N255CA

Part: CONTROL PANEL — FAILED · airframe 2,158 hrs · 2,511 cycles

PILOT REPORTED STALL HEAT INOPERATIVE. MAINTENANCE INSPECTED AND FOUND THE LIFT TRANSDUCER HEATING ELEMENT SWITCH AND CONNECTOR MELTED. THE CONTROL PANEL WAS REPLACED WITH NO FURTHER DEFECTS.

Part: BLOWER — FAILED · airframe 1,560 hrs · 1,887 cycles

PILOT REPORTED SMOKE SMELL IN THE COCKPIT ASSOCIATED WITH THE HEATER. MAINTENANCE INVESTIGATED AND CONFIRMED FAULT TO BE HEATER RELATED AND PLACED SYSTEM ON MEL.

Part: HINGE — OUT OF LIMITS (ZONE 300) · airframe 1,539 hrs · 1,861 cycles

DURING SCHEDULED INSPECTION, EXCESSIVE RADIAL END PLAY WAS NOTED IN THE AFT ATTACH BEARINGS (HINGE ASSY.) FOR THE HORIZONTAL STABILIZER PN: 212-55-10-1006-000. THESE ATTACH BEARING ASSEMBLIES WILL BE REMOVED AND REPLACED USING NEW PARTS.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 320 hrs · 399 cycles

THE NLG ATTACH STRUCTURE WAS FOUND TO BE DAMAGED DURING AN INSPECTION INITIATED DUE TO SIMILAR FINDINGS ON OTHER COMPANY AIRCRAFT. THE DAMAGE IS LOCATED AT FWD MOST FUSELAGE BULKHEAD, LWR CENTER SECTION, IN THE AREA CORRESPONDING TO THE NLG MOUNTS. THE STRUCTURE AFT OF NLG BULKHEAD WAS INSPECTED WITH THE FOLLOWING DEFECTS NOTED: THE FWD SECTIONS OF FLOORBOARD SUPPORTS AS THEY ARE RIVETED TO FORWARD-MOST FUSELAGE BULKHEAD ARE CRACKED. THE OEM HAS BEEN NOTIFIED AND A FLEETWIDE INSPECTION HAS BEEN ISSUED FOR ALL COMPANY AIRCRAFT.

Part: CONNECTOR — LOOSE (LANDING GEAR)

LANDING GEAR SELECTOR LOCK DID NOT RELEASE AFTER TAKEOFF. SECURED LOOSE AIR/GROUND SENSOR WIRING CONNECTION (PO316).

Part: SEQUENCE VALVE — LEAKING (RT MLG DOOR)

HYDRAULIC LEAK, RIGHT HAND WHEEL WELL. REPLACED O RING AT DOOR SEQUENCE VALVE.

Part: DOOR — NOT LATCHED (FUEL SERVICE)

DOOR WARNING DURING TAKEOFF. FOUND FUEL SERVICE DOOR OPEN, CLOSED AND LATCHED DOOR.

Part: DOOR — NOT LATCHED (FUEL SYST)

DOOR WARNING DURING TAKEOFF. SINGLE POINT FUEL SERVICE DOOR NOT LATCHED. SECURED DOOR.

Part: STRAP — CORRODED (CABIN)

DURING AIRCRAFT MAINTENANCE, CORROSION WAS FOUND ON THE FUSELAGE FORWARD CABIN FLOOR SUPPORT STRUCTURE CENTER BUTT STRAP. THE BUTT STRAP WAS REPLACED PER AERODESIGN REPORT NR 1671-1, REV A, 1-28-97.

Part: TEE SECTION — CORRODED (CABIN)

DURING AIRCRAFT MAINTENANCE, CORROSION WAS FOUND ON THE FUSELAGE FORWARD CABIN FLOOR SUPPORT STRUCTURE LEFT HAND T-SECTION AT FRAME 16. THE T-SECTION WAS REPLACED PER SRM STANDARD PRACTICES.

Part: TEE SECTION — CORRODED (CABIN)

DURING AIRCRAFT MAINTENANCE, CORROSION WAS FOUND ON THE FUSELAGE FORWARD CABIN FLOOR SUPPORT STRUCTURE RIGHT HAND T-SECTION AT FRAME 16. THE T-SECTION WAS REPLACED PER SRM STANDARD PRACTICES.

Part: BEAM — CORRODED (CABIN)

DURING AIRCRAFT MAINTENANCE, CORROSION WAS FOUND ON THE FUSELAGE FORWARD CABIN FLOOR SUPPORT STRUCTURE CENTER OMEGA BEAM. THE OMEGA BEAM WAS REPAIRED PER AERODESIGN REPORT NR 1957-5, REV IR, 6-23-98.

Part: STRAP — CORRODED (FUSELAGE)

DURING AIRCRAFT MAINTENANCE, CORROSION WAS FOUND ON THE FUSELAGE FORWARD CABIN FLOOR SUPPORT STRUCTURE CENTER BUTT STRAP. THE BUTT-STRAP WAS REPLACED PER SRM STANDARD PRACTICES.

Part: FCU — MALFUNCTION (E/E COMPT)

FLAP AND ADVANCED SWS INDICATIONS ON MAP. REPLACED THE FLAP CONTROL UNIT.

Part: HOSE — LEAKING (RT OIL COOLER)

LOW OIL PRESSURE WARNING ON RIGHT HAND ENGINE INFLIGHT SHUTDOWN. REPLACED OIL COOLER HOSE ASSEMBLY THAT WAS LEAKING DUE TO CHAFING DAMAGE.

Part: SENSOR — DIRTY (LT MLG)

THE LT MLG INTRANSIT LIGHTS REMAINED ON AFTER GEAR RETRACTION. LANDING GEAR WAS CYCLED AND 2ND RETRACTION WAS NORMAL. COULD NOT DUPLICATE DISCREPANCY. CLEANED INDICATION SENSORS AND CONNECTIONS. AIRCRAFT RETURNED TO SERVICE.

Part: SPINNER BULKHEAD — CRACKED (RT PROP)

DURING PREFLIGHT INSPECTION, THE RIGHT PROPELLER SPINNER BULKHEAD WAS FOUND TO BE CRACKED APPROXIMATELY 1.5 INCH ALONG THE BULKHEAD OUTER WALL BEHIND BLADE NR 2. AIRCRAFT WAS FERRIED BACK TO CVG HANGAR AND BULKHEAD REMOVED FOR REPAIR. DAMAGE APPEARS TO BE DUE TO MATERIAL DEFECT, NO EXTERNAL DAMAGE WAS FOUND.

Part: SENSOR — DEFECTIVE (RT MLG)

LANDING GEAR DID NOT EXTEND WHEN SELECTED DOWN. EMERGENCY SYSTEM USED TO LOWER LANDING GEAR. REPLACED DEFECTIVE RT MLG DOWNLOCK PROXIMITY SENSOR.

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: TEE SECTION — CORRODED (FUSELAGE)

DURING 4C INSEPCTION TASK 5320-151-01I, REVEALED RIGHT T-SECTION AT FRAME 28 TO BE CORRODED. REMOVED CORRODED T-SECTION AND INSTALLED SERVICEABLE PART USING EMB SRM STANDARD PRACTICES CHAPTER 51.

Part: FLOORBEAM — CORRODED (FUSELAGE)

DURING 4C INSPECTION TASK 5320-151-01I, REVEALED RIGHT FLOORBEAM AT FRAME 33 TO BE HEAVILY CORRODED. REMOVED CORRODED PART AND INSTALLED SERVICEABLE PART USING EMB SRM STANDARD PRACTICES CHAPTER 51 FOR LIKE TO LIKE PART REPLACEMENT.

Part: ANGLE — CORRODED (FUSELAGE)

DURING 4C INSPECTION TASK 5320-151-01I, REVEALED AFT EMERGENCY EXIT GUIDE PIN FITTINGS TO HAVE CORROSION BETWEEN FITTINGS AND THE EXIT SILL LOWER ATTACHE ANGLE. FURTHER INVESTIGATION REVEALED THAT THERE IS NO PRIMER OR SEALANT BETWEEN OR ON THESE PIECES. REPLACED CORRODED ANGLE WITH SERVICEABLE PART IAW EMB SRM CHAPTER 51.

Part: FITTING — CORRODED (FUSELAGE)

DURING 4C INSPECTION TASK 5320-151-01I, REVEALED AFT EMERGENCY EXIT GUIDE PIN FITTINGS TO HAVE CORROSION BETWEEN THE FITTINGS AND THE EXIT SILL LOWER ATTACH ANGLE. FURTHER INVESTIGATION REVEALED THAT THERE IS NO PRIMER OR SEALANT BETWEEN OR ON THESE PIECES. REPLACED CORRODED FITTINGS WITH SERVICEABLE PARTS. INSTALLED PARTS WITH PRIMER AND SEALANT USING EMB STANDARD SRM PRACTICES CHAPTER 51.

Part: SILL — CORRODED (CARGO COMPT)

DURING 4C INSPECTION TASK 5330-161-01I, REVEALED RIGHT CARGO COMPARTMENT SILL TO BE CORRODED BEYOND LIMITS. REMOVED SILL AND INSTALLED SERVICEABLE SILL USING EMB SRM STANDARD PRACTICES CHAPTER 51.

Part: SOLENOID — FAILED (CABIN)

ON C-CHECK TASK 35-09, THE PASSENGER OXYGEN MASKS AT SEAT 1BC FAILED TO DEPLOY. THE OXYGEN MASK DOOR SOLENOID AT THAT LOCATION WAS REPLACED, SYSTEM TESTS NORMAL.

Part: CONNECTOR — BROKEN (RT MLG)

LANDING GEAR WOULD NOT RETRACT. REPLACED DEFECTIVE WIRING CONNECTOR AT RT MLG UPLOCK.

Part: PITCHLOCK SCREW — DAMAGED (FEATHER STOP TAB)

PROPELLER ASSEMBLY REMOVED FROM AIRCRAFT DUE TO BEING STRUCK BY LAVORATORY CART WHILE STATIC ON AIRCRAFT RAMP. DURING PROPELLER IMPACT INSPECTION ACTUATOR FEATHER STOP TAB WAS FOUND TO BE DISPLACED APPROXIMATELY .125 FEET. ACTUATOR S/N 20383 WAS SUBSEQUENTLY REMOVED FROM THE PROPELLER ASSEMBLY AND THE PITCHLOCK SCREW S/N 49 WAS REMOVED FROM ACTUATOR AND RETURNED TO MANUFACTURER.

Part: ROLLERS — DIRTY (RT LE FLAP)

OUTBOARD FLAPS FAILED TO RETRACT. REPLACED THE ROLLERS ON THE RT OUTBOARD FLAP.

Part: FLAP TRACKS — DIRTY (TE FLAPS)

FLAP DISAGREEMENT AFTER TAKEOFF. CLEANED LEFT OUTBOARD FLAP TRACKS.

Part: FLAP — BENT (LT TE FLAP)

FLAP FAIL WARNING. REPLACED LEFT OUTBOARD FLAP, OPERATIONAL CHECK GOOD.

Part: ROLLER — MALFUNCTIONED (LT TE FLAP)

FLAP DISAGREEMENT UPON FLAP RETRACTION AFTER TAKEOFF. REPLACED LT OUTBOARD FLAP ROLLERS 4 EACH. OPERATIONAL CHECK GOOD.

Part: FUEL DOOR — LOOSE (WING)

DOOR LIGHT ON MAP CAME ON DURING TAKEOFF. RESECURED FUEL DOOR FASTENERS.

Part: STRINGER — CRACKED (RT NACELLE)

INSPECTION REVEALED A CRACK IN THE RIGHT NACELLE LT STRINGER 1. THE STRINGER WAS REPAIRED PER AERODESIGN REPORT NR 2000-1, DATED 8-17-96.

Part: BUTT STRAP — CORRODED (CABIN FLOOR)

INSPECTION REVEALED CORROSION ON THE FORWARD CABIN FLOOR SUPPORT OM26A BEAM BUTT STRAP ON THE LEFT SIDE GALLEY AREA. THE BUTT STRAP WAS REPLACED WITH A NEW PART PER EMB120 5RM STANDARD PRACTICES.

Part: HYD SYST — MOISTURE CONTAM (RIGHT)

RT HYDRAULIC RESERVOIR LOW PRESSURE WARNING ILLUMINATED. DRAINED MOISTURE FROM RESERVOIR, SYSTEM CHECK NORMAL.

Part: OVERHEAT SWITCH — DEFECTIVE (RT WING)

RT BLEED AIR DUCT OVERHEAT WARNING CAME ON DURING FLIGHT. REPLACED DEFECTIVE DUCT OVERHEAT SWITCH.

Part: SIG COND UNIT — MALFUNCTION (RT ENGINE)

AUTO FEATHER SYSTEM WILL NOT TEST OR ARM. REPLACED THE RT ENGINE SIGNAL CONDITIONER UNIT.

Part: PROX SENSOR — DEFECTIVE (ELEV TRIM)

TAKEOFF TRIM AURAL WARNING SOUNDED DURING TAKEOFF. TRIM WAS CONFIRMED IN THE GREEN BAND. REPLACED THE LT ELEVATOR TRIM PROXIMITY SENSOR.

Part: HOSE ASSY — LEAKING (RT ENGINE)

RT ENGINE IS LEAKING FUEL. REPLACED THE MOTIVE FLOW FUEL RETURN HOSE AND FITTING AT THE ENGINE HMU, DUE TO DAMAGED THREADS.

Part: AURAL WARN UNIT — MALFUNCTIONED (AVIONICS)

TAKEOFF AURAL WARNING SOUNDED DURING TAKEOFF ROLL. REPLACED THE AURAL WARNING UNIT.

Part: PUMP HYD — FAILED (RIGHT)

RT ELECTRIC HYDRAULIC PUMP IS INOP. REPLACED THE RT ELECTRIC MOTOR DRIVEN HYDRAULIC PUMP.

Part: VSI — DEFECTIVE (LEFT)

PILOTS VSI TUBE BLANK. REPLACED THE 1VA-81A TA/VS1.

Part: ROLLERS — DEFECTIVE (TE FLAPS)

FLAP DISAGREEMENT WARNING DURING TAKEOFF CLIMB. REPLACED THE OUTBD FLAP SECTION ROLLERS.

Part: POWER WIRE — FAILED (GALLEY)

STRONG SMELL OF ELECTRICAL BURNING IN COCKPIT AREA. FOUND BURNED GALLEY POWER WIRE. SECURED POWER TO GALLEY BY PULLING BREAKERS AND PLACED ON DEFERRED MAINT LIST.

Part: COMPUTER — DEFECTIVE (E/E COMPT)

DURING TAKEOFF ROLL, THE STALL WARNING CAME ON. REPLACED STALL WARNING COMPUTER.

Part: POWER LEVER — WORN (FLIGHT COMPT)

CREW REPORTED, THAT POWER LEVERS WERE NOT EVEN AT FLIGHT IDLE STOP. THE RT POWER LEVER FLIGHT IDLE STOP PIN AND ROLLER WERE FOUND TO BE WORN OVER 50 PERCENT. THE RT POWER LEVER ASSY WAS REPLACED.

Part: TRIM ACTUATOR — BINDING (RT ELEV)

ELEVATOR TRIM IS BINDING. REPLACED THE RT ELEVATOR TRIM ACTUATOR.

Part: ANGLE — CRACKED (VERT STAB)

DURING INSPECTION TASK 5530-324-03I AND 5530-324-02I, VERTICAL STABILIZER TO FUSELAGE ANGLE WAS FOUND TO BE CRACKED. REPLACED ANGLE IAW AERODESIGN REPORT 1446-1 AND EMB SRM.

Part: SWIVEL — LEAKING (LT MLG BRAKE)

HYDRAULIC LEAK, LEFT MLG. REPLACED LEAKING BRAKE LINE SWIVEL.

Part: SWIVEL — LEAKING (LT MLG)

HYDRAULIC LEAK, LEFT MLG. TIGHTENED FITTINGS ON HYDRAULIC SWIVEL.

Part: PROX SENSOR — DEFECTIVE (LT MLG)

LT MLG GREEN SAFE LIGHT IS INOP, AND RED INTRANSIT LIGHT IS ILLUMINATED. REPLACED THE DOWN LOCK PROXIMITY SENSOR.