N632NW
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
22 reports on file, 2004-01-06 – 2010-10-14.
Part: LIGHT — INOPERATIVE (CABIN) · airframe 93,931 hrs · 14,626 cycles
EMERGENCY LIGHT AT TOP OF UPPER DECK STAIRS IS INOP.
Part: SKIN — DAMAGED (PYLON) · airframe 93,931 hrs · 14,626 cycles
NR 3 PYLON I/B AFT SECTION OF LOWER SKIN DAMAGED AT NAC STA 240.
Part: FIRESHIELD — DAMAGED (PYLON) · airframe 93,931 hrs · 14,626 cycles
NR 3 PYLON I/B LOWER FIRESHIELD DAMAGED AT NAC STA 225.
Part: DOUBLER — CRACKED (FUSELAGE) · airframe 93,931 hrs · 14,626 cycles
BS 400 FUSELAGE FRAME DOUBLER CRACKED AT STR 15L.
Part: FIRESHIELD — DAMAGED (PYLON) · airframe 93,931 hrs · 14,626 cycles
NR 3 PYLON FIRESHIELD DAMAGED AT NAC STA 237.
Part: FRAME — CRACKED (FUSELAGE) · airframe 93,931 hrs · 14,626 cycles
BS 520 FUSELAGE FRAME CRACKED BETWEEN STR 10R AND STR 10A R.
Part: STOP FITTING — CRACKED (FUSELAGE) · airframe 93,931 hrs · 14,626 cycles
R-3 MAIN ENTRY DOOR OPENING FORWARD DOOR STOP FITTING CRACKED, BS 1273, WL 233.
Part: FRAME — CRACKED (FUSELAGE) · airframe 93,931 hrs · 14,626 cycles
BS 520 FUSELAGE FRAME CRACKED BETWEEN STR 8R AND STR 9R.
Part: FRAME — CRACKED (FUSELAGE) · airframe 93,931 hrs · 14,626 cycles
BS 520 FUSELAGE FRAME CRACKED BETWEEN STR 9R AND 10R.
Part: FRAME — CRACKED (PYLON) · airframe 93,931 hrs · 14,626 cycles
NR 4 PYLON I/B FRAME CRACKED AT NAC STA 221 BULKHEAD.
Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 93,931 hrs · 14,626 cycles
MAIN DECK STA-1239 BETWEEN STR-11R AND STR-10R CORROSION ON SKIN.
Part: FRAME — CRACKED (FUSELAGE) · airframe 93,931 hrs · 14,626 cycles
STA 200 FRAME HAS 1 INCH CRACK AT STR 14B RT CUTOUT.
Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 93,931 hrs · 14,626 cycles
STA -1800 TO STA -1820 AT STR -51L HAS CORROSION.
Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 93,931 hrs · 14,626 cycles
STA -740 AT STR-47L HAS AREA OF BULGING SKIN.
Part: STRAP — CRACKED (FUSELAGE) · airframe 93,931 hrs · 14,626 cycles
CRACKED FRAME STRAP AT STA -800 BELOW STR-16L APPROX .250 INCH.
Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 93,931 hrs · 14,626 cycles
STA - 1810 AT STR - 51R HAS AREA OF BULGING SKIN.
Earlier reports · 2004–2008 · 6 reports
2008
Part: BATTERY — DISCHARGED (CABIN) · airframe 90,967 hrs · 14,067 cycles
DURING OVERNIGHT LINE CHECK FOUND UPPER DECK ESCAPE SLIDE LIGHTS INOP. MX R&R BATTERY. OPS CHECKED GOOD AND ACFT WAS RETURNED TO SERVICE.
Part: TIRE — WORN (MLG) · airframe 89,257 hrs · 13,744 cycles
PERFORMED ABORTED TAKEOFF AT 120 KNOTS. EXPERIENCED HIGH VIBRATION DURING T/O ROLL THAT GOT WORSE AND A DRAGGING SENSATION FROM THE RIGHT SIDE OF AIRCRAFT. RETURNED TO GATE AND FOUND BOTH NOSE TIRES WORN ON LEFT EDGE. MAINTENANCE REMOVED AND REPLACED BOTH NOSE TIRES AND CHECKED ALL MAIN AND BODY TIRES FOR BRAKE FREE RUN. OPERATIONAL CHECKED GOOD AND AIRCRAFT WAS RETURNED TO SERVICE.
2007
Part: WIRE — CHAFED (NR 4 ENGINE GEN) · airframe 87,166 hrs · 13,317 cycles
AT ROTATION THE FIRE DETECTION LIGHT ON THE FOREWARD PANEL AND THE FAULT LIGHT ON THE S/O PANEL FLASHED (4 TO 5 TIMES). THE NACELLE TEMP GAUGE NR 4 ENGINE, A LOOP WAS FLUCTUATING BETWEEN 3 AND 8. DUE TO PREVIOUS HISTORY RETURNED TO LAND. RETURNED TO YWG AND LANDING WAS UNEVENTFUL. MAINTENANCE PREPARED AIRCRAFT FOR A 3 ENGINE FERRY FLIGHT TO MSP FOR REPAIRS. MAINTENANCE FOUND NR 4 ENGINE GENERATOR WIRES WERE CHAFED AND SHORTED TO NR 4 ENGINE A LOOP. REMOVED AND REPLACED NR 4 ENGINE. OPERATIONAL CHECKED GOOD, AND AIRCRAFT RETURNED TO SERVICE.
Part: CIRCUIT CARD — BURNED (FIRE DETECTION) · airframe 87,165 hrs · 13,315 cycles
DURING CRUISE, HAD INDICATION OF FAULT ON NR 4 ENGINE FAULT GAUGE. NEEDLE BOUNCING BETWEEN 6 AND 8 WITH FLASHING FAULT LIGHT/FIRE DETECTION LIGHT. FAULT LIGHT CAME ON STEADY. THEN PERFORMED COM 2.26.32. THEN SMELLED ODOR OF BURNING INSULATION AND/OR ELECTRICAL FLAMES. S/O OBSERVED ODOR/FLAMES WITHIN THE P-6 C/B PANEL UPPER PORTION BEHIND FIRE DETECTION CONTROL PANEL. AT THAT POINT, PERFORMED ELECTRICAL FIRE OR SMOKE RED BORDERED CHECKLIST AND INITIATED EMERGENCY DESCENT, DECLARED EMERGENCY. ENGINE FIRE DETECTION 3A-4A C/B OPENED POPPED. CONTINUED COM 2.26.6. FLAMES STILL IN VIEW AND INCREASING IN INTENSITY. AT THE POINT OF TRIPPING GBâS FOR THE NR 1 AND NR 2 GENERATORS, THE FLAMES DIMINISHED AND EVENTUAL
2006
Part: BOLT — SHEARED (HYD FITTING) · airframe 83,959 hrs · 1,265 cycles
DURING APPROACH, AND AFTER GEAR EXTENSION, NR 1 HYDRAULIC SYSTEM QUANTITY WENT TO ZERO. SYSTEM NR 1 FAILURE. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND INBOARD FLAP CONTROL MODULE HYDRAULIC INLET LINE FITTING MOUNT BOLTS (3) SHEARED. REMOVED AND REPLACED FLAP CONTROL MODULE, PRESSURE MODULE FILTERS, EDP & ADP. OPERATION CHECKED GOOD, AIRCRAFT RETURNED TO SERVICE. Â
2004
Part: PUMP — MALFUNCTIONED (FUEL SYSTEM) · airframe 74,540 hrs · 11,094 cycles
AT FL380, THE CREW OBSERVED DECREASING PARAMETERS ON THE NR 4 ENGINE. THE COM PROCEDURES WERE FOLLOWED BUT THE ENGINE REMAINED AT IDLE. ALL INDICATIONS REMAINED IN THE NORMAL RANGE, SO THE ENGINE WAS LEFT AT IDLE POWER. WHEN DESCENDING THROUGH 8000 FEET ON APPROACH, THE ENGINE ROLLED BACK BELOW IDLE AND THE CREW SECURED THE ENGINE. THE FLIGHT CONTINUED TO ITS DESTINATION LANDING WITHOUT INCIDENT. MAINTENANCE REPLACED THE ENGINE DRIVEN FUEL PUMP, FUEL CONTROL, AND FUEL HEAT VALVE. AN ENGINE RUN AND LEAK CHECK WERE COMPLETED WITH NORMAL INDICATIONS.