CONDITIONS, ESCAPE ROPES USED TO EXIT COCKPIT WITH NO PROBLEMS. A/C DESTROYESDR 96FDEA01267Check Valve · brokenDISCREPANCY: (MOCC 96-138) DURING LEVEL FLIGHT AT 27,000 FEET, NR 1 HYDRAULIC QUANTITY WENT TO ZERO. ACCOMPLISHED APPROPRIATE CHECK LIST. CORRECTIVE ACTION: FOUND NR 2 STABILIZER CONTROL VALVE CHECK VALVE BROKEN. REMOVED AND REPLACED CHECK VALVE, MOA FILTSDR 96FDEA01258Control Cable · out of positionDISCREPANCY: GOT FLAP DISAGREE FLAG ON TOUCHDOWN, DID NOT RETRACT FLAPS. CORRECTIVE ACTION: FOUND LEFT FLAP CABLE OFF TRACK. REMOVED AND REPLACED LEFT BUS CABLES RIGGED PER MM 27-50-00. OPERATION CHECKED OK, I/B O/B OPERATIONALLY CHECKS NORMAL.SDR 96FDEA01245Cap Angle · corrodedBELL FRAME CORRODED AT BS 1761. REMOVED BELL FRAME AND INSTALLED A NEW BELLFRAME AND SPLICE ANGLE DOUBLER PER SRM 53-40-00 FIG 1L.SDR 97FDEA01207Stiffener · crackedSNRM NR 4225 NR 2 ENGINE NOSE COWL BLKHD STIFFENER ON D-DUCT WEB CRACKED 10:00 POS AS SEEN THROUGH PANEL 361 KL. REMOVED STIFFENER, WELDED CRACK AND REINSTALLED STIFFENER PER SRM 57-00-00, CLOSED 7/11/96.SDR 96FDEA01268Blkhd Stiffener · crackedDISCREPANCY: NR 2 ENGINE NOSE COWL BLKHD STIFFENER ON D-DUCT WEB CRACKED AT 10 O'CLOCK POSITION. REFERENCE: FCD 08-55-005 SNRM 4225. CORRECTIVE ACTION: REMOVED STIFFENER, WELDED CRACK, AND RE-INSTALLED STIFFENER PER SRM 57-00-00.SDR 96FDEA01207Cowl Stiffener · crackedSNRM NR 4225, NR 2 ENGINE NOSE COWL BLKHD STIFFENER ON DUCT WEB CRACKED 10 O'CLOCK POS AS SEEN THROUGH PANEL 361 KL.SDR 96FDEA01185Frame · corrodedSTA 1781 LONGERONS 49 TO 52R BILGE SUMP FRAM/LONGERONS HAVE EXFOLIATION CORROSION AT AFT END OF CTR CARGO COMPARTMENT. *S/D* REMOVED AND REPLACED FRAME SECTION AND SPLICE PER SRM 53-30-00.SDR 96FDEA01001Stiffener Ring · crackedSNRM 4260, CIRCUMFERENTIAL STIFFENER RING CRACKED AT THE NR 2 ENG NOSE COWL L/E AS SEEN THROUGH ACCESS PANEL 361 FL. REPLACED NOSE COWL LEADING EDGE ASSY IAW MM 54-22-01 WITH LEASED UNIT. DAMAGED NOSE COWL L/E ROUTED TO VENDOR OR SHOP FOR REPAIR (S/N 572826)SDR 96FDEA01000Blkhd Stiffener · crackedSNRM 4259. BULKHEAD STIFFENER CRACKED AT THE NR 2 ENGINE NOSE COWL L/E AS SEEN THROUGH ACCESS PANEL NR 361FL. S/D COMING.SDR 96FDEA00982Bell Frame · corrosionSNRM 1137, SURFACE CORROSION ON BELL FRAME AT STA 1841 STR 49L AND 49R. REMOVED CORROSION BEYOND SRM 51-21-01 REMOVED FASTENERS, FACTORY SPLICE AND TWO VERTICAL STIFFENERS, FABRICATED NEW SPLICES AND NEW SECTION OF BELL FRAME PER SRM 51-30-00 VOL 1 FIG 5 AND SDR 96FDEA00997Hinge Fitting · crackedSNRM 7009, LT MAIN GEAR DOOR CENTER HINGE ATTACH FITTING, CRACKED, APPROX BELOW DOOR ACT. FABRICATED REPAIR PER SRM 52-00-00 AND INSTALLED.SDR 96FDEA00981Bellframe · corrosionSNRM 1144, SURFACE CORROSION ON BELLFRAME AT STA 1942 STR 51L AND 51 R. BURNISHED SURFACE CORROSION AND REMOVED DAMAGED AREA PER SRM 51-21-01, FABRICATED NEW SPLICES AND SECTION OF FRAME PER SRM 53-30-00, INSTALLED REPAIR SRM 53-30-00 FIG 5.SDR 96FDEA00976Bellframe · corrosionSURFACE CORROSION ON BELLFRAME AT STA 919 STR 48L TO 48R. CLEANED OUT CORROSION, FOUND TO BE OUT OF LIMITS. FABRICATED DOUBLER PER SRM 53-30-00 FIG 8L, INSTALLED DOUBLER REPAIR PER SRM 53-30-00 FIG 8.SDR 96FDEA00951Bulkhead · loose boltsNR 1 ENG PYLON AFT BULKHEAD AFT FACE TWO ATTACH BOLTS ARE LOOSE AT UPPER AREA. REMOVED BOLTS FOR INSPECTION AND CLEANED BOLT HOLES. COMPLIED WITH HFEC INSPECTION ON 2 BOLT HOLES, NO DEFECTS NOTED. INSTALLED AND TORQUED BOLTS PER MM 20-50-02.SDR 96FDEA00950Bulkhead · loose screwsNR 1 ENG PYLON I/B SIDE AFT BULKHEAD AREA, THERE ARE 8 LOOSE TRI-WING SCREWS ON STA YN 417.212. REMOVED BOLTS FOR INSPECTION AND CLEARED BOLT HOLES. COMPLIED WITH HFEC INSPECTION ON 8 BOLTS HOLES, NO DEFECT NOTED. INSTALLED BOLTS AND TORQUED PER MM 20-50-02SDR 96FDEA00779Angle · crackedTHE RT HORIZ STAB CENTER L/E SECTION O/B RIB UPPER CHORD ANGLE IS CRACKED IN 3 PLACES ON IN FLANGE BETWEEN RADIUS AND FASTENERS HOLES. REMOVED AND REPLACED UPPER CHORD ANGLE PER SRM 55-00-01.SDR 96FDEA00659Skin · crackedRT HORIZ STAB FWD UPPER PANEL HAS CRACK IND AT 2 FASTENER HOLES, FWD UPPER SPAR CAP AFT TANG, I/B OF CLOSING RIB PLANE, BEING THE 2ND AND 3RD HOLES. CRACK LENGTHS ARE APPROX .0937 TO .1875 INCH LONG AT THE PERIPHERY. C/W HFEC ON FWD SPAR UPPER REAR TANG NO DSDR 96FDEA00018Plank · crackedLT HORIZ STAB FWD UPPER PLANK CRACKED JUST INBOARD OF CLOSING RIB, FROM FWD EDGE AFT THROUGH FASTENER HOLE 1.5 TOTAL CRACK CONTINUES PAST HOLE. REMOVED FASTENERS AND TRIMMED OUT CRACKED AREA. NDT AT CRACKED AREA AND OPEN HOLES C/W. COLD WORKED HOLES FINAL RSDR 95FDEA01802Spar · crackedREF EO 8-5510-7-3312 PT 4, RT HORIZ STAB, FWD SPAR, UPPER CHORD, FWD TANG CRACKED AT 2ND HOLE I/B OF CLOSING RIB PLANE. CRACK MOVES AFT FROM HOLE .375 INCH. TRIMMED OUT CRACKED AREA PER SRM 55-20-00, FABRICATED DOUBLER, FILLER, SHIM PER SRM 55-20-00. INSTALSDR 9DEA01780Mixer Bracket · crackedLT LATERAL CONTROL MIXER BRACKET ASSY WAS FOUND CRACKED ON HFEC INSP, PART 1 OF EO 8-2760-7-3310 C1. CRACK IS .25 INCH LONG ON RT LEG OF BRACKET AT RADIUS.SDR 95FDEA01779Skin · crackedHORIZONTAL STAB HAS ONE CRACK .948 INCH LONG IN THE AFT UPPER CONSTANT SECTION PANEL. CRACK STARTS AT AFT BOLT HOLE GOING FWD AND CRACK IS WITHIN FLYABLE LIMITS. REPETITIVE INSP PART 1 AT 24 MONTHS INTERVALS AND SPECIAL INSP TO START PART 2 AT 3 MONTHS INTERSDR 95FDEA01598Gear Lever · dirtyAFTER LANDING GEAR EXTENSION, BOTH LANDING GEAR ANNUNCIATOR PANELS REMAINED ALL RED, RECYCLED GEAR ANNUNCIATORS REMAINED ALL RED. AFTER PUSHING HARD AND DOWN ON LANDING GEAR HANDLE ALL INDICATIONS BECAME GREEN, NORMAL LANDING ACCOMPLISHED. PINNED LANDING GEA
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