N156CA

Part: SMOKE — DETECTED (CABIN) · airframe 27,130 hrs · 31,775 cycles

LIGHT SMOKE IN CABIN ON DESCENT TO RDD. RAN MEMORY/FLOW CHECK LIST (NO OXY OR SMOKE GOGGLES), RECIRC/GASPER OFF, THEN RIGHT, THEN LEFT PAC AND STOPPED SMOKE. DID FULL RAMP CHECK OF PACKS, UNABLE TO DUPLICATE. INSPECTED BOTH PACKS AND RAM AIR VALVES FOR DISCREPANCIES. NONE FOUND. RAN PACKS WITH ENGINE AND APU BLEEDS. OPS CHECK GOOD. NO SMOKE NOTED.

Part: REGULATOR — OUT OF ADJ (OIL PRESSURE) · airframe 26,885 hrs · 31,422 cycles

PILOT REPORTED LOSS OF OIL PRESSURE (DROPPED IN YELLOW BAND) AND LOSS OF POWER (LEFT). DIVERTED TO EUGENE. ADJUSTED OIL PRESSURE REGULATOR PER MM 72-1-50. OPS AND LEAK CHECKS GOOD. REPLACED LEAKING FUEL OIL HEATER PER MM 72-01-40. OPS AND LEAK CHECKS ON GROUND. PERFORMED HIGH POWER RUNS FOR 10 MINUTES. NO SYSTEM DEFECTS NOTED.

Part: CONTROL UNIT — FAILED (LANDING GEAR) · airframe 26,364 hrs · 30,737 cycles

LANDING GEAR WOULD NOT RETRACT. RETURNED TO SEA. REMOVED AND REPLACED LANDING GEAR CONTROL MODULE IAW MM 32-31-01. P/N ON: 120-38594-501, S/N: 120027, S/N OFF: 120085.

Part: TQ INDICATOR — MALFUNCTIONED (RIGHT ENGINE)

LARGE RIGHT ENGINE TORQUE FLUCTUATIONS FROM 60 PERCENT TO 84 PERCENT ON CLIMB THROUGH 5000. RETURNED TO PDX. RAN RIGHT ENGINE BUT COULD NOT DUPLICATE PROBLEM.

Part: VALVE — FAILED (LT ENGINE)

EN ROUTE TO CLD LEFT DUCT LEAK LIGHT ILLUMINATED. FOLLOWED QRH AND LIGHT DID NOT EXTINGUISH. SHUT DOWN LEFT ENGINE AND RETURNED TO LAX. RAN AIRCRAFT AND DUPLICATED DISCREPANCY. ISOLATED REGULATOR/RELIEF VALVE AS FAULTY. INSTALLED SERVICEABLE VALVE AND RAN AIRCRAFT EXTENSIVELY AT 100 PERCENT TQ. BLEEDS AUTO PACK NORMAL. NO DISCREPANCY OR DUCT LEAK LIGHT NOTED. OPS CHECKED GOOD.

Part: O RING — FAILED (LT ENG BLEED AIR)

LEFT ENGINE DUCT LEAK LIGHT ILLUMINATED SHORTLY AFTER TAKEOFF. COMPLIED WITH QRH AND RETURNED TO PSP AND CONTACTED MAINTENANCE. FOUND O-RINGS WORN ON COUPLER SLEEVE CAUSING LEFT ENGINE BLEED AIR DUCT TUBE ASSEMBLY TO LEAK AT LEADING EDGE AND AT WING TO FUSELAGE. REMOVED AND REPLACED O-RING.

Part: WARNING — ACTIVATED (TE FLAPS)

AFTER TAKEOFF, CONTROL FAULT ILLUMINATED. QRH DID NOT CLEAR FAULT. RETURNED FOR LANDING AT SMF. OPERATED FLAPS UP AND DOWN COUPLE OF TIMES, NO DISCREPANCY NOTED. COULD NOT DUPLICATE PROBLEM.

Part: IAS INDICATOR — LEAKING (RT COCKPIT)

ON TAKEOFF, FO'S AIRSPEED, ALTIMETER AND VSI VERY ERRATIC. ALTIMETER AS MUCH AS 1,500 FEET BEHIND CAPTAINS. AIRSPEED INDICATOR 0 KNOTS MOST OF THE TIME. RETURNED TO SEA. COPILOTS IAS INDICATOR HAS A STATIC LEAK. REMOVED AND REPLACED COPILOTS IAS INDICATOR IAW MM 34-12-01. TESTED IAW MM 34-11-00. OPS CHECKS GOOD.

Part: ACTUATOR — MALFUNCTIONED (NLG)

ON APPROACH HAD US DO A GO-AROUND. ON GO-AROUND, NOSE GEAR A AND B REMAINED ON, (NO GROUND LIGHTS). NOSE GEAR WOULD NOT COME UP. REPLACED NOSE GEAR ACTUATOR FOR TROUBLESHOOTING. ALSO, REPLACED BAD ROD-END ASSY. SWUNG GEAR SEVERAL TIMES. ALL CHECKS GOOD.

Part: TRIM TAB — OUT OF POSITION (ELEVATOR)

DURING DESCENT, AUTO PILOT DISCONNECTED. FOUND TRIM WHEEL AT FORWARD LIMIT AND TRIM INDICATOR AT 1-8 UNITS DOWN. AIRCRAFT SPEED REDUCTION REQUIRED TO REDUCE STICK FORCES TO NORMAL. ACCOMPLISHED ELEVATOR TRIM TAB DEFLECTION CHECK PER MM 27-32-00, TRAVEL WITHIN LIMITS AT THIS TIME.

Part: ACTUATOR — FAILED (LT ELEVATOR TRIM)

IN DESCENT FLIGHT MAP TRIM FAIL AP DISCONNECT. AIRCRAFT PITCHED UP. DIFFICULT TO CONTROL PITCH. TO DESCEND, IT TOOK ALL NOSE DOWN TRIM AND FORWARD YOKE PRESSURE, (AP TRIM SEVO NOT ILLUMINATED WHEN LOOK AT IT). INSPECTED AND FOUND LEFT ELEVATOR TRIM ACTUATOR JAMMING AND NOT ALLOWING FULL NOSE DOWN TRIM. REMOVED AND REPLACED LEFT ELEVATOR TRIM ACTUATOR PER MM 27-32-02 AND ADJUSTED RIGHT ELEVATOR TRIM TAB. AIRCRAFT TRIM OPERATIONAL CHECKS GOOD.

Part: CONTROL PANEL — FAILED (COCKPIT)

DURING INITIAL CLIMB AT 1000 FT, ELECTRIC TRIM RAN AWAY FORWARD TO STOP. ROLLED TRIM BACK AND IT RAN FORWARD TO STOP AGAIN, EACH TIME SOUNDING AUTO PILOT AURAL WARNING. THE AUTO PILOT WAS NOT ON AT THE TIME. TRIED TO TURN RIGHT, WAS UNABLE BECAUSE AUTO PILOT SERVOS WERE IN CONTROL. PRESSED AUTO PILOT ENGAGE ON AND OFF SEVERAL TIMES BUT AUTO PILOT WOULD NOT DISENGAGE. DIALING THE HEADING TO THE RIGHT, AIRCRAFT WOULD ROLL LEFT. EVENTUALLY, THE AUTO PILOT DISENGAGED. RETURNED TO LAX. REMOVED AND REPLACED AUTO PILOT CONTROL PANEL, OPS CHECKS GOOD ON GROUND. COULD NOT DUPLICATE PROBLEM.

Part: WIRE — SHORTED (RT WING)

NAVIGATION LIGHTS CIRCUIT BREAKER TRIPPED. REPAIRED SHORTED WIRE RIGHT HAND WING.

Part: BATTERY — DISCHAGED (CABIN)

EMERGENCY FLOOR LIGHTING IS INOP. REPLACED EMERGENCY BATTERIES.

Part: FRAME — CRACKED (LT NACELLE)

DURING 1C INSPECTION, TASK 419-012 REVEALED A CRACK IN LEFT NACELLE UPPER HALF FRAME. THE CRACK WAS .52 LONG AND STARTED AT A NUTPLATE FASTENER. THE NUTPLATE IS ONE OF FOUR INSTALLED TO ATTACH THE EXHAUST DUCT MOUNT BRACKET. REPAIRED HALF-FRAME USING AERODESIGN REPORT 2524-2.

Part: FRAME — CRACKED (LT NACELLE)

DURING 1C INSPECTION, TASK 419-012 REVEALED A CRACK IN LEFT NACELLE UPPER HALF-FRAME. REPLACED HALF-FRAME USING AERODESIGN REPORT 2524-2.

Part: SEQUENCE VALVE — OUT OF ADJUST (RT MLG DOOR)

THE RIGHT HAND MLG DOES NOT RETRACT. ADJUSTED THE RIGHT HAND MLG DOORS SEQUENCE VALVES.

Part: AURAL WARNING — SOUNDED (COCKPIT)

TAKEOFF TRIM AURAL WARNING SOUNDED DURING TAKEOFF. TRIM WAS CONFIRMED AT TAKEOFF SETTING. COULD NOT DUPLICATE DISCREPANCY. RESET AURAL WARNING UNIT, SYSTEM TEST NORMAL.

Part: BLADE — DELAMINATED (NR 3 BLADE)

PROPELLER ASSEMBLY REMOVED FROM AIRCRAFT FOR HUB MAJOR INSPECTION. UPON FURTHER INSPECTION, THE NR 3 BLADE WAS FOUND TO HAVE A DELAMINATION OF 40 SQ INCHES LOCATED ON THE CAMBER SIDE OF THE BLADE AND BEGINNING AT BLADE STATION 38. BLADE WAS REMOVED FROM SERVICE AT THIS TIME AND IS BEING REPAIRED IAW HAM STD MAINTENANCE MANUAL.

Part: BLADE — DELAMINATED (PROP NR 2)

PROPELLER ASSEMBLY REMOVED FROM AIRCRAFT FOR HUB MAJOR INSPECTION. UPON FURTHER INSPECTION, THE NR 2 BLADE WAS FOUND TO HAVE A DELAMINATION OF 74 SQ INCHES LOCATED ON THE CAMBER SIDE OF THE BLADE AND BEGINNING AT BLADE STATION 32. BLADE WAS REMOVED FROM SERVICE AT THIS TIME AND IS BEING REPAIRED IAW HAM STD MAINTENANCE MANUAL.

Part: ANTENNA — FAILED (NOSE RADOME)

WEATHER RADAR DISPLAY INOPERATIVE DURING CLIMB OUT. REPLACED THE WEATHER RADAR ANTENNA.

Part: ANTENNA — FAILED (RADAR COMPT)

WEATHER RADAR IS INOP. REPLACED THE RADAR ANTENNA.

Part: STOP TAB — BENT (PROPELLER)

PROPELLER ASSEMBLY REMOVED FROM AIRCRAFT FOR HUB MAJOR INSPECTION. UPON INITIAL RECEIVING INSPECTION THE FEATHER STOP TAB S/N 248 WAS FOUND TO BE BENT APPROXIMATELY 0.125. PITCHLOCK SCREW WAS REMOVED FROM ASSEMBLY AND HELD FOR PROPOSED FUTURE REPAIR.

Part: BEARING INSERT — WORN (PROPELLER)

PROPELLER ASSEMBLY REMOVED FROM AIRCRAFT FOR HUB MAJOR INSPECTION. UPON INITIAL RECEIVING INSPECTION THE BLADE PIN BEARING INSERT WAS FOUND TO BE IN AN OVAL FASHION. FURTHER INSPECTION SHOWED THAT THE INSERT HAD WORN TO .082 AT THE THINNEST POINT AND .099 AT THE THICKEST POINT. INSERT WAS REMOVED AND SENT TO MANUFACTURER FOR FURTHER EVALUATION.

Part: BEARING INSERT — WORN (PROPELLER)

PROPELLER ASSEMBLY REMOVED FROM AIRCRAFT FOR HUB MAJOR INSPECTION. UPON INITIAL RECEIVING INSPECTION THE BLADE PIN BEARING INSERT WAS FOUND TO BE WORN IN AN OVAL FASHION. FURTHER INSPECTION SHOWED THAT THE INSERT HAD WORN TO .083 AT THE THINNEST POINT AND .097 AT THE THICKEST POINT. INSERT WAS REMOVED AND SENT TO MANUFACTURER FOR FURTHER EVALUATION.

Part: HYDRAULIC SYST — REQD SERVICE (GREEN HYD SYST)

THE LT (GREEN) HYDRAULIC SYSTEM LOW QUANTITY WARNING WAS ON DURING GEAR RETRACTION. THE RESERVOIR QUANTITY WAS AT THE BOTTOM OF THE GREEN RANGE. SERVICED HYDRAULIC SYSTEM TO FULL LEVEL, SYSTEM OPERATION NORMAL.

Part: COUPLER — INOPERATIVE (AVIONICS)

ILS COURSE MOVES PLUS OR MINUS 1 DOT ON FINAL. REPLACED INBOARD COUPLER, OPERATIONAL CHECK GOOD.

Part: FILTER — CLOGGED (RT ENGINE)

FUEL FILTER IMPENDING BYPASS WARNING DURING FLIGHT. REPLACED RT ENGINE FUEL FILTERS.

Part: SEPARATOR — CRACKED (WING CENTER)

WING AND STABILIZER INBD DE-ICE BOOTS ARE INOP. REPLACED A CRACKED BLEED AIR WATER SEPARATOR.

Part: CROSSBEAM — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE FWD FLOOR SUPPORT LT CROSSBEAM CORRODED. REPLACED CROSSBEAM WITH NEW PART PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: SKIN — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE BELLY SKIN SEVERELY CORRODED AT FRAME 23. THE DAMAGE WAS REPAIRED PER EMB120 SRM 53-00-01, FIG 202.

Part: CROSSBEAM — CRACKED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE FLOOR SUPPORT CROSSBEAM AT FRAME 20 WAS CRACKED BY MAINTENANCE PERSONNEL. THE CROSSBEAM WAS REPAIRED PER ERODESIGN REPORT NR 2117-1, REV IR, DATED 12-3-96.

Part: BUTT STRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE FWD FLOOR SUPPORT STRUCTURE CENTER BUTT STRAP CORRODED. REPLACED CENTER BUTT STRAP WITH NEW PART PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: CROSSBEAM — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE FLOOR SUPPORT RT CROSSBEAM AT FRAME 16 HAD CORROSION. REPLACED RT CROSSBEAM WITH NEW PART PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: BUTT STRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE FWD FLOOR SUPPORT STRUCTURE LT BUTT STRAP CORRODED. REPLACED LT BUTT STRAP WITH NEW PART PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51 AND AERODESIGN REPORT 31671-2, REV IR, DATED 12-4-96.

Part: BUTT STRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE FWD CENTER FLOOR SUPPORT STRUCTURE BUTT STRAP CORRODED. REPLACED CENTER BUTT STRAP WITH NEW PART PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: BUTT STRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE FWD FLOOR STRUCTURE RT BUTT STRAP CORRODED. REPLACED BUTT STRAP WITH NEW PART PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: SUPPORT SECTION — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE FWD RT SIDEWALL SEAT TRACK SUPPORTING SECTION CORRODED. REPLACED RT SUPPORT SECTION WITH NEW PART PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: STRINGER — CORRODED (BS 4088)

DURING 2C INSPECTION, FOUND FUSELAGE STRINGER 18L CORRODED AT FWD END, FS 4088.0. REPAIRED STRINGER PER AERODESIGN REPORT NR 1990-2, REV IR DATED 9-15-96.

Part: SILL — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE FWD FLOOR STRUCTURE RT SILL CORRODED. REPLACED SILL WITH NEW PART PER EMB120 SRM STANDARD PRACTICES CHAPTER 51.

Part: SILL — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE CENTER SECTION FLOOR SUPPORT STRUCTURE RT SILL CORRODED. REPLACED RT SILL WITH NEW PART PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: SUPPORT SECTION — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE FWD LT SIDEWALL SEAT TRACK SUPPORTING SECTION CORRODED. REPLACED SUPPORTING SECTION WITH NEW PART PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: SILL — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE FWD FLOOR SUPPORT STRUCTURE LT SILL CORRODED. REPLACED LT SILL PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: SKIN — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FUSELAGE INNER SKIN FOUND CORRODED AT PAX DOOR CUTOUT, BENEATH BOTTOM FWD DOOR CUTOUT REINFORCEMENT DOUBLER. THE DAMGE WAS REPAIRED PER AERODESIGN REPORT NR 2118-1, REV IR, DATED 12-3-96.

Part: BUTT STRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND FWD FUSELAGE FLOOR SUPPORT STRUCTURE LT BUTT STRAP CORRODED. REPLACED LT BUTT STRAP WITH NEW PART PER EMB120 SRM STANDARD PRACTICES, CHAPTER 51.

Part: ROLLER — WORN (RT TE FLAP)

FLAP DISAGREEMENT WARNING WHEN FLAPS RETRACTED. REPLACED THE RT OUTBOARD FLAP ROLLERS.

Part: WARNING HORN — ACTIVATED (CENTRAL WARNING)

TAKE OFF TRIM AURAL WARNING SOUNDED ON TAKEOFF ROLL. COULD NOT DUPLICATE DISCREPANCY. RESET AURAL WARNING UNIT AND ACFT CONTINUED SERVICE.

Part: PITOT SYST — CONTAMINATED (RIGHT)

COPILOT'S AIR SPEED INDICATOR FAILED DURING FLIGHT. CLEANED MOISTURE FROM COPILOT'S PITOT SYSTEM. ACFT RETURNED TO SERVICE.

Part: ACTUATOR — DEFECTIVE (LT TE FLAPS)

RECEIVED TAKEOFF FLAPS AURAL WARNING DURING TAKEOFF AND FLAP DISAGREEMENT WARNING WHEN FLAPS SELECTED UP AFTER TAKEOFF. REPLACED THE LT OUTBD FLAP ACTUATOR.

Part: CONTROL BOX — DEFECTIVE (LANDING GEAR)

WHEN LANDING GEAR SELECTED TO UP, THE A-SYSTEM DISAGREEMENT LIGHTS ILLUMINATED. CYCLED LANDING GEAR WITH SAME RESULTS. REPLACED THE LANDING GEAR CONTROL BOX.

Part: ACTUATOR — LEAKING (LT TE FLAP)

HYDRAULIC FLUID LEAKING FROM LT NACELLE FLAP AREA. REPLACED LEAKING NACELLE FLAP ACTUATOR.

Part: PACK — MALFUNCTIONED (RIGHT)

RT DUCT LEAK WARNING ACTIVATED WHILE RUNNING A/C PACKS ON APU BLEED AIR AND NOTED SOME SMOKE IN CABIN. PLACED RT A/C PACK ON DEFERRED MAINTENANCE LIST. ACFT CONTINUED SERVICE.

Part: HYDRAULIC PUMP — LEAKING (LT NACELLE)

FLIGHT CREW REPORTED, LEFT ELECTRIC HYDRAULIC PUMP LEAKING. REMOVED AND REPLACED ELECTRIC HYDRAULIC PUMP WITH SERVICEABLE UNIT.

Part: WOW SENSOR — DEFECTIVE (LT MLG)

LANDING GEAR SELECTOR HANDLE COULD NOT BE SELECTED TO RAISE THE LANDING GEAR. REPLACED THE LT MLG WEIGHT ON WHEELS PROXIMITY SENSOR.

Part: BOLTS — BROKEN (LT MLG WHEEL)

LEFT MAIN INBOARD WHEEL S/N 2280 HAD 6 WHEEL HALVE BOLTS SHEARED AND TIRE IS FLAT. DISASSEMBLED WHEEL ASSY, CLEANED AND INSPECTED WHEEL HALVES VISUALLY, NO DEFECTES NOTED. EDDY CURRENT WHEEL ASSY AND BOLT HOLES, NO DEFECTS NOTED.

Part: SUPPORT — CRACKED (LT/RT WING)

THE FOLLOWING P/N WING SKIN SUPPORTS WERE FOUND CRACKED, DURING INSPECTION TASK 5720-551/651-01I AND 5720-552/652-01I. THE SKIN SUPPORTS WERE REPAIRED IAW AERODESIGN REPORT NR 1327-2. P/N 120-17056-007, 8 EA; 120-17056-009, 1 EA; 120-17056-019, 1 EA; 120-17056-017, 2 EA; 120-17056-015, 3 EA; 120-17056-013, 2 EA; 120-17057-006, 1 EA; 120-17057-007, 1 EA; 120-17059-017, 1 EA; 120-17059-015, 1 EA.

Part: ACTUATOR — DEFECTIVE (LT TE FLAP)

FLAP CONTROL FAULT WARNING ACTIVATED. REPLACED LT NACELLE FLAP ACTUATOR.

Part: WIRE — DAMAGED (LT WING TIP)

NAVIGATION LIGHTS CIRCUIT BREAKER TRIPPED AND WILL NOT RESET. REPAIRED CHAFED WIRE IN LT WING TIP. AIRCRAFT RETURNED TO SERVICE.

Part: FRAME — CRACKED (LT NACELLE)

INSPECTION REVEALED THE LEFT NACELLE OUTBOARD BACK-UP FRAME, ON THE FWD SIDE OF THE HYDRAULIC BAY FIREWALL, TO BE CRACKED. THE BACK-UP FRAME WAS REPAIRED PER AERODESIGN REPORT NR 658-3, REV IR DATED 2-9-94.

Part: PRESS SWITCH — DEFECTIVE (RUDDER)

RUDDER, GREEN HYDRAULIC SYSTEM FAIL WARNING, DOES NOT FUNCTION. REPLACED RUDDER SYSTEM PRESSURE SWITCH.