# Canadair CL-601-2A12

- Type: Aircraft model (FAA registry)
- Registry code: 1900303
- Manufacturer (registry): CANADAIR
- Model: CL-601-2A12
- Aircraft type: Fixed wing multi engine
- Category: Airplane
- Engines: 2 · Reciprocating
- Seats: 21
- Weight class: 20,000 lb and over
- Certification: Type certificated
- Registered aircraft: 1
- Page: https://openairdocs.org/model/canadair-cl-601-2a12

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 (1)

- [N28FM](https://openairdocs.org/aircraft/N28FM): [N28fm LLC](https://openairdocs.org/faa-owner/N28FM%20LLC), [Williamsburg, VA](https://openairdocs.org/faa-place/VA/Williamsburg), built 1986, S/N 3064

## NTSB investigations

None matched to aircraft with this model.

## FAA accident and incident reports

None matched to aircraft with this model.

## Service difficulty reports (88, newest 50)

As reported by operators and repair stations, by the model named in the report.

- [SDR CA120928001](https://openairdocs.org/sdr/CA120928001), Sep 21, 2012: HEATER. FAILED. (CAN) AFT GALLEY WATER TANK HEATING ELEMENT STAYED ON AND CAUSED THE SURROUNDING INSULATION BLANKET TO BURN AND CREATED SMOKE IN CABIN OF ACFT WHICH CAUSED A FL
- [SDR CA101108005](https://openairdocs.org/sdr/CA101108005), Nov 6, 2010: TIRE. FAILED. (CAN) ON POST FLIGHT/DI INSPECTION (NEXT AM) NR 3 MAIN TIRE WAS FOUND TO BE DEFLATED AND ONE INNER RIB/STRIP OF RUBBER MISSING 3/4 AROUND TIRE. APPEARS TO HAVE 
- [SDR DJFA2009006](https://openairdocs.org/sdr/DJFA2009006), Jan 27, 2009: WINDSCREEN. CRACKED. DURING CRUISE, CREW NOTED WHISTILING SOUNDS FROM THE LT WINDSCREEN. AFTER A BRIEF INSP, CREW NOTED (2) VERTICAL CRACKS SPANNING THE WINDSCREEN. AS THE ACFT BEGA
- [SDR CA081016003](https://openairdocs.org/sdr/CA081016003), Oct 10, 2008: O-RING. FAILED. (CAN) ACFT, PRIOR TO ENG START APU HAD AN UNCOMMANDED SHUTDOWN. WHILE CARRYING OUT COCKPIT TROUBLESHOOTING PILOTS OBSERVED APU BOOST PUMP FAIL LIGHT WAS ILLUMIN
- [SDR CA080806007](https://openairdocs.org/sdr/CA080806007), Aug 5, 2008: GEARBOX. DEFECTIVE. (CAN) DURING FLIGHT, CREW NOTICED THEY LOST THE NR1 ENGINE OIL INDICATION AND GOT THE RED LED. SHUTDOWN ENGINE AND MADE AN UNEVENTFUL LANDING. CREW NOTICED A PU
- [SDR DJFA2008055](https://openairdocs.org/sdr/DJFA2008055), Jun 15, 2008: HEAT TAPE. BURNED. WHILE REFUELING THE AC, THE CREW NOTED A SIGNIFICANT AMOUNT OF SMOKE IN THE COCKPIT. OPEN (A)
- [SDR DJF2008F00004](https://openairdocs.org/sdr/DJF2008F00004), Jun 15, 2008: UNKNOWN. SMOKE. WHILE REFUELING THE AC, THE CREW NOTED A SIGNIFICANT AMOUNT OF SMOKE IN THE COCKPIT. (SDR WILL BE COMPLETED AFTER MAINTENANCE/ INSPECTION IS COMPLETE). (K)
- [SDR CA080625008](https://openairdocs.org/sdr/CA080625008), Jun 12, 2008: ACTUATOR. MALFUNCTIONED. (CAN) DURING A FLIGHT, PILOT REPORTED A PITCH TRIM CHANNEL NR1 INOP LIGHT ON. TROUBLESHOOT THE TRIM SYS AND FOUND NR1 TRIM ACTUATOR BRAKE COIL OPEN. HORIZ STAB 
- [SDR CA080225005](https://openairdocs.org/sdr/CA080225005), Feb 22, 2008: SHAFT. BROKEN. (CAN) 3 MINUTES AFTER TAKEOFF, GENERATOR FAILED, AC RETURNED TO BASE. GENERATOR REMOVED, FOUND BROKEN SHAFT INSIDE THE IDG (NOT THE MAIN SHAFT). IT BROKE, MELTE
- [SDR DJFA2007133](https://openairdocs.org/sdr/DJFA2007133), Nov 2, 2007: ADG. BURNED. DURING POST MAINTENANCE CHECK FLIGHT, CREW TESTED THE AIR DRIVEN GENERATOR SYSTEM (ADG). DURING THE TEST THE ADG FAILED LEAVING THE CREW IN COMPLETE ELECTRICAL 
- [SDR CA070328003](https://openairdocs.org/sdr/CA070328003), Mar 23, 2007: LINE. FAILED. (CAN) DURING ROUTINE SERVICING AFTER A/C ARRIVAL, HYD FLUID WAS NOTICED LEAKING OUT OF THE BOTTOM OF THE RUDDER AND RUNNING DOWN THE TAILCONE AND TO THE GROUND.
- [SDR CA070301004](https://openairdocs.org/sdr/CA070301004), Mar 1, 2007: ROD. CORRODED. (CAN) DURING THE PILOT PRE-FLIGHT CHECKS THE LT FLIGHT SPOILER INDICATED DEPLOYED WHEN STOW WAS SELECTED. THE FLIGHT SPOILER STOW/DEPLOY HANDLE WAS STIFF AT THE
- [SDR CA070221001](https://openairdocs.org/sdr/CA070221001), Feb 19, 2007: BUSHING. FAILED. (CAN) DURING FLIGHT THE CO-PILOTS RUDDER PEDAL ADJUSTMENT MECHANISM FAILED ALLOWING THE RUDDER PEDALS TO FALL FORWARD TO THE LIMIT OF THEIR TRAVEL. INSPECTION R
- [SDR CA070125001](https://openairdocs.org/sdr/CA070125001), Jan 25, 2007: ACTUATOR. INOPERATIVE. (CAN) RT MAIN LANDING GEAR UNLOCK INDICATION APPROX. 15 - 20 MIN. AFTER ARRIVAL, NO PUMP, NO GEAR COMMAND, LOCK PARTIALLY MOVED TO UNLOCK POSITION. RETRACTING A
- [SDR CA061010005](https://openairdocs.org/sdr/CA061010005), Oct 9, 2006: FLAP SYSTEM. MALFUNCTIONED. (CAN) FLAP FAIL BETWEEN 20 DEGREES TO 0 DEGREE DURING RETRACTION OF THE FLAPS AT TAKEOFF , FLAPS RESET ON GROUND IAW OPERATING MANUAL NR 1 ABNORMAL PROCEDURE SE
- [SDR CA060918001](https://openairdocs.org/sdr/CA060918001), Sep 18, 2006: FLAP SYSTEM. MALFUNCTIONED. (CAN) FLAP FAILED ON TAKEOFF, A/C RETURNED AND LANDED SAFELY AT QB MAIN BASE, BREAKER WAS RESET IAW OPERATING MANUAL, COULDN`T DUPLICATED THE SNAG. A/C DID ONE 
- [SDR CA060828001](https://openairdocs.org/sdr/CA060828001), Aug 28, 2006: PUMP. BROKEN. (CAN) LT MAIN AND SCAVENGE EJECTOR FAILURE (MOTIVE FLOW FAILURE). FUEL PUMP SHAFT FOUND BROKEN. FUEL PUMP REPLACED AND AIRCRAFT RETURNED TO SERVICE. A/C HOURS; 
- [SDR CA070720009](https://openairdocs.org/sdr/CA070720009), Jul 27, 2006: WINDSHIELD. CRACKED. (CAN) LT WINDSHIELD OUTER PANE CRACKED IN FLIGHT WITH NO LOSS OF PRESSURIZATION. FLIGHT CONTINUED NORMALLY. NEW WINDSHIELD INSTALLED AND AIRCRAFT RETURNED TO SE
- [SDR CA060728006](https://openairdocs.org/sdr/CA060728006), Jul 22, 2006: ENGINE. OIL CONSUMPTION. (CAN) AIRCRAFT HAD TO SHUTDOWN THE RT ENGINE DURING FLIGHT, DUE TO LOW OIL PRESSURE. APPROX 3 HOURS INTO THE FLIGHT, THE PILOT REPORTED THE OIL PRESSURE WAS FLU
- [SDR CA060515003](https://openairdocs.org/sdr/CA060515003), May 3, 2006: VENT LINE. CORRODED. (CAN) REFUELLING WAS C/O, MASTER REFUEL PANEL CHECK C/O TO CHECK VALVE FOR OPERATION, WHAT WAS NOTICED, FUEL CAME OUT OUT OF THE LT NACA SCOOP APPROXIMATE 2 GAL
- [SDR CA060428002](https://openairdocs.org/sdr/CA060428002), Apr 28, 2006: TRANSFORMER. INOPERATIVE. (CAN) LOSS OF NR 1 MASI, NR 1 ALTIMETER, FDR, NR 1 ADI PITCH AND ROLL INFO, COMPASS INFO, NR 1 ESSENTIAL BUS AND LOSS 26 VAC. CAUSE OF FAULT FOUND TO BE BROKEN 
- [SDR CA060407005](https://openairdocs.org/sdr/CA060407005), Apr 5, 2006: HINGE FITTING. CRACKED. LHS MAIN LANDING GEAR (MLG) P/N CC670-10520-965, S/N 15042 AND RT MLG DOOR P/N CC670-10520-966, S/N (SAME AS RHS) WERE CRACKED AT THE AFT HINGE FITTING P/N CC67
- [SDR DJFA2005179](https://openairdocs.org/sdr/DJFA2005179), Dec 21, 2005: BULKHEAD. CRACKED. DURING A SCHEDULED MAINTENANCE VISIT, A CRACK WAS DISCOVERED IN THE PRESSURE BULKHEAD WEB AT FUSELAGE STATION 409.00 WHILE PERFORMING AIRWORTHINESS DIRECTIVE 97
- [SDR CA051121001](https://openairdocs.org/sdr/CA051121001), Nov 21, 2005: FUEL HEATER. CRACKED. (CAN) FUEL LEAK AS BEEN FOUND ON SEVEN DAYS INSPECTION, TECHNICIAN HAS FOUND A CRACK IN A SOLDERED JOINT ON FUEL HEATER. THE FUEL HEATER HAS BEEN REPLACED AND T
- [SDR DJFA2005159](https://openairdocs.org/sdr/DJFA2005159), Oct 19, 2005: BULKHEAD. CRACKED. DURING A ROUTINE MAINTENANCE VISIT, A CRACK WAS DISCOVERED IN THE PRESSURE BULKHEAD WEB AT FUSELAGE STATION 409.00 WHILE PERFORMING AD 97-24-02. THE CRACK WAS R
- [SDR CA050826001](https://openairdocs.org/sdr/CA050826001), Aug 19, 2005: HEAT EXCHANGER. LEAKING. (CAN) DURING TROUBLESHOOTING TO FIND CAUSE FOR LOW OIL PRESSURE AT HIGH POWER IT WAS DISCOVERED THAT THE OIL HAD BECOME CONTAMINATED WITH FUEL AND SUBSEQUENTLY 
- [SDR DJFA2005111](https://openairdocs.org/sdr/DJFA2005111), Jun 19, 2005: SELECTOR VALVE. INOPERATIVE. THE CREW REPORTED THAT DURING A NORMAL GEAR EXTENSION, THE NOSE WHEEL WOULD NOT EXTEND. THE LANDING GEAR WAS CYCLED TWICE, AND THE NOSE GEAR REMAINED RETRACTED.
- [SDR DJFA2005104](https://openairdocs.org/sdr/DJFA2005104), May 31, 2005: CONTROLLER. BROKEN. AFTER MLG SELECTED DOWN, LT MLG INDICATOR LIGHTS DID NOT ILLUMINATE. CREW TESTED BULBS AND PERFORMED A FLY-BY PAST TOWER. CONTROLLER REPORTED THAT MLG APPEARED 
- [SDR CA050413003](https://openairdocs.org/sdr/CA050413003), Apr 13, 2005: ELEMENT. BROKEN. (CAN) DURING A SCHEDULED 1200-HOUR CHECK, A FUNCTIONAL TEST OF THE RIGHT THRUST REVERSER AUTO THROTTLE RETARDER WAS CARRIED OUT. THE RIGHT THROTTLE FAILED TO RE
- [SDR CA050406005](https://openairdocs.org/sdr/CA050406005), Apr 6, 2005: ACTUATOR. LEAKING. (CAN) NOSE LANDING GEAR ACTUATOR LEAKING AT ROD END PISTON. LIFE LIMITED PART AT 19480 CYCLES. A/C RETURN TO BASE ON SPECIAL FLIGHT PERMIT WITH GEAR DOWN.
- [SDR CA050222008](https://openairdocs.org/sdr/CA050222008), Feb 19, 2005: GCU. INOPERATIVE. (CAN) A FEW MINUTES AFTER TAKE-OFF FROM AIRPORT WHILE SHUTTING DOWN THE APU, THE FLIGHT CREW HAD A SEVERE ELECTRICAL SMELL IN THE COCKPIT, BUT NO SMOKE APPEARS.
- [SDR CA050215012](https://openairdocs.org/sdr/CA050215012), Feb 10, 2005: CONNECTOR. LOOSE. (CAN) ON APPROACH, NLG WOULD NOT DEPLOY UPON NORMAL SELECTION OF LANDING GEAR DOWN. EMER EXTENSION WAS COMPLETED, AC LANDED WITHOUT FURTHER INCIDENT, FOUND THAT
- [SDR CA050120008](https://openairdocs.org/sdr/CA050120008), Jan 20, 2005: ANTI-ICE VALVE. FAILED. (CAN) FOLLOWING AN FAA, SUSPECTED UNAPPROVED PART REPORT, FOR A COWL ANTI ICE VALVE P/N: 300013000-002 S/N: 1596, MFG P/N: 601-97097-5, AN ADDITIONAL VALVE S/N:
- [SDR CA050125009](https://openairdocs.org/sdr/CA050125009), Jan 19, 2005: ACCESS DOOR. DISTORTED. (CAN) THIS AIRCRAFT WAS INSPECTED AND TESTED AND FOUND TO EXHIBIT UNACCEPTABLE NOSE AVIONICS ACCESS DOOR DEFORMATION IN EXTREME COLD CONDITIONS. THE DEGREE OF D
- [SDR CA050125008](https://openairdocs.org/sdr/CA050125008), Jan 19, 2005: ACCESS DOOR. DISTORTED. (CAN) THIS AIRCRAFT WAS INSPECTED AND TESTED AND FOUND TO EXHIBIT UNACCEPTABLE NOSE AVIONICS ACCESS DOOR DEFORMATION IN EXTREME COLD CONDITIONS. THE DEGREE OF D
- [SDR CA050119002](https://openairdocs.org/sdr/CA050119002), Jan 18, 2005: ACCESS PANEL. DISTORTED. (CAN) AC REMOVED FROM HEATED HANGAR (20 DEG C) TO RAMP (-27 DEG C) T/E OF UPPER ELEC BAY ACCESS PANEL DEFLECTED .345 FROM AIRFRAME. FURTHER INVESTIGATION SHOWED
- [SDR CA050119001](https://openairdocs.org/sdr/CA050119001), Jan 17, 2005: VALVE. IMPROPER PART. (CAN) FOLLOWING AN FAA, SUSPECTED UNAPPROVED PART REPORT, FOR A COWL ANTI-ICE VALVE PN 300013000-002, SN 1596, THREE (3) ADDITIONAL VALVES WERE FOUND TO HAVE BE
- [SDR CA040729002](https://openairdocs.org/sdr/CA040729002), Jul 27, 2004: GENERATOR. FAILED. DURING A ROUTINE POST MAJOR MAINTENANCE FLIGHT CHECK OF THE AIR DRIVEN TURBINE GENERATOR SYSTEM, THE SYSTEM FAILED TO TAKE THE ELECTRICAL LOAD, AS INDICATED BY 
- [SDR CA040603004](https://openairdocs.org/sdr/CA040603004), Jun 3, 2004: AILERON. MISMANUFACTURED. (CAN) WHILE INVESTIGATING A SNAG, DISCOVERED AN AILERON A/P QUADRANT ASSEMBLY P/N 40E22-84-1069-1 WHICH DID NOT MEET THE MANUFACTURER'S DRAWING IN THE INSTALLAT
- [SDR CA040423007](https://openairdocs.org/sdr/CA040423007), Apr 16, 2004: POTENTIOMETER. INTERMITTENT. (CAN) DURING TAKEOFF ROTATION, THE STICK SHAKER ACTIVATED ON THE LOW LEVEL, THE STALL PROTECT SYSTEM (SPS) WARBLER SOUNDED, THE SPS FAIL LIGHTS WENT TO A FLASH 
- [SDR CA031113001](https://openairdocs.org/sdr/CA031113001), Oct 14, 2003: ENGINE. SHUTDOWN. (CAN) DURING CRUISE AT FL 390, THE RT ENGINE SHUTDOWN. THE CREW REPORTED ALL ENGINE PARAMETERS WERE NORMAL AT THE TIME AND NO MESSAGES OR CAUTIONS WERE POSTED. 
- [SDR CA030903006](https://openairdocs.org/sdr/CA030903006), Aug 27, 2003: ACTUATOR. FAILED. (CAN) ATTEMPT TO TRIM AIRCRAFT NOSE UP OR NOSE DOWN CAUSED BOTH PITCH TRIM CHANNELS TO INDICATE (OFF). THUS HORIZONTAL PITCH TRIM SYSTEM DE-ACTIVATED.
- [SDR CA030724002](https://openairdocs.org/sdr/CA030724002), Jul 21, 2003: BATTERY PACK. OVERHEATED. (CAN) THE BATTERY ASSEMBLY FOR NR 4 EMERGENCY LIGHTING POWER SUPPLY WAS REMOVED FOR BENCH CHECK. THE ASSEMBLY WAS INSPECTED AND FOUND THAT THE CELL TABS HAD BEE
- [SDR CA030731005](https://openairdocs.org/sdr/CA030731005), Jul 15, 2003: BUSHING. FAILED. (CAN) AFTER COMPLETION OF TASK, INSPECT ELEVATOR ATTACH BOLTS, VISUAL AND NDT INSPECTION, AND DURING POST INSTALLATION/INDEPENDENT INSPECTION, INSPECTOR NOTICED
- [SDR CA030122001](https://openairdocs.org/sdr/CA030122001), Jan 19, 2003: FITTING. BROKEN. (CAN) DOOR TENSION FITTING (UPPER FORWARD) BROKEN IN FLIGHT.
- [SDR CA021217006](https://openairdocs.org/sdr/CA021217006), Nov 11, 2002: BEARING. BROKEN. (CAN) DURING 300-600 HOUR INSPECTION AILERON PCU OPERATION TEST. FOUND AILERON QUADRANT IN RT WHEEL WELL IS NOISY (SNAPPING). AFTER REMOVING RT AILERON QUADRANT
- [SDR CA021125002](https://openairdocs.org/sdr/CA021125002), Nov 11, 2002: BEARING. BROKEN. (CAN) DURING 300-600 HOURS INSPECTION AILERON PCU OPERATION TEST, FOUND AILERON QUADRANT IN RT WHEEL WELL IS NOISY (SNAPPING).AFTER REMOVING RT/ AILERON QUADRAN
- [SDR CA020926001](https://openairdocs.org/sdr/CA020926001), Sep 19, 2002: WIRE. EXPOSED. (CAN) WIRING HARNESS FOR THE ENGINE FIRE BOTTLE SQUIBS LOCATED IN THE APU AREA HAD EXPOSED WIRES WHERE THEHARNESS ENTERS THE CONNECTOR PLUG FOR THE SQUIB.
- [SDR CA020925003](https://openairdocs.org/sdr/CA020925003), Sep 18, 2002: WIRE HARNESS. EXPOSED. (CAN) WIRING HARNESS FOR THE ENGINE FIRE BOTTLE SQUIBS LOCATED IN THE APU AREA HAD EXPOSED WIRES WHERE THEHARNESS ENTERS THE CONNECTOR PLUG FOR THE SQUIB.
- [SDR CA020913010](https://openairdocs.org/sdr/CA020913010), Sep 9, 2002: WIRE. SHORTED. (CAN) ON A SCHEDULED MAINTENANCE INSPECTION OF THE FIRE BOTTLES, MECHANIC FOUND ON RT BOTTLE LT SQUIB WIRING TO BE EXPOSED AND TOUCHING EACH OTHER IN THE APU AR

All 88: https://openairdocs.org/model/canadair-cl-601-2a12/reports.md

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