N152CA

Part: WARNING SYSTEM — ACTIVATED (SERVICE DOOR)

SERVICE DOOR WARNING DURING TAKEOFF. CLOSED AND SECURED SIGNLE POINT FUEL SERVICE DOOR.

Part: NP INDICATOR — FAILED (RT PROP)

DURING TAKEOFF ROLL, THE RIGHT PROPELLER INDICATED 97.6 PERCENT NP. TAKEOFF WAS ABORTED AND AIRCRAFT RETURNED TO THE GATE. REPLACED THE RIGHT NP INDICATOR.

Part: SIGN — BROKEN (ROW 5)

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

Part: BATTERIES — DISCHARGED (CABIN)

HTS - FLT 5730 - EMERGENCY LIGHTS ARE INOPERABLE. REPLACED THE EMERGENCY BATTERIES. (M)

Part: BATTERY — DISCHARGED (CABIN)

LAN - FLT 5076 - EMERGENCY FLOOR LIGHTING IS INOPERABLE. REPLACED EMERGENCY LIGHTS BATTERIES. (M)

Part: ACTUATOR — FAILED (RT TE FLAP)

FLAP CONTROL FAULT AT 80 KTS ON TAKEOFF. REPLACED RIGHT INBOARD FLAP ACTUATOR.

Part: WARNING — ACTIVATED (TE FLAPS)

FLAP CONTROL FAULT WARNING. COULD NOT DUPLICATE, NO DEFECTS FOUND.

Part: BULB — FAILED (CABIN)

EMERGENCY LIGHT AT SEAT 2A IS INOPERABLE. REPLACED LIGHT BULB.

Part: ACTUATOR — MALFUNCTION (LT TE FLAP)

FLAP CONTROL FAULT DURING APPROACH. REPLACED THE LEFT HAND NACELLE FLAP ACTUATOR.

Part: CONNECTOR — DEFECTIVE (TE FLAPS)

FLAP CONTROL FAULT. REPLACED ACTUATOR WIRNG CONNECTOR JO 365.

Part: BATTERY — DISCHARGED (CABIN)

ROW 1 AND ROW 4 EXIT LIGHTS ARE INOPERABLE. REPLACED EMERGENCY BATTERY.

Part: SIGN — BROKEN (CABIN)

EMERGENCY LIGHT COVER AT 5C IS BROKEN. REPLACED EXIT SIGN.

Part: WARNING — ACTIVATED (TE FLAPS)

FLAP SYSTEM WARNING DURING TAKEOFF. COULD NOT DUPLICATE, SYSTEM TEST NORMAL.

Part: BATTERY — DISCHARGED (CABIN)

FORWARD CABIN EMERGENCY LIGHTING IS INOP. REPLACED EMERGENCY BATTERY.

Part: SIGN — BROKEN (CABIN)

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

Part: DE-ICE BOOT — WORN (RT ENGINE INLET)

RIGHT ENGINE INLET DE-ICE SYSTEM FAILURE DURING CRUISE FLIGHT. REPLACED LEFT AND RIGHT ENGINE INLET DE-ICE BOOTS.

Part: ROLLERS — WORN (TE FLAPS)

FLAP CONTROL FAULT WHEN FLAPS SELECTED FOR LANDING APPROACH. REPLACED THE RIGHT HAND INBOARD FLAP ROLLERS.

Part: ACTUATOR — MALFUNCTION (RT TE FLAP)

FLAP CONTROL FAULT WARNING. REPLACED THE RIGHT HAND NACELLE FLAP ACTUATOR.

Part: PRESS REGULATOR — MALFUNCTION (WING DE-ICE)

LEFT AIR FOIL DE-ICE SYSTEM INOP. REPLACED THE DE-ICE PRESSURE REGULATOR.

Part: BATTERY — DISCHARGED (CABIN)

FORWARD CABIN EMERGENCY LIGHTS ARE INOP. REPLACED EMERGENCY LIGHT BATTERY.

Part: CHANNEL — WORN (LT WING)

LEFT WING FAIRING COMPOSITE HAS SLIGHT DELAMINATION AT EDGE. REPAIRED WING FAIRING IAW SRM.

Part: BATTERY — DISCHARGED (CABIN)

EMERGENCY LIGHTS FAIL AFTER 5 SECONDS OF USE. REPLACED THE EMERGENCY LIGHT BATTERIES (S/N 1236, 810, AND 956).

Part: ROLLERS — WORN (RT TE FLAP)

FLAP DISAGREEMENT AFTER TAKEOFF. REPLACED RT OUTBOARD FLAP ROLLERS.

Part: PITCHLOCK SCREW — MALFUNCTIONED (PROP ASSY)

PROPELLER ASSEMBLY REMOVED FROM AIRCRAFT FOR ACTUATOR AND HUB MAJOR INSPECTION. UPON INITIAL RECEIVING INSPECTION THE FEATHER STOP TAB WAS FOUND DISPLACED .025 INCH. PITCHLOCK SCREW WAS REMOVED FROM ASSEMBLY AND RETURNED TO MANUFACTURER. PART TOTAL CYCLES, 18,787.

Part: CONNECTOR — LOOSE (FLAP CONTL UNIT)

WHEN FLAPS EXTENDED, INBOARD FLAPS REMAINED UP AND OUTBOARD FLAPS WENT FULL DOWN. REPAIRED LOOSE WIRE CONNECTOR AT THE FLAP CONTROL UNIT.

Part: FLAP CONTL UNIT — MALFUNCTION (TE FLAPS)

FLAP CONTROL FAULT WARNING DURING TAXI. REPLACED THE FLAP CONTROL UNIT. PART TOTAL CYCLES, 2,093.

Part: HINGE — BROKEN (LT MLG DOOR)

LT M.L.G. DOORS DO NOT CLOSE PROPERLY. REPLACED BROKEN DOOR HINGE ON LT M.L.G. AFT DOOR.

Part: BUTT STRAP — MISDRILLED (FUSELAGE)

DURING 2C CHECK THE FUSELAGE AFT FLOOR SUPPORT STRUCTURE BUTT STRAP AT CARGO DOOR OPENING WAS FOUND TO HAVE MISDRILLED HOLES. THE BUTT STRAP WAS REPAIRED PER AERODESIGN REPORT NR 2139-1, REV IR, DATED 12-22-96. AIRCRAFT TOTAL CYCLES, 20,051.

Part: BUTT STRAP — CORRODED (FUSELAGE)

DURING 2C CHECK FUSELAGE FWD FLOOR SUPPORT STRUCTURE LT BUTT STRAP FOUND CORRODED. BUTT STRAP WAS REPLACED WITH NEW PART PER SRM CHAPT 51, STANDARD PRACTICES. AIRCRAFT TOTAL CYCLES, 20,051.

Part: SILL — CORRODED (PAX DOOR)

DURING 2C CHECK FUSELAGE CENTER SECTION FLOOR SUPPORT STRUCTURE LT SILL CORRODED. SILL WAS REPAIRED PER AERODESIGN REPORT NR 2140-1, REV IR, DATED 12-22-96. AIRCRAFT TOTAL CYCLES, 20,051.

Part: JOINT SHEET — GOUGED (WING AUX SPAR)

DURING 2C CHECK, INSPECTION REVEALED THE WING AUX SPAR CENTER SECTION JOINT SHEET DAMAGED BY SCREWS THAT ATTACH THE LOWER FAIRING. THE DAMAGE CONSISTS OF A SMALL GOUGE ALONG THE BOTTOM EDGE, ONE ON THE LEFT SIDE AND ONE ON THE RIGHT SIDE OF THE SHEET. THE SHEET WAS REPAIRED PER AERODESIGN REPORT NR 2138-1, REV A., DATED 12-22-96. AIRCRAFT TOTAL CYCLES, 20,051.

Part: BUTT STRAP — CORRODED (FUSELAGE)

DURING 2C CHECK FUSELAGE FWD FLOOR SUPPORT STRUCTURE CENTER BUTT STRAP FOUND CORRODED. REPLACED BUTT STRAP WITH NEW PART PER SRM CHAPT. 51, STANDARD PRACTICES. AIRCRAFT TOTAL CYCLES, 20,051.

Part: BUTT STRAP — CORRODED (FUSELAGE)

DURING 2C CHECK FUSELAGE CENTER SECTION FLOOR SUPPORT RT BUTT STRAP FOUND CORRODED. BUTT STRAP REPLACED WITH NEW PART PER SRM CHAPT. 51, STANDARD PRACTICES. AIRCRAFT TOTAL CYCLES, 20,051.

Part: SILL — CORRODED (PAX DOOR)

DURING 2C CHECK FUSELAGE FWD FLOOR SUPPORT STRUCTURE RT SILL FOUND CORRODED. REPLACED SILL WITH NEW PART PER SRM CHAPT. 51, STANDARD PRACTICES. AIRCRAFT TOTAL CYCLES, 20,051.

Part: SILL — CORRODED (PAX DOOR)

DURING 2C CHECK FUSELAGE CENTER SECTION FLOOR SUPPORT STRUCTURE LT SILL FOUND CORRODED. SILL REPLACED WITH NEW PART PER SRM CHAPT. 51 STANDARD PRACTICES. AIRCRAFT TOTAL CYCLES, 20,051.

Part: SILL — CORRODED (PAX DOOR)

DURING 2C CHECK FUSELAGE CENTER SECTION FLOOR SUPPORT STRUCTURE RT SILL FOUND CORRODED. SILL WAS REPLACED WITH NEW PART PER SRM CHAPT. 51, STANDARD PRACTICES.

Part: BUTT STRAP — CORRODED (FUSELAGE)

DURING 2C CHECK FWD FUSELAGE FLOOR SUPPORT STRUCTURE CENTER BUTT STRAP FOUND CORRODED. BUTT STRAP REPLACED WITH NEW PART PER SRM CHAPT. 51, STANDARD PRACTICES. AIRCRAFT TOTAL CYCLES, 20,051.

Part: SILL — CORRODED (LT PAX DOOR)

DURING 2C CHECK FUSELAGE FWD CABIN FLOOR SUPPORT STRUCTURE LT SILL FOUND CORRODED. SILL WAS REPLACED WITH NEW PART PER SRM 51-40, STANDARD PRACTICES. AIRCRAFT TOTAL CYCLES, 20,051.

Part: STRINGER — CORRODED (FUSELAGE)

DURING 2C CHECK INSPECTION FOUND CORROSION ON FUSELAGE STRINGER 19L BETWEEN FRAMES 19 AND 20. STRINGER 19L WAS REPAIRED PER AERODESIGN REPORT NR 1990-2, REV.IR DATED 9-15-96.

Part: HYDRAULIC HOSE — FAILED (LT MLG)

HYDRAULIC FLUID LEAKING FROM LT LANDING GEAR AREA. REPLACED LEAKING LANDING GEAR ACTUATOR HYDRAULIC HOSE.

Part: FLAP CONTL UNIT — MALFUNCTION (E/E BAY)

FLAP CONTROL FAULT WARNING, INBD FLAPS ARE FAILED. REPLACED THE FLAP CONTROL UNIT.

Part: FLAP SELECTOR — MALFUNCTION (INST PANEL)

FLAP CONTROL FAULT WARNING. REPLACED THE FLAP SELECTOR UNIT.

Part: BUTT STRAP — CORRODED (FUSELAGE)

FOUND FUSELAGE FLOOR SUPPORT STRUCTURE FORWARD LT BUTT STRAP CORRODED. REMOVED CORRODED BUTT STRAP AND INSTALLED NEW PART PER EMB120 SRM STANDARD PRACTICES, CH 51-40-02. AIRCRAFT TOTAL CYCLES, 19,871.

Part: T SECTION — CORRODED (FUSELAGE)

FOUND FUSELAGE FLOOR SUPPORT STRUCTURE T-SECTION CORRODED IN FWD CABIN AREA. REMOVED CORRODED T-SECTION AND INSTALLED NEW PART PER REPORT NR 2057-1, REV. IR, DATED 10-6-96. AIRCRAFT TOTAL CYCLES, 19,871.

Part: BATTERY — DISCHARGED (CABIN)

AFT SECTION OF CABIN EMERGENCY LIGHTING IS INOPERATIVE. REPLACED EMERGENCY LIGHTING BATTERY. PART TOTAL CYCLES, 13,088.

Part: CIRCUIT BREAKER — DAMAGED (COCKPIT)

EMERGENCY BUS LOST POWER, CONTROL BUS INOP, RT ENGINE INSTRUMENTS INOP, COPILOTS EFIS AND COMM RADIO INOP, A LANDING GEAR INDICATION INOP. FOUND BUS BAR CONNECTION TO CIRCUIT BREAKER 0470 LOOSE WITH HEAT DAMAGE TO BREAKER. REPLACED C/B 0470 AND ATTACHING HARDWARE.

Part: FLAP WARNING — ACTIVATED (TE FLAP SYST)

FLAP CONTROL FAULT WARNING AFTER LANDING. INSPECTED FLAP SYSTEM AND FOUND TO OPERATE NORMALLY. COULD NOT DUPLICATE DISCREPANCY.

Part: SKIN — CORRODED (FRAME 21)

DURING AN E9 INSPECTION, FOUND CORROSION ON FUSELAGE LOWER SKIN AT FRAME 21 (FS 6842.6). AT 7 O'CLOCK POSITION, AIRCRAFT HAD A PREVIOUS REPAIR ON FRAME 21 FOR CORROSION AT THE 6 O'CLOCK POSITION. REMOVED PREVIOUS REPAIR DOUBLER, CUT OUT NEW DAMAGED AREA OF FUSELAGE, FABRICATED FILLER AND DOUBLER AS PER SRM 53-00-01.

Part: ROLLERS — WORN (RT TE FLAP)

AFTER TAKEOFF, FLAP DISAGREEMENT WARNING WHEN FLAPS SELECTED UP. REPLACED WORN ROLLERS AT RT OUTBD FLAP.

Part: AURAL WARN UNIT — DEFECTIVE (AVIONICS)

AURAL WARNING DURING TAKEOFF - TRIM FAIL AFTER TAKEOFF. REPLACED THE AURAL WARNING UNIT.

Part: WARNING — ACTIVATED (TE FLAPS)

FLAP CONTROL FAULT WARNING. RE-RACKED FLAP CONTROL UNIT. COULD NOT DUPLICATE PROBLEM.

Part: SUPPORT — CRACKED (LT/RT WINGS)

THE FOLLOWING P/N WING SKIN SUPPORTS WERE FOUND CRACKED DURING INSPECTION TASK 5720-551/651-01I. THE SKIN SUPPORTS WERE REPAIRED IAW AERODESIGN REPORT 1327-2 P/N: 120-17056-019, 2 EA; 120-17056-017, 2 EA; 120-17056-015, 4 EA; 120-17056-013, 1 EA; 120-17057-006, 1 EA; 120-17057-007, 2 EA; 120-17056-007, 3 EA; 120-17057-005, 1 EA.

Part: COUPLER — BROKEN (RT ACM)

RT DUCT LEAK WARNING DURING TAXI. REPLACED BROKEN CLAMP ON RT ACM.

Part: RIB — CRACKED (RT TE FLAP)

DURING INSPECTION, FOUND RIGHT OUTBOARD FLAP END RIB TO HAVE A SMALL PART OF UPPER FRAME OF END RIB TO BE MISSING. REMOVE END RIB AND MANUFACTURED NEW END RIB OUT OF .040 202V. INSTALLED WITH CR 3212-4 FASTENERS. ALL WORK DONE IAW AERODESIGN REPORT NR 1490-1 DATED 3-30-95.

Part: SKIN — CORRODED (FS 6842.6)

DURING EXTERNAL INSPECTION LOWER FUSELAGE STA FS 6842.6 SHOWED SIGNS OF CORROSION. FURTHER INSPECTION, REVEALED FUSELAGE SKIN (P/N 120-19230-001), TO HAVE CORROSION BETWEEN SKIN AND TITANIUM STRAP (P/N 120-22409-001). AIRCRAFT WAS REPAIRED IN ACCORDANCE WITH EMBRAER REPAIR EST-061/95 AND AERODESIGN AIRCRAFT ENGINEERING REPORT 1437-1.

Part: VALVE — LEAKING (WING CENTER)

RT DUCT LEAK WARNING LIGHT ILLUMINATED. REPLACED THE AIR FOIL DE-ICE REGULATING VALVE.