N256CA

Part: OIL SYSTEM — LOW PRESSURE · airframe 24,233 hrs

PILOT REPORTED IN CRUISE, BOTH ENGINES LOST OIL PRESSURE AND STARTED TO RUN ROUGH. NO LEAKS WERE NOTED, BUT LOW OIL LEVELS WERE NOTED ON BOTH SIDES OIL DIPSTICKS. ENGINES ARE BEING REPLACED.

Part: EXHAUST VALVE — BROKEN (ENGINE) · airframe 23,934 hrs

PILOT REPORTED IN CLIMB POWER, AIRCRAFT YAWED AND SEVERE ENGINE VIBRATION ENSUED. UPON INSPECTION MAINTENANCE FOUND THE CYLINDER TO HAVE ZERO COMPRESSION AND THE EXHAUST VALVE BROKEN AT THE STEM. THE CYLINDER WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: EXHAUST VALVE — BROKEN (NR 4 CYLINDER) · airframe 23,676 hrs

PILOT REPORTED RIGHT ENGINE ROUGH AND VIBRATION IN FLIGHT. UPON INSPECTION MX DISCOVERED THE NR 4 EXHAUST VALVE TO BE BROKEN.

Part: EXHAUST VALVE — DAMAGED (NR 3 CYLINDER) · airframe 22,995 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 1 CYLINDER) · airframe 22,867 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: NUT — FRACTURED (ENGINE)

DURING ROUTINE INSPECTION, A THRU-BOLT NUT, TWELVE POINT PN 652541, WAS FOUND FRACTURED & LAYING IN THE BOTTOM OF THE ENG COWLING. THERE WERE NO SIGNS OF CORROSION ON THE NUT. THE ENG WAS REMOVED TO BE DISASSEMBLED, INSPECTED & OVERHAULED. THE NUT WAS RETURNED TO THE ENG MFG FOR FURTHER EXAMINATION.

Part: FDAU — MALFUNCTIONED (AVIONICS COMP)

FDAU CIRCUIT BREAKER TRIPPED. REPLACED THE FDAU.

Part: BLEED VALVE — FAILED (ENGINE)

DURING CLIMB-OUT OF MCO, THE CROSS BLEED VALVE WOULD NOT CLOSE. AIRCRAFT RETURNED TO THE FIELD. REPLACED THE CROSS BLEED VALVE.

Part: BULB — FAILED (NR 2 STALL IND)

STALL WARNING LIGHT ILLUMINATED. REPLACED THE NR 2 STALL PANEL LIGHT BULB.

Part: RADAR — FAILED (FWD COMPT)

RADAR STUCK IN MAP MODE. COULD NOT DUPLICATE. REPLACED THE WXT-250B FOR TROUBLESHOOTING.

Part: CONTROL MODULE — MALFUNCTION (LANDING GEAR)

LANDING GEAR WOULD NOT RETRACT. REPLACED CONTROL MODULE.

Part: CONNECTOR — LOOSE (ROW 5)

EMERGENCY FLOOR LIGHTS AFT OF ROW 5 ARE INOPERATIVE. SECURED LOOSE WIRING CONNECTOR.

Part: SIGN — BROKEN (ROW 5)

EXIT SIGN AT ROW 5 IS BROKEN. REPLACED EXIT SIGN.

Part: PRESSURE SWITCH — MALFUNCTIONED (LT ENGINE)

LEFT ENGINE LOW FUEL PRESSURE WARNING. REPLACED THE LOW PRESSURE SWITCH.

Part: SIGN — MISSING (ROW 5)

EXIT SIGN MISSING AT ROW 5. REPLACED EXIT SIGN.

Part: DOOR — NOT LATCHED (FUEL SERVICE)

DOORS WARNING DURING TAKEOFF. FUEL SERVICE DOOR NOT CLOSED PROPERLY. CLOSED AND LATCHED FUEL SERVICE PANEL.

Part: SIGN — BROKEN (ROW 5)

EMERGENCY EXIT SIGN AT ROW 5 IS BROKEN. REPLACED SIGN.

Part: ALTIMETER — LOOSE (LT COCKPIT)

PILOTS ALTIMETER VIBRATED DURING TAKEOFF. SECURED ALTIMETER.

Part: BEAM — CORRODED (CABIN)

DURING AN E5 PART A INSPECTION, CORROSION DAMAGE WAS FOUND ON THE UPPER SURFACE OF THE CENTER OMEGA BEAM AT FRAME 16. THE DAMAGE CONSISTS OF 1 HOLE AND 4 AREAS OF PITTING. THE HOLE WAS CLEANED UP, DEBURNED AND SHARP EDGES REMOVED. THE 4 AREAS OF PITTING WAS ALSO CLEANED UP. AN EXTERNAL DOUBLER WAS THEN ADDED TO COVER ALL DAMAGED AREAS IAW AERODESIGN AIRCRAFT ENGINEERING REPORT NR 2181-7.

Part: DOOR — NOT SECURED (FUEL SERVICE)

DOOR LIGHT ILLUMINATED DURING TAKEOFF ROLL, AIRCRAFT RETURNED TO THE GATE. SECURED FUEL SERVICE DOOR FASTENER.

Part: BATTERY — DISCHARGED (CABIN)

EMERGENCY LIGHTS ARE INOPERABLE. REPLACED EMERGENCY LIGHTS BATTERY.

Part: DOOR — NOT LATCHED (FUEL SYSTEM)

SERVICE DOOR WARNING DURING TAKEOFF. CLOSED AND LATCHED SINGLE POINT FUEL SERVICE DOOR.

Part: SIGN — LOOSE (ROW 5)

ROW 5 EXIT SIGN FELL OFF. REPLACED THE EXIT SIGN.

Part: LATCH — NOT SECURED (SERVICE DOOR)

DOOR WARNING DURING TAKEOFF. FUEL SERVICE DOOR NOT CLOSED. SECURED SERVICE DOOR.

Part: SIGN — BROKEN (SEAT 5A)

CREW REPORTED EMERGENCY EXIT SIGN BROKEN. REPLACED EXIT SIGN AT SEAT 5A.

Part: DOOR — NOT LATCHED (FUEL SERVICE)

SERVICE DOOR WARNING DURING TAKEOFF. SECURED LATCHES ON SINGLE POINT FUEL SERVICE DOOR.

Part: DOOR — NOT LATCHED (FUEL SERVICE)

SERVICE DOOR WARNING ON DURING FLIGHT. CLOSE AND LATCHED SINGLE POINT FUEL SERVICE DOOR.

Part: DOOR — UNLATCHED (FUEL SERVICE)

DOORS WARNING AFTER TAKEOFF. SINGLE POINT FUEL SERVICE DOOR NOT SECURED. CLOSED AND LATCHED DOOR.

Part: SEQUENCE VALVE — FAILED (NLG)

NLG WOULD NOT RETRACT. REPLACED THE LEFT HAND NLG DOOR SEQUENCE VALVE.

Part: SIGN — BROKEN (CABIN)

EMERGENCY EXIT SIGN AT ROW 5 IS BROKEN. REPLACED SIGN ASSY.

Part: PUMP — INOPERATIVE (LT ENGINE)

LEFT ENGINE ELECTRIC FEATHER PUMP IS INOP. REPLACED AUXILIARY FEATHER PUMP.

Part: STATOR — CRACKED (NR 1 BRAKE ASSY)

DURING TEARDOWN OF BRAKE ASSY P/N 2-1585, THE ACCESSORY SHOP FOUND THE NUMBER ONE STATOR CRACKED. OVERHAULED BRAKE.

Part: FRAME — CHAFED (FUSELAGE)

RIGHT AFT EMERGENCY EXIT FRAME NIB HAS GOUGES AT FORWARD SECTION OF NIB. REMOVED DAMAGED FRAME. INSTALLED NEW SERVICEABLE FRAME P/N 120-26331-002 IN ACCORDANCE WITH EMBRAER EMB 120 SRM 51-10-02 PART 3 AND 51-40-02.

Part: FRAME — CHAFED (FUSELAGE)

RIGHT AFT EMERGECY EXIT AFT FUSELAGE FRAME HAS CHAFE DAMAGE FROM SCREW HEAD. REMOVED DAMAGED FRAME. INSTALLED NEW SERVICEABLE FRAME P/N 120-26331-001 IAW EMBRAER EMB 120 SRM 51-10-02 PART 3 AND 51-40-02.

Part: AHRS — FAILED (NR 1)

NR 1 AHRS IS INOP. REPLACED THE NR 1 AHRS.

Part: STRIKER PLATE — BROKEN (CARGO DOOR)

CARGO DOOR UNSAFE WARNING CAME ON DURING FLIGHT. REPLACED BROKEN DOOR WARNING SWITCH STRIKER PLATE.

Part: SKIN — GOUGED (FUSELAGE)

C2 INSPECTION FOUND THE LOWER FUSELAGE CENTER SECTION SKIN TO BE GOUGED BY THE RIGHT WING DE-ICE PRESSURE REGULATOR. THE DAMAGED SKIN WAS REPAIRED PER SRM 53-00-01, FIGURE 201, SHEET 3, PAGE 204. THE DE-ICE PRESSURE REGULATOR WAS REPOSITIONED FOR PROPER CLEARANCE.

Part: STRINGER — CORRODED (BS 3293-3596)

C2 INSPECTION FOUND A SMALL AREA OF CORROSION ON FWD FUSELAGE STRINGER 21L BETWEEN FS 3293 AND 3596.5. THE DAMAGED AREA OF THE STRINGER WAS REMOVED AND REPAIRED PER AERODESIGN REPORT NR 1990-3, REV IR, DATED 10-26-96.

Part: PROP GOVERNOR — MALFUNCTIONED (LEFT)

LT PROPELLER WILL NOT AUTO-FEATHER OR MANUAL FEATHER. COULD NOT DUPLICAE DISCREPANCY, SYSTEM TEST NORMAL AND ACFT RETURNED TO SERVICE.

Part: STEERING — PULLED LEFT (NLG)

NOSE WHEEL STEERING PULLED TO LEFT TWICE DURING LANDING ROLL. COULD NOT DUPLICATE. INSPECTED N.W.S. SYSTEM AND TAXI CHECK NORMAL.

Part: UPLOCK SENSOR — OUT OF ADJUST (LT MLG)

LT MLG INTRANSIT LIGHTS REMAINED ON AFTER GEAR RETRACTED. ADJUSTED THE UPLOCK PROXIMITY SENSOR TO M/M SPECIFICATIONS.

Part: INTRANSIT LIGHT — MALFUNCTIONED (LT MLG)

LEFT MLG INTRANSIT LIGHTS REMAIN ON AFTER LANDING GEAR RETRACTED. COULD NOT DUPLICATE DISCREPANCY. FOUND ALL ADJUSTMENTS AND CLEARANCES WITHIN LIMITS. ACFT RETURNED TO SERVICE.

Part: FILTER — DIRTY (LT HYD SYST)

LEFT HYDRAULIC SYSTEM FILTER BYPASS WARNING ILLUMINATED. REPLACED HYDRAULIC SYSTEM FILTER.

Part: HYD PUMP — LEAKING (RT ENGINE)

HYDRAULIC FLUID LEAKING FROM RT ENGINE NACELLE. REPLACED THE ENGINE DRIVEN HYDRAULIC PUMP. PART TOTAL CYCLES, 7,269.

Part: PUMP — DEFECTIVE (LT PROP)

LEFT ENGINE PROPELLER WILL NOT UNFEATHER. REPLACED THE PROPELLER OVERSPEED GOVERNOR OIL PUMP.

Part: INDICATION — MALFUNCTIONED (TE FLAPS)

FLAP DISAGREEMENT INDICATION AFTER TAKEOFF. COULD NOT DUPLICATE DISCREPANCY - ACFT RETURNED TO SERVICE.

Part: ROLLER — WORN (LT FLAP)

FLAP DISAGREEMENT INDICATION AFTER TAKEOFF. REPLACED WORN ROLLERS ON LT OUTBOARD FLAP.

Part: ROLLER — WORN (RT TE FLAP)

RECEIVED FLAP DISAGREE WARNING, WHEN FLAPS SELECTED TO ZERO DEGREES. REPLACED THE ROLLERS ON THE RT OUTBD FLAP.

Part: SENSOR — DEFECTIVE (RT DUCT)

RT DUCT OVERHEAT WARNING, WARNING REMAINED ON WHEN THE TEMPERATURE WAS SELECTED TO FULL COLD. REPLACED THE DUCT OVER TEMPERATURE SENSOR.

Part: COOLING FAN — FAILED (RT PACK)

DURING TAXI, RT A/C PACK PRODUCED SMOKE IN CABIN. PACK FAILED AND DUCT LEAK INDICATOR ON. REPLACED THE RT GROUND COOLING FAN.

Part: LATCH — BROKEN (RT MLG DOOR)

RT MLG INBD DOOR LATCH IS BROKEN. REPLACED LATCH ASSY.

Part: LATCH — BROKEN (RT NACELLE)

RIGHT HYDRAULIC PACK SERVICE DOOR HAS A BROKEN LATCH. REPLACED LATCH.

Part: GCU — DEFECTIVE (ELEC BAY)

RIGHT ENGINE STARTER DOES NOT TERMINATE START SEQUENCE AT 50 PERCENT. REPLACED THE GCU.

Part: SERVO — DEFECTIVE (PITCH TRIM)

ELECRIC TRIM IS INOP, AND MANUAL TRIM FEELS ROUGH. REPLACED THE PITCH TRIM SERVO.

Part: HYD SYST — FROZEN (LT NACELLE)

GREEN SYSTEM HYDRAULIC RESEVOIR LOW PRESSURE INDICATOR ON. RESERVOIR PRESSURIZATION SYSTEM CONTAINED MOISTURE WHICH FROZE. PURGED MOISTURE FROM SYSTEM.

Part: CONTROL BOX — DEFECTIVE (ANTI-SKID SYST)

DURING LANDING ANTI-SKID FAILED. REPLACED THE ANTI-SKID CONTROL BOX.