N196CA

Part: INDICATOR — FAILED (WX RADAR) · airframe 17,766 hrs

DURING FLIGHT THE PILOT REPORTED THE WEATHER RADAR SHUT OFF BY ITSELF ACCOMPANIED BY A BURNED PLASTIC ODOR IN THE COCKPIT FOR A SHORT TIME. THE COMPONENT WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: EXHAUST VALVE — DAMAGED (NR 4 CYLINDER) · airframe 16,304 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 5 CYLINDER) · airframe 15,998 hrs

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

Part: WINDOW FRAME — CRACKED (LT COCKPIT)

PILOTS SIDE WINDOW LOWER STRUCTURAL BEAM IS CRACKED AT LEFT WINDSHIELD AFT BEAM. NORMAL OPS. (K)

Part: ENGINE — OVERTEMP (LEFT) · airframe 28,430 hrs · 33,120 cycles

ON CLIMBOUT (LEFT) T6 RAISED WITH POWER REDUCTION. T6 CONTINUED TO RISE TO THE POINT OF T6 WARNING. T6 FINALLY CAME DOWN TO ABOUT 684 DEGREES, PRODUCING NO TORQUE. DID A PRECAUTIONARY ENGINE SHUTDOWN. RETURNED TO LAX. REMOVED AND REPLACED LEFT ENGINE IAW EMB120 MM 71-00-00.

Part: CONTROL BOX — MALFUNCTIONED (LANDING GEAR) · airframe 28,369 hrs · 33,024 cycles

LEFT LANDING RED LIGHTS REMAIN ON (A & B) WITH GEAR HANDLE SELECTED. INSTALLED SERVICEABLE LANDING GEAR RELAY BOX ASSY, SWUNG LANDING GEAR 35 PLUS TIMES. OPS CHECKS GOOD.

Part: BATTERY — DISCHARGED (CABIN) · airframe 28,304 hrs · 32,904 cycles

DURING TAXI FOR TAKEOFF, FLOOR LEVEL EMERGENCY LIGHTING FROM ROW 6 TO AFT OF AIRCRAFT ILLUMINATED. COULD NOT BE EXTINGUISHED. REPLACED EMERGENCY LIGHT BATTERY AT ROW 8. OPS CHECK GOOD.

Part: STRIKER — OUT OF ADJUST (CARGO DOOR) · airframe 28,129 hrs · 32,616 cycles

AFTER TAKEOFF, CARGO DOOR LIGHT ILLUMINATED, MASTER WARNING DOORS AND DOOR CAPTION ON MAP ILLUMINATED. WARNING DOES NOT OCCUR ON GROUND. RETURNED TO RDD. ADJUSTED CARGO DOOR AFT STRIKER PLATE. OPS CHECK GOOD.

Part: WIRE HARNESS — FAULTY (LT MLG) · airframe 27,799 hrs · 32,136 cycles

WITH GEAR HANDLE DOWN THE LANDING GEAR REMAINED UP AND LOCKED. LEFT THE GEAR HANDLE DOWN AND ON GO-AROUND THE LANDING GEAR CAME DOWN AND LOCKED. REPLACED WIRING HARNESS FOR LEFT MAIN LANDING GEAR PROXIMITY SENSOR. OPS CHECKS GOOD.

Part: BATTERY — DISCHARGED (CABIN) · airframe 27,582 hrs · 31,804 cycles

FORWARD FLOOR EMERGENCY LIGHTS ARE OUT. REMOVED AND REPLACED EMERGENCY LIGHTS BATTERY PACK PER MM 33-50-02. OPS CHECK GOOD.

Part: WIRE HARNESS — MALFUNCTIONED (LT ENGINE) · airframe 27,205 hrs · 31,236 cycles

LEFT EEC FAILED ON TAKEOFF. ABORTED TAKEOFF. REMOVED AND REPLACED LEFT ENGINE UPPER WIRE HARNESS IAW POWER PLANT BUILDUP MANUAL 71-00-00. OPS CHECKED IAW MM 71-00-00. ALL PARAMETERS GOOD. P/N ON 31159-11-01, S/N OFF AA9663.

Part: STRUCTURE — CRACKED (PAX DOOR) · airframe 27,168 hrs · 31,179 cycles

C-CHECK, PAX DOOR LOWER AFT TRACK, CRACK ON DOOR STRUCTURE. PERFORMED REPAIR ON PASSENGER DOOR UNDER LOWER AFT TRACK PER SB 120-052-0034.

Part: FASTENER — LOOSE (FUEL DOOR) · airframe 26,975 hrs · 30,854 cycles

SERVICE DOOR LIGHT ILLUMINATED ON CLIMB THROUGH 10,000 FEET. LIGHT WENT OUT ON DESCENT WHILE SLOWING. RETURNED TO FAT. FOUND 1 CAMLOCK ON INBOARD FUEL SERVICE DOOR LOOSE. RESECURED CAMLOCK AND INSPECTED ALL SERVICE DOORS MICROSWITCHES. NO FAULTS FOUND. WARNING SYSTEM CHECKS GOOD.

Part: UPLOCK SENSOR — DIRTY (RIGHT MLG) · airframe 26,681 hrs · 30,405 cycles

RIGHT 'A' RED GEAR LIGHT DID NOT EXTINGUISH AFTER TAKEOFF. ALL GEAR DOORS REMAINED OPEN WITH GEAR SELECTED IN UP POSITION. CYCLED AS PER QRH.CLEANED AND INSPECTED RIGHT MAIN UPLOCK SENSORS AND SWUNG GEAR 20+ TIMES. NO FAULTS FOUND.

Part: WINDOW POST — CRACKED (COCKPIT) · airframe 3,801 hrs · 5,532 cycles

CRACK FOUND IN RIGHT POST BETWEEN DIRECT VIEW WINDOW AND WINDSHIELD.FABRICATED AND INSTALLED DOUBLER IAW SB120-053-0010/3-18-88.

Part: BATTERY — DISCHARGED (CABIN) · airframe 25,323 hrs · 28,391 cycles

EMERGENCY LIGHTS WILL NOT STAY ON WHEN TURNED ON. REPLACED FORWARD EMERGENCY LIGHT BATTERY. OPS CHECKS GOOD. P/N ON: D366-04-00, S/N ON: 1213, S/N OFF: 349.

Part: FIRE LOOP — DAMAGED (RT ENGINE) · airframe 25,323 hrs · 28,391 cycles

RIGHT DET INOP ENGINE/WW LIGHT ILLUMINATED INFLIGHT. RETURNED TO LAX. INSTALLED SERVICEABLE ENGINE FIRE DETECTION LOOP ON RIGHT ENGINE IAW MM 26-11-00. OPS CHECKS GOOD. S/N ON: 92233, S/N OFF: 80052.

Part: SEQUENCE VALVE — MALFUNCTIONED (MLG) · airframe 25,059 hrs · 27,983 cycles

ON DEPARTURE RETRACTED LANDING GEAR, RIGHT MAIN WOULD NOT RETRACT. BOTH A & B RED LIGHTS ILLUMINATED. CREW IN AIRCRAFT BEHIND US NOTED THE RIGHT GEAR WOULD NOT RETRACT. NOSE/LEFT RETRACTED FINE. RETURNED TO PDX. TROUBLESHOT SYSTEM, FOUND RIGHT GEAR SEQUENCE VALVE OUT OF ADJUSTMENT. ADJUSTED VALVES PER 32-32-04. SWUNG GEAR SEVERAL TIMNES WITH NO FAILURE. TEST FLIGHT FOR GEAR RETRACTION WAS SUCCESSFUL.

Part: ACTUATOR — STUCK (ELEVATOR TRIM) · airframe 24,663 hrs · 27,417 cycles

AT SETTINGS BEYOND 1.0 UNITS NOSE DOWN, ELEVATOR TRIM WHEEL STICKS. THE ELECTRIC TRIM WHEEL ACTUATOR IS INCAPABLE OF OVERCOMING BEING STUCK, BUT IT CAN BE MANUALLY FORCED. NOTICEABLE AT SPEEDS GREATER THAN APPROXIMATELY 250 KIAS. REMOVED MOISTURE AND LUBED ELEVATOR TRIM ACTUATORS IAW EMB MM 27-32-02, OPS CHECKS GOOD. THIS IS A SUPPLEMENT TO SDR 2035 SUBMITTED ON 10/17/00. 11/01/00 - ACTUATOR (P/N 5299) (SN 266) FAILED LEAK TEST, LOAD TEST AND NO LOAD TEST. LEAKAGE OF SEALS CAUSED CORROSION AND BEARINGS TO BE ROUGH AND BINDING. ACTUATOR P/N 5299 S/N RS330D WAS UNABLE TO BE TESTED DUE TO BEING COMPLETELY BOUND UP AND WOULD NOT ROTATE. DISASSEMBLY REVEALED EXTREME CORROSION DUE TO WATER CONTAMINATION.

Part: HARNESS — CHAFED (NH INDICATOR) · airframe 24,312 hrs · 26,955 cycles

LEFT NH GAUGE BOTH ANALOG AND DIGITAL INOP DURING FLIGHT. ANALOG NEEDLE JUMPING BETWEEN 10 - 70 PERCENT AND DIGITAL JUMPING 90 - 150 PERCENT NH. DIVERTED TO PDX FROM RDM. REMOVED AND REPLACED LEFT NH GAUGE IAW 77-11-00. ALSO PERFORMED RESISTANCE CHECK OF WIRING HARNESS BETWEEN P1047-P0305. FOUND SLIGHT CHAFING AT ENTRANCE TO BOTTOM OF NACELLE WHERE HARNESS PASSES THROUGH. APPLIED ANTI CHAF TO HARNESS AS NEEDED. RESISTANCE CHECKS GOOD. ALSO OPS CHECK OF NH GAUGE CHECKS GOOD.(P/N OC2917) (S/N 102) ON, (S/N 176)

Part: UPLOCK — OUT OF ADJUST (RT MLG)

UPON GEAR RETRACTION THE RIGHT MAIN GEAR RED A LIGHT WORLD NOT EXTINGUISH. ALSO HEARD BANGING SOUNDS AND FELT VIBRATION. RETURNED TO FAT. ADJUSTED RIGHT MLG UPLOCK INDICATION PLUNGER SCREW IAW 32-61-01. ALL GEAR SWING CHECKS GOOD.

Part: PIN — BENT (RT MLG DOOR)

RIGHT MAIN FORWARD GEAR DOOR HAS COME UNLATCHED TWO TIMES IN LAST TWO FLIGHTS. STRAIGHTENED LOCK PIN AND FUNCTION APPEARS NORMAL ON GROUND.

Part: LAMP — FAILED (CABIN)

EMERGENCY FLOOR LIGHT AT ROW 9 IS INOPERABLE. REPLACED LAMP.

Part: ACTUATORS — MALFUNCTION (TE FLAPS)

INBOARD FLAPS ASYMMETRY WARNING DURING TAKEOFF. REPLACED THE INBOARD FLAPS ACTUATORS.

Part: MECHANISM — MALFUNCTIONED (TE FLAPS)

FLAP ASYMMETRY, INBOARD FLAPS WOULD NOT DEPLOY. COULD NOT DUPLICATE DISCREPANCY, SYSTEM OPERATIONAL CHECK SATISFACTORY.

Part: SUPPORT — CRACKED (FUSELAGE)

CREW PREFLIGHT INSPECTION FOUND ONE RIVET HEAD BROKEN OFF IN FUSELAGE SKIN, LEFT HAND SIDE, FRAME NR 9, JUST BELOW CAPTAIN'S DV WINDOW. FURTHER INVESTIGATION REVEALED A CRACKED SKIN SUPPORT AT THAT LOCATION. THE SUPPORT WAS REPLACED PER AERODESIGN REPORT NR 660-1, IR, 2-16-93. AIRCRAFT RETURNED TO SERVICE.

Part: ACTUATOR — FAILED (RT TE FLAP)

FLAP CONTROL FAULT WARNING. REPLACED THE RIGHT OUTBOARD FLAP ACTUATOR.

Part: AUTOPILOT — MALFUNCTIONED (E/E COMPT)

AUTO PILOT AND TRIM FAIL WARNINGS DURING TAKEOFF. DEFERRED AUTO PILOT SYSTEM PER MEL.

Part: ANGLE — CRACKED (WING/FUSELAGE)

DURING 2C INSPECTION, TASK 5320-244-02I FOUND WING TO FUSELAGE FAIRING ATTACH ANGLE PART NR 120-31657-002 CRACKED. REPAIRED ANGLE IAW APPROVED AERO-DESIGN REPORT 1226-3 REV A 2-18-95.

Part: SILL — CORRODED (CARGO COMPT)

DURING 2C INSPECTION, TASK 162-01Z, FOUND RIGHT FORWARD CARGO SILL CORRODED BEYOND LIMITS. REPLACED SILL IAW EMB-120-SRM.

Part: SILL — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 151-01Z REVEALED RIGHT SILL TO BE CORRODED. REPLACED SILL USING EMB 120 SRM STANDARD PRACTICES.

Part: BUTTSTRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION, TASK 5310-132-01I, FOUND NR 1 RIGHT SIDE BUTTSTRAP CORRODED BEYOND LIMITS. REPLACED BUTTSTRAP IAW SRM EMB-120.

Part: BUTTSTRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5320-147-03I REVEALED CENTER BUTTSTRAP TO BE CORRODED. REPLACED BUTTSTRAP USING EMB 120 SRM STANDARD PRACTICES.

Part: BUTTSTRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 0 152-01Z, REVEALED LEFT HAND BUTTSTRAP TO BE CORRODED. REPLACED BUTTSTRAP USING EMB SRM STANDARD PRACTICES.

Part: T SECTION — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 141-012 REVEALED T-SECTION AT FRAME 23 TO BE CORRODED. REPLACED T-SECTION USING EMB 120 STANDARD PRACTICES.

Part: CONTROL CABLE — WORN (LT AILERON)

WHILE PERFORMING TASK 5720-581-01I ON LEFT WING, 2C INSPECTION, FOUND BOTH AILERON CABLES WORN BADLY AT NACELLE FAIRLEADS. REPLACED CABLES IAW EMB 120 MM.

Part: CROSSBEAM — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131-O1I REVEALED LEFT FLOOR CROSSBEAM AT FRAME 15 TO BE CORRODED. REPLACED CROSSBEAM USING EMB 120 SRM STANDARD PRACTICES.

Part: T SECTION — CORRODED (FUSELAGE)

DURING 2C INSPECTION, TASK 5310-132-O1I FOUND RIGHT FRAME 16 T-SECTION CORRODED BEYOND LIMITS. REPLACED T-SECTION IAW EMB-120 SRM.

Part: CROSSBEAM — CORRODED (FUSELAGE)

DURING 2C INSPECTION, TASK 5320-142-03I, FOUND RIGHT CROSSBEAM AT FRAME 23 CORRODED BEYOND LIMITS. REPLACED CROSSBEAM IAW EMB 120 SRM.

Part: BUTTSTRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 161-01Z, FOUND LEFT HAND CARGO THRESHOLD BUTTSTRAP CORRODED BEYOND LIMITS. REPLACED BUTTSTRAP USING EMB 120 SRM STANDARD PRACTICES.

Part: SILL — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131-O1I REVEALED RIGHT FLOOR SILL (UNDER LAV) TO HAVE HEAVY CORROSION. REPLACED SILL USING EMB 120 SRM STANDARD PRACTICES.

Part: CABLES — WORN (RT AILERON)

WHILE PERFORMING TASK 5720-681-01I ON RIGHT WING, 2C INSPECTION, FOUND BOTH AILERON CABLES WORN BADLY AT NACELLE FAIR LEADS. REPLACED CABLES IAW EMB 120 MM.

Part: BUTT PLATE — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131-01I REVEALED CENTER BUTT PLATE TO BE CORRODED. REPLACED CENTER BUTT PLATE USING APPROVED AERODESIGN REPORT NR 1671-1.

Part: CROSSBEAM — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 141-01Z REVEALED FLOOR CROSSBEAMS LEFT AT FRAME 20 AND LEFT AT FRAME 23 (BOTH THE SAME PART NUMBER) TO HAVE CORRODED BEYOND LIMITS. REPLACED CROSSBEAMS USING EMB 120 SRM STANDARD PRACTICES.

Part: CROSSBEAM — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 151-01Z REVEALED RIGHT FLOOR CROSSBEAM AT FRAME 33 TO BE CORRODED BEYOND LIMITS. REPLACED CROSSBEAM USING EMB120 SRM STANDARD PRACTICES.

Part: T SECTION — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 141-012 REVEALED LEFT CENTER T-SECTION TO BE CORRODED. REPLACED T-SECTION USING EMB 120 SRM STANDARD PRACTICES.

Part: SILL — CORRODED (CARGO COMPT)

DURING 2C INSPECTION TASK 161-01Z, FOUND LEFT HAND CARGO FLOOR SILL CORRODED BEYOND LIMITS. REPLACED CORRODED SILL IAW EMB 120 SRM.

Part: CROSSBEAM — CORRODED (FUSELAGE)

DURING 2C INSPECTIN TASK 5310-132-01I, FOUND RIGHT CROSSBEAM AT FRAME 16 CORRODED BEYOND LIMITS. REPLACED CROSSBEAM IAW EMB 120 SRM.

Part: SILL — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131-01I REVEALED LEFT SILL (UNDER GALLEY) TO BE CORRODED. REPLACED SILL USING EMB 120 SRM STANDARD PRACTICES.

Part: T SECTION — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131-01I REVEALED LEFT CENTER T-SECTION TO BE CORRODED BEYOND LIMITS. REPLACED T-SECTION USING EMB 120 SRM STANDARD PRACTICES.

Part: SILL — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-141-03I REVEALED LEFT NR 2 SILL TO BE CORRODED. REPLACED SILL USING EMB 120 SRM STANDARD PRACTICES.

Part: BUTTSTRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 161-01Z REVEALED LEFT HAND CARGO BUTTSTRAP TO BE CORRODED. ALSO, FOUND THAT CARGO LINING SCREW HAD BEEN SCREWED INTO STRAP. REPLACED BUTTSTRAP USING EMB SRM STANDARD PRACTICES.

Part: BUTTSTRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131-01I REVEALED LEFT BUTTSTRAP TO BE CORRODED. REPLACED BUTTSTRAP USING EMB SRM STANDARD PRACTICES.

Part: BUTTSTRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131-01I REVEALED CENTER BUTTSTRAP TO BE CORRODED. REPLACED BUTTSTRAP USING EMB SRM STANDARD PRACTICES.

Part: CIRCUIT BREAKER — TRIPPED (AURAL WARNING)

'TAKEOFF TRIM' AURAL WARNING SOUNDED DURING TAKEOFF ROLL. AURAL WARNING CIRCUIT BREAKER WAS TRIPPED. RESET BREAKER AND SYSTEM TEST NORMAL.

Part: BRAKE DISK — BROKEN (LT MLG)

LEFT BRAKE LOCKED UP WHILE TAXIING OUT TO RUNWAY. FOUND BRAKE DISC HAD BROKEN. REMOVED AND REPLACED BRAKE ASSY WITH SERVICEABLE UNIT.

Part: ACTUATOR — MALFUNCTION (LT MLG UPLOCK)

LT MLG DID NOT INDICATE DOWN AND LOCK WHEN GEAR SELECTED DOWN. CONTROL HANDLE CYCLED AND INDICATION WAS NORMAL. REPLACED THE LEFT HAND MLG UPLOCK ACTUATOR.

Part: SENSOR — OVERHEATED (COCKPIT)

CREW SMELLED BURNING RUBBER ODOR AND OBSERVED SMOKE COMING FROM COPILOTS INSTRUMENT PANEL. REPLACED OVERHEATED, IOCE PROTECTION CIRCUIT, CURRENT SENSOR.

Part: DUCT — CRACKED (LT BLEED AIR)

LEFT HAND BLEED AIR DUCT LEAK WARNING ON. REPLACED CRACKED BLEED AIR DUCT IN LEFT HAND WING LEADING EDGE.

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

FLAP CONTROL FAULT MESSAGE, INTERMITTENT DISAGREEMENT AND ASYMMETRY WARNINGS. REPLACED THE FLAP CONTROL UNIT.

Part: INVERTER — FAILED (E/E COMPT)

THE NR 1 INVERTER FAILED AND MOMENTS LATER THE NR 2 FAILED. REPLACED THE NR 1 AND 2 STATIC INVERTERS (S/N 3360 AND 5463).

Part: RCCB — OVERHEATED (COCKPIT)

BURNING ODOR IN COCKPIT. REPLACED GROUND COOLING FAN RCCB.

Part: AIR SPEED IND — INACCURATE (LT COCKPIT)

20 KNOT DIFFERENCE BETWEEN PILOTS AND CO-PILOTS AIRSPEED INDICATORS. REPLACED PILOTS AIR SPEED INDICATOR.

Part: ROLLER — WORN (LT/RT TE FLAPS)

FLAPS RETRACT SLOWLY AND DISAGREE MESSAGE. REPLACED LEFT AND RIGHT INBOARD FLAP ROLLERS, OPERATIONAL CHECK GOOD.

Part: PNEUMATIC LINES — FROZEN (LEFT)

HYDRAULIC LOW PRESS LEFT ILLUMINATED. THAWED AND PURGED PNEUMATIC LINES.

Part: HYD SYSTEM — MOISTURE CONTAM (LT/RT GREEN)

BOTH LOW PRESS RES L/R AND GREEN SYS INDICATORS WENT TO 0 QUANTITY. THAWED OUT PNEUMATIC LINERS AND PURGED MOISTURE FROM SYS, OPERATIONAL CHECK GOOD.

Part: DOOR — NOT CLOSED (RT WING)

SERVICE DOOR WARNING LIGHT ILLUMINATED DURING TAKEOFF. SECURED SINGLE POINT FUEL SERVICE DOOR.

Part: BOLT — BROKEN (RT ENGINE)

NO NP OR TORQUE INDICATION AFTER ENGINE START. PROPELLER WAS NOT ROTATING. AFTER ENGINE SHUT DOWN THE PROPELLER COULD NOT BE TURNED BY HAND. WHEN ENGINE DISASSEMBLED, A BROKEN INTERSTAGE CASE BOLT WAS FOUND TO BE JAMMING THE 1ST STAGE POWER TURBINE DISK. BOLT AND POWER TURBINE WERE REPLACED AND ENGINE RETURNED TO SERVICE.

Part: BRACKET — BROKEN (LT MLG DOOR)

LT MLG AFT GEAR DOOR BRACKET IS BROKEN. REPLACED BRACKET.

Part: CHECK VALVE — LEAKING (RT ENGINE)

FUEL LEAKING FROM RT ENGINE NACELLE. REPLACED THE EPA TANK CHECK VALVE.

Part: ROLLERS — CONTAMINATED (RT TE FLAPS)

AFTER TAKEOFF, FLAP DISAGREEMENT WHEN FLAPS SELECTED UP. FOUND RT WING FLAP ROLLERS CONTAMINATED WITH ANTI-SEIZE COMPOUND. REPLACED ROLLERS.

Part: ROLLERS — WORN (RT TE FLAPS)

AFTER TAKEOFF, FLAP DISAGREEMENT WHEN FLAPS SELECTED UP. REPLACED WORN ROLLERS ON RT WING FLAPS.

Part: SENSOR — DEFECTIVE (LT MLG)

AFTER LANDING GEAR RETRACTED, A RUMBLING SOUND WAS HEARD AS IF GEAR DOORS WERE OPEN. FOUND LT MLG UPLOCK PROXIMITY SENSOR, SYSTEM-A DEFECTIVE. DEFERRED SYSTEM PER EMB SNL 32-015 AND ACFT RETURNED TO SERVICE.

Part: BATTERY — FALSE WARNING (FUSELAGE)

BATTERY AURAL WARNING SOUNDED AFTER TAKEOFF. BATTERY TEMP GAUGE INDICATED NORMAL. REPLACED THE BATTERY.

Part: FLAP TRACKS — DIRTY (TE FLAPS)

FLAP DISAGREEMENT WARNING WHEN FLAPS SELECTED UP AFTER TAKEOFF. CLEANED THE FLAP TRACKS AND ACFT RETURNED TO SERVICE.

Part: ACCUMULATOR — REQUIRED SERVICE (CENTER WING)

DURING TAKEOFF, RECEIVED EMERGENCY PARKING BRAKE LOW PRESSURE WARNING. SERVICED THE EMERGENCY PARKING BRAKE ACCUMULATOR TO CORRECT NITROGEN CHARGE. ACFT RETURNED TO SERVICE.

Part: O-RINGS — LEAKING (LT ENIGNE)

FUEL LEAKING FROM THE LEFT ENGINE NACELLE. REPLACED THE FUEL NOZZLES TRANSFER TUBE O-RINGS.

Part: SHUTOFF VALVE — INOP (LT PACK)

LT COOLING PACK PRESSURE REDUCING SHUTOFF VALVE FAILED TO CLOSE WHEN PACK FAILED. REPLACED THE LT PRESSURE REDUCING SHUTOFF VALVE.

Part: FITTING — LEAKING (RT NACELLE)

FUEL LEAKING FROM RT MLG WHEELWELL AREA. REPAIRED PERMASWAGE FITTING ON MOTIVE FLOW LINE IN RT NACELLE.