N267CA

Part: CYLINDER — SEPARATED (LT ENGINE) · airframe 13,090 hrs · 23,947 cycles

DURING POWER REDUCTION AT 20" LEFT ENGINE STARTED TO SHUTTER AND VIBRATE MAP INDICATION FLUCTUATED BETWEEN 20 AND 24" INCHES. ENGINE WAS NEVER SHUT DOWN AIRCRAFT WAS ON SHORT FINAL AND LANDED WITHOUT ISSUE. POSTFLIGHT INSPECTION REVEALED THE HEAD PORTION OF THE NR 4 CYLINDER OF THE LT ENGINE HAD SEPARATED COMPLETELY FROM THE BARREL SECTION. THE EXHAUST VALVE WAS FOUND TO BE BROKEN AT THE STEM AND HAD CAUSED SIGNIFICANT MECHANICAL DAMAGE TO THE PISTON AND HEAD PORTION OF CYLINDER. THE ENGINE MANUFACTURE HAS BEEN NOTIFIED AND WILL PARTICIPATE IN A COMPLETE TEAR DOWN INSPECTION TO IDENTIFY ROOT CAUSE OF FAILURE IF ABLE. THE CYLINDER HAD ACCUMULATED 916.7 SNEW.

Part: TORQUE TUBE — CRACKED (RUDDER PEDAL) · airframe 12,663 hrs · 23,593 cycles

DURING A SCHEDULED INSPECTION, THE RT RUDDER PEDAL TORQUE TUBE WAS CRACKED AND FAILED AT THE WELD INTERSECTION OF THE RT PEDAL 'POST'. THIS FINDING IS A RESULT OF A RECENTLY IMPLEMENTED MAGNIFIED VISUAL INSPECTION OF THESE WELDS AT EACH 180 FLIGHT HOURS OF OPERATION BASED ON A RECENT SIMILAR FINDING WITHIN THIS OPERATORS FLEET. THIS TORQUE TUBE IS BELIEVED TO BE ORIGINAL TO MANUFACTURE. PICTURES CAN BE PROVIDED UPON REQUEST.

Part: EXHAUST VALVE — DAMAGED (NR 2 CYLINDER) · airframe 11,155 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 4 CYLINDER) · airframe 11,155 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 1 CYLINDER) · airframe 11,057 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 2 CYLINDER) · airframe 11,057 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 3 CYLINDER) · airframe 10,930 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 5 CYLINDER) · airframe 10,866 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 4 CYLINDER) · airframe 10,866 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 1 CYLINDER) · airframe 10,866 hrs

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

Part: LAMP · airframe 23,732 hrs · 24,910 cycles

FLIGHT 5005 ONE EMERGENCY FLOOR LIGHT AT ROW 8 IS INOP.DEFERRED MAINT PER MEL.

Part: SIGN — BROKEN (CABIN) · airframe 23,563 hrs · 24,709 cycles

FLIGHT 5021 EMERGENCY EXIT SIGN AT ROW 5 IS BROKEN.REPLACED EXIT SIGN.

Part: DOOR · airframe 23,478 hrs · 24,605 cycles

FLIGHT 5061 SERVICE DOOR WARNING DURING T/O.CLOSED AND LATCHED SERVICE DOOR.

Part: SERVO — BINDING (AVIONICS) · airframe 23,117 hrs · 24,186 cycles

FLIGHT 5009 PILOT AND COPILOT RUDDER PEDALS BINDING.REPLACED THE RUDDER SERVO.

Part: PIN — BROKEN (BRAKE ASSY) · airframe 22,437 hrs · 23,392 cycles

FLIGHT MECHANICS TAXIED A/C TO HANGAR FROM GATE AND FELT A BRAKE DRAGGING. A/C WAS JACKED AND THE LEFT INBD BRAKE WAS FOUND TO BE DRAGGING. AFTER THE BRAKE WAS REMOVED, IT WAS DISCOVERED THAT ONE OF THE RETURN SPRING ASSEMBLIES "PIN" WAS BROKEN AT END THAT ATTACHES TO THE PRESSURE PLATE. REMOVED BRAKE ASSEMBLY AND INSTALLED SERVICEABLE BRAKE ASSEMBLY I/A/W EMB-120 MM 32-41-05 P401-404.

Part: CONTROLLER — FAULTY (COCKPIT) · airframe 22,437 hrs · 23,392 cycles

FLIGHT #5009. DURING CLIMB OUT OF MCO A LOUD AIR NOISE EMANATING FROM THE NOSE AREA, AIRCRAFT RETURNED TO THE FIELD.REPLACED THE LANDING GEAR RELAY BOX.

Part: SENSOR — MALFUNCTIONED (L/H) · airframe 22,305 hrs · 23,231 cycles

FLIGHT 5038. T/O TRIM AURAL WARNING WHEN POWER LEVERS ADVANCED. COULD NOT DUPLICATE DISCREPANCY AND A/C RETURNED TO SERVICE. DURING CALLBACK MAINTENANCE THE LEFT ELEVATOR TRIM PROXIMITY SENSOR WAS DETERMINED TO BE DEFECTIVE AND WAS REPLACED.

Part: COMPUTER — FAULTY (AVIONICS BAY) · airframe 22,169 hrs · 23,059 cycles

FLIGHT #5027. DURING CLIMB-OUT OF MCO RECEIVED HEADING AND PITCH CAPTIONS, RE-SETTING THE HEADING MONITOR CLEARED THE PITCH CAPTION, BUT HEADING CAPTION REMAINED.REPLACED THE AHC-85.

Part: PROXIMITY SWITCH — MALFUNCTIONED · airframe 22,004 hrs · 22,856 cycles

TAKE OFF TRIM AURAL WARNING. REPLACED DEFECTIVE ELEV. TRIM PROXIMITY SENSOR.

Part: PROXIMITY SWITCH — MALFUNCTIONED · airframe 22,004 hrs · 22,856 cycles

TAKE OFF TRIM AURAL WARNING.REPLACED DEFECTIVE ELEV. TRIM PROXIMITY SENSOR.

Part: FRAME — NICKED (FUSELAGE) · airframe 21,508 hrs · 22,304 cycles

THE AIRCRAFT''S FRAME 46A HAS A NICK IN THE UPPER FRAME FLANGE AT A PREVIOUSLY INSTALLED ANGLE. THE FRAME WAS REPAIRED BY REMOVING THE OLD ANGLE, DRESSING AND BLENDING THE NICK AND INSTALLING A SERVICEABLE ANGLE IN ACCORDANCE WITH AERODESIGN REPORT NR 2400-4.

Part: FIREWALL — CRACKED (APU BAY) · airframe 21,508 hrs · 22,304 cycles

THE AIRCRAFT HAS A CRACK IN THE APU FIREWALL WEB. INSTALLED A DOUBLER IN ACCORDANCE WITH AERODESIGN REPORT NR 2677-3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 21,508 hrs · 22,304 cycles

THE AIRCRAFT''S TWO FLOOR SUPPORT ANGLES UNDER THE PAX DOOR ENTRYWAY THRESHOLD ARE CORRODED. THE PARTS WERE REPLACED IN ACCORDANCE WITH AERODESIGN REPORT NR 3711-1.

Part: FLOOR SUPPORT — CRACKED (COCKPIT) · airframe 21,508 hrs · 22,304 cycles

THE AIRCRAFT FLOOR PROPS IN THE COCKPIT ARE CRACKED. THE REPAIR CONSISTS OF CUTTING OUT THE DAMAGED AREA AND SPLICING IN A NEW PIECE IN ACCORDANCE WITH AERODESIGN REPORT 3647-1.

Part: SKIN — GOUGED (FUSELAGE) · airframe 21,508 hrs · 22,304 cycles

THE AIRCRAFT SKIN BELOW THE LAVATORY DUMP VALVE DOUBLER IS GOUGED. THE DAMAGE WAS REPAIRED BY INSTALLING AN INTERNAL PATCH (DOUBLER) IN ACCORDANCE WITH EMBRAER FAX SST-1403/003.

Part: FAIRING — CRACKED (FUSELAGE) · airframe 21,508 hrs · 22,304 cycles

THE AIRCRAFT LEFT AND RIGHT WING ATTACH ANGLES ARE CRACKED. THE ANGLES WERE REPAIRED IN ACCORDANCE WITH SRM CHAPTER 53-20-13 PAGES 205 AND 206 AND AERODESIGN REPORT 1226-21.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 21,508 hrs · 22,304 cycles

THE AIRCRAFT SUSTAINED DAMAGE IN THE FORM OF CORROSION TO THE UPPER SURFACE OF THE CENTER OMEGA FLOORBEAM. THE OMEGA FLOORBEAM WAS REPAIRED IN ACCORDANCE WITH AERODESIGN REPORT NR 2181-11.

Part: ATTACH ANGLE — CRACKED (LT & RT WING) · airframe 21,508 hrs · 22,304 cycles

THE AIRCRAFT LEFT AND RIGHT WING ATTACH ANGLES ARE CRACKED. THE ANGLES WERE REPAIRED IN ACCORDANCE WITH SRM CHAPTER 53-20-13 PAGES 205 AND 206 AND AERODESIGN REPORT 1226-21.

Part: SKIN — CRACKED (LEFT NACELLE) · airframe 21,508 hrs · 22,304 cycles

THE LEFT HAND NACELLE AFT OUTBOARD SKIN IS CRACKED. A DOUBLER WAS INSTALLED IN ACCORDANCE WITH AERODESIGN REPORT NR 3860-1.

Part: BRACKET — CRACKED (CARGO DOOR) · airframe 21,508 hrs · 22,304 cycles

THE AIRCRAFT''S CARGO DOOR TRACK BRACKET IS CRACKED. THE CARGO DOOR AFT TRACK BRACKET WAS REPLACED USING ALTERNATE RIVETS IN ACCORDANCE WITH AERODESING REPORT NR 1657-3.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 21,508 hrs · 22,304 cycles

THE AIRCRAFT OMEGA BEAMS (P/N 120-46158-001) QTY 2, AND 120-46258-002 QTY 1, HAVE EXCESSIVE CORROSION. THE OMEGA BEAMS WERE REPLACED IN ACCORDANCE WITH AERODESIGN REPORT NR 2174-1.

Part: SUPPORT BRACKET — CRACKED (FUSELAGE) · airframe 21,508 hrs · 22,304 cycles

THE AIRCRAFT''S SKIN SUPPORT FOR FRAME 40 IS CRACKED. SKIN SUPPORT WAS REPLACED WITH A SERVICEABLE UNIT IN ACCORDANCE WITH AERODESIGN REPORT NR 3859-1.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,508 hrs · 22,304 cycles

THE AIRCRAFT HAS CORROSION PAST THE LIMIT ON THE FLOORBEAM BUTT STRAP UNDER THE FLOOR PANEL, LOCATED AT FRAME 13A. THE FLOORBEAM BUTT STRAP WAS REPLACED IN ACCORDANCE WITH AERODESIGN REPORT NR 1671-2.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,508 hrs · 22,304 cycles

THE AIRCRAFT HAS CORROSION PAST THE LIMIT ON THE FLOORBEAM BUTT STRAP UNDER THE FLOOR PANEL, LOCATED AT FRAME 13A. THE FLOORBEAM BUTT STRAP WAS REPLACED IN ACCORDANCE WITH AERODESIGN REPORT NR 1671-2.

Part: SUPPORT BRACKET — CRACKED (FUSELAGE) · airframe 21,508 hrs · 22,304 cycles

A SKIN SUPPORT FOR FRAME 13A IS CRACKED. THE REPAIR IS TO INSTALL A DOUBLER IN ACCORDANCE WITH AERODESIGN REPORT NR 3653-1.

Part: SOLENOID — SHORTED (LT ENGINE) · airframe 20,928 hrs · 21,656 cycles

LEFT HAND FLIGHT IDLE STOP CIRCUIT BREAKER IS TRIPPED. REPLACED FIS SOLENOID.

Part: SWITCH — BROKEN (POWER LEVER) · airframe 20,806 hrs · 21,525 cycles

AUTOFEATHER WARNING DURING TAKEOFF ROLL, AIRCRAFT RETURNED TO THE GATE. REPLACED BROKEN MICRO-SWITCH ON THE LEFT POWER LEVER.

Part: SKIN — CRACKED (FUSELAGE) · airframe 20,689 hrs · 21,398 cycles

DURING A 1C INSPECTION FOUND A CRACK APPROXIMATELY .125 INCH LONG EXTENDING FROM A RIVET ON THE RIGHT SIDE POST SKIN BETWEEN THE RIGHT DV WINDOW AND THE RIGHT WINDSHIELD. STOP DRILLED CRACK AND INSTALLED A DOUBLER IAW EMBRAER REPAIR EST - 474/95.

Part: SOLENOID — FAILED (ENGINE CONTROL) · airframe 20,410 hrs · 21,088 cycles

FLIGHT IDLE STOP SOLENOID CIRCUIT BREAKER IS TRIPPED.\NREPLACED THE FLIGHT-IDLE STOP SOLENOID.

Part: COMPUTER — MALFUNCTIONED (NR 2 AHRS) · airframe 20,400 hrs · 21,074 cycles

ATTITUDE DISPLAY WARNING ON MAP. REPLACED THE NR 2 AHRS COMPUTER.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 20,385 hrs · 21,060 cycles

TAKE OFF TRIM CONFIG WARNING. COULD NOT DUPLICATE. TRIM AURAL WARNING SYSTEM CHECKS SATISFACTORY.

Part: SENSOR — MALFUNCTIONED (LT ELEVATOR) · airframe 20,263 hrs · 20,929 cycles

TAKEOFF TRIM WARNING. REPLACED THE LEFT HAND ELEVATOR TRIM PROXIMITY SENSOR.

Part: SOLENOID — MALFUNCTIONED (LEFT) · airframe 19,886 hrs · 20,488 cycles

FLIGHT IDLE SOLENOID CIRCUIT BREAKER TRIPPED. REPLACED THE LEFT HAND SOLENOID.

Part: WARNING SYSTEM — ACTIVATED (COCKPIT) · airframe 19,777 hrs · 20,353 cycles

TRIM FAIL T/O CONFIG WARNING. COULD NOT DUPLICATE. SYSTEM TEST WAS NORMAL.

Part: WIRE — DISCONNECTED (PROX SENSOR)

TAKEOFF CONFIG WARNING. REPAIRED ELEVATOR TRIM PROXIMITY SENSOR WIRING CONNECTIONS.

Part: BLADE — DAMAGED (RT PROPELLER)

FOUND NR 4 BLADE RIGHT PROP HAD TIP DAMAGE. REMOVED AND REPLACED NR 4 BLADE RIGHT PROP.

Part: BULB — FAILED (ROW 9A)

FLOOR TRACK LIGHT AT SEAT 9A IS INOPERABLE. REMOVED AND REPLACED BULB.

Part: LIGHT — MISSING (ROW 5)

EMERGENCY EXIT LIGHT CONVER MISSING ROW 5. REPLACED LIGHT ASSY.

Part: HYD PUMP — LEAKING (BLUE HYD SYS)

BLUE HYDRAULIC SYSTEM LOW PRESSURE WARNING. REPLACED ENGINE HYDRAULIC PUMP.

Part: LIGHT — INOPERATIVE (CABIN)

GRR - FLT 5024 - EMERGENCY LIGHTS ARE INOPERABLE. COULD NOT DUPLICATE. EMERGENCY LIGHTS OPERATE NORMAL. (M)

Part: PCU — MALFUNCTIONED (RT ENGINE)

RIGHT HAND PROPELLER OVER SPEED TO 103 DEGREES. REPLACED THE PROPELLER CONTROL UNIT.

Part: FUEL DOOR — MISSING (RT WING)

SINGLE POINT FUEL SERVICE DOOR MISSING. REPAIRED DAMAGE CAUSED BY SEPARATION OF FUEL SERVICE DOOR AND REPLACED DOOR.

Part: SENSOR — BURNT (COCKPIT)

LAVATORY SMOKE ALARM ACTIVATED SMOKE IN COCKPIT. REPLACED BURNT AOA VANE CURRENT SENSOR.

Part: CONTROL UNIT — FAILED (E/E COMPT)

AIRCRAFT HAS NO BRAKES DURING LANDING ROLL. REPLACED THE BRAKE CONTROL UNIT.

Part: SENSOR — MALFUNCTION (RT MLG)

RT MLG, GREEN DOWN INDICATION, CAME ON WITH GEAR RETRACTED. REPLACED THE RT MLG DOWNLOCK SENSOR.

Part: CONTROL BOX — MALFUNCTION (LANDING GEAR)

LANDING GEAR WILL NOT RETRACT. REPLACED THE LANDING GEAR CONTROL BOX.

Part: SENSOR — MALFUNCTION (ELEV TRIM TAB)

TAKEOFF TRIM WARNING SOUNDED. REPLACED THE ELEVATOR TRIM TAB PROXIMITY SENSORS.

Part: BULB — FAILED (CABIN)

FLOOR EMERGENCY LIGHT AT GALLEY AREA IS INOP. REPLACED BULB.

Part: BATTERY — DISCHARGED (CABIN)

EMERGENCY LIGHTS ARE INOP. REPLACED THE EMERGENCY LIGHTS BATTERIES.

Part: BUTT STRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132-01I, FOUND NR 1 CENTER BUTT STRAP TO BE CORRODED. REMOVED CORRODED BUTT STRAP AND INSTALLED SERV PART IAW EMB 120 SRM CHAPTER 51.

Part: TEE SECTION — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132-O1I, FOUND LEFT MID T-SECTION TO BE CORRODED AT FRAME 16. REMOVED CORRODED T-SECTION AND INSTALLED SERV PART IAW EMB 120 SRM CHAPTER 51.

Part: SILL — CORRODED (FUSELAGE)

DURING 4C INSPECTION TASK 5320-151/152 O1I, FOUND RT NR 3 SILL AT AFT EXIT TO BE CORRODED. REMOVED CORRODED SILL AND INSTALLED SERV PART IAW EMB SRM CHAPTER 51.

Part: FLOORBEAM — CORRODED (FUSELAGE)

DURING 4C INSEPCTION TASK 5320-151/152-01I, FOUND RIGHT HAND FLOORBEAM AT FRAME 33 TO BE CORRODED. REMOVED CORRODED FLOORBEAM AND INSTALLED SERV PART IAW EMB 120 SRM CHAPTER 51.

Part: BUTT PLATE — CORRODED (FWD FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132-01I, REVEALED CENTER BUTT PLATE TO BE HEAVILY CORRODED. REMOVED BUTT PLATE AND INSTALLED SERVICEABLE PART USING EMB SRM STANDARD PRACTICES CHAPTER 51.

Part: CROSSBEAM — CORRODED (FUSELAGE)

DURING 2C INSEPCTION TASK 5310-131/132-01I, REVEALED LEFT HAND FLOOR CROSSBEAM TO BE CORRODED. REMOVED CROSSBEAM AND INSTALLED SERVICEABLE CROSSBEAM USING EMB 120 SRM STANDARD PRACTICES CHAPTER 51.

Part: CROSSBEAM — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132-01I, REVEALED RIGHT HAND FLOOR CROSSBEAM TO BE CORRODED. REMOVED CROSSBEAM AND INSTALLED SERVICEABLE CROSSBEAM USING EMB 120 SRM STANDARD PRACTICES CHAPTER 51.

Part: SILL — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132-O1I, REVEALED CORROSION ON LEFT FORWARD SILL TO BE BEYOND LIMITS. REMOVED SILL AND INSTALLED SERVICEABLE SILL USING EMB SRM STANDARD PRACTICES FOR LIKE PART REPLACEMENT.

Part: CROSSBEAM — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132 O1I, FOUND LEFT HAND FLOOR CROSSBEAM AT FRAME 20 TO BE CORRODED. REMOVED CORRODED CROSSBEAM AND INSTALLED SERV PART IAW EMB 120 SRM CHAPTER 51.

Part: BUTTSTRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132-O1I, REVEALED FWD BUTT STRAP TO BE HEAVILY CORRODED. REMOVED CORRODED BUTT STRAP AND INSTALLED SERVICEABLE PART USING EMB SRM STANDARD PRACTICES CHAPTER 51.

Part: ANGLE — CORRODED (FUSELAGE)

WHILE PERFORMING TASK 5320-152-01I, FOUND CORROSION BETWEEN ANGLE AND RECEPTACLE FOR AFT EMERGENCY EXIT. REMOVED ITEMS AND REPLACED WITH SERV ITEMS IAW EMB 120 SRM CHAPTER 51.

Part: ANGLE — CORRODED (FUSELAGE)

WHILE PERFORMING TASK 5320-152-01F, FOUND CORROSION BETWEEN ANGLE AND RECEPTACLE FOR AFT EMERGENCY EXIT. REMOVED ITEMS AND REPLACED WITH SERV ITEMS IAW EMB120 SRM CHAPTER 51.

Part: LAV BASE SUPPORT — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132 O1F, FOUND TOILET BASE SUPPORT STRUCTURE CORRODED. REMOVED CORRODED BASE AND INSTALLED SERV BASE IAW EMB 120 MM.

Part: CROSSBEAM — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132-O1I, FOUND RT CROSSBEAM AT FRAME 16 TO BE CORRODED. REMOVED CORRODED PART AND INSTALLED SERV PART IAW EMB 120 SRM CHAPTER 51.

Part: BUTT STRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132-01I, REVEALED FWD BUTT STRAP TO BE HEAVILY CORRODED. REMOVED CORRODED BUTT STRAP AND INSTALLED SERVICEABLE PART USING EMB SRM STANDARD PRACTICES CHAPTER 51.

Part: INLET DUCT — BIRD STRIKE (LT NACELLE)

ROUTINE INSPECTION FOUND THE LEFT NACELLE, ENGINE OIL COOLER INLET NACA DUCT, TO HAVE BIRDSTRIKE DAMAGE. A BIRDSTRIKE INSPECTION WAS PERFORMED ON THE AIRCRAFT. THE NACA DUCT WAS REPLACED PER AERODESIGN REPORT NR 2170-1, REV. A, DATED 1-14-97.

Part: BRAKE — LOCKED UP (LT MLG)

THE LT MLG INBD BRAKE LOCKED UP DURING TAXI. REPLACED THE LT INBD BRAKE ASSY.

Part: RCCB — OVERHEATED (COCKPIT)

BURNING ODOR COMING FROM PILOTS SIDE PANEL. REPLACED RCCB0217.

Part: CONTROL MODULE — MALFUNCTION (LANDING GEAR)

LANDING GEAR CONTROL HAD TO BE CYCLED 3 TIMES BEFORE GEAR EXTENDED. REPLACED THE LANDING GEAR CONTROL MODULE.

Part: TQ SIG COND — MALFUNCTION (LT ENGINE)

AUTO FEATHER WARNING DURING TAKEOFF. REPLACED THE LT ENGINE TORQUE SIGNAL CONDITIONER.

Part: CONTROL BOX — MALFUNCTION (LANDING GEAR)

WHEN LANDING GEAR SELECTED DOWN, THE INDICATION WAS BOTH DOWN LOCK GREEN AND RED UNSAFE AT THE SAME TIME. REPLACED THE LANDING GEAR CONTROL BOX.

Part: TRIM TAB — DAMAGED (LT ELEVATOR)

ELEVATOR CONTROLS ARE BINDING. FOUND LT ELEVATOR TRIM TAB RUBBING AGAINST TAIL FAIRING, TRIM TAB SHEET METAL WAS DAMAGED. REPLACED THE ELEVATOR TRIM TAB AND CORRECTED THE ALIGNMENT OF TAIL CONE FAIRING.

Part: SOLENOID — FAILED (RT ENGINE)

RT ENGINE POWER LEVER, FLIGHT IDLE STOP SYSTEM, WAS INOP. REPLACED THE RT FLIGHT IDLE STOP SOLENOID.

Part: SOLENOID — FAILED (RT ENGINE)

POWER LEVER, FLIGHT IDLE STOP, CIRCUIT BREAKERS WERE TRIPPED. REPLACED THE RT POWER LEVER FLIGHT IDLE STOP SOLENOID, RESET LT BREAKER.

Part: AIR DISTR — ODOR (COCKPIT)

BURNING ELECTRICAL SMELL IN COCKPIT. COULD NOT DUPLICATE DISCREPANCY, INSPECTED WIRING, PANELS AND OPERATED ALL SYSTEMS.

Part: HEAT EXCHANGER — LEAKING (LT ENGINE)

LEFT ENGINE LEAKING FUEL. REPLACED THE FUEL TO OIL HEAT EXCHANGER.

Part: ROLLERS — WORN (LT TE FLAP)

AFTER TAKEOFF, FLAP DISAGREEMENT WHEN FLAPS SELECTED UP. REPLACED ROLLERS ON LT OUTBD FLAP.

Part: RETRACT MECH — LACK OF LUBE (TE FLAPS)

AFTER TAKEOFF, FLAP DISAGREEMENT WHEN FLAPS SELECTED UP. CLEANED, LUBRICATED FLAP TRACKS AND ROLLERS, ACFT RETURNED TO SERVICE.

Part: PROX SENSOR — DEFECTIVE (ELEVATOR)

TRIM AURAL WARNING SOUNDS WHEN POWER LEVERS ADVANCED. REPLACED THE ELEVATOR TRIM PROXIMITY SENSORS.

Part: ROLLERS — WORN (RT FLAP)

FLAP DISAGREEMENT WARNING AFTER TAKEOFF. REPLACED WORN ROLLERS ON RT OUTBOARD FLAP.

Part: PRESS LINE — FROZEN (BLUE HYD SYST)

RT BLUE HYDRAULIC SYSTEM, LOW RESERVOIR PRESSURE, WARNING LIGHT ILLUMINATED. THAWED FROZEN MOISTURE IN RESERVOIR PRESSURIZATION LINE.

Part: TRACKS — DIRTY (TE FLAPS)

FLAPS DID NOT RETRACT AFTER TAKEOFF. FLAP DISAGREEMENT WARNING. CLEANED FLAP TRACKS AND SYSTEM CHECK NORMAL. ACFT RETURNED TO SERVICE.

Part: ACTUATOR — DEFECTIVE (RT TE FLAP)

FLAP DISAGREEMENT WARNING AFTER TAKEOFF. REPLACED THE RT OTBD FLAP ACTUATOR.

Part: CROSS FEED LIGHT — ILLUMINATED (FUEL SYST)

BOTH FUEL CROSS-FEED LIGHTS ILLUMINATED WITH CROSS-FEED SWITCH IN THE OFF POSITION. DISCREPANCY COULD NOT BE DUPLICATED BY MAINTENANCE, AIRCRAFT WAS RETURNED TO SERVICE.

Part: RELAY — DEFECTIVE (E/E COMP)

DURING TAKEOFF ROLL, AUTOFEATHER SYSTEM DID NOT ARM. REPLACED RELAYS K0039 AND K0161, SYSTEM TEST NORMAL.

Part: FUEL HEATER — LEAKING (LT ENGINE)

FUEL IS LEAKING FROM THE LEFT ENGINE NACELLE. REPLACED LEAKING FUEL HEATER ASSEMBLY ON THE LEFT ENGINE.

Part: ACTUATOR — WORN (LT MLG)

WHEN LANDING GEAR SELECTED UP, THE LT MLG INDICATED INTRANSIT. CYCLED GEAR AND ALL INDICATIONS NORMAL. REPLACED THE LT MLG RETRACT ACTUATOR.

Part: FLAP CONTL UNIT — DEFECTIVE (TE FLAPS)

OUTBD FLAPS WILL NOT RETRACT. REPLACED THE FLAP CONTROL UNIT.

Part: RIGGING — OUT OF ADJUST (RT PROP)

RIGHT PROPELLER WILL NOT FEATHER BY USING THE CONDITION LEVER. ADJUSTED ENGINE RIGGING.

Part: RELAY BOX — DEFECTIVE (LANDING GEAR)

LT MLG INTRANSIT LIGHTS REMAIN ON AFTER GEAR RETRACTION. REPLACED THE LANDING GEAR RELAY BOX.

Part: AUDIO WARNING — DEFECTIVE (E/E BAY)

AURAL TRIM WARNING DURING TAKEOFF. ELEVATOR TRIM WAS CONFIRMED TO BE IN THE TAKEOFF RANGE. REPLACED THE AURAL WARNING UNIT.

Part: TRIM WARNING — MALFUNCTIONED (COCKPIT)

AURAL TRIM WARNING DURING TAKEOFF. RESET CIRCUIT BREAKER, SYSTEM TEST NORMAL. AIRCRAFT RETURNED TO SERVICE.

Part: FUEL HEATER — LEAKING (RT ENGINE)

FUEL LEAKING FROM RT ENGINE NACELLE. REPLACED THE ENGINE FUEL TO OIL HEAT EXCHANGER.

Part: CONTROL BOX — DEFECTIVE (LANDING GEAR)

LANDING GEAR SELECTOR CONTROL COULD NOT BE MOVED TO THE RETREAT POSITION. REPLACED THE LANDING GEAR CONTROL BOX.

Part: CIRCUIT BREAKER — TRIPPED (COCKPIT)

FLIGHT IDLE STOP LOCKOUT SOLENOID CIRCUIT BREAKER TRIPPED. RESET CIRCUIT BREAKER AND SYSTEM TEST NORMAL.

Part: HYD LINE — DAMAGED (RT NACELLE)

HYDRAULIC LEAK, RT ENGINE NACELLE. ENGINE DRIVEN PUMP SUCTION LINE WAS DAMAGED BY CHAFING. C/W A TEMPORARY REPAIR BY SUBSTITUTION OF A FLEX LINE ASSY. AIRCRAFT RETURNED TO SERVICE.

Part: SENSOR — DEFECTIVE (LT MLG)

LANDING GEAR WILL NOT RETRACT. REPLACED DEFECTIVE PROXIMITY SENSOR ON LT MLG UPLOCK.

Part: SUPPORT — CRACKED (LT/RT WING)

THE FOLLOWING P/N WING SKIN SUPPORTS WERE FOUND CRACKED DURING INSPECTION TASK NR 5720-551/651-O1I AT WING RIBS 15 AND 16. THE SKIN SUPPORTS WERE REPAIRED IAW AERO DESIGN REPORT 1327-2, 120-17056-019 (2 EA), 120-17056-017 (2 EA), 120-17056-015 (4 EA), 120-17056-013, 120-17057-006, 120-17057-005, 120-17057-007, 120-17056-011.

Part: SIGNAL COND — DEFECTIVE (LT ENG)

AUTO FEATHER WARNING CAME ON AFTER TAKEOFF. REPLACED THE LT TORQUE SIGNAL CONDITIONER.

Part: BONDING STRAP — BINDING (TE FLAPS)

FLAP DISAGREE WARNING WHENS FLAPS SELECTED UP. FLAP BONDING STRAP WAS INTERFERRING WITH INBD LT FLAP. REPLACED BONDING STRAP.