N705S
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.
6 reports on file, 2000-04-09 – 2000-06-26.
Part: LIGHT — DEFECTIVE (COCKPIT) · airframe 37,989 hrs · 30,995 cycles
DURING SCHEDULED CHECK, THE COCKPIT EMERGENCY EXIT LIGHT WAS FOUND DIMLY ILLUMINATING. THE LIGHT ASSEMBLY WAS REPLACED. SUBSEQUENT SYSTEM CHECK WAS SATISFACTORY PER MM 33-51-01.
Part: INTERMED GEARBOX — LEAKING (NR 2 ENGINE) · airframe 37,919 hrs · 30,952 cycles
FLT 214 FROM IFP TO DTW: NR 2 ENGINE WAS SHUT DOWN IN FLIGHT FOR LOSS OF OIL QUANTITY AND PRESSURE. THE AIRCRAFT DIVERTED TO ABQ. INVESTIGATION REVEALED THAT THE LP5 PORT FITTING ON THE NR 2 ENGINE ACCESSORY GEARBOX WAS LOOSE DUE TO DAMAGED INTERNAL THREADS THUS CAUSING THE OIL LOSS. THE ACCESSORY GEARBOX WAS REPLACED PER P&W MM 72-60. AIRCRAFT WAS RETURNED TO SERVICE.
Part: CONTROL UNIT — MALFUNCTIONED (RUDDER) · airframe 37,902 hrs · 30,941 cycles
ON DESCENT INTO IFP, AIRCRAFT HAD UNCONTROLLED, MILD DUTCH ROLLING (LATER DESCRIBED AS FISH-TAILING) WITH AUTO-PILOT DISENGAGED. EXTENSIVE TROUBLESHOOTING REVEALED AN ANOMALY WITH THE MAIN RUDDER PCU YAW DAMPER SERVO CONTROL AS INDICATED THROUGH THE YAW DAMPER COUPLER BITE FUNCTION (REF: B-737 MM 22-12-01, PAGE 12). THE MAIN RUDDER PCU WAS REPLACED PER B-737 MM 27-21-91. SUBSEQUENT YAW DAMPER COUPLER BITE TESTS REVEALED NO FURTHER DISCREPANCY. THE AIRPLANE WAS TEST FLOWN AND RETURNED TO SERVICE.
Part: STRINGER — CORRODED (FUSELAGE) · airframe 37,868 hrs · 30,920 cycles
DURING COMPLIANCE WITH CPCP TASK C53-202-04, AD 90-25-01, STRINGER 27L AT BS 947.6 WAS FOUND CORRODED. THE DAMAGE WAS REPAIRED IN ACCORDANCE WITH THE 737-200 SRM 53-10-3, FIGURE 1.
Part: POWER SUPPLY — INOPERATIVE (CARGO BAY) · airframe 37,822 hrs · 30,891 cycles
DURING SCHEDULED CHECK, THE LT EXTERIOR OVERWING EMERGENCY EXIT LIGHT WAS FOUND INOPERATIVE. THE ASSOCIATED SYSTEM POWER SUPPLY WAS REPLACED PER MM 33-51-31. SUBSEQUENT SYSTEM TEST WAS SATISFACTORY.
Part: ACTUATOR — CRACKED (SPOILER) · airframe 37,685 hrs · 30,815 cycles
FLIGHT 214 IFP-SAT AFTER LANDING, DURING TAXI TO GATE, AIRCRAFT EXPERIENCED LOSS OF HYDRAULIC FLUID. IT WAS DETERMINED THAT THE NR 8 GROUND SPOILER ACTUATOR HOUSING HAD CRACKED AT THE PISTON END. THE ACTUATOR WAS REPLACED PER BOEING MM 27-62-101. HYDRAULIC SYSTEM PUMP CASE DRAIN FILTERS WERE REPLACED. HYDRAULIC SYSTEM WAS RE-SERVICED. AIRCRAFT RETURNED TO SERVICE.