N179CA

Part: WIRE — FAILED (PROX SENSOR)

TRIM FAIL WARNING DURING TAKEOFF. REPAIRED PROX SENSOR WIRE SPLICE AT ELEVATOR TRIM.

Part: WINDSHIELD — BIRD STRIKE (COCKPIT)

BIRD STRIKE DURING TAKEOFF. C/W BIRD STRIKE INSPECTION, NO DAMAGE FOUND.

Part: ACTUATOR — MALFUNCTIONED (LT TE FLAP)

FLAP CONTROL FAULT. REPLACED THE LEFT HAND OUTBOARD FLAP ACTUATOR.

Part: STRINGER — CRACKED (LT WING)

WHILE PERFORMING A MAINTENANCE SERVICE CHECK, MECHANIC NOTICED SMALL FUEL LEAK ON BOTTOM SKIN OF LEFT WING JUST FORWARD OF AND OUTBOARD OF ACCESS PANEL 522EB. INTERNAL INVESTIGATION REVEALED A CRACK IN STRINGER 10A AT THE RIVET HOLE THAT WAS LEAKING FUEL, SEVEN INCHES OUTBOARD OF RIB NR 8. THE STRINGER WAS REPAIRED PER EMB120 SRM 57-20-03, FIGURE 201, PAGES 201-204 AND EMBRAER REPAIR NR SST-1849/99. AIRCRAFT RETURNED TO SERVICE.

Part: PCU — LEAKING (RUDDER)

RUDDER POWER CONTROL UNIT LEAKING HYDRAULIC FLUID. CHANGED RUDDER POWER CONTROL UNIT.

Part: ANNUNCIATOR — MALFUNCTIONED (COCKPIT)

FLAPS FAIL WARNING. REPLACED THE FLAP ANNUNCIATOR UNIT.

Part: T6 WARNING — ACTIVATED (ENGINE)

ABORTED TAKEOFF DUE TO T6 WARNING. DOWNLOADED DFDR, FOUND ALL PARAMETERS TO BE WITHIN LIMITS PER PRATT P WHITNEY MAINT MANUAL 02-10-00. NO ACTION REQUIRED.

Part: SIGN — INOPERATIVE (ROW 5A)

EMERGENCY EXIT SIGN AT 5A IS INOPERABLE. REPLACED EXIT SIGN.

Part: WIRE — SHORTED (CABIN)

EMERGENCY LIGHTS CIRCUIT BREAKER TRIPS WHEN SYSTEM TESTED. REPAIRED SHORTED WIRING AT F/A LIGHT PANEL.

Part: SELECTOR — MALFUNCTION (TE FLAPS)

FLAP CONTROL FAULT. REPLACED FLAP SELECTOR LEVER.

Part: RETRACT MECH — DIRTY (TE FLAPS)

FLAP DISAGREEMENT WARNING ATER TAKEOFF. CLEANED DIRT FROM FLAP TRUCKS.

Part: BUSHING — OUT OF POSITION (LT MLG)

WHILE PERFORMING LANDING GEAR FREE-FALL CHECK, THE LEFT MAIN LANDING GEAR WOULD NOT GO TO THE LOCKED POSITION WITHOUT EXCEEDING THE MAX PULL LIMITS. FURTHER INVESTIGATION REVEALED THE OUTBOARD BUSHING FOR THE MAIN DRAG AND LOCKING STRUT HINGE PIN TO HAVE MIGRATED FROM THE BORE APPROX .50MM. THE BUSHING APPEARS TO HAVE CAUSED THE SHIMS TO SHIFT AND LIMIT THE DRAG AND LOCKING STRUST MOVEMENT DURING FREE-FALL. REMOVED DRAG AND LOCKING STRUT AND INSTALLED SERVICEABLE DRAG AND LOCKING STRUT IN ACCORDANCE WITH EMB MM CHAPTER 32.

Part: CONNECTOR — LOOSE (RT MLG)

DURING CLIMBOUT FROM MCO WITH GEAR SELECTED UP, RT GEAR RED LIGHT ILLUMINATED. AIRCRAFT RETURNED TO THE FIELD. REINSTALLED RT GEAR A AND B PROXIMITY SENSOR CONNECTOR.

Part: HYD FLUID — CONTAMINATED (RIGHT)

RIGHT HAND HYDRAULIC RESERVOIR LOW PRESSURE WARNING. REMOVED CONDENSATE WATER FROM RESERVOIR.

Part: WIRE — SHORTED (CABIN)

EMERGENCY FLOOR LIGHT SYSTEM CIRCUIT BREAKER TRIPPED. WOULD NOT RESET. REPAIRED SHORTED WIRE NR W272-0009-24.

Part: AUTO PILOT — MALFUNCTIONED (E/E COMPT)

AUTOPILOT AND TRIM FAIL WARNING DURING TAKEOFF. DEFERRED AUTOPILOT SYSTEM. AIRCRAFT RETURNED TO SERVICE.

Part: FLAP ANNUNCIATOR — MALFUNCTIONED (INST PANEL)

FLAP CONTROL FAULT WARNING DURING TAKEOFF. REPLACED THE FLAP ANNUNCIATOR UNIT.

Part: VALVE — MALFUNCTION (LT BLEED SOV)

LEFT HAND BLEED AIR OVERHEAT WARNING ON AFTER TAKEOFF. REPLACED THE LEFT HAND HIGH PRESSURE BLEED AIR SHUT OFF VALVE.

Part: STRAP — CORRODED (CABIN)

ON 2C TASK 151-01Z, THE CABIN FLOOR SUPPORT LT BUTT STRAP WAS FOUND CORRODED. REPLACED PER SRM CHAPT 51 STANDARD PRACTICES.

Part: SILL — CORRODED (CABIN)

ON 2C TASK 5310-132-01I, THE CABIN FLOOR SUPPORT RT SILL WAS FOUND CORRODED. REPLACED PER SRM CHAPT 51 STANDARD PRACTICES.

Part: SUPPORT — CORRODED (CABIN)

ON 2C INSPECTION, THE CABIN AFT RT SIDEWALL SEAT TRACK SUPPORT WAS FOUND CORRODED. REPLACED PER SRM STANDARD PRACTICES. THE SEAT TRACK WAS FOUND CORRODED AND REPLACED, AT WHICH TIME THE SUPPORTING SECTION WAS FOUND CORRODED. NEITHER IS COVERED BY A 2C TASK BUT BOTH WERE REPLACED DURING 2C INSPECTION.

Part: STRAP — CORRODED (CARGO COMPT)

ON 2C TASK 164-01Z, THE CARGO COMPARTMENT AFT RT BUTT STRAP WAS FOUND CORRODED. REPLACED PER SRM STANDARD PRACTICES.

Part: STRAP — CORRODED (CARGO COMPT)

ON 2C TASK 161-01Z, THE CARGO COMPARTMENT LT BUTT STRAP, AT CARGO DOOR OPENING, WAS FOUND CORRODED. REPLACED PER SRM STANDARD PRACTICES.

Part: STRAP — CORRODED (CARGO COMPT)

ON 2C TASK 162-01Z, THE CARGO COMPARTMENT FLOOR SUPPORT FWD RT BUTT STRAP WAS FOUND CORRODED. REPLACED PER SRM STANDARD PRACTICES.

Part: STRAP — CORRODED (CABIN)

ON 2C TASK 5310-132-01I, THE CABIN FLOOR SUPPORT RT BUTT STRAP WAS FOUND CORRODED AND REPLACED PER SRM CHAPT 51 STANDARD PRACTICES.

Part: BEAM — CORRODED (CABIN)

ON 2C TASK 5310-131-91I, THE CABIN FLOOR SUPPORT FWD CENTER OMEGA BEAM WAS FOUND CORRODED AND DAMAGED BY SCREW IMPROPERLY INSTALLED. THE OMEGA BEAM WAS REPAIRED PER AERODESIGN REPORT NR 2181-6, REV IR, 5-19-97.

Part: STRAP — CORRODED (CABIN)

ON 2C TASK 5310-131-01I, THE CABIN FLOOR SUPPORT FWD CENTER BUTT STRAP WAS FOUND CORRODED. REPLACED PER SRM CHAPT 51 STANDARD PRACTICES, AND AERODESIGN REPORT NR 1671-1, REV A, 1-28-97.

Part: CROSSBEAM — CORRODED (CABIN)

ON 2C TASK 152-01Z, THE CABIN FLOOR SUPPORT RT CROSSBEAM WAS FOUND CORRODED. REPLACED PER SRM CHAPT 51 STANDARD PRACTICES.

Part: ANGLE — CORRODED (EMER EXIT CUTOUT)

ON 2C TASK 152-01Z, THE AFT EMERGENCY EXIT CUTOUT LOWER ANGLE WAS FOUND CORRODED. REPLACED PER SRM STANDARD PRACTICES.

Part: STRAP — CORRODED (CABIN)

ON 2C TASK 152-01Z, THE CABIN FLOOR SUPPORT RT BUTT STRAP WAS FOUND CORRODED. REPLACED PER SRM CHAPT 51 STANDARD PRACTICES.

Part: STRAP — CORRODED (CABIN)

ON 2C TASK 5310-131-01I, THE CABIN FLOOR SUPPORT LT BUTT STRAP WAS FOUND CORRODED. REPLACED PER SRM CHAPT 51 STANDARD PRACTICES.

Part: SUPPORT — CORRODED (CABIN)

ON 2C TASK 5310-131-01I, THE CABIN FLOOR SUPPORT LT T-SECTION WAS FOUND CORRODED. REPLACED PER SRM CHAPT 51 STANDARD PRACTICES.

Part: CROSSBEAM — CORRODED (CABIN)

ON 2C TASK 5310-132-01I, THE CABIN FLOOR SUPPORT RT CROSSBEAM WAS FOUND CORRODE. REPLACED PER SRM CHAPT 51 STANDARD PRACTICES.

Part: STRAP — CORRODED (CABIN)

ON 2C TASK 5310-131-01I, THE CABIN FLOOR SUPPORT CENTER BUTT STRAP WAS FOUND CORRODED. REPLACED PER SRM CHAPT 51 STANDARD PRACTICES.

Part: SILL — CORRODED (CABIN)

ON 2C TASK 5310-131-01I, THE CABIN FLOOR SUPPORT LT SILL WAS FOUND CORRODED. REPLACED PER SRM CHAPT 51 STANDARD PRACTICES.

Part: STRAP — CORRODED (CABIN)

ON 2C TASK 152-01Z, THE CABIN FLOOR SUPPORT RT BUTT STRAP WAS FOUND CORRODED. REPLACED PER SRM CHAPT 51 STANDARD PRACTICES.

Part: CROSSBEAM — CORRODED (CABIN)

ON 2C TASK 151-01Z, THE CABIN FLOOR SUPPORT LT CROSSBEAM WAS FOUND CORRODED. REPLACED PER SRM CHAPT 51 STANDARD PRACTICES.

Part: STRAP — CORRODED (CARGO COMPT)

ON 2C TASK 161-01Z, THE CARGO COMPARTMENT FLOOR SUPPORT LT BUTT STRAP WAS FOUND CORRODED. REPLACED PER SRM STANDARD PRACTICES.

Part: LIGHT — BROKEN (CABIN)

FLOOR PATH EMERGENCY LIGHT IS BROKEN AT THE GALLEY AREA. REPLACED THE LIGHT ASSY.

Part: LIGHT — INOPERATIVE (CABIN)

RT FORWARD OVERWING EMERGENCY LIGHT INOPERATIVE. DEFERRED RT FWD OVERWING EMERGENCY LIGHT PER MEL 33-50-01, CAT C.

Part: FIRE MODULE — FAILED (E/E COMPT)

RT ENGINE FIRE WARNING LIGHT ON. REPLACED DEFECTIVE FIRE DETECTION CONTROL MODULE.

Part: AUTOFEATHER SYS — MALFUNCTIONED (RT ENGINE)

DURING APPROACH TO TLH, THE RIGHT HAND ENGINE AUTOFEATHER SYSTEM ACTIVATED. COULD NOT DUPLICATE DISCREPANCY. INSPECTION OF AUTOFEATHER SYSTEM FOUND NO DEFECTS.

Part: BEARING — WORN (PROPELLER)

PROPELLER ASSEMBLY WAS ORIGINALLY REMOVED FOR ENGINE RELATED MAINTENANCE. INSPECTION REVEALED UNEVEN WEAR ON THE BLADE BEARING INSERT. WEAR HAD OCCURED IN AN OVAL FASHION AND INSERT WALL THICKNESS HAD DETERIORATED FROM ORIGINAL .100\ WITH THICKNESS RANGING FROM .069\ TO .090\. BEARINGS WERE REMOVED FROM SERVICE AND REPLACED WITH SERVICEABLE UNITS.

Part: BEARING — WORN (PROPELLER)

PROPELLER ASSEMBLY WAS ORIGINALLY REMOVED FOR ENGINE RELATED MAINTENANCE. INSPECTION REVEALED UNEVEN WEAR ON THE BLADE BEARING INSERT. WEAR HAD OCCURED IN AN OVAL FASHIION AND INSERT WALL THICKNESS HAD DETERIORATED FROM ORIGINAL .100\ WITH THE THICKNESSES RANGING FROM .076\ TO .088\. BEARINGS WERE REMOVED FROM SERVICE AND REPLACED WITH SERVICEABLE UNITS.

Part: BEARING — WORN (PROPELLER)

PROPELLER ASSEMBLY WAS ORIGINALLY REMOVED FOR ENGINE RELATED MAINTENANCE. INSPECTION REVEALED UNEVEN WEAR ON THE BLADE BEARING INSERT. WEAR HAD OCCURED IN AN OVAL FASHION AND INSERT WALL THICKNESS HAD DETEIORATED FROM ORIGINAL .100\ WITH THE THICKNESSES RANGING FROM .073\ TO .086\. BEARINGS WERE REMOVED FROM SERVICE AND REPLACED WITH SERVICEABLE UNITS.

Part: PITCHLOCK SCREW — FAILED (PROP ACTUATOR)

PROPELLER ASSEMBLY WAS ORIGINALLY REMOVED FOR ENGINE RELATED MAINTENANCE. ONCE REMOVED, THE ACTUATOR PITCHLOCK SCREW FEATHER STOP TAB WAS FOUND TO BE DISPLACED APPROXIMATELY .125 INCH. PITCHLOCK SCREW WAS REMOVED FROM SERVICE AND RETURNED TO MANUFACTURER.

Part: AHC 85 — FAILED (E/E COMPT)

COPILOT'S AHRS FAILED. REPLACED THE AHC-85.

Part: ATUATOR — MALFUNCTION (R/HRT TE FLAP)

FLAP DISAGREEMENT WARNING DURING LANDING APPROACH. REPLACED THE RT FLAP OUTBD ACTUATOR.

Part: ACTUATOR — MALFUNCTIONED (RT TE FLAP)

AFTER LANDING, WHEN FLAPS SELECTED UP, THE LT INBD FLAP INDICATED 15 DEGREES AND THE RT INBD FLAP INDICATED 45 DEGREES. COULD NOT DUPLICATE DISCREPANCY. REPLACED THE RT INBD FLAP ACTUATOR FOR TROUBLESHOOTING.

Part: INDICATION — MALFUNCTIONED (LT TE FLAP)

AFTER TOUCHDOWN, FLAP ASYMMETRY WARING. FLAP WERE SET AT 45 DEGREES, LEFT INBD FLAP INDICATED 25 DEGREES. COULD NOT DUPLICATE DISCREPANCY, OPERATIONAL CHECK OF FLAP SYSTEM NORMAL.

Part: DOOR ASSY — BROKEN (COCKPIT FLOOR)

EMERGENCY LANDING GEAR EXTEND COMPARTMENT DOOR HINGE WAS BROKEN. REPAIRED BROKEN HINGE.

Part: BATTERY — DISCHARGED (CABIN)

MIDDLE SECTION OF FLOOR PATH EMERGENCY LIGHTING IS INOPERATIVE. REPLACED EMERGENCY LIGHT BATTERY. PART TOTAL CYCLES, 11,171.

Part: SERVO — DEFECTIVE (RUDDER CONTROLS)

WHEN AUTOPILOT DISENGAGED DURING APPROACH PHASE OF FLIGHT, THE RUDDER CONTROLS JAMMED AND EXCESSIVE FORCE WAS REQUIRED TO MOVE RUDDER CONTROLS. REPLACED DEFECTIVE RUDDER SERVO.

Part: WARNING SYST — ACTIVATED (TE FLAPS)

FLAP CONTROL FAULT WARNING WHEN SELECTED TO 25 DEGREES. RESET FLAP SYSTEM - NO FAULT CODES FOUND IN MEMORY. ACFT RETURNED TO SERVICE.

Part: TRACK — WORN (LT TE FLAP)

FLAP DISAGREEMENT WARNING SHORTLY AFTER TAKEOFF. REPLACED WORN FLAP TRACKS ON LEFT OUTBOARD FLAP.

Part: DEICE LEAD — BROKEN (LT PROP)

LEFT PROPELLER DEICE IS INOP. REPLACED DEICE LEAD WIRE ON LT PROPELLER.

Part: FLAP CONTL UNIT — DEFECTIVE (TE FLAPS)

FLAP CONTROL FAULT WARNING WHEN FLAPS SELECTED TO 15 DEGREES. REPLACED THE FLAP CONTROL UNIT. PART TOTAL CYCLES, 10,658.

Part: TRACKS — DIRTY (TE FLAPS)

FLAP DISAGREEMENT WARNING AFTER TAKEOFF. COULD NOT DUPLICATE - CLEANED FLAP TRACKS AND ROLLERS AND RETURNED TO SERVICE.

Part: RELAY — FAILED (AUTO FEATHER)

AUTO FEATHER AURAL WARNING DURING TAKEOFF. REPLACED THE AUTO FEATHER ARMING RELAY.

Part: FUEL FILTER — DIRTY (LT ENGINE)

LT ENGINE FUEL FILTER BYPASS WARNING CAME ON. REPLACED FUEL FILTER.

Part: COMPUTER — DEFECTIVE (NR 2 STALL WARN)

NR 2 STALL WARNING SYSTEM RED LIGHT IS ON. REPLACED THE NR 2 STALL COMPUTER.

Part: STALL COMPUTER — DEFECTIVE (AVIONICS)

DURING TAKEOFF, STALL AURAL WARNING, STICK SHAKER AND STICK PUSHER ACTIVATED. REPLACED THE STALL COMPUTER.

Part: CONTROL BOX — DEFECTIVE (LANDING GEAR)

LANDING GEAR INDICATION 'A' SYSTEM IS INOP AND CIRCUIT BREAKER IS TRIPPED. REPLACED THE LANDING GEAR CONTROL BOX ASSY.