N259CA

Part: SKIN — DAMAGED (ZONE 200) · airframe 53,174 hrs · 22,661 cycles

FUSELAGE SKIN APPROX BS 600 AT S5R, DAMAGED, DAMAGE FOUND TO BE OUT OF SRM LIMITS.

Part: CHANNEL — CRACKED (FUSELAGE) · airframe 53,174 hrs · 22,661 cycles

STATION BS 345 - BS 355 AT RBL 24.75, "U" CHANNEL CRACKED. CRACK LENGTH IS 2 INCHES.

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

BS 1645 AT RBL 60, HEAVY EXFOLIATION CORROSION ON R-4 DOOR SILL.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 53,174 hrs · 22,661 cycles

FUSELAGE STATION BS 1280 BETWEEN S4L & SA2L, FRAME DAMAGED.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 53,174 hrs · 22,661 cycles

STATION BS 750 AT LBL 10, FORWARD CARGO COMPARTMENT, FLOOR SUPPORT CRACKED. CRACK LENGTH 1.250 INCHES

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

STATION BS 1720 AT RBL 55, HEAVY CORROSION ON CORNER FITTING AT AFT PRESSURE BULKHEAD (APB).

Part: CHANNEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

MAIN CABIN AT FUSELAGE STATION BS326 AND LBL12, FLOOR CHANNEL CORRODED.

Part: PAN — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

FUSELAGE STATION BS1640 TO BS 1681 AT LBL50, CORROSION ON L-4 DRAIN PAN AREA. INTERCOSTAL CORRODED OUT OF LIMITS - REPLACED INTERCOSTAL (PN 146N5246-7). SUPPORT CORRODED OUT OF LIMITS, REPLACED SUPPORT (PN 146N5246-5).

Part: ATTACH BRACKET — CORRODED (BS 1360) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

RT AFT PIT AT STATION 1360, BELOW LONGERON NR 26, VERTICAL ATTACH BRACKET HAS CORROSION UNDERNEATH BOTTOM NUTPLATE.

Part: FRAME — ELONGATED (BS 440 S5R) · airframe 53,174 hrs · 22,661 cycles

ELONGATED HOLE AT FUSELAGE STA 440 BULKHEAD, RT SIDE ADJACENT TO STRINGER S5R. CUTOUT ELONGATED HOLE L=1.50", W=2.0".

Part: CHANNEL — SEVERED (BS 422) · airframe 53,174 hrs · 22,661 cycles

E & E FLOOR SUPPORT "U" - CHANNEL CRACKED (SEVERED) AT BS 422, RBL 30. CRACK LENGTH APPROX 2.25 INCHES LONG.

Part: STRINGER — CRACKED (ZONE 200) · airframe 53,174 hrs · 22,661 cycles

STRINGER 3L, AT STA 600 HAS CRACK AND DAMAGE, APPROX 1.250" LONG.

Part: ATTACH ANGLE — CRACKED (BS 1460) · airframe 53,174 hrs · 22,661 cycles

AFT CARGO COMPARTMENT, STA 1460 AT LBL4, FLOOR SUPPORT ATTACH ANGLE CRACKED. CRACK LENGTH APPROX 0.75" LONG.

Part: FLOORBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

MAIN CABIN, STATION 365 AT BL 0, THRU RBL 62, FLOORBEAM HAS CORROSION.

Part: DOUBLER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

AFT CARGO AREA, STA 1670 BETWEEN S25R AND S26R. DRAIN MAST INTERNAL DOUBLER HAS CORROSION.

Part: STANCHION — CRACKED (ZONE 100) · airframe 53,174 hrs · 22,661 cycles

AFT PIT STA 1500, VERTICAL COMPOSITE ATTACH ANGLE FOR SIDEWALL PANEL CRACKED.

Part: PLATE — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

AFT CARGO, STA 1690, BLADDER DRAIN PLATE HAS CORROSION BETWEEN S29L AND S29R.

Part: ANGLE — CRACKED (ZONE 100) · airframe 53,174 hrs · 22,661 cycles

AFT CARGO AT APPROX FUSELAGE STATION 1460 AND LOWER BUTT LINE 2.9, "Z" ANGLE HAS 1" CRACK.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 53,174 hrs · 22,661 cycles

FUSELAGE STA BS1560 TO BS1580 AT RBL 43, SEAT TRACK HAS GOUGES.

Part: CHANNEL — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

FUSELAGE STA BS1645 TO 1680, RBL65, CORROSION ON ALL SCUFF PLATE ATTACH CHANNELS.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

FUSELAGE STA 1660, RBL 12, CORROSION ON FLOORBEAM AROUND HOLE.

Part: FITTING — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

STA 1715, RBL 52", GALLEY MOUNT HAS HEAVY CORROSION.

Part: MOUNT — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

STA 1684, LBL50", GALLEY MOUNT HAS CORROSION IN MOUNT HOLES AND ON FITTING.

Part: MOUNT — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

STA 1720, LBL 50", GALLEY MOUNT HAS CORROSION IN HOLES.

Part: MOUNT — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

STA 1684, RBL 52", GALLEY MOUNT HAS HEAVY CORROSION.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

MAIN CABIN STA 1640, FRAME AT STR 17R CUSP WEB HAS CORROSION.

Part: WEB — CRACKED (ZONE 100) · airframe 53,174 hrs · 22,661 cycles

CABIN BEAM SUPPORT WEB AT STR 17, FWD SIDE, STA 1640.

Part: FLOORBEAM — DAMAGED (ZONE 100) · airframe 53,174 hrs · 2,261 cycles

STA 1640, RBL 56, TOOLING DAMAGE BELOW FLOORBEAM NEAR HI-LOCK COLLAR.

Part: SHEAR WEB — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

STATION 1681 LBL 27-50, CORROSION ON SHEAR WEB.

Part: FRAME — CRACKED (ZONE 100) · airframe 53,174 hrs · 22,661 cycles

AFT CARGO COMPT STA 1540, STR 25R FRAME CRACKED (2").

Part: LONGERON — CRACKED (BS 1580-1600) · airframe 53,174 hrs · 22,661 cycles

MAIN PASSENGER CABIN BETWEEN STA 1580-1600 LONGERON 14L IS CRACKED (4").

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

STA 1620-1640 BL10 FLOOR SUPPORT ON WEB HAS CORROSION AROUND FASTENER HOLES.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

STA 1620 LBL6-RBL6 CORROSION ON FLOORBEAM AROUND HOLES.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

STA 1620, RBL 24-LBL 24 CORROSION ON FLOORBEAM AROUND HOLES.

Part: FLOOR PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,174 hrs · 22,661 cycles

AFT CARGO COMPT, STA 1706, LBL 48, CABIN SUB FLOOR HAS CORRODED NUT PLATES.

Part: INTERCOSTAL — CRACKED (ZONE 100) · airframe 53,174 hrs · 22,661 cycles

RT MLG WW STA 1070 OTBD INTERCOSTAL WEB ABOVE DOOR STOP HAS A CRACK.

Part: BRAKE ASSY — FAILED (L/H MLG) · airframe 24,510 hrs · 25,637 cycles

FLIGHT 5042 ANTI-SKID WARNING DURING T/O ROLL.REPLACED THE L/H INBD BRAKE ASSY.

Part: ENGINE · airframe 24,273 hrs · 25,374 cycles

FLIGHT 5057 LT AND RT ENGINES T6 EXCEEDS 800 DEGREES C AT TAKE OFF POWER.C/W LT AND RT ENGINE COMPRESSOR WASH.

Part: SENSOR — MALFUNCTIONED (L/H) · airframe 24,237 hrs · 25,332 cycles

FLIGHT 5029 T6 WARING DURING T/O.REPLACED THE L/H ENGINE TORQUE.

Part: CONTROL BOX — MALFUNCTIONED (INST PANEL) · airframe 24,050 hrs · 25,124 cycles

FLIGHT 5061 LANDING GEAR DISAGREEMENT WARNING WHEN GEAR RETRACTED.REPLACED THE L/G CONTROL BOX.

Part: CONTROL BOX — MALFUNCTIONED (INST PANEL) · airframe 24,049 hrs · 25,124 cycles

FLIGHT 5018 L/H MLG DISAGREEMENT WARNING WHEN GEAR RETRACTED.REPLACED THE L/G CONTROL BOX.

Part: EEC — MALFUNCTIONED (L/H) · airframe 23,641 hrs · 24,665 cycles

FLIGHT 5061 - LEFT ENGINE WILL NOT ACHIEVE REQUIRED TORQUE.REPLACED THE L/H ENGINE EEC.

Part: WHEEL — CRACKED (RT MLG) · airframe 23,404 hrs · 24,396 cycles

FLIGHT 5825 DURING PREFLIGHT INSPECTION, THE CREW NOTICED THAT THE RIGHT MAIN INBOARD WHEEL INNER HALF WAS CRACKED AND A PORTION OF THE FLANGE WAS SLIGHTLY PROTRUDING. THE WHEEL FLANGE HAD GOUGED THE LOWER TORQUE-LINK OF THE RIGHT MAIN GEAR.THE WHEEL ASSEMBLY, AND THE LOWER TORQUE-LINK WERE REPLACED. AIRCRAFT RETURNED TO SERVICE.

Part: CAP · airframe 23,290 hrs · 24,258 cycles

FLIGHT #5057. DURING CRUISE FLIGHT THE RIGHT ENGINE OIL PRESSURE DROPPED BELOW 40 PSI, CREW DECLARED AN EMERGENCY AND PERFORMED AN INFLIGHT SHUT DOWN OF THE RIGHT ENGINE.REPLACED THE RIGHT ENGINE OIL SERVICING FILLER CAP AND NECK.

Part: GAUGE — FAULTY (COCKPIT) · airframe 13,176 hrs · 24,115 cycles

FLIGHT #5062. DURING TAKE OFF FROM NAS THE RIGHT ENGINE PROPELLER AUTO FEATHERED AT 80 KNOTS, ABORTED TAKE OFF AND RETURNED TO THE GATE.REPLACED THE RIGHT ENGINE TORQUE GAUGE.

Part: SKIN — DENTED (FUSELAGE CTR SEC) · airframe 23,056 hrs · 23,995 cycles

CREW REPORTS DENT ON RIGHT SIDE OF FUSELAGE BETWEEN FRAME 18 AND FRAME 19 AFTER DEBRIS STRUCK RIGHT PROPELLER.DAMAGED AREA WAS CUT OUT. FILLER AND DOUBLER WERE FABRICATED AND INSTALLED. WORK DONE IN ACCORDANCE WITH EMBRAER STRUCTURES REPAIR MANUAL CHAPTER 53-00-01.

Part: DOOR · airframe 23,045 hrs · 23,987 cycles

FLIGHT #5017. DURING TAXI OUT FLIGHT ATTENDANT NOTICED LIGHT SHOWING THROUGH BETWEEN CABIN DOOR AND DOOR FRAME, AIRCRAFT RETURNED TO THE GATE.RE-SHIMMED CABIN DOOR SEAL.

Part: BATTERY — DISCHARGED (CABIN) · airframe 22,757 hrs · 23,656 cycles

EMERGENCY LIGHTS, ROWS 7 TO 10 ARE INOPERABLE. REPLACED THE EMERGENCY BATTERY.

Part: CONTROL VALVE — MALFUNCTIONED (LT ENGINE DEICE) · airframe 22,459 hrs · 23,288 cycles

LEFT ENGINE INTAKE DEICE IS INOP. REPLACED THE INTAKE EJECTOR VALVE.

Part: LINE — WORN (LT ENGINE DEICE) · airframe 22,458 hrs · 23,286 cycles

LEFT ENGINE INTAKE DEICE IS INOPERABLE. REPLACED WORN AIR HOSE.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 22,087 hrs · 22,863 cycles

EMERGENCY LIGHTS FROM ROW 5 AFT ARE INOP. COULD NOT DUPLICATE. EMERGENCY LIGHTS FUNCTION NORMAL.

Part: SKIN — CHAFED (LT NACELLE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5410-432-04I, THE LEFT NACELLE OUTBOARD INNER SKIN WAS FOUND TO BE CHAFED. THE DAMAGED PART WAS REPLACED IAW EMB-120 STURCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT NR 3364-1, IR, 7/25/99.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TAXK 131-01Z, THE CABIN FLOOR SUPPORT ANGLE UNDER PAX DOOR THRESHOLD WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #3711-1, IR 6/24/00.

Part: THRESHOLD — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 132-01Z, THE RIGHT HAND CABIN FLOOR SUPPORT SILL WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: STRAP — GOUGED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 163-01Z, THE CARGO COMPARTMENT AFT LT FLOOR SUPPORT BUTT STRAP WAS FOUND TO BE GOUGED BY INTERIOR LINING SCREWS. THE DAMAGED PART WAS REPLACED IAW EMB 120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: SKIN — CHAFED (LT NACELLE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5410-432-04I, THE LEFT NACELLE INBOARD INNER SKIN WAS FOUND TO BE CHAFED. THE DAMAGED PART WAS REPLACED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #3364-1, IR, 7/25/99.

Part: FRAME — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 151/152-01Z, THE FUSELAGE FRAME 38 CHANNEL AT 6 O''CLOCK WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPAIRED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #3674-4, IR, 6/24/00.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 131-01Z, THE CABIN FLOOR SUPPORT ANGLE UNDER PAX DOOR THRESHOLD WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #3711-1, IR, 6/24/00.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5310-122-01I, THE RIGHT FLOOR PROP AT FUSELAGE FRAME 13 WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPAIRED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #3647-1, IR, 5/3/00.

Part: SKIN — GOUGED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2 YEAR CORROSION INSPECTION TASK 5310-132-COIE, THE FUSELAGE SKIN BELOW THE LAV DUMP VALVE DOUBLER WAS FOUND TO BE GOUGED. THE DAMAGED PART WAS REPAIRED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND EMBRAER REPAIR #SST-1569/00.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5310-121/122-O1I, THE CABIN FLOOR SUPPORT CENTER CROSSBEAM AT FRAME 12 WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 141-01Z, THE LEFT HAND CABIN FLOOR SUPPORT BUTT STRAP WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5310-222-05I, THE RIGHT HAND FUSELAGE SKIN SUPPORT AT FRAME 9 WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #660-1, IR, 2/16/93.

Part: BUTTSTRAP — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 131/132-01Z, THE CABIN FLOOR SUPPORT FORWARD CENTER BUTT STRAP WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #1671-1, REV A, 1/28/97.

Part: SUPPORT BRACKET — CRACKED (COCKPIT) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5310-221-05I, THE FUSELAGE SKIN SUPPORT, COCKPIT OVERHEAD LEFT SIDE WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPLACED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: BULKHEAD — CRACKED (LT NACELLE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5410-432-04I, THE LEFT NACELLE BULKHEAD SUPPORT AT FRAME 14 WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPLACED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #3712-1, IR, 6/24/00.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 131-01Z, THE CABIN FLOOR SUPPORT LT BUTT STRAP WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: THRESHOLD — CORRODED (FUSLEAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 131-01Z, THE CABIN FLOOR SUPPORT FWD LT SILL WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: ANGLE — CRACKED (RT WING) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5320-244-01I, THE RIGHT WING ATTACH ANGLE FOR FAIRING 194 WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPLACED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #1226-21, IR, 7/6/99.

Part: SUPPORT BRACKET — CRACKED (COCKPIT) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5310-221-05I, THE FUSELAGE SKIN SUPPORT BEHIND THE CAPTAIN''S DV WINDOW AS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPLACED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: BEAM — CRACKED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 131/132-01Z, THE CABIN FLOOR SUPPORT FWD CENTER OMEGA BEAM WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPAIRED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #2181-9, IR, 6/23/00.

Part: BRACKET — CRACKED (CARGO DOOR) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 262-01Z, THE CARGO DOOR AFT TRACTS TOP MOUNT BRACKET WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #1657-3, IR, 6/12/00.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 131/132-01Z, THE CABIN FORWARD CENTER FLOOR SUPPORT BUTT STRAP WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 132-01Z, THE RIGHT HAND CABIN FLOOR SUPPORT CROSSBEAM AT FRAME 16 WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5310-121-01I, THE LEFT FLOOR PROP AT FUSELAGE FRAME 13 WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPAIRED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #3647-1, IR, 5/3/00.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 131-01Z, THE LEFT HAND CABIN FLOOR SUPPORT BUTTSTRAP WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: SUPPORT BRACKET — CRACKED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 232-01Z, THE FUSELAGE FRAME 13A SKIN SUPPORT AT STRINGER 14R WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPAIRED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #3653-I, IR, 5/6/00.

Part: STRAP — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 132-01Z, THE CABIN FWD RT FLOOR SUPPORT BUTT STRAP WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 141-01Z, THE LEFT HAND CABIN FLOOR SUPPORT CROSSBEAM AT FRAME 20 WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARED PRACTICES.

Part: SPAR CAP — CHAFED (LT WING) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 191-01Z, THE LEFT WING AUX SPAR UPPER CAP WAS FOUND TO BE CHAFED BY FAIRING 191. THE DAMAGED PART WAS REPAIRED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND EMBRAER REPAIR #SST-1567-/00.

Part: SKIN — CHAFED (RT NACELLE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5410-442-04I, THE RIGHT NACELLE INBOARD INNER SKIN WAS FOUND TO BE CHAFED. THE DAMAGED PART WAS REPLACED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #3364-IR, 7/25/99.

Part: ANGLE — CRACKED (LT WING) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5320-243-01I, THE LEFT WING ATTACH ANGLE FOR FAIRING 193 WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPLACED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #1226-21, REV IR, 7/6/99.

Part: THRESHOLD — CORRODED (FUSLEAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 131-01Z, THE CABIN FLOOR SUPPORT LT SILL WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 142-01Z, THE RIGHT HAND FLOOR SUPPORT CROSSBEAM AT FRAME 20 WAS FOUND TO BE CORRODED. THE DAMAGED PART WAS REPLACED IAW EMB120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES.

Part: SKIN — CHAFED (RT NACELLE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5410-442-04I, THE RIGHT NACELLE OUTBOARD INNER SKIN WAS FOUND TO BE CHAFED. THE DAMAGED PART WAS REPLACED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #3364-1, IR, 7/25/99.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 21,185 hrs · 21,829 cycles

UPON COMPLIANCE OF 2C INSPECTION TASK 5310-221-O5I, THE FUSELAGE SKIN SUPPORT AT FRAME 9 WAS FOUND TO BE CRACKED. THE DAMAGED PART WAS REPLACED IAW EMB-120 STRUCTURAL REPAIR MANUAL STANDARD PRACTICES AND AERODESIGN REPORT #660-1, IR, 2/16/93.

Part: DUCT — LEAKING (BLEED AIR) · airframe 20,848 hrs · 21,431 cycles

LEFT HAND BLEED AIR DUCT LEAK WARNING. TIGHTENED LOOSE HOSE CLAMPS AT LEFT HAND ACM.

Part: SWITCH — OUT OF ADJ (FUEL DOOR) · airframe 20,774 hrs · 21,346 cycles

DOOR WARNING AFTER TAKEOFF. ADJUSTED THE FUEL SERVICE DOOR MICRO SWITCH.

Part: RADAR — MALFUNCTIONED (COCKPIT) · airframe 20,695 hrs · 21,259 cycles

WEATHER RADAR NOT OPERATING PROPERLY. COULD NOT DUPLICATE. SECURED CONNECTIONS ON ANT SYSTEM, TEST NORMAL.

Part: WARNING SYSTEM — ACTIVATED (COCKPIT)

FLAP DISAGREEMENT WARNING. COULD NOT DUPLICATE. OPERATION OF FLAP SYSTEM NORMAL.

Part: PUMP — MALFUNCTIONED (HYD SYSTEM)

RIGHT HYDRAULIC SYSTEM LOW QUANTITY WARNING. REPLACED THE ENGINE DRIVEN HYDRAULIC PUMP.

Part: RESERVOIR — LEAKING (HYD SYSTEM)

HYDRAULIC RESERVOIR LOW LEVEL WARNING. QUANTITY INDICATED EMPTY. REPLACED THE RIGHT HAND HYDRAULIC RESERVOIR ASSY.

Part: SENSOR — FAILED (RT MLG)

RIGHT MLG DISAGREE INDICATION WHEN GEAR RETRACTED. REPLACED THE UPLOCK PROXIMITY SENSOR.

Part: WIRE — BROKEN (TRIM SENSOR)

TAKEOFF TRIM WARNING. REPAIRED BROKEN WIRE AT ELEVATOR TRIM PROXIMITY SENSOR.

Part: EFIS — FAILED (RT COCKPIT)

THE CO-PILOTS TOP EFIS TUBE WENT BLANK DURING TAKEOFF, AIRCRAFT RETURNED TO THE GATE. RESET THE CO-PILOTS AHRS SYSTEM.

Part: STRINGER — CRACKED (RT WING)

DURING MAINTENANCE SERVICE CHECK, FUEL WAS FOUND LEAKING FROM RIGHT WING LOWER SKIN RIVET ON AFT OUTBOARD SIDE OF PANEL 622EB. INTERNAL INSPECTION FOUND WING STRINGER NR 8 CRACKED AT THAT LOCATION. THE STRINGER WAS REPAIRED PER EMB120 SRM 57-20-03, PAGE 201-204 AND EMB FAX SST-2243/99 DATED AUGUST 27, 1999. AIRCRAFT RETURNED TO SERVICE.

Part: BOX CONTROL — MALFUNCTIONED (LANDING GEAR)

LEFT HAND MLG DISAGREEMENT LIGHTS FLASHING DURING TAKEOFF. REPLACED THE LANDING GEAR CONTROL BOX.

Part: DOOR — NOT CLOSED (FUEL SERVICE)

SERVICE DOOR WARNING DURING TAKEOFF. FUEL SERVICE DOOR NOT COMPLETELY CLOSED.

Part: SIGN — BROKEN (ROW 5)

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

Part: PITOT TUBE — LOOSE (LT SYSTEM)

A 40 KT DIFFERENCE BETWEEN PILOT AND CO-PILOT AIRSPEED INDICATION. TIGHTENED LOOSE CONNECTION AT FRAME 8 IN PILOTS PITOT SYSTEM. LEAK CHECK SATISFACTORY.

Part: WIRE — BROKEN (LT STICK SHAKER)

STALL AURAL WARNING WILL NOT SILENCE. REPAIRED BROKEN WIRE AT CONNECTOR PO194 COPILOTS STICK SHAKER.

Part: ENGINE — DAMAGED (RIGHT)

RT ENGINE HOT START, TEMP REACHED 978 DEGREES. REMOVED ENGINE FOR INSPECTION.

Part: GENERATOR — FAILED (LT ENGINE)

UNUSUAL AND STRONG VIBRATION BETWEEN 12,500 AND 13,000 FEET. INSPECTED AIRCRAFT FOR CAUSE OF VIBRATION AND FOUND NO DEFECTS. REPLACED LT ENGINE AUX GENERATOR FOR TROUBLE SHOOTING.

Part: BATTERY — DISCHARGED (CABIN)

EMERGENCY EXIT LIGHTS AT ROW 5 ARE INOP. REPLACED THE NR 2 EMERGENCY BATTERY PACK.

Part: BATTERY — DISCHARGED (CABIN)

EMERGENCY EXIT SIGNS AT ROW 5 ARE INOP. REPLACED EMERGENCY BATTERY PACK.

Part: PRESS REGULATOR — LEAKING (LT ENGINE)

LEFT AIR DUCT LEAK WARNING ACTIVATED. WARNING CEASED AFTER ENGINE SHUT DOWN. REPLACED THE LEFT BLEED AIR PRESSURE REGULATOR.

Part: DOOR — DIRTY (CARGO COMPT)

CARGO DOOR WARNING DURING TAKEOFF. CLEANED DEBRIS FROM CARGO DOOR AREA. DOOR AND WARNING SYSTEM OPERATE NORMAL.

Part: LIGHT — INOPERATIVE (CABIN)

CENTER CEILING AND SIDEWALL EMERGENCY LIGHTS ARE INOP. RESEATED FUSES, SYSTEM OPERATION NORMAL.

Part: SILL — CORRODED (CABIN)

A 4C INSPECTION TASK 5320-152-01I, REVEALED HEAVY PITTING CORROSION ON RIGHT SILL. REMOVED SILL AND INSTALLED SERVICEABLE SILL USING EMB 120 SRM.

Part: BOLT — RUSTED (HORIZ STAB)

DURING 4C INSPECTION MRB TASK 5510-333-04I AND 5510-334-04I, REVEALED THAT THE EXPOSED AREAS OF THE BOLTS THAT ATTACH THE ELEVATOR ATTACH BRACKETS TO THE HORIZONTAL STABILIZER (I.E. HEAD OF BOLT AND EXPOSED THREADS) TO BE RUSTED. REMOVED BOLTS FOR FURTHER INSPECTION AND FOUND THAT ONLY THE EXPOSED PORTION OF THE BOLTS WERE RUSTED. NO RUST ON BOLT SHANK OR THREADS UNDER THE NUT. INSTALLED SERVICEABLE BOLTS WITH MASTINOX AND TORQUEST USING EMB MM 20-10-01.

Part: BRACKET — CRACKED (CARGO DOOR)

DURING 4C INSPECTION TASK 251-012 AND 252-012, REVEALED THAT THE ATTACH BRACKET FOR THE CARGO DOOR TENSIONER MOUNT WAS CRACKED BENEATH MOUNT BOLTS. REMOVED BRACKET AND INSTALLED SERVICEABLE BRACKET.

Part: SEAT TRACKS — CORRODED (CABIN)

DURING 4C INSPECTION MRB TASK 5320-151-01I, REVEALED MODERATE CORROSION AROUND SCREW HEAD ON THE PAX SEAT TRACKS. REMOVED CORRODED SEAT TRACKS AND INSTALLED SERVICEABLE SEAT TRACKS USING MASTINOX ON ALL SCREWS. ALL DONE IAW AERODESIGN REPORT NR 2141-1.

Part: SILL — CORRODED (CABIN)

DURING 4C INSPECTION TASK 5320-151-01I AND 5320-152-01I, REVEALED THE LEFT SILL TO HAVE HEAVY PITTING CORROSION. REMOVED SILL AND INSTALLED SERVICEABLE SILL USING EMB 120 SRM.

Part: SILL — CORRODED (CABIN)

DURING 4C INSPECTION TASK 5320-152-01I, REVEALED CORROSION BETWEEN AFT EMERGENCY EXIT SILL AND PIN RECEPTICALS DUE TO LACK OF INTERFACE SEALANT. REMOVED CORRODED SILL AND RECEPTICALS AND INSTALLED SERVICEABLE RECEPTICALS TO SILL USING INTERFACE SEALANT AND REINSTALLED IN AIRCRAFT.

Part: ACTUATOR — FAILED (LT TE FLAP)

NACELLE FLAPS WILL NOT MOVE. REPLACED THE LEFT HAND NACELLE FLAP ACTUATOR.

Part: CROSSBEAM — CORRODED (CABIN)

ON 2C TASK 5320-241-03I, THE LT CABIN FLOORBEAM CROSSBEAM AT FRAME 20 WAS FOUND CORRODED. REPLACED PER SRM STANDARD PRACTICES.

Part: BATTERY — DISCHARGED (CABIN)

EMERGENCY EXIT SIGNS AND FLOOR PATH LIGHTING AT ROW 5 WILL NOT TEST. REPLACED THREE EMERGENCY LIGHTING BATTERY PACKS.

Part: ENGINE — HIGH OIL CONSUM (RIGHT)

RIGHT ENGINE OIL PRESSURE DROPPED TO 52 PSI. OIL CONSUMPTION WAS EXCESSIVE. REPLACED ENGINE.

Part: PROP BLADE — OUT OF BALANCE (RT PROP)

VIBRATION FELT DURING TAXI, SUSPECT OUT OF BALANCE PROPELLER. REPLACED NR 4 BLADE ON RT PROPELLER.

Part: SILL — CORRODED (CABIN)

ON 2C CHECK, FOUND THE FOLLOWING PART TO BE CORRODED. FLOOR SUPPORT STRUCTURE RT FWD SILL. THE PART WAS REPLACED WITH A NEW FACTORY PART PER EMB120 SRM CHAPTER 51, STANDARD PRACTICES.

Part: BUTT STRP — CORRODED (CABIN)

ON 2C CHECK, FOUND THE FOLLOWING PART TO BE CORRODED. FUSELAGE FLOOR SUPPORT STRUCTURE RT BUTT STRAP. THE PART WAS REPLACED WITH A NEW FACTORY PART PER EMB120 SRM CHAPTER 51, STANDARD PRACTICES.

Part: BUTT STRAP — CORRODED (FUSELAGE)

ON 2C CHECK, FOUND THE FOLLOWING PART TO BE CORRODED. CARGO FLOOR SUPPORT STRUCTURE RT BUTT STRAP. THE PART WAS REPLACED WITH A NEW FACTORY PART PER EMB120 SRM CHAPTER 51, STANDARD PRACTICES.

Part: BUTT STRAP — CORRODED (CARGO COMPT)

ON 2C CHECK, FOUND THE FOLLOWING PART TO BE CORRODED. CARGO FLOOR SUPPORT STRUCTURE RT BUTT STRAP. THE PART WAS REPLACED WITH A NEW FACTORY PART PER EMB120 SRM CHAPTER 51, STANDARD PRACTICES.

Part: BUTT STRAP — CORRODED (FUSELAGE)

ON 2C CHECK, FOUND THE FOLLOWING PART TO BE CORRODED. FUSELAGE FLOOR SUPPORT STRUCTURE FWD CENTER BUTT STRAP. THE PART WAS REPLACED WITH A NEW FACTORY PART PER EMB120 SRM CHAPTER 51, STANDARD PRACTICES.

Part: BUTT STRAP — CORRODED (FUSELAGE)

ON 2C CHECK, FOUND THE FOLLOWING PART TO BE CORRODED. FUSELAGE FLOOR SUPPORT STRUCTURE RT BUTT STRAP. THE PART WAS REPLACED WITH A NEW FACTORY PART PER EMB120 SRM CHAPTER 51, STANDARD PRACTICES.

Part: BUTT STRAP — CORRODED (FUSELAGE)

ON 2C CHECK, FOUND THE FOLLOWING PART TO BE CORRODED. FUSELAGE FLOOR SUPPORT LT BUTT STRAP. THE PART WAS REPLACED WITH A NEW FACTORY PART PER EMB120 SRM CHAPTER 51, STANDARD PRACTICES.

Part: SKIN — GOUGED (CARGO DOOR)

ON 2C CHECK, FOUND THE CARGO DOOR SKIN GOUGED AT THE TOP CENTER. SKIN REPAIRD PER EMB120 SRM 52-30-01, PG 201 TO 203.

Part: BUTT STRAP — CORRODED (FUSELAGE)

ON 2C CHECK, FOUND THE FOLLOWING PART TO BE CORRODED. FLOOR SUPPORT STRUCTURE RT FWD BUTT STRAP. THE PART WAS REPLACED WITH A NEW FACTORY PART PER EMB120 SRM CHAPTER 51, STANDARD PRACTICES.

Part: BUTT STRAP — CORRODED (FUSELAGE)

ON 2C CHECK, FOUND THE FOLLOWING PART TO BE CORRODED. FLOOR SUPPORT STRUCTURE LT FWD BUTT STRAP. THE PART WAS REPLACED WITH A NEW FACTORY PART PER EMB120 SRM CHAPTER 51, STANDARD PRACTICES.

Part: SPAR CAP — MISDRILLED (WS 2902)

UPON REMOVAL OF A DAMAGED HI-LOCK PIN FOUND ON 2C CHECK, THE HOLE WAS MISDRILLED IN THE LEFT WING AUX SPAR, AT STATION Y=2902, AT THE LOWER SPAR-TO-NACELLE FITTING. THE DAMAGE EXTENDED THROUGH THE FWD FITTING, THE DOUBLER, THE AUX SPAR, THE LOWER SPAR CAP, AND THE AFT FITTING. THE HOLE WAS REPAIRED AND THE HI-LOCK REPLACED PER EMBRAER APPROVED REPAIR PROCEDURE NR EST-564/96.

Part: BOLT — CORRODED (PAX DOOR)

DURING 2C INSPECTION, FOUND PAX DOOR ROTATING ARM ATTACH BOLTS TO BE HEAVILY CORRODED. FORWARD AND AFT PASSENGER DOOR ROTATING ARM ATTACH BOLTS REPLACED WITH SERVICEABLE BOLTS AS PER EMB120 MAINTENANCE MANUAL 52-10-00 PG 401 TO 403.

Part: SELECTOR — DEFECTIVE (TE FLAPS)

FLAP CONTROL FAULT WARNING WHEN FLAPS SELECTED UP AFTER LANDING. REPLACED THE FLAP SELECTOR LEVER ASSY. PART TOTAL CYCLES, 14,618.

Part: BATTERY — DISCHARGED (CABIN)

SEVERAL EMERGENCY LIGHTS ARE DIM OR INOPERATIVE. REPLACED EMERGENCY LIGHT BATTERY.

Part: FUEL HEATER — LEAKING (RT ENG)

FUEL LEAK RT ENGINE. REPLACED LEAKING FUEL TO OIL HEAT EXCHANGER. PART TOTAL CYCLES, 16,641.

Part: ECCENTRIC SHAFT — SHEARED (RUDDER)

DURING C-1 INSPECTION, FOUND RUDDER ECCENTRIC SHAFT TO BE SHEARED JUST ABOVE SPLINED SHAFT. INSTALLED SERVICEABLE (P/N 120-48563-001) AND RETURNED AIRCRAFT TO SERVICE. ECCENTRIC SHAFT AND FAIL-SAFE PIN SENT TO EMBRAER FOR ANALYSIS.

Part: DOOR — UNLATCHED (FUEL SERVICE)

DURING TAKEOFF ROLL, SERVICE DOOR WARNING LIGHT ILLUMINATED. FOUND FUEL SERVICE DOOR UNLATCHED. SECURED DOOR AND ACFT CONTINUED SERVICE.

Part: LEAD WIRE — BROKEN (LT PROP)

LEFT PROPELLER DE-ICE IS INOP. REPLACED BROKEN DE-ICE LEAD WIRE AND ACFT RETURNED TO SERVICE.

Part: UPLOCK ACTUATOR — FAILED (LT MLG)

LT MAIN LANDING GEAR A-SYSTEM INTRANSIT INDICATOR REMAINED ON WHEN GEAR SELECTED DOWN. CYCLED GEAR WITH SAME RESULTS. REPLACED THE LT MLG UPLOCK ACTUATOR.

Part: LATCH — BROKEN (RT MLG DOOR)

THE RIGHT MAIN LANDING GEAR DID NOT RETRACT. REPLACED BROKEN MAIN LANDING GEAR DOOR LATCH.

Part: O-RING — LEAKING (RT ENGINE)

FUEL LEAK RIGHT ENGINE. REPLACED O-RING ON FUEL FLOW TRANSMITTER.

Part: HMU — LEAKING (RT ENGINE)

RT ENGINE IS LEAKING FUEL. REPLACED THE ENGINE HMU.

Part: CONNECTOR — DEFECTIVE (RT MLG)

LANDING GEAR WOULD NOT RETRACT. REPLACED THE WOW PROXIMITY SENSOR WIRING CONNECTOR ON THE RT MLG.

Part: SUPPORTS — CRACKED (LT/RT WING)

THE FOLLOWING P/N WING SKIN SUPPORTS WERE FOUND CRACKED DURING INSPECTION TASK NR 5720-551/651-01I. THE SKIN SUPPORTS WERE REPLACED IAW AERODESIGN REPORT NR 1387-2. P/N 120-17056-019 2 EA; 120-17056-017 2 EA; 120-17056-015 1 EA; 120-17056-013 1 EA; 120-17057-005 1 EA; 120-17057-007 1 EA; 120-17057-006 1 EA.

Part: AOA HEAT RELAY — DEFECTIVE (LEFT)

LEFT A.O.A. VANE HEAT INOP WARNING ACTIVATED. REPLACED RELAY KO187, SYSTEM CHECK NORMAL.