N247CA
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| AMERIFLIGHT, LLC (JIKA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
UPON COMPLIANCE OF 1C-CHECK TASK 193-01Z, THE LEFT WING UPPER SKIN ATTACH ANGLE FOR FAIRING 193 WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPLACED IN ACORDANCE WITH EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT NR 1226-21, IR, 7-6-99.
WHILE PERFORMING OTHER MAINTENANCE, THE FUSELAGE FORWARD CENTER CABIN FLOOR BEAM BUTT-STRAP WAS FOUND TO BE CORRODED. THE BUTT-STRAP WAS REPLACED IN ACCORDANCE WITH THE EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.
UPON COMPLIANCE OF 1C-CHECK TASK 5720-622-02E, THE RIGHT WING LOWER SKIN RIVET HOLE AT RIB 6, STRINGER 10 WAS FOUND TO BE IMPROPERLY COUNTERSUNK. THE DAMAGED SKIN WAS REPAIRED IN ACCORDANCE WITH EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT NR 3745-1,IR,7-25-00.
UPON COMPLIANCE OF 1C-CHECK TASK 52-14, THE PASSENGER DOOR INNER CHANNEL WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPLACED IN ACCORDANCE WITH EMB-120 STUCTURAL REPAIR MANUAL STANDARD PRACTICES.
UPON COMPLIANCE OF 1C-CHECK TASK 433-01Z, THE LEFT NACELLE FRAME 14 EXHAUST PAN SUPPORT BULKHEAD WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPLACED IN ACCORDANCE WITH EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT 33712-1, IR-7-28-00.
UPON COMPLIANCE OF 1C-CHECK TASK 100-01Z, THE FUSELGE FWD LOWER RT SKIN JUST BELOW LAV DUMP VALVE DOUBLER WAS FOUND TO BE GOUGED. THE DAMAGED PART WAS REPAIRED IN ACCORDANCE WITH EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND EMBRAER REPAIR NR SST-1872/00 DATED 7-25-00.
UPON COMPLIANCE OF 1C-CHECK TASK 5310-122-01E, THE FUSELAGE RT FWD LOWER SKIN WAS FOUND TO BE DENTED. THE DAMAGED PART WAS REPAIRED IN ACCORDANCE WITH EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND EMB120 SRM 53-00-01, FIGURE 201.
WHILE PERFORMING OTHER MAINTENANCE, THE FUSELAGE LEFT HAND SKIN SUPPORT AT FRAME 9, WAS FOUND TO BE CRACKED. THE SKIN SUPPORT WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES AND AERODESIGN REPORT NR 660-1, IR, 2-16-93.
UPON COMPLIANCE OF 1C-CHECK TASK 813-01Z THE CARGO DOOR SKIN WAS FOUND TO BE GOUGED. THE DAMAGED PART WAS REPAIRED IN ACCORDANCE WITH EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND EMB-120 SRM 52-30-01, FIGURE 201.
UPON COMPLIANCE OF 1C-CHECK TASK 194-01Z THE RIGHT WING UPPER SKIN ATTACH ANGLE FOR FAIRING 194 WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPLACED IN ACCORDANCE WITH EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT NR 1226-21, IR, 7-6-99.
EMERGENCY FLOOR PATH LIGHTING IS INOPERABLE. REPLACED EMERGENCY LIGHT BATTERY.
WING DE-ICE FAIL WARNING. REPLACED THE RIGHT WING INBOARD DE-ICE BOOT.
CABIN EMERGENCY LIGHT SYSTEM WAS PARTIALLY INOP. REPLACED EMERGENCY BATTERY.
5 EXIT LIGHTS ON FLOOR AND 1 ON OVERHEAD ARE INOPERABLE. REPLACED THE NR 1 AND NR 2 EMERGENCY BATTERIES.
EMERGENCY EXIT SIGN AT ROW 8 IS INOPERABLE. REPAIRED DAMAGED WIRES AT EXIT SIGN.
RT PROPELLER RPM WAS 99.2 TO 99.6 AFTER TAKEOFF. GROUND RUNS SHOWED PROPELLER RPM TO BE IN LIMITATIONS.
RIGHT HAND PROPELLER DEICE FAIL WARNING. REPLACED RCCB (CB0226).
FWD EMERGENCY FLOOR LIGHT WAS INOP. REPLACED LIGHT ASSY.
SERVICE DOOR WARNING DURING TAKEOFF. DOOR WARNING SYSTEM PREVIOUSLY DEFERRED PER MEL.
SERVICE DOOR WARNING DURING TAKEOFF. DEFERRED DOOR WARNING SYSTEM PER MEL.
LEFT MLG DOWN INDICATOR ON WITH GEAR RETRACTED. LANDING GEAR WOULD NOT EXTEND WHEN SELECTED. FREE FALL SYSTEM USED TO EXTEND GEAR. REPLACED DOWN LOCK PROXIMITY SENSOR. (M)
RIGHT HAND PROPELLER DEICE IS INOPERABLE. REPLACED THE NR 3 BLADE ON RIGHT HAND PROPELLER.
LEFT NACELLE, FRAME WEB NR 10 CRACKED AT INBOARD RADIUS OF THE FLANGE. REPAIRED BY SPLICING IN A NEW FLANGE PER AERODESIGN REPORT NR 1076-2 AND EMB120 SRM 51-40-02.
FORWARD SECTION OF CABIN EMERGENCY LIGHTS ARE INOPERATIVE. REPLACED BATTERY PACK FOR THE FORWARD EMERGENCY LIGHTING.
EXTERNAL POWER CONTACTOR BURNT/OVERHEATED AT TERMINAL ENDS. REPLACED CONTACTOR AND POSITIVE CABLE.
SERVICE DOOR WARNING DURING TAKEOFF. REPLACED BROKEN CAM LOCK FASTENER ON SINGLE POINT FUEL SERVICE DOOR.
AFTER LANDING GEAR RETRACTED, RIGHT HAND MLG DOWN INDICATOR REMAINED ON. REPLACED DEFECTIVE DOWNLOCK PROXIMITY SENSOR.
SERVICE DOOR WARNING DURING CLIMBOUT. AIRCRAFT RETURNED TO THE FIELD. CLOSED DOOR AND SECURED LATCH.
NOSE LANDING GEAR WOULD NOT RETRACT. REMOVED NLG PIN. GEAR SWINGS GOOD.
DURING 2C INSPECTION TASK 151-01Z REVEALED LEFT NR 5 BUTTSTRAP TO BE CORRODED. REMOVED BUTTSTRAP AND INSTALLED SERVICEABLE BUTTSTRAP USING EMB 120 STANDARD PRACTICES.
DURING 2C INSPECTION, TASK 5310-131-01I REVEALED LEFT CENTER CROSSBEAM TO BE CORRODED AT FRAME 16. REMOVED AND REPLACED CROSSBEAM USING EMB 120 SRM STANDARD PRACTICES.
DURING 2C INSPECTION, TASK 5310-131-01I REVEALED LEFT FORWARD BUTTSTRAP TO BE CORRODED. REMOVED BUTTSTRAP AND INSTALLED SERVICEABLE BUTTSTRAP USING EMB 120 SRM STANDARD PRACTICES.
DURING 2C INSPECTION, TASK 5310-131-01I REVEALED LEFT NR 1 STILL TO BE CORRODED. REMOVED SILL AND INSTALLED SERVICEABLE SILL USING EMB 120 SRM STANDARD PRACTICES.
DURING 2C INSPECTION TASK 5310-131-01I REVEALED RIGHT NR 1 SILL TO BE CORRODED. REMOVED SILL AND INSTALLED SERVICEABLE SILL USING EMB 120 SRM STANDARD PRACTICES.
DURING 2C INSPECTION, TASK 5720-622-01I, REVEALED THE WIRE HARNESS FOR THE RIGHT WING FORWARD FUEL BOOST PUMP TO BE CHAFFING ON THE METAL BRAIDED FUEL LINE. PUMP WIRE INSULATION WAS NOT DAMAGED ONLY WIRE HARNESS PROTECTIVE COVERING. REMOVED PUMP AND HARNESS AND INSTALLED SERVICEABLE PUMP MAKING SURE THE WIRE HARNESS WAS CLEAR OF ALL STRUCTURE AND FUEL LINES.
DURING 2C INSPECTION TASK 5310-131-O1I REVEALED CENTER BUTTPLATE TO HAVE SPOTS OF CORROSION THAT WERE BEYOND LIMITS. REMOVED CENTER BUTTPLATE AND INSTALLED SERVICEABLE BUTTPLATE USING EMB120 SRM STANDARD PRACTICES AND AERODESIGN REPORT NR 1671-1.
DURING TEARDOWN VISUAL INSPECTION FOR TIRE CHANGE, THE INNER HALF OF THE MAIN WHEEL ASSY WAS FOUND TO HAVE A CRACK APPROXIMATELY 2 INCHES IN LENGTH RUNNING INWARD IN THE WEB AREA, STARTING FROM UNDER THE BEARING CUP. THE WHEEL WAS REMOVED FROM SERVICE AT THIS TIME.
SOME OF THE CABIN EMERGENCY LIGHTS ARE INOPERABLE. REPLACED EMERGENCY BATTERY.
SOME OF THE CABIN FLOOR PATH EMERGENCY LIGHTS ARE INOP. REPAIRED BROKEN WIRE.
SERVICE DOOR WARNING CAME ON AFTER TAKEOFF. SINGLE POINT FUEL SERVICE DOOR NOT LATCHED. SECURED DOOR AND AIRCRAFT RETURNED TO SERVICE.
FLAP DISAGREEMENT AFTER FLAPS SELECTED TO 0 DEGREES. REPLACED FLAP ROLLERS ON LEFT AND RIGHT OUTBOARD FLAPS.
EMERGENCY LIGHTING NOT ARMED WARNING ON MAP, CIRCUIT BREAKER TRIPPED. COULD NOT DUPLCIATE DISCREPANCY. REPLACED RELAY K201 FOR TROUBLESHOOTING.
HYDRAULIC FLUID LEAKING FROM LT ENGINE NACELLE. REPLACED DAMAGED SECTION OF GREEN SYSTEM HYDRAULIC PRESSURE TUBING BETWEEN NACELLE 13 AND 14.
CLUNKING SOUND AND UNCOMMANDED MOVEMENT FROM NOSE WHEEL STEERING SYSTEM. REPLACED THE NWS FEEDBACK POTENTIOMETER.
CARGO DOOR WARNING SOUNDED DURING TAKEOFF. ADJUSTED CARGO DOOR MICROSWITCH. AIRCRAFT CONTINUED SERVICE.
TRANSPONDER NR 1 AND NR 2 REPORTED INOPERATIVE BY AIR TRAFFIC CONTROL. REPLACED CTL-92.
FUEL LEAKING FROM RT ENGINE NACELLE. REPLACED THE RT ENGINE FUEL NOZZLES.
WHEN LANDING GEAR SELECTED DOWN, GEAR DID NOT EXTEND. INDICATION WAS 5 RED INTRANSIT AND ONE GREEN DOWNLOCK. EMERGENCY SYSTEM USED TO EXTEND GEAR. REPLACED DEFECTIVE DOWNLOCK PROXIMITY SENSOR ON LEFT MLG.
RIGHT MLG OUTBOARD GEAR DOOR WILL NOT CLOSE. REPLACED BROKEN DOOR LATCH ASSY.
LEFT PROPELLER TAKES 30 SECONDS TO TRANSITION FROM FEATHER TO BETA RANGE. REPLACED THE PROPELLER CONTROL UNIT.
DOOR LIGHT ON M.A.P. ILLUMINATED ON TAKEOFF ROLL. SECURED FORWARD FASTENER ON INBOARD FUEL DOOR.
LT PROPELLER IS SLOW COMING OUT OF FEATHER. REPLACED THE LEFT OVER SPEED GOVERNOR.
RT MLG TIRE FAILED DURING TAKEOFF ROLL. REPLACED RT WHEEL TIRE ASSY.
CARGO DOOR WARNING CAME ON DURING TAKEOFF. COULD NOT DUPLICATE - INSPECTED DOOR SYSTEM AND OPERATIONAL CHECK SATISFACTORY. AIRCRAFT RETURNED TO SERVICE.
LEFT PROPELLER TAKES 15 SECONDS TO UNFEATHER. REPLACED THE PITCH CONTROL UNIT.
LANDING GEAR WILL NOT RETRACT. REPLACED THE LANDING GEAR CONTROL BOX.
LEFT PROPELLER IS SLOW TO UNFEATHER. REPLACED THE PROP PITCH CONTROL UNIT.
THE FOLLOWING P/N WING SKIN SUPPORTS WERE FOUND CRACKED DURING INSPECTION TASK 5720-551/651-01i AND 5720-552/652-01I AT WING RIBS NR 15, 16, AND 18. P/N 120-17056-019, 2 EA; 120-17056-017, 2 EA; 120-17056-015, 4 EA; 120-17056-013, 2 EA; 120-17056-007, 2 EA; 120-17057-005, 1 EA; 120-17057-007, 2 EA; 120-17059-015, 2 EA; 120-17057-006, 1 EA. THE SKIN SUPPORTS WERE REPLACED IAW AERO DESIGN REPORT NR 1327-2.
RT ENGINE WILL NOT START. REPLACED THE HMU.
CONTROL FAULT WARNING WHEN FLAPS SELECTED FOR APPROACH. REPLACED FLAP CONTROL UNIT.