N462CA

Part: BRAKE ASSY · airframe 23,187 hrs · 25,267 cycles

FLIGHT 5064 DURING LANDING ALL 4 MLG TIRES BLEW OUT. REPLACED 4 MLG BRAKE ASSY, 4 MLG WHEEL AND TIRES. REPLACED BOTH BRAKE CONTROL VALVES FOR PREVENTIVE MAINT. & ANTI SKID CONTROL BOX - CAUSE OF LOCK UP UNDETERMINED.

Part: BRACKET — CRACKED (FWD RIGHT WINGBO) · airframe 22,858 hrs · 17,079 cycles

DUIRNG A 2,000 FLIGHT CYCLE INSPECTION, THE FUEL SHUT-OFF SUPPORT BRACKET (P/N 120-24373-002) ON THE RIGHT WING BOX FORWARD SIDE AFT OF FRAME 10 WAS FOUND TO BE CRACKED.THE CRACKED BRACKET (P/N 120-24373-002) WAS REMOVED FROM THE AIRCRAFT, REPAIRED AND RE-INSTALLED. WORK WAS ACCOMPLISHED IN ACCORDANCE WITH EMB 120 SRM 514-70-05 AND AERODESIGN REPORT #4249-1, REV IR DATED 4-13-02.

Part: GAUGE — MALFUNCTIONED (INST. PANEL) · airframe 22,118 hrs · 23,995 cycles

FLIGHT 5070 R/H ENGINE TORQUE GAUGE FAILED DURING T/O.REPLACED THE TORQUE INDICATOR.

Part: LIGHT — BROKEN · airframe 21,354 hrs · 23,073 cycles

EMERGENCY LIGHT AT ROW 5 IS BROKEN.REPLACED LIGHT ASSY.

Part: CHANNEL — CRACKED (PAX DOOR) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 811-02Z, THE PAX DOOR 3RD U-CHANNEL WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: FRAME — GOUGED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 163-01Z, THE FUSELAGE FRAME 46A WAS FOUND TO BE GOUGED BY AN INTERIOR LINING SCREW AT FLOOR LEVEL ON THE LEFT SIDE. THE FRAME WAS REPAIRED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES AND AERODESIGN REPORT 2400=5, REV IR, 3-5-01.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 121-01Z, THE FUSELAGE LT FLOOR PROP AT FRAME 13 WAS FOUND CRACKED. THE PART WAS REPAIRED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES AND AERODESIGN REPORT 3647-1, REV IR, 5-3-00.

Part: CROSSBEAM — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 131-01Z, THE FUSELAGE LT FLOOR CROSSBEAM AT FRAME 15 WAS FOUND CORRODED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: CROSSBEAM — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 132-01Z, THE FUSELAGE RT FLOOR CROSSBEAM AT FRAME 16 WAS FOUND CORRODED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 232-01Z, THE FUSELAGE RT SKIN SUPPORT AT FRAME 13A, STRINGER 14R WAS FOUND CRACKED. THE PART WAS REPAIRED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES AND AERODESIGN REPORT 3653-2, REV IR, 11-7-00.

Part: SUPPORT — CRACKED (LT WING) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 5720-552-01I, THE LT WING SUPPER SKIN SUPPORT AT RIB 20, BETWEEN STRINGERS 2A AND 3A, WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 131/132-01Z, THE FUSELAGE CENTER FORWARD FLOORBEAM BUTTSTRAP WAS FOUND CORRODED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 131/132-01Z, THE FUSELAGE CENTER FORWARD FLOORBEAM BUTTSTRAP WAS FOUND CORRODED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES AND AERODESIGN REPORT 1671-1, REV A, 1-28-97.

Part: STIFFENER — CRACKED (NACELLE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 5410-442-04I, THE RT NACELLE FRAME 10 STIFFENER ANGLE, WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 142-01Z, THE RT FLOORBEAM BUTTSTRAP WAS FOUND CORRODED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES AND AERODESIGN REPORT 2174-1, REV IR, 1-15-97.

Part: BEAM — CRACKED (PAX DOOR) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 811-02Z, THE PAX DOOR AFT LATERAL BEAM WAS FOUND CRACKED. THE PART WAS REPAIRED IN ACCORDANCE WITH EMB-120 SRM 52-10-02, FIGURE 201.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 141-01Z, THE FUSELAGE LT FLOORBEAM BUTT STRAP WAS FOUND CORRODED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES AND AERODESIGN REPORT 2174-1, REV IR, 1-15-97.

Part: SKIN — GOUGED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2 YEAR CORROSION CHECK TASK 5310-132-CO1E, THE FUSELAGE LOWER SKIN WAS FOUND TO BE GOUGED JUST BELOW THE LAV DUMP VALVE DOUBLER. THE SKIN WAS REPAIRED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES AND EMBRAER REPAIR FAX GST-0738/01.

Part: SUPPORT — CRACKED (LT WING) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 5720-522-011, THE LT WING LOWER SKIN SUPPORT AT RIB 8, AND STRINGER 10, WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES AND AERODESIGN REPORT 3813-1, REV IR, 11-5-00.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 261-01Z, THE FUSELAGE LT SKIN SUPPORT AT FRAME 40, BETWEEN STRINGERS 3L AND 4L, WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: SUPPORT — CRACKED (COCKPIT) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 5310-221-05I, THE FUSELAGE LT SKIN SUPPORT BEHIND AND ABOVE THE CAPTAIN''S DV WINDOW, BETWEEN FRAMES 12A AND 13, WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: SUPPORT — CRACKED (LT WING) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 5720-561-01I, THE LT WING UPPER SUPPORT AT RIB 23, BETWEEN STRINGERS 2A AND 3A, WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: SUPPORT — CRACKED (LT WING) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 5720-561-01I, THE LT WING UPPER SKIN SUPPORT AT RIB 23, BETWEEN STRINGER 5A AND REAR SPAR, WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: SILL — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 132-01Z, THE FUSELAGE RT FORWARD FLOORBEAM SILL WAS FOUND CORRODED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 131-01Z, THE FUSELAGE LT FORWARD FLOORBEAM BUTTSTRAP WAS FOUND CORRODED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 131-01Z, THE FUSELAGE LT FLOORBEAM T-SECTION AT FRAME 16 WAS FOUND CORRODED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: SUPPORT — CRACKED (LT WING) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 5720-552-01I, THE LT WING UPPER SUPPORT AT RIB 20, BETWEEN STRINGERS 3A AND 4A, WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRCTICES.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 131/132-01Z, THE FUSELAGE CENTER FORWARD FLOOR OMEGA BEAM WAS FOUND CORRODED. THE PART WAS REPAIRED IN ACCORDANCE WITH EMB-120 STANDARD PRACTICES AND AERODESIGN REPORT 2181-12, REV IR, 3-4-01.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 152-01Z, THE FUSELAGE RT FLOOR T-SECTION AT FRAME 36 WAS FOUND CORRODED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 122-01Z, THE FUSELAGE RT FLOOR PROP AT FRAME 13 WAS FOUND CRACKED. THE PART WAS REPAIRED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES AND AERODESIGN REPORT NR 3647-1, REV IR, 5-3-00.

Part: CHANNEL — CRACKED (PAX DOOR) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 811-02Z, THE PAX DOOR 1ST U-CHANNEL WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: SUPPORT — CRACKED (LT WING) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 5720-561-01I, THE LT WING UPPER SKIN SUPPORT AT RIB 23, BETWEEN STRINGERS 3A AND 4A, WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: CHANNEL — CRACKED (PAX DOOR) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 811-02Z, THE PAX DOOR AFT U-CHANNEL WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: SILL — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 131-01Z, THE FUSELAGE LT FORWARD FLOOR BEAM SILL WAS FOUND CORRODED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 132-01Z, THE FUSELAGE RT FORWARD FLOOR BEAM BUTTSTRAP WAS FOUND CORRODED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 5310-222-05I, THE RT FUSELAGE SKIN SUPPORT AT FRAME 9, WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES AND AERODESIGN REPORT 660-1, REV IR, 2-16-93.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 5310-221-05I, THE LT FUSELAGE SKIN SUPPORT AT FRAME 9, WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES AND AERODESIGN REPORT 660-1, REV IR, 2-16-93.

Part: STRINGER — CRACKED (LT NACELLE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 5410-432-04I, THE LEFT NACELLE OUTBOARD STRINGER NR 1 WAS FOUND TO BE CRACKED JUST AFT OF NACELLE FRAME 10. THE STRINGER WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 162-01Z, THE FORWARD RT FLOORBEAM BUTTSTRAP IN THE CARGO COMPARTMENT, WAS FOUND CORRODED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: SUPPORT — CRACKED (COCKPIT) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 5310-221-05I, THE FUSELAGE LT SKIN SUPPORT BEHIND THE CAPTAIN''S DV WINDOW, BETWEEN FRAMES 12A AND 13, WAS FOUND CRCKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: SUPPORT — CRACKED (LT WING) · airframe 21,213 hrs · 22,886 cycles

DURING 2C CHECK TASK 5720-552-01I, THE LT WING UPPER SKIN SUPPORT AT RIB 21, BETWEEN FR ON SPAR AND STRINGERS 2A, WAS FOUND CRACKED. THE PART WAS REPLACED IN ACCORDANCE WITH EMB-120 SRM STANDARD PRACTICES.

Part: RELAY — MALFUNCTIONED (E/E BAY) · airframe 20,890 hrs · 22,375 cycles

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

Part: RELAY — INOPERATIVE (CABIN)

EMERGENCY LIGHTS WILL NOT ARM. REPLACED RELAY KO201.

Part: SIGN — MISSING (PASSENGER DOOR)

EMERGENCY EXIT SIGN ON BULKHEAD AT CABIN DOOR WAS MISSING. REPLACED EXIT SIGN ASSY.

Part: WINDSHIELD — SHATTERED (LEFT COCKPIT)

PILOTS WINDSHIELD SHATTERED. REPLACED WINDSHIELD.

Part: FUEL LINE — CRACKED (RT WING)

WHILE REPLACING LEAKING RIVET IN RIGHT OUTBOARD WING, FOUND RE-FUEL LINE (P/N 120-08728-009) CRACKED AT BEND RADIUS. REPLACED CRACKED FUEL LINE.

Part: BATTERY — DISCHARGED (CABIN)

EMERGENCY LIGHTS INOPERABLE. REPLACED BATTERY.

Part: LAMP — FAILED (CABIN)

THREE EMERGENCY LIGHTS ARE INOP ROW 6 AND 7. REPLACED INOP LAMPS.

Part: BATTERY — DISCHARGED (CABIN)

EMERGENCY LIGHTS AFT OF ROW 6 ARE INOPERABLE. REPLACED EMERGENCY LIGHTS BATTERY.

Part: HARNESS — DAMAGED (LT MLG)

WEIGHT ON WHEELS SAFETY LATCH ON LANDING GEAR CONTROL DID NOT RELEASE AFTER TAKEOFF. REPLACED THE LEFT MLG WEIGHT ON WHEELS SWITCH HARNESS.

Part: BATTERY — DISCHARGED (CABIN)

EMERGENCY LIGHTS ARE INOP. REPLACED EMERGENCY BATTERY PACKS.

Part: SELECTOR — MALFUNCTION (TE FLAPS)

FLAP CONTROL FAULT WARNING. REPLACED THE FLAP CONTROL HANDLE.

Part: CROSSBEAM — CORRODED (FUSELAGE)

WHILE PERFORMING 2C INSPECTION TASK 5310-131-01I, FOUND LEFT CROSSBEAM AT FRAME 13 TO BE CORRODED. REMOVED CORRODED CROSSBEAM AND INSTALLED SERVICEABLE CROSSBEAM OF SAME PART NUMBER USING FASTENERS OF SAME PART NUMBER IAW SRM CHAPTER 51.

Part: STRINGER — CORRODED (FUSELAGE)

WHILE PERFORMING 2C TASK 5310-131-01I, FOUND FUSELAGE STRINGER 18L TO BE CORRODED BETWEEN FUSELAGE FRAMES 14 AND 15. REMOVED CORRODED PORTION OF STRINGER AND SPLICED IN SERVICEABLE STRINGER SECTION AS PER EMB120 SRM CHAPTER 53-10-03 PAGES 201-209.

Part: BUTT STRAP — CORRODED (FUSELAGE)

WHILE PERFORMING 2C INSPECTION TASK 5310-141-03I, FOUND RIGHT BUTT STRAP TO HAVE HEAVY SURFACE CORROSION. REMOVED CORRODED BUTT STRAP AND INSTALLED SERVICABLE BUTT STRAP OF SAME PART NUMBER USING SAME PART NUMBER FASTNERS IAW SRM CHAPTER 51.

Part: SILL — CORRODED (FUSELAGE)

ON 2C INSPECTION TASK 5310-142-01I, REVEALED RIGHT FORWARD SILL TO BE HEAVILY CORRODED. REMOVED CORRODED SILL AND INSTALLED SERVICEABLE SILL USING EMB SRM STANDARD PRACTICES, CHAPTER 51.

Part: TEE SECTION — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131-00I, REVEALED RIGHT T-SECTION TO BE CORRODED AT FRAME 20. REMOVED AND INSTALLED SERVICEABLE T-SECTION USING EMB 120 SRM STANDARD PRACTICES CHAPTER 51.

Part: SUPPORT — CORRODED (FUSELAGE)

WHILE PERFORMING 2C INSPECTION TASK 5310-131-01I, FOUND FRAME 14 SKIN SUPPORT TO BE CORRODED. REMOVED CORRODED SKIN SUPPORT AND INSTALLED SERVICEABLE SUPPORT OF SAME PART NUMBER USING SAME PART NUMBER RIVETS AS ORIGINAL IAW SRM CHAPTER 51.

Part: BUTT PLATE — CORRODED (FUSELAGE)

ON 2C INSPECTION TASK 5310-131-01I, REVEALED LEFT BUTT PLATE TO BE CORRODED. REMOVED CORRODED PART AND INSTALLED SERVICEABLE PART USING EMB SRM STANDARD PRACTICES AND AERODESIGN REPORT NR 1671-2.

Part: STRINGER — CORRODED (FUSELAGE)

WHILE PERFORMING 2C TASK 5310-131-01I, FOUND FUSELAGE STRINGER 19L TO BE CORRODED BETWEEN FUSELAGE FRAME 13 AND 15.\NREMOVED CORRODED PORTION OF STRINGER AND SPLICED IN SERVICABLE STRINGER SECTION AS PER EMB 120 SRM CHAPTER 53-10-03 PAGES 201-209.

Part: FITTING — CORRODED (EMERGENCY EXIT)

DURING 4C INSPECTION TASK 5320-254-01I, REVEALED LIGHT SURFACE CORROSION BETWEEN AFT EMERGENCY EXIT GUIDE PIN RECEPTICALS AND THE LOWER FRAME OF EXIT CUTOUT. THESE RECEPTICALS WERE ORIGINALLY INSTALLED WITHOUT PRIMER OR SEALANT BETWEEN THEM AND THE MATING SURFACE. APPLIED PRIMER TO RECEPTICAL AND MATING SURFACE OF FRAME USING EMB SRM STANDARD PREACTICE, CHAPTER 51.

Part: BUTT STRAP — CORRODED (FUSELAGE)

ON 2C INSPECTION TASK 5310-131-01I, REVEALED LEFT BUTT STRAP TO BE CORRODED. REMOVED DAMAGED PART AND INSTALLED SERVICEABLE PART USING EMB SRM STANDARD PRACTICES CHAPTER 51.

Part: CHANNEL — CORRODED (FUSELAGE)

WHILE PERFORMING 2C INSPECTION TASK 5210-131-01I, FOUND CHANNEL BELOW PAX DOOR SILL JUST AFT OF FUSELAGE FRAME 13A TO HAVE HEAVY CORROSION ON LOWER FLANGE. REMOVED CORRODED PART AND INSTALLED SERVICEABLE CHANNEL OF SAME PART NUMBER, USING SAME PART NUMBER FASTENERS IAW SRM CHAPTER 51.

Part: SILL — CORRODED (FUSELAGE)

ON 2C INSPECTION TASK 5310-131-01I, REVEALED PAX DOOR LOWER SILL TO BE HEAVILY CORRODED. REMOVED PART AND INSTALLED SERVICEABLE PART AS PER EMB 120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: TEE SECTION — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131-01I, REVEALED RIGHT T-SECTION AT FRAME 16 TO BE CORRODED. REMOVED PART AND INSTALLED SERVICEABLE PART USING EMB 120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: CROSSBEAM — CORRODED (FUSELAGE FR 16)

DURING 2C INSPECTION TASK 5310-131-00I, REVEALED RIGHT FLOOR CROSSBEAM AT FRAME 16 TO BE CORRODED. REMOVED CROSSBEAM AND INSTALLED SERVICEABLE PART USING EMB 120 SRM STANDARD PRACTICES CHAPTER 51.

Part: SKIN — GOUGED (CARGO DOOR)

WHILE PERFORMING 2C INSPECTION TASK 5310-131-01I, FOUND CARGO DOOR SKIN TO HAVE GOUGES IN IT AT UPPER EDGE. REPAIRED SKIN USING EMB SRM REPAIR SHOWN IN CHAPTER 53-30-01 PAGES 201-203.

Part: DOOR — NOT LATCHED (RT WING)

SERVICE DOOR WARNING ON AFTER TAKEOFF. FOUND FUEL SERVICE DOOR OPEN. CLOSED AND LATCHED DOOR.

Part: SENSOR — MALFUNCTIONED (ELEVATOR)

TRIM AURAL WARNING SOUNDED DURING TAKEOFF ROLL. REPLACED ELEVATOR TRIM PROXIMITY SENSOR.

Part: RELAY BOX — FAILED (LANDING GEAR)

LANDING GEAR DID NOT EXTEND WHEN SELECTED DOWN FOR LANDING. ALTERNATE EXTENSION SYSTEM WAS USED. REPLACED THE LANDING GEAR RELAY BOX. PART TOTAL CYCLES, 18,624.

Part: WIRE — DEFECTIVE (ELEVATOR TRIM)

'TAKE OFF TRIM' AURAL WARNING. REPAIRED DEFECTIVE WIRING AT THE ELEVATOR TRIM PROXIMITY SENSORS.

Part: FLAP ROLLERS — WORN (LT TE FLAP)

FLAP DISAGREEMENT WARNING AFTER DEPARTURE WHEN FLAPS SELECTED FROM 15 DEGREES TO 0 DEGREES. REPLACED LEFT OUTBOARD FLAP TRACK ROLLERS, OPERATIONAL CHECK GOOD.

Part: PITCHLOCK SCREW — FAILED (PROP ACTUATOR)

PROPELLER ASSEMBLY WAS ORIGINALLY REMOVED FOR EXCESSIVE VIBRATION. UPON DISASSEMBLY AND VISUAL INSPECTION, ACTUATOR (S/N 880601) WAS FOUND UNSERVICEABLE DUE TO THE FEATHER STOP TAB ON THE PITCHLOCK SCREW BEING DISPLACED APPROXIMATELY .5 IN FROM ORIGINAL POSITION.

Part: BEARING — WORN (PROP BLADE)

PROPELLER ASSEMBLY WAS REMOVED FOR EXCESSIVE VIBRATION. DURING DISASSEMBLY AND INSPECTION, IT WAS DETERMINED THAT THE VIBRATION WAS DUE TO THE UNEVEN WEAR OF THE BEARING INSERT. INSERT HAD DETERIORATED FROM .100\ TO .0875\ AT THE THINEST WALL TO .0995\ AT THE THICKEST WALL WEARING IN AN OVAL FASHION. BLADE AND BEARING WERE REMOVED FROM SERVICE AND REPLACED WITH SERVICABLE UNITS.

Part: BEARING — WORN (PROP BLADE)

PROPELLER ASSEMBLY WAS REMOVED FOR EXCESSIVE VIBRATION. DURING DISASSEMBLY AND INSPECTION, IT WAS DETERMINED THAT THE VIBRATION WAS DUE TO THE UNEVEN WEAR OF THE BEARING INSERT. INSERT HAD DETERIORATED FROM .100\ TO .0255\ AT THE THINEST WALL TO .092\ AT THE THICKEST WALL WEARNING IN AN OVAL FASHION. BLADE PIN AND BEARING WERE REMOVED FROM SERVICE AND REPLACED WITH SERVICABLE UNITS.

Part: PRESS SYST — MALFUNCTIONED (CABIN)

AIRCRAFT PRESSURIZATION SYSTEM FAILED. TRANSFERRED DISCREPANCY TO DEFERRED MAINTENANCE LIST AND AIRCRAFT CONTINUED SERVICE.

Part: INSERT — WORN (PROP BEARING)

PROPELLER ASSEMBLY WAS REMOVED FOR EXCESSIVE VIBRATION DURING DISASSEMBLY AND INSPECTION, IT WAS DETERMINED THAT THE VIBRATION WAS DUE TO THE UNEVEN WEAR OF THE BEARING INSERT. INSERT HAD DETERIORATED FROM .100 INCH TO .0840 INCH AT THE THINEST WALL TO .098 INCH AT THE THICKEST WALL WEARING IN AN OVAL FASHION. BLADE PIN AND BEARING WERE REMOVED FROM SERVICE AND REPLACED WITH SERVICABLE UNITS. PART TOTAL CYCLES, 2,044.

Part: BEARING — WORN (PROP BLADE)

PROPELLER ASSEMBLY WAS REMOVED FOR EXCESSIVE VIBRATION. DURING DISASSEMBLY AND INSPECTION, IT WAS DETERMINED THAT THE VIBRATION WAS DUE TO THE UNEVEN WEAR OF THE BEARING INSERT. INSERT HAD DETERIORATED FROM .100\ TO .0650\ AT THE THINEST WALL TO .095\ AT THE THICKEST WALL WEARING IN AN OVAL FASHION. BLADE PIN AND BEARING WERE REMOVED FROM SERVICE AND REPLACED WITH SERVICEABLE UNITS.

Part: FUEL DOOR — NOT CLOSED (R/H WING)

SERVICE DOOR WARNING DURING TAKEOFF. FOUND FUEL SERVICE DOOR OPEN - SECURED DOOR CLOSED AND AIRCRAFT CONTINUED SERVICE.

Part: PROX SENSOR — MALFUNCTIONED (ELEV TRIM)

TRIM AURAL WARNING SOUNDED DURING TAKEOFF. REPAIRED WIRING AT ELEVATOR TRIM PROXIMITY SENSOR.

Part: WARNING LIGHT — ILLUMINATED (CARGO DOOR)

AFTER TAKEOFF CARGO DOOR WARNING LIGHT ILLUMINATED. TRANSFERRED TO DEFERRED LIST CAT, MEL 52-70-1.

Part: INDICATION — MALFUNCTIONED (TE FLAPS)

FLAP DISAGREEMENT AFTER TAKEOFF. INSPECTED FLAPS, NO DEFECTS NOTED.

Part: PROX SENSOR — OUT OF ADJUST (ELEVATOR)

TAKEOFF TRIM WARNING SOUNDED DURING TAKEOFF ROLL. ADJUSTED THE ELEVATOR TRIM TAB PROXIMITY SENSORS. ACFT RETURNED TO SERVICE.

Part: OIL PRESS GAUGE — DEFECTIVE (RT ENGINE)

RIGHT ENGINE OIL PRESSURE INDICATES ZERO. REPLACED THE RT ENGINE OIL PRESSURE GAUGE. PART TOTAL CYCLES, 12,823.

Part: LATCH — BROKEN (LT MLG DOOR)

LEFT MLG OUTBD DOOR IS HANGING OPEN. REPLACED BROKEN LATCH ASSY ON GEAR DOOR.

Part: PROX SENSOR — BROKEN (LT MLG)

LEFT MLG GREEN "A" SYSTEM LIGHT FLICKERS ON AND OFF DURING FLIGHT WITH GEAR RETRACTED. REPLACED BROKEN DOWNLOCK PROXIMITY SENSOR.

Part: SKIN SUPPORT — CRACKED (WING RIBS)

THE FOLLOWING P/N WING SKIN SUPPORTS WERE FOUND CRACKED DURING INSPECTION TASK 5720-551/651-01I AND 5720-552/652-01I. THE CRACKED SKIN SUPPORTS WERE REPLACED IAW AERO DESIGN REPORT NR 1327-2. P/N 120-17056-007, 6 EA; 120-17056-017, 2 EA; 120-17056-015, 4 EA; 120-17056-013, 2 EA; 120-17056-011, 1 EA; 120-17057-006, 1 EA; 120-17057-007, 2 EA; 120-17057-005, 1 EA; 120-17056-019, 1 EA; 120-17062-011, 1 EA; 120-17060-011, 1 EA.