N168CA

Part: FLOORBEAM — CORRODED (BS 365) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

BS 365, RBL 45.5, UPPER FLOORBEAM CAP CORRODED OUT OF LIMITS. CUTOUT 10.6", FABRICATED AND INSTALLED REPAIR CHORD, 2 EA REPAIR ANGLES, 2 EA REPAIR STRAPS IAW EA PD57-53-265. 8110-3 ISSUED.

Part: FLOORBEAM — CRACKED (ZONE 100) · airframe 45,589 hrs · 23,492 cycles

BS 720 AT RBL57, FLOORBEAM CRACKED AND CORRODED. CUTOUT DAMAGED RBL 35.125 TO RBL70 FLOORBEAM UPPER CAP AND REPAIRED FLOORBEAM IAW EA PD57-53-303. APPROVING REPAIR FOR 1ST STAGE APPROVAL.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

AFT CARGO RBL 16.1, BS 1310 TO 1400, FLOOR SUPPORT CORRODED.

Part: FLOOR SUPPORT — CORRODED (BS 1330) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

AFT CARGO COMPARTMENT RBL 10.45, BE 1330, FLOOR SUPPORT HAS CORROSION.

Part: FLOOR SUPPORT — CORRODED (BS 1320) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

AFT CARGO COMPARTMENT, RBL 7.5 AT BS1320, HOLES DRILLED IN RADIUS OF FLOOR SUPPORT.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

AFT CARGO COMPARTMENT AT BS 1335, RBL 2.9, FOUND FLOOR SUPPORT CORRODED.

Part: FRAME — DAMAGED (ZONE 100) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

AFT CARGO BS 1560 STRINGER 27L, TOP OF FRAME HAS CORROSION AND HAS ONE MISDRILLED HOLE.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

AFT CARGO AT BS 1330 LBL 11, FLOOR SUPPORT WAS FOUND TO BE CORRODED.

Part: ATTACH ANGLE — CORRODED (INTERCOSTAL) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

AFT CARGO AT BS 1360 - 1380, BETWEEN S25L & S26L, INTERCOSTAL UPPER ATTACH ANGLE HAS CORROSION AROUND NUTPLATES.

Part: INTERCOSTAL — CORRODED (ZONE 100) · corrosion level 2 · airframe 45,589 hrs · 23,065 cycles

AFT CARGO AT BS 1540 - 1560, INTERCOSTAL HAS CORROSION AROUND NUTPLATES.

Part: INTERCOSTAL — CORRODED (ZONE 100) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

AFT CARGO BS 1280 - 1300 AT S27L INTERCOSTAL (ANGLE) CORRODED.

Part: ATTACH ANGLE — CORRODED (ZONE 100) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

AFT CARGO COMPARTMENT BS 1380 - 1420, AFT CARGO THRESHOLD ATTACH ANGLE HAS CORROSION.

Part: INTERCOSTAL — CORRODED (ZONE 100) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

AFT CARGO AT BS 1480 - 1500, BETWEEN STRINGERS 25 & 26R - INTERCOSTAL IS CORRODED.

Part: SUPPORT ANGLE — CORRODED (BS 1560) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

AFT CARGO COMPARTMENT, RT SIDE AT BS 1560, BETWEEN S24R & S27R ON LOWER SIDE WALL SUPPORT ANGLE HAS CORROSION.

Part: WEB — CRACKED (THRESHOLD) · airframe 45,589 hrs · 23,492 cycles

AFT CARGO COMPT, BS1400 - BS1420 THRESHOLD WEB CRACK AND HAS ELONGATED HOLES (CRACKS ARE WITHIN THE HOLES).

Part: STRINGER — CRACKED (ZONE 100) · airframe 45,589 hrs · 23,492 cycles

THE UPPER WEB OF BS 550, STRINGER 20L WAS FOUND TO HAVE A 2.5" LONG CRACK.

Part: LONGERON SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

FORWARD CARGO COMPARTMENT AT BS580, LONGERON 26L, LOWER FWD SPLICE TOP AND BOTTOM ARE CORRODED.

Part: INTERCOSTAL — CRACKED (ZONE 200) · airframe 45,589 hrs · 23,492 cycles

STA 1665.5 AT BL0 FOUND INTERCOSTAL CRACKED. CRACK LENGTH 1.5" LONG.

Part: ANGLE — CORRODED (ZONE 200) · corrosion level 2 · airframe 45,589 hrs · 23,492 cycles

MAIN PASSENGER CABIN BS 682 RBL 64, CUSP ANGLE CORRODED.

Part: INTERCOSTAL — CRACKED (ZONE 200) · airframe 45,589 hrs · 23,492 cycles

MAIN CABIN INTERCOSTAL LOWER FLANGE CRACKED AT BL 0 BS 792.

Part: INTERCOSTAL — CRACKED (ZONE 200)

MAIN CABIN INTERCOSTAL FLANGE CRACKED AT BS 792 ABD BL 0.

Part: SIGN — BROKEN (ROW 5)

EXIT SIGN DETACHED AT SEAT 5A. REPLACED EXIT SIGN.

Part: SENSOR — FAILED (NLG)

GEAR WOULD NOT RETRACT AFTER TAKEOFF. REMOVED AND REPLACED NOSE LANDING GEAR A SYSTEM PROX SENSOR.

Part: LAMP — FAILED (CABIN)

EMERGENCY FLOOR LIGHT AT CABIN DOOR IS INOPERABLE. REPALCED LIGHT BULB.

Part: FITTING — FAILED (LT ENGINE)

LEFT ENGINE OIL PRESSURE DROPPED BELOW 40 PSI, IN FLIGHT SHUT DOWN. REPLACED ELBOW FITTING THAT HAD BUCKED OUT ON THE OIL PUMP COVER.

Part: SUPPORT — CRACKED (LT WING)

WING SKIN SUPPORT CRACKED. REPLACED SKIN SUPPORT.

Part: SUPPORT — CRACKED (RT WING)

RIGHT WING SKIN SUPPORT NR 37 AT RIB NR 9 CRACKED. REPLACED SKIN SUPPORT.

Part: SUPPORT — CRACKED (RT WING)

RIGHT WING SKIN SUPPORT NR 30 AT RIB 6 CRACKED. REPLACED SKIN SUPPORT.

Part: STRINGER — CRACKED (RT WING)

RIGHT WING STRINGER NR 10 CRACKED BETWEEN RIBS NR 7 AND NR 8. REPAIRED WITH TWO PIECE DOUBLER.

Part: SUPPORT — BROKEN (RT WING)

DURING FUEL LEAK REPAIR, FOUND SKIN SUPPORT BROKEN IN THE RIGHT WING, RIB 16, BOTTOM CENTER. REPLACED SKIN SUPPORT.

Part: WINDOW POST — CRACKED (COCKPIT)

FOUND CRACK ON POST BETWEEN PILOTS WINDSHIELD AND DV WINDOW. INSTALLED DOUBLER ON WINDOW POST IAW EMB EST-474/95 DATE 01NOV95.

Part: SIGN — BROKEN (CABIN)

EXIT SIGN ROW 5 IS BROKEN. REPLACED EXIT SIGN.

Part: CONNECTOR — LOOSE (COCKPIT)

EAD1 AND EHS1 TUBES FAILED DURING TAKEOFF. REPAIRED LOOSE WIRE CONNECTION AT CIRCUIT BREAKER CB0256.

Part: DEICE INDICATION — MALFUNCTIONED (RT COCKPIT)

ABNORMAL DEICE, F/O FCP AND FO EFIS TUBE INDICATIONS DURING TAKEOFF. COULD NOT DUPLICATE DISCREPANCY. AIRCRAFT RETURNED TO SERVICE.

Part: RELAY BOX — MALFUNCTION (LANDING GEAR)

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

Part: BATTERY — DISCHARGED (CABIN)

EMERGENCY FLOOR PATH LIGHTING VERY DIM. REPLACED EMERGENCY BATTERY.

Part: BATTERY — DISCHARGED (CABIN)

CABIN DOOR EMERGENCY EXIT SIGN IS INOPERABLE, EMERGENCY FLOOR PATH LIGHTING TO ROW 3 IS INOPERABLE. REPLACED EMERGENCY LIGHTS BATTERY.

Part: TEE SECTION — CORRODED (FUSELAGE)

DURING 2C INSPECTION, TASK REVEALED CORROSION ON FLOOR T-SECTION THAT WAS OUT OF LIMITS. REMOVED CORRODED FLOOR T-SECTION AND INSTALLED SERVICEABLE T-SECTION USING EMB SRM STANDARD PRACTICES.

Part: SILL — CORRODED (SERVICE DOOR)

DURING 2C INSPECTION, TASK 5310-131-01I REVEALED CORROSION ON FLOOR SILL THAT IS BEHIND GALLEY. REMOVED SILL AND INSTALLED SERVICEABLE SILL USING EMB SRM STANDARD PRACTICES.

Part: SILL — CORRODED (CARGO COMPT)

DURING 2C INSPECTION, TASK REVEALED RIGHT CARGO FLOOR SILL TO BE CORRODED. REMOVED SILL AND INSTALLED SERVICEABLE SILL USING EMB SRM STANDARD PRACTICES.

Part: CROSSBEAM — CORRODED (FUSELAGE)

DURING 2C INSPECTION, TASK REVEALED RIGHT MIDDLE FLOOR CROSSBEAM AT FRAME 23 TO BE CORRODED. REMOVED CROSSBEAM AND INSTALLED SERVICEABLE CROSSBEAM USING EMB SRM STANDARD PRACTICES.

Part: TEE SECTION — CORRODED (FUSELAGE)

DURING 2C INSPECTION, TASK REVEALED FLOOR T-SECTION AT FRAME 28 TO BE CORRODED. REMOVED T-SECTION AND INSTALLED SERVICEABLE PART USING EMB SRM STANDARD PRACTICES.

Part: SUPPORT — CORRODED (FUSELAGE)

DURING 2C INSPECTION, TASK 5310-132-01I REVEALED LAV SUPPORT ASSY TO BE HEAVILY CORRODED. REMOVED CORRODED LAV SUPPORT AND INSTALLED SERVICEABLE SUPPORT AS PER EMB 120 MAINTENANCE MANUAL.

Part: CROSSBEAM — CORRODED (FUSELAGE)

DURING 2C INSPECTION, TASK REVEALED LEFT FLOOR CROSSBEAM TO BE CORRODED. REMOVED CROSSBEAM AND INSTALLED SERVICEABLE PART USING EMB-SRM STANDARD PRACTICES.

Part: WIRE — CHAFED (CENTER WING)

LEFTHAND BLEED AIR DUCT WARNING CAME ON DURING BOARDING. REPAIRED DAMAGED WIRE AT CENTER WING BLEED LEAK DETECTOR.

Part: WINDSHIELD — CRACKED (LT COCKPIT)

CAPTAIN'S WINDSHIELD CRACKED IN LOWER LEFT CORNER. REPLACED CAPTAIN'S WINDSHIELD.

Part: TIRE — FAILED (RT MLG)

RT INBOARD MAIN TIRE BLEW ON LANDING ROLL ANTI-SKID WARNING SOUNDED. REPLACED RT BRAKE CONTROL VALVE AND RT INBOARD WHEEL AND TIRE ASSY.

Part: SKIN — DAMAGED (CTR WING)

DETAILED INSPECTION FOLLOWING GEAR UP LANDING REVEALED THE FOLLOWING DAMAGE: WING LOWER SKIN NR 2 LEFT AND RIGHT DAMAGED. PERFORMED REPAIRS IAW EMBRAER ENGINEERING DRAWING 120-44623.

Part: SILL — CORRODED (FUSELAGE)

INSPECTION REVEALED THE FUSELAGE FWD FLOOR SUPPORT RT SILL CORRODED. THE RT SILL WAS REPLACED WITH A NEW PART PER EMB 120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: SUPPORT — CORRODED (FUSELAGE)

INSPECTION REVEALED THE FUSELAGE CENTER SECTION AFT LT SIDEWALL SEAT TRACK SUPPORT CORRODED. THE SUPPORT WAS REPLACED PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: SUPPORT — LOOSE (RT EMER EXIT)

INSPECTION REVEALED THE AFT RIGHT EMERGENCY EXIT MECHANISM BELLCRANK SUPPORT MOUNTING RIVETS, THROUGH DOOR SKIN TO BE LOOSE CAUSING EXCESSIVE PLAY IN THE DOOR OPENING MECHANISM. THE RIVETS WERE REPLACED PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51, NO OTHER DEFECTS FOUND.

Part: SKIN — CRACKED (LT WING)

DURING 20K LANDING INSPECTION, FOUND ONE FASTENER HOLE CRACK INDICATION ON LEFT WING UPPER SKIN AT RIB NR 11. HOLE WAS REPAIRED PER EMBRAER DOCUMENT EST431/96.

Part: RIB — DAMAGED (CENTER WING)

DETAILED INSPECTION FOLLOWING GEAR UP LANDING REVEALED THE FOLLOWING DAMAGE: WING RIB NR 1, CL RIB DAMAGED. REMOVED AND REPLACED IAW EMBRAER ENGINEERING DRAWING 120-44623.

Part: SUPPORT — CORRODED (FUSELAGE)

INSPECTION REVEALED THE FUSELAGE CENTER SECTION RT SIDEWALL SEAT TRACK SUPPORT CORRODED. THE SUPPORT WAS REPLACED WITH A NEW PART PER EMB120SRM STANDARD PRACTICES, CHAPTER 51.

Part: SUPPORT — CORRODED (FUSELAGE)

INSPECTION REVEALED THE FUSELAGE CENTER SECTION LT SIDEWALL SEAT TRACK SUPPORT CORRODED. THE SUPPORT WAS REPLACED WITH A NEW PART PER EMB 120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: AUX SPAR CAP — DAMAGED (CTR WING)

DETAILED INSPECTION FOLLOWING GEAR UP LANDING REVEALED THE FOLLOWING DAMAGE: WING AUXILIARY SPAR CAPS, LOWER LT AND RT DAMAGED. PERFORMED REPAIR IAW EMBRAER ENGINEERING DRAWING 120-44623.

Part: SKIN — MISDRILLED (LT WING)

DURING COMPLIANCE OF S/B 120-57-0031, ONE FASTENER HOLE IN THE LEFT WING UPPER SKIN WAS MISDRILLED AT RIB 18. THE HOLE WAS REPAIRED PER EMBRAER DOCUMENT EST 430/96.

Part: SKIN — DAMAGED (LT/RT NACELLE)

DETAILED INSPECTION FOLLOWING GEAR UP LANDING REVEALED THE FOLLOWING DAMAGE: LEFT AND RIGHT NACELLE LOWER SKINS DAMAGED. REMOVED AND REPLACED LT AND RT NACELLE LOWER SKINS IAW COMAIR ENGINEERING ORDER 54-005.

Part: AUX SPAR WEB — DAMAGED (CTR WING)

DETAILED INSPECTION FOLLOWING GEAR UP LANDING REVEALED THE FOLLOWING DAMAGE: WING AUXILIARY SPAR WEB LT AND RT DAMAGED. PERFORMED REPAIR IAW EMBRAER ENGINEERING DRAWING 120-44623.

Part: BUTT STRAP — CORRODED (FUSELAGE)

INSPECTION REVEALED THE FUSELAGE FWD FLOOR SUPPORT RT BUTT STRAP CORRODED. THE BUTT STRAP WAS REPLACED WITH A NEW PART PER EMB 120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: SUPPORT — CORRODED (FUSELAGE)

INSPECTION REVEALED THE FUSELAGE FWD LT SIDEWALL SEAT TRACK SUPPORT CORRODED. THE SUPPORT WAS REPLACED WITH A NEW PART PER EMB 120 SRM PRACTICES, CHAPTER 51.

Part: SUPPORT — CORRODED (FUSELAGE)

INSPECTION REVEALED THE FUSELAGE FWD FLOOR SUPPORT T-SECTION, AT FRAME 16 CORRODED. THE T-SECTION WAS REPLACED WITH A NEW PART PER EMB 120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: SKIN — CORRODED (FUSELAGE)

INSPECTION REVEALED THE LOWER FUSELAGE SKIN CORRODED BENEATH THE NR 2 COM ANTENNA. THE SKIN WAS REPAIRED PER AERODESIGN REPORT NR 2089-1 REV IR, DATED 11-7-96.

Part: BUTT STRAP — CORRODED (FUSELAGE)

INSPECTION REVEALED THE FUSELAGE FWD FLOOR SUPPORT CENTER BUTT STRAP CORRODED. THE BUTT STRAP WAS REPLACED WITH A NEW PART PER EMB 120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: STRINGER — CORRODED (FUSELAGE)

INSPECTION REVEALED THE FUSELAGE FWD SECTION OF STRINGER 18L CORRODED. THE STRINGER WAS REPAIRED PER AERODESIGN REPORT NR 1990-A, REV IR, DATED 11-6-96.

Part: SILL — CORRODED (EMERGENCY EXIT)

INSPECTION REVEALED SEVERE CORROSION ON THE FUSELAGE RIGHT AFT EMERGENCY EXIT CUTOUT LOWER SILL. THE SILL WAS REPLACED WITH A NEW PART PER EMB 120 SRM STANDARD PRACTICES CHAPTER 51.

Part: BRACKET — CRACKED (FUSELAGE)

INSPECTION REVEALED THE LEFT FWD FUSELAGE SKIN SUPPORT BRACKET, AT FRAME 9 TO BE CRACKED. THE BRACKET WAS REPLACED PER AERODESIGN REPORT 660-1.

Part: SPAR CAP — DAMAGED (CTR WING)

DETAILED INSPECTION FOLLOWING GEAR UP LANDING REVEALED THE FOLLOWING DAMAGE: WING FRONT SPAR CAPS, LOWER LT AND RT DAMAGED. PERFORMED REPAIRS IAW EMBRAER ENGINEERING DRAWING 120-44623.

Part: SPAR WEB — DAMAGED (CTR WING)

DETAILED INSPECTION FOLLOWING GEAR UP LANDING REVEALED THE FOLLOWING DAMAGE: WING FRONT SPAR WEB LT AND RT DAMAGED. PERFORMED REPAIRS IAW EMBRAER ENGINEERING DRAWING 120-44623.

Part: BULKHEAD — DAMAGED (FWD FUSELAGE)

DETAILED INSPECTION FOLLOWING GEAR UP LANDING REVEALED THE FOLLOWING DAMAGE: FWD PRESSURE BULKHEAD DAMGED. PERFORMED REPAIR IAW COMAIR ENGINEERING 53-012.

Part: SKIN — DAMAGED (CTR WING)

DETAILED INSPECTION FOLLOWING GEAR UP LANDING REVEALED THE FOLLOWING DAMAGE: WING LOWER SKIN NR 1 LEFT AND RIGHT DAMAGED. PERFORMED REPAIRS IAW EMBRAER ENGINEERING DRAWING 120-44623.

Part: CROSSBEAM — CORRODED (FUSELAGE)

INSPECTION REVEALED THE FUSELAGE FLOOR SUPPORT CROSSBEAM AT FRAME 16 CORRODED. THE CROSSBEAM WAS REPLACED WITH A NEW PART PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: BUTT STRAP — CORRODED (FUSELAGE)

INSPECTION REVEALED THE FUSELAGE FWD FLOOR SUPPORT LT BUTT STRAP TO BE CORRODED. THE BUTT STRAP WAS REPLACED PER EMB 120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: SKIN — DAMAGED (FWD FUSELAGE)

DETAILED INSPECTION FOLLOWING GEAR UP LANDING REVEALED THE FOLLOWING DAMAGE: FWD LOWER SKIN PANEL JUST AFT OF THE NLG DAMGED. PERFORMED REPAIR IAW COMAIR ENGINEERING ORDER 53-012.

Part: SKIN — DAMAGED (BS 9964.5-13056)

DETAILED INSPECTION FOLLOWING GEAR UP LANDING REVEALED THE FOLLOWING DAMAGE: FUSELAGE CENTER SECTION II, LOWER SKIN PANEL FROM FS 9964.5 TO FS 13056.0 DAMAGED. REMOVED AND REPLACED SKIN IAW ENGINEERING ORDER 53-012.

Part: STRINGER — DAMAGED (RT NACELLE)

DETAILED INSPECTION FOLLOWING GEAR UP LANDING REVEALED THE FOLLOWING DAMAGE: RIGHT NACELLE INBD STRINGER NR 1 DAMAGED. REMOVED AND REPLACED STRINGER IAW EMBRAER DOCUMENTS EDU-014/96 AND EST-420-96.

Part: FRAME — DAMAGED (LT/RT NACELLE)

DETAILED INSPECTION FOLLOWING GEAR UP LANDING REVEALED THE FOLLOWING DAMAGE: LEFT AND RIGHT NACELLE FRAME 10 WEB, INBD AND OUTBD SIDES DAMAGED. PERFORMED REPAIRS IAW COMAIR ENGINEERING ORDER 54-005.

Part: BUTT STRAP — CORRODED (FUSELAGE)

INSPECTION REVEALED THE FUSELAGE FWD FLOOR SUPPORT CENTER BUTT-STRAP CORRODED. THE BUTT STRAP WAS REPLACED WITH A NEW PART PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: CHECK VALVE — FAILED (GREEN HYD SYST)

THE GREEN SYSTEM AUX HYD PUMP CYCLES ON AND OFF WITH MAIN PRESSUE AT 0 PSI. SUSPECT THE ENGINE PUMP CHECK VALVE TO BE AT FAULT LETTING AUX HYD PRESSURE TO REACH THE HIGH PRESSURE SWITCH CAUSING THE AUX HYD PUMP TO CYCLE ON AND OFF. THE RESERVIOR ASSY WHERE THE CHECK VALVE WAS INSTALLED WAS REMOVED FOR ANALYSIS PER NTSB INVESTIGATOR.

Part: VALVE — FAILED (LANDING GEAR DR)

EMERGENCY EXTENSION PROCEDURE FAILED, AIRCRAFT MADE GEAR UP LANDING. SUSPECT LANDING GEAR DOORS STAYED CLOSED RESTRICTING EXTENSION OF LANDING GEAR. REMOVED LANDING GEAR DOOR SOLENOID VALVE PER NTSB INVESTIGATOR.

Part: HYD HOSE — CHAFED (LT ENGINE)

LANDING GEAR FAILED TO EXTEND FOR LANDING. EMERGENCY EXTENSION PROCEDURES FAILED, AIRCRAFT MADE GEAR UP LANDING. INSPECTION REVEALED THE LEFT GREEN HYD SYSTEM RESERVOIR WAS EMPTY. FOUND LEFT ENGINE DRIVEN HYD PUMP PRESSURE HOSE CHAFED THROUGH CAUSING HYD FLUID LEAKAGE. SUSPECT PRESSURE HOSE WAS CHAFED AGAINST THE LEFT OTBD COWLING DOOR SUPPORT ROD HOLDER.

Part: AHRS COMPUTER — FAILED (NR 1)

NR 1 AHRS FAILED. REPLACED THE NR 1 AHRS COMPUTER.

Part: HOSE — LOOSE (CENTER WING)

LEFT BLEED AIR DUCT LEAK WARNING CAME ON SHORTLY AFTER TAKEOFF. ENGINE WAS SECURED AND ACFT DIVERTED BACK TO FIELD. TIGHTENED LOOSE VENT LINE ON DE-ICE SYSTEM PRESSURE REGULATOR.

Part: OIL COOLER — LEAKING (RT ENGINE)

RT ENGINE LOST OIL PRESSURE DURING TAKEOFF. REPLACED THE ENGINE OIL COOLER.

Part: PITOT TUBE — DEFECTIVE (NR 1)

PILOTS AIR SPEED INDICATOR FAILED DURING FLIGHT. REPLACED THE NR 1 PITOT TUBE.

Part: CONNECTOR — LOOSE (ELEV TRIM)

TAKEOFF TRIM AURAL WARNING SOUNDED WHEN POWER ADVANCED FOR TAKEOFF. REPLACED LOOSE WIRING CONNECTIONS AT ELEVATOR TRIM PROXIMITY SENSORS.

Part: RELAY — MALFUNCTIONED (E/E BAY)

DURING PUSH BACK THE AIRCRAFT FILLED WITH SMOKE. APU AUTO SHUT DOWN. INSPECTED APU AND FOUND NO DEFECTS. REPLACED RELAY KO 194 FOR TROUBLESHOOTING.

Part: PROX SENSORS — OUT OF ADJUST (NLG)

A-SYSTEM NLG INTRANSIT LIGHT REMAINS ON AFTER LANDING GEAR RETRACTED. ADJUSTED UPLOCK PROXIMITY SENSORS TO M/M SPECIFICATIONS.

Part: SENSOR — DEFECTIVE (RT ENGINE)

R/T ENGINE WILL NOT START, NO NH INDICATION. REPLACED THE NH SENSOR.

Part: BALLSCREW SERVO — DEFECTIVE (RED GEARBOX)

WHILE PERFORMING HAMILTON STANDARDS S/B 14RF-9-61-A53 REV S, FOUND THE SPLINES OF THE BALLSCREW SERVO WORN BEYOND LIMITS PRIMARILY ON THE RIGHT SIDE OF THE SPLINES. THE PCU WAS SENT TO HAMILTON STANDARD FOR FURTHER EVALUATION.

Part: CONNECTOR — DEFECTIVE (RT MLG)

LANDING GEAR CONTROL CANNOT BE SELECTED TO UP POSITION. REPLACED DEFECTIVE WOW PROXIMITY SENSOR WIRING CONNECTOR AT RT MLG.

Part: SEAL — LEAKING (RT ENGINE)

RT ENGINE OIL PRESSURE FLUCTUATING. REPLACED THE CENTRIFUGAL AIR/OIL SEPARATOR SEAL.