# Douglas DC-10-10CF - Type: Aircraft model (FAA registry) - Registry code: 3022114 - Manufacturer (registry): DOUGLAS - Model: DC-10-10CF - Aircraft type: Fixed wing multi engine - Category: Airplane - Engines: 3 ยท Turbo-jet - Seats: 345 - Weight class: 20,000 lb and over - Cruise speed: 435 mph - Certification: Type certificated - Registered aircraft: 0 - Page: https://openairdocs.org/model/douglas-dc-10-10cf Model codes come from the FAA registry's reference file. ADs are matched to them by model name and maker. ## ADs that may apply (OpenAirDocs) Matched to this model by model name and maker. Each AD's applicability may narrow it by serial number, part number or equipment. None matched. ## Registered aircraft None registered with this model now. ## NTSB investigations None matched to aircraft with this model. ## FAA accident and incident reports None matched to aircraft with this model. ## Service difficulty reports (37) As reported by operators and repair stations, by the model named in the report. - [SDR 05FDEA00152](https://openairdocs.org/sdr/05FDEA00152), Jan 24, 2005: SUPPORT. CORRODED. COMPLY WITH EA 8-5750-55430 WINGS - FLAP VANE SUPPORT CORROSION REWORK RIGHT O/B FLAP. COMPLIED WITH EA 8-5750-55430. - [SDR 02FDEA00083](https://openairdocs.org/sdr/02FDEA00083), Jan 30, 2002: SHUTOFF VALVE. LEAKING. AFTER 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 01FDEA01019](https://openairdocs.org/sdr/01FDEA01019), Dec 3, 2001: CONTROL UNIT. FAILED. ON 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 01FDEA00793](https://openairdocs.org/sdr/01FDEA00793), Aug 29, 2001: HYDRAULIC LINE. LEAKING. HYD NR 1 QUANTITY DECREASED TO ZERO & PRESS LESS THAN 1000. REMOVED AND REPLACED HYD LINES. LEAK CHECK OK. - [SDR 01FDEA00679](https://openairdocs.org/sdr/01FDEA00679), Aug 11, 2001: LIGHT. ILLUMINATED. NR 3 MANIFOLD FAIL LIGHT ILLUM. RED TABS ACCOMPLISHED. - [SDR 01FDEA00626](https://openairdocs.org/sdr/01FDEA00626), Jul 30, 2001: FRAME. CORRODED. BS 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- - [SDR 00FDEA00869](https://openairdocs.org/sdr/00FDEA00869), Dec 9, 2000: TRANSMITTER. DAMAGED. 00-350 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 SERVIC - [SDR 98FDEA00039](https://openairdocs.org/sdr/98FDEA00039), Jan 17, 1998: START VALVE. FAILED. DURING CLIMBOUT, ENGINE 1 START VALVE OPEN LIGHT ILLUMINATED. REMOVED PNEUMATIC SUPPLY FROM NR 1 MANIFOLD AND RETURNED TO OAK. ENGINE OPERATION APPEARED NORMAL. - [SDR 98FDEA00038](https://openairdocs.org/sdr/98FDEA00038), Jan 17, 1998: START VALVE. FAILED. DURING CLIMBOUT, ENG NR 1 START VALVE OPEN LIGHT ILLUMINATED. REMOVED PNEUM SUPPLY FROM NR 1 MANIFOLD AND RETURNED TO OAK. ENGINE OPERATION APPEARED NORMAL. DUM - [SDR 98FDEA00037](https://openairdocs.org/sdr/98FDEA00037), Jan 16, 1998: FIRE DETECTOR. FAILED. ON 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 FIR - [SDR 97FDEA00316](https://openairdocs.org/sdr/97FDEA00316), May 28, 1997: RESERVOIR. LEAKING. 97-0098, 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 F - [SDR 97FDEA00251](https://openairdocs.org/sdr/97FDEA00251), Apr 29, 1997: RETRACT MECH. MALFUNCTION. AFTER 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 - [SDR 97FDEA00066](https://openairdocs.org/sdr/97FDEA00066), Jan 25, 1997: TRANSMITTER. LEAKING. THIRTY 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 - [SDR 96FDEA01575](https://openairdocs.org/sdr/96FDEA01575), Oct 13, 1996: WINDOW. SHATTERED. AT 1100Z F/O'S WINDSCREEN OUTER PANEL SHATTERED, FL350, TAT - 48, COMPLIED WITH RED TABS. REMOVED AND REPLACED WINDOW AND WINDOW HEAT CONTROLLER PRECAUTIONARY P - [SDR 96FDEA01434](https://openairdocs.org/sdr/96FDEA01434), Sep 5, 1996: CARGO COMPT. FIRE. AIRCRAFT 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 NORMAL - [SDR 96FDEA01267](https://openairdocs.org/sdr/96FDEA01267), Jul 19, 1996: CHECK VALVE. BROKEN. DISCREPANCY: (MOCC 96-138) DURING LEVEL FLIGHT AT 27,000 FEET, NR 1 HYDRAULIC QUANTITY WENT TO ZERO. ACCOMPLISHED APPROPRIATE CHECK LIST. CORRECTIVE ACTION: FOU - [SDR 96FDEA01258](https://openairdocs.org/sdr/96FDEA01258), Jul 16, 1996: CONTROL CABLE. OUT OF POSITION. DISCREPANCY: GOT FLAP DISAGREE FLAG ON TOUCHDOWN, DID NOT RETRACT FLAPS. CORRECTIVE ACTION: FOUND LEFT FLAP CABLE OFF TRACK. REMOVED AND REPLACED LEFT BUS CABLE - [SDR 96FDEA01245](https://openairdocs.org/sdr/96FDEA01245), Jul 13, 1996: CAP ANGLE. CORRODED. BELL 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 97FDEA01207](https://openairdocs.org/sdr/97FDEA01207), Jul 8, 1996: STIFFENER. CRACKED. SNRM 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 - [SDR 96FDEA01268](https://openairdocs.org/sdr/96FDEA01268), Jul 8, 1996: BLKHD STIFFENER. CRACKED. DISCREPANCY: 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 - [SDR 96FDEA01207](https://openairdocs.org/sdr/96FDEA01207), Jul 8, 1996: COWL STIFFENER. CRACKED. SNRM NR 4225, NR 2 ENGINE NOSE COWL BLKHD STIFFENER ON DUCT WEB CRACKED 10 O'CLOCK POS AS SEEN THROUGH PANEL 361 KL. - [SDR 96FDEA01185](https://openairdocs.org/sdr/96FDEA01185), Jun 29, 1996: FRAME. CORRODED. STA 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 - [SDR 96FDEA01001](https://openairdocs.org/sdr/96FDEA01001), May 20, 1996: STIFFENER RING. CRACKED. SNRM 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 - [SDR 96FDEA01000](https://openairdocs.org/sdr/96FDEA01000), May 20, 1996: BLKHD STIFFENER. CRACKED. SNRM 4259. BULKHEAD STIFFENER CRACKED AT THE NR 2 ENGINE NOSE COWL L/E AS SEEN THROUGH ACCESS PANEL NR 361FL. S/D COMING. - [SDR 96FDEA00982](https://openairdocs.org/sdr/96FDEA00982), May 20, 1996: BELL FRAME. CORROSION. SNRM 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 - [SDR 96FDEA00997](https://openairdocs.org/sdr/96FDEA00997), May 16, 1996: HINGE FITTING. CRACKED. SNRM 7009, LT MAIN GEAR DOOR CENTER HINGE ATTACH FITTING, CRACKED, APPROX BELOW DOOR ACT. FABRICATED REPAIR PER SRM 52-00-00 AND INSTALLED. - [SDR 96FDEA00981](https://openairdocs.org/sdr/96FDEA00981), May 16, 1996: BELLFRAME. CORROSION. SNRM 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 SP - [SDR 96FDEA00976](https://openairdocs.org/sdr/96FDEA00976), May 15, 1996: BELLFRAME. CORROSION. SURFACE 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, INSTALLE - [SDR 96FDEA00951](https://openairdocs.org/sdr/96FDEA00951), May 10, 1996: BULKHEAD. LOOSE BOLTS. NR 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 INSPECTIO - [SDR 96FDEA00950](https://openairdocs.org/sdr/96FDEA00950), May 10, 1996: BULKHEAD. LOOSE SCREWS. NR 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 WI - [SDR 96FDEA00779](https://openairdocs.org/sdr/96FDEA00779), Apr 14, 1996: ANGLE. CRACKED. THE 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 UPPE - [SDR 96FDEA00659](https://openairdocs.org/sdr/96FDEA00659), Mar 19, 1996: SKIN. CRACKED. RT 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 LENGT - [SDR 96FDEA00018](https://openairdocs.org/sdr/96FDEA00018), Jan 6, 1996: PLANK. CRACKED. LT 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 FASTENER - [SDR 95FDEA01802](https://openairdocs.org/sdr/95FDEA01802), Nov 24, 1995: SPAR. CRACKED. REF 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. TRI - [SDR 9DEA01780](https://openairdocs.org/sdr/9DEA01780), Nov 19, 1995: MIXER BRACKET. CRACKED. LT 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 95FDEA01779](https://openairdocs.org/sdr/95FDEA01779), Nov 19, 1995: SKIN. CRACKED. HORIZONTAL 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 - [SDR 95FDEA01598](https://openairdocs.org/sdr/95FDEA01598), Oct 25, 1995: GEAR LEVER. DIRTY. AFTER LANDING GEAR EXTENSION, BOTH LANDING GEAR ANNUNCIATOR PANELS REMAINED ALL RED, RECYCLED GEAR ANNUNCIATORS REMAINED ALL RED. AFTER PUSHING HARD AND DOWN ON --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.