N400WA
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
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.
4 reports on file, 1996-09-01 – 1999-09-24.
Part: ENGINE — FAILED (RIGHT)
DURING THE TURN FROM BASE TO FINAL APPROACH, THE RT ENGINE FLAMED OUT. THE PILOT MADE AN UNEVENTFUL LANDING. MAINTENANCE PERSONNEL FOUND THE ENGINE INLET DE-ICE VALVE CANNON PLUG LOOSE ALLOWING ICE ACCUMULATION THAT EVENTUALLY WAS INGESTED RESULTING IN THE FLAMEOUT. A VISUAL INSPECTION OF THE FIRST IMPELLER SHOWED NO APPARENT DAMAGE. THE ENGINE WAS THEN RUN WITH ALL INDICATIONS NORMAL.
Part: RELAY — FAILED (MLG)
ON APPROACH FOR LANDING, PILOT SELECTED LANDING GEAR DOWN, BUT THE GEAR REMAINED IN THE UP POSITION. PILOT ALSO REPORTED A SMELL LIKE 'ELECTRICAL SMOKE'. MAINTENANCE PERSONNEL PUT ACFT ON JACKS AND PERFORMED A RETRACTION TEST, AND THE GEAR RETRACTED NORMALLY. HOWEVER, WHEN THE GEAR DOWN POSITION WAS SELECTED, THE GEAR FAILED TO EXTEND. THE LANDING GEAR DYNAMIC BRAKE RELAY WAS REPLACED, AND THE SYSTEM FUNCTIONED NORMALLY. OLD RELAY SHOWED NO EXTERNAL SIGNS OF DAMAGE, AND NO C/B'S TRIPPED DURING MALFUNCTION. INTERNAL INVEST OF RELAY FOUND CONTACT POINTS PITTED AND SIGNS OF ARCING. SUBMITTER SUGGESTED THE CONTACT POINTS BE INSPECTED ON A 5-YEAR BASIS.
Part: PLENUM ASSEMBLY — CRACKED (BLEED AIR)
DURING A FUEL NOZZLE TIME CHANGE, FOUND A ONE INCH CRACK IN THE PLENUM BETWEEN THE BLEEED AIR BOSS AND P2 BOSS. THIS IS AN AREA WHERE THE WELDS FOR THE TWO BOSSES TOUCH AT THEIR OUTER EDGES, AND THIS IS WHERE THE CRACK OCCURRED. THE CRACKS EXTEND .1250 INCH PAST THE WELDED AREA BOTH FORE AND AFT. IT IS LIKELY THE CRACKS WOULD HAVE CONTINUED TO EXPAND. SUBMITTER STATED POSSIBLE CAUSE IS THAT ONE OR BOTH OF THE BOSSES WERE IMPROPERLY WELDED TO THE PLENUM, THOUGH FROM OUTWARD APPEARANCE THE WELDS LOOKED GOOD AND SUGGESTED THIS AREA BE CLOSELY INSPECTED AT ALL REGULAR ENGINE INSPECTIONS.
Part: ELEVATOR — FABRIC FAILED (ELEVATOR LT)
ELEVATOR FABRIC FAILED IN-FLIGHT CAUSING SEVERE CONTROL SURFACE FLUTTER. DAMAGE TO ELEVATOR ATTACH POINT HINGE. LEFT ELEVATOR TRIM ACTUATOR DEPARTED THE AIRCRAFT. FABRIC WAS VERY OLD AND HAD NUMEROUS REPAIRS. REMOVED ELEVATOR AND REPLACED WITH METALLIZED ELEVATOR PER HAMILTON AVIATION CO. STC NR SA2815 WE. TAT: 15,998.5 HOURS.