N130G

Part: LIGHT — ILLUMINATED (ENG FUEL FILTER) · airframe 27,502 hrs · 32,129 cycles

ABORTED TAKEOFF AT 90 - 100 KNOTS DUE TO FUEL LIGHT ON MAIN ANNUNCIATOR PANEL. DUE TO ABORT COULDN''T TELL WHICH SIDE HAD LOW FUEL PRESSURE. FOUND THE LEFT FUEL FILTER LIGHT WAS ILLUMINATING. REMOVED AND REPLACED LEFT LOW PRESS FUEL FILTER IAW MM 73-00-00. OPS AND LEAKS CHECKS GOOD. REPLACED CANNON PLUG ON LOW PRESS FILTER AND INSPECTED WIRE BUNDLE. ALL CHECKS GOOD.

Part: FCU — FAILED (TE FLAPS) · airframe 27,451 hrs · 32,058 cycles

OUTBOARD PAIR OF FLAPS DID NOT EXTEND BEYOND 25 DEGREES TO 45 DEGREES (LAST 2 SEGMENTS) WHEN COMMANDED. DIVERTED TO RDD FROM CEC. RERACKED FLAP CONTROL UNIT. OPS CHECKS GOOD.

Part: ALTIMETER — MALFUNCTIONED (COCKPIT) · airframe 27,340 hrs · 31,895 cycles

AT 2000 FT ON CAPTAINS ALTIMETER, FIRST OFFICERS ALTIMETER READS 2100 FT. AT 5000 FT ON CAPTAINS ALTIMETER FIRST OFFICERS READS 5200 FT, AT 8000 FT ON CAPTAINS ALTIMETER FIRST OFFICERS ALTIMETER READS 8250 FT AND AT 14000 FT FIRST OFFICERS READS 14300 FT. TROUBLESHOT PILOTS AND CO-PILOTS ALTIMETER SYSTEMS. CHECKED BOTH SYSTEMS IAW FAR 91.41 AND 91.413 AND SWA ST 34-302, SYSTEMS OPS CHECKS GOOD. NO DISCREPANCIES FOUND.

Part: SEQUENCE VALVE — OUT OF ADJ (RT MLG DOOR) · airframe 27,150 hrs · 31,639 cycles

AFTER TAKEOFF, RIGHT MAIN GEAR WOULD NOT RETRACT. RETURNED TO PDX. FOUND RIGHT GEAR DOOR SEQUENCE VALVE OUT OF ADJUSTMENT. ADJUSTED PER MM 32-32-04. PERFORMED MULTIPLE GEAR SWINGS. OPS CHECKS GOOD.

Part: DPU — FAILED (NR 2)

CO-PILOT EHSI WENT BLANK IN FLIGHT. COULD NOT TRANSFER ANY NAVIGATION INFORMATION TO SCREEN. RETURN TO LAX, INSTALLED SERVICEABLE DPU 864 ON NR 2 SIDE. OPS CK GOOD, SN: 7059, SN OFF: 4381.

Part: CONTROL UNIT — MALFUNCTIONED (TE FLAP)

ON CLIMB-OUT, CONTROL FAULT APPEARED WITH FLAP HANDLE UP, OVERHEAD FLAP CONTROL PANEL INDICATED NAC WAS FULLY EXTENDED. CONTROL FAULT INITIALLY WOULD NOT RESET, RESET SUCCESSFUL PER QRH 3RD TRY. RETURNED TO PDX. REPLACED FLAP CONTROL UNIT IAW 270000 AND CLEANED ACTUATOR CANNON PLUGS. OPS CHECKS GOOD ON GROUND AND PASSED SUCCESSFUL TEST FLIGHT. PN ON: 3075001001, SN: 0133, SN OFF: 0167.

Part: CONTROLLER — MALFUNCTIONED (TE FLAP)

CONTROL FAULT ILLUMINATED IN FLIGHT AND WOULD NOT CANCEL. FAULT CORRECTED ITSELF AFTER 5 MINUTES. RETURNED TO SEA. PERFORMED FUNCTIONAL TEST PER MM 275000. FUNCTIONAL TEST GOOD, NO DISCREPENCIES NOTED. UNABLE TO DUPLICATE PROBLEM.

Part: OIL SYST — REQD SERVICE (LT ENGINE)

OIL PRESSURE 1 WARNING AT V1 AND INTERMITTENT PRESSURE DROPS DURING CLIMBOUT. RETURNED TO AIRPORT. VISUALLY INSPECTED LEFT ENGINE AND NO OIL LEAKS EVIDENT. INSPECTED FILTER BY PASS AND CHIP DETECTOR LIGHTS, CHECKS NORMAL. SERVICED ENGINE WITH 2 QUARTS EXXON 2380 TURBINE OIL. PERFORMED GROUND RUN AND ALL PARAMETERS NORMAL.

Part: AHRS — OUT OF ADJUST (NR 1 & 2)

RECEIVED HEADING FLAG, RMI FLAG BOTH SIDES WITH GYRO PRECESSING ALL THE TIME INFLIGHT. RETURNED TO LAX. RE-ORIENTED NR 1 AND NR 2 AHRS IAW MM 34-00-00. OPERATED SYSTEM ON GROUND AND ALL CHECKS OK.

Part: WHEEL — CRACKED (MLG)

MECHANIC REMOVED WHEEL ASSEMBLY FROM A/C DUE TO TIRE WAS FOUND FLAT. WHEEL SHOP INFLATED TIRE AND FOUND INBOARD HALF CRACKED AT BOTTOM OF KEY INSERT BOSS. WHEEL HALF (P/N 300-604-1) HAS BEEN REMOVED FROM SERVICE.

Part: ACM — FAILED (LEFT)

LAV SMOKE DETECTOR ACTIVATED. CABIN FILLED WITH SMOKE. REPLACED THE LEFT AIR CYCLE MACHINE.

Part: SIGN — LOOSE (CABIN)

EMERGENCY EXIT SIGN AT ROW 5C IS LOOSE. REPLACED SIGN ASSY.

Part: SIGN — BROKEN (CABIN)

EMERGENCY EXIT SIGN AT 5C BROKEN. REPLACED EXIT SIGN.

Part: SAFETY PIN — NOT REMOVED (RT MLG)

THE RT MLG WOULD NOT RETRACT. REMOVED DOWN LOCK SAFETY PIN FROM LANDING GEAR.

Part: FLAP WARNING — ILLUMINATED (COCKPIT)

FLAPS FAIL WARNING DURING TAKEOFF ROLL. INSPECTED FLAP SYSTEM, FOUND NO DEFECTS. COULD NOT DUPLICATE DISCREPANCY.

Part: LEAD — BROKEN (RT PROPELLER)

RT PROPELLER DE-ICE SYSTEM INOP. REPLACED DEFECTIVE ELECTRICAL LEAD ON RT PROPELLER.

Part: DOOR — NOT LATCHED (FUEL SERVICE)

SERVICE DOOR WARNING DURING TAKEOFF. FOUND THE FUEL SINGLE POINT SERVICE DOOR UNLATCHED. SECURED DOOR LATCHES AND AIRCRAFT CONTINUED SERVICE.

Part: CONTROL — MALFUNCTIONED (LANDING GEAR)

NLG GREEN LIGHTS ARE INTERMITTENT. COULD NOT DUPLICATE DISCREPANCY. REPLACED THE LANDING GEAR CONTROL FOR TROUBLESHOOTING.

Part: PITCHLOCK SCREW — BENT (FEATHER STOP TAB)

ACTUATOR ASSEMBLY REMOVED ORIGINALLY FOR PROPELLER FEATHERING PROBLEMS. UPON INITIAL RECEIVING INSPECTION THE FEATHER STOP TAB S/N S0159 WAS FOUND TO BE BENT APPROXIMATELY 0.25 INCH. PITCHLOCK SCREW WAS REMOVED FROM ASSEMBLY AND RETURNED TO MANUFACTURER. PART TOTAL CYCLES, 20,016.

Part: TEST SWITCH — STICKS (COCKPIT)

COPILOTS STALL WARNING SYSTEM ACTIVATES PERIODICALLY. TEST BUTTON IS STICKING. REPLACED THE STALL WARNING TEST PANEL.

Part: CONTROL UNIT — MALFUNCTION (LANDING GEAR)

AFTER TAKEOFF, WHEN LANDING GEAR SELECTED UP, THE LT MLG INDICATED DOWN. CYCLED GEAR CONTROL WITH SAME RESULTS. ELECTRICAL OVERRIDE PROCEDURE WAS USED TO EXTEND LANDING GEAR FOR LANDING. REPLACED THE LANDING GEAR CONTROL ASSY.

Part: ANNUNCIATOR — MALFUNCTIONED (INST PANEL)

REPEATED FLAP CONTROL FAULT WARNINGS DURING FLIGHT. REPLACED THE FLAP ANNUCIATOR UNIT.

Part: SEALS — WORN (LT PROP)

LEFT PROPELLER IS SLOW TO FEATHER OR UNFEATHER. REPLACED PROPELLER TRANSFER TUBE SEALS.

Part: SEAT TRACK — CORRODED (CABIN)

DURING 2C INSPECTION, FOUND SEAT TRACKS FOR LEFT HAND SIDE PASSENGER SEATS TO BE CORRODED. REMOVED CORRODED SEAT TRACKS AND REPLACED WITH SERVICEABLE TRACKS.

Part: FLOOR BEAM — CORRODED (FWD FUSELAGE)

DURING 2C INSPECTION, THE FLOOR BEAM NEXT TO THE ELEVATOR CONTROL COLUMN RIGHT WAS FOUND WITH SURFACE CORROSION. CLEANED, TREATED AND PAINTED AREA PER M/M 51-21-04.

Part: BUTT STRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION, SEVERAL RIVETS WERE FOUND LOOSE OR WITH CORROSION AT ENTRY FLOOR, LT BUTT STRAP. REMOVED AND REPLACED WITH ORIGINAL TYPE AND SIZE RIVETS, 19 TOTAL PER EMB 120 SRM CHAPTER 51.

Part: SUPPORT SECTION — CORRODED (CABIN)

DURING 2C INSPECTION, FOUND PASSENGER SEAT RIGHT HAND SIDE WALL SEAT TRACK SUPPORT SECTION CORRODED ON SURFACE. CLEANED, TREATED, PAINTED CORRODED AREA PER EMB 120 M/M 51-21-04, OK FOR SERVICE.

Part: FLOOR BEAM — CORRODED (FWD FUSELAGE)

DURING 2C INSPECTION, THE FLOOR BEAM NEXT TO THE ELEVATOR CONTROL COLUMN LEFT WAS FOUND WITH SURFACE CORROSION. CLEANED, TREATED AND PAINTED AREA PER M/M 51-21-04.

Part: TRACK — CORRODED (GALLEY FLOOR)

DURING 2C INSPECTION, FOUND GALLEY FLOOR ATTACHMENT TRACK TO BE CORRODED. REMOVED CORRODED TRACK AND REPLACED WITH A SERVICEABLE TRACK.

Part: BOLT — RUSTED (NLG)

DURING 2C INSPECTION, FOUND FORWARD INBOARD CORNER OF BATTERY COMPARTMENT AT FRAME 4 TO HAVE SIGNS OF CORROSION. FURTHER INSPECTION FOUND NOSE GEAR FORWARD DOOR, AFT HINGE, HARDWARE TO BE CORRODED. REPLACED HARDWARE AND CLEANED BATTERY COMPARTMENT.

Part: FLOOR BEAM — CORRODED (UNDER GALLEY)

DURING 2C INSPECTION, FOUND SURFACE CORROSION ON FLOOR BEAM THAT GALLEY FLOOR ATTACHMENT TRACK MOUNTS TO. REMOVED SURFACE CORROSION TREATED AREA AND PAINTED TO SERVICEABLE CONDITION.

Part: BUTT STRAP — CORRODED (FWD FUSELAGE)

DURING 2C INSPECTION, FOUND BUTT STRAPS TO HAVE SURFACE CORROSION. CLEANED, TREATED AND PAINTED AREA PER EMB M/M 51-21-04.

Part: CROSS BEAM — CORRODED (FLOOR SUPPORT)

DURING 2C INSPECTION, FOUND PASSENGER FLOOR SUPPORT CROSSBEAM T-SECTION CORRODED AT FUSELAGE FRAME 16. REMOVED CORRODED T-SECTION, LOCATED, DRILLED AND INSTALLED NEW PART PER EMB 120 SRM STANDARD PRACTICES.

Part: STRINGER — CORRODED (FUSELAGE)

DURING 2C INSPECTION, FOUND STRINGERS IN LOWER FUSELAGE AREA BELOW LAV TO HAVE SURFACE CORROSION. CLEANED LIGHT CORROSION, TREATED AND PAINTED PER M/M 51-20-04.

Part: SEAT TRACK — CORRODED (CABIN)

DURING 2C INSPECTION, FOUND SEAT TRACKS FOR RIGHT HAND SIDE PASSENGERS SEATS TO BE CORRODED. REMOVED CORRODED SEAT TRACKS AND REPLACED WITH SERVICEABLE TRACKS.

Part: SUPPORT SECTION — CORRODED (CABIN)

DURING 2C INSPECTION, FOUND PASSENGER SEAT LEFT HAND SIDE WALL SEAT TRACK SUPPORT SECTION CORRODED ON SURFACE. CLEANED, TREATED, PAINTED CORRODED AREA PER EMB 120 M/M 51-21-04, OK FOR SERVICE.

Part: BOLT — BROKEN (RT INBD WHEEL)

ON PREFLIGHT INSPECTION, MECHANIC NOTICED TWO BOLTS MISSING FROM THE RIGHT MAIN INBOARD WHEEL ASSEMBLY. BOLTS ARE PRESUMED TO HAVE BROKEN AND FALLEN OUT. WHEEL/TIRE ASSEMBLY WAS REMOVED AND REPLACED.

Part: ROLLER — WORN (CARGO DOOR)

CARGO DOOR WILL NOT OPEN. FORWARD LOWER ROLLER CAME OUT OF THE TRACK. REPLACED DOOR ROLLER, OPERATES NORMAL.

Part: BOLT — MISSING (LT MLG DOOR)

LEFT MLG INTRANSIT INDICATOR REMAINED ON AFTER LANDING GEAR RETRACTED. REPLACED MISSING BOLT ON INBOARD FORWARD GEAR DOOR LATCH HANDLE. ACFT RETURNED TO SERVICE.

Part: FCU — DEFECTIVE (LT ENGINE)

LEFT ENGINE WILL NOT START. REPLACED THE LEFT ENGINE FUEL CONTROL UNIT.

Part: LATCH ASSY — BROKEN (LT MLG DOOR)

THE LEFT MAIN LANDING GEAR DID NOT RETRACT. REPLACED A BROKEN LANDING GEAR DOOR LATCH ASSEMBLY.

Part: ANTENNA — DEFECTIVE (RADAR BAY)

RADAR CIRCUIT BREAKER TRIPPED AND WOULD NOT RESET. REPLACED THE RADAR ANTENNA.

Part: TRANSPONDER — DEFECTIVE (NR 2)

NR 2 TRANSPONDER INOPERATIVE. REPLACED THE NR 2 TRANSPONDER.

Part: PCU — DEFECTIVE (RT ENGINE)

RT PROPELLER FEATHERED DURING TAKEOFF. FDR DATA INDICATED TORQUE REACHED 132 PERCENT. REPLACED PROPELLER DUE TO OVER TORQUE AND REPLACED PROPELLER PITCH CONTROL FOR UNCOMMANDED FEATHERING.

Part: SUPPORT — CRACKED (LT/RT WINGS)

THE FOLLOWING P/N WING SKIN SUPPORTS WERE FOUND CRACKED DURING INSPECTION TASK NR 5720-551/651-01I AND 5720-552/652-01I. THE SKIN SUPPORTS WERE REPAIRED IAW AERODESIGN REPAIR 1327-2. P/N: 120-17062-005, 1 EA; 120-17056-017, 2 EA; 120-17056-015, 4 EA; 120-17056-013, 2 EA; 120-17057-005, 1 EA; 120-17057-007, 2 EA; 120-17056-011, 1 EA; 120-17056-019, 1 EA; 120-17057-006, 1 EA; 120-17059-017, 1 EA.

Part: LATCH — BROKEN (LT MLG DOOR)

LT MLG INBD GEAR DOOR DOES NOT CLOSE. REPAIRED BROKEN LATCH ASSY ON LANDING GEAR DOOR.

Part: SKIN — CORRODED (FUSELAGE)

INSPECTION REVEALED SEVERE CORROSION TO THE LOWER FUSELAGE SKIN AT FRAME 21, BETWEEN STRINGERS 21L AND 21R. THE DAMAGED AREA WAS REMOVED AND AN EXTERNAL DOUBLER AND FILLER REPAIR WAS INSTALLED PER AERODESIGN REPORT NR 1437-2.

Part: LINE ASSY — CHAFED (PARKING BRAKE)

RT HYDRAULIC SYSTEM LOST ALL PRESSURE AND QUANTITY. REPLACED THE PARKING BRAKE ACCUMULATOR PRESSURE SUPPLY LINE, DUE TO CHAF DAMAGE.