N63BV
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
DURING CRUISE AT FL240 APPROX 80 TO 90 MILES FROM KCPR, THE RT SIDE FRONT WINDSHIELD CRACKED. AT THE TIME, THE TEMPERATURE OUTSIDE WAS -38 DEGREES CELSIUS AND THE WINDSHIELD HEAT WAS OFF WITH CLEAR SKIES OBSERVED. THE PILOT CONTACTED ATC AND LET THEM KNOW THE WINDOW WAS BROKEN AND THE PRESSURIZATION WAS HOLDING. AFTER LOOKING AT THE CHECKLIST FOR THIS PROBLEM, THE PILOT ASCERTAINED THE INNER PANEL WAS BROKEN AND REQUESTED A DESCENT. THE PILOT WAS GIVEN DISCRETION TO 15,000 FEET. THE PILOT CALLED INTO FLIGHT CONTROL AND WAS ADVISED TO RETURN TO DEPARTURE. THE PILOT RETURNED AND NO FURTHER ISSUES WERE OBSERVED WITH THE FLIGHT. THE PILOT COORDINATED WITH THE PASSENGERS AND ATC WITH NO ISSUES.
DURING TAKEOFF ROLL OF THE AC, AT THE POINT OF LIFTOFF, THE PILOT NOTICED THE LT ENGINE UPPER AFT COWLING HAD COME OPEN. THE TAKEOFF WAS ABORTED AND THE AC CAME TO A SAFE STOP ON THE RUNWAY. THE PILOT SHUTDOWN THE LT ENGINE AND TAXIED BACK TO THE HANGAR ON THE RT ENGINE. MAINT INSPECTED THE COWLING AND WAS UNABLE TO FIND ANY MECHANICAL REASON FOR THE COWLING TO HAVE COME OPEN. THERE WAS DAMAGE TO THE LT UPPER AFT COWLING AND TO THE UPPER NACELLE AREA AFT OF THE ENGINE FIREWALL. THERE WAS DAMAGE TO THE HINGE POINT OF THE ENGINE COWLING ON THE LT SIDE OF THE COWLING; HOWEVER THE COWLING DID NOT DEPART THE AC. THE ENGINE WAS INSPECTED FOR POSSIBLE INGESTION OF DEBRIS AND NONE WAS NOTED. BOTH COWLING LATCHES
DURING A DETAILED INSPECTION OF THE AIRCRAFT THE RUDDER TRIM TAB HORN BUSHING WAS FOUND TO BE WORN BEYOND ALLOWED LIMITS. REPLACEMENT OF THE HORN IN THE TRIM TAB IS NOT A GOOD OPTION, DUE TO THE AMOUNT OF DISASSEMBLY OF THE TAB IN ORDER TO ACCOMPLISH THE TASK. A REPLACEMENT TRIM TAB WAS PURCHASED. DURING THE INSPECTION OF THE NEW TRIM TAB IT WAS NOTED THAT THE WATER DRAIN HOLE REQUIRED BY AD 91-12-12, AMENDMENT 39-7023 WHICH HAS BEEN SUPERSEDED BY AD 92-07-05 AMENDMENT 39-8201, WHICH WAS EFFECTIVE APRIL 30, 1992, WAS NOT INSTALLED ON THE NEW TAB. THESE AIRWORTHINESS DIRECTIVES REFER TO BEECHCRAFT SERVICE BULLETIN 2365 DATED JANUARY 1991. THE REPLACEMENT TRIM TAB RECEIVED WAS MANUFACTURED ON 03-05-2002.
AFTER LANDING THE PILOT WROTE UP, RIGHT BRAKE HAS INTERMITTENT RAPID CYCLES OF, ON AND OFF BRAKE PRESSURE. ALSO INDICATED, APPEARS TO BE LEAKING HYDRAULIC FLUID. MAINTENANCE INSPECTED THE BRAKE AND FOUND THE INNER BRAKE CARRIER LINING BROKEN. THE PIECE OF THE INNER CARRIER LINING ASSEMBLY, APPROXIMATELY 3 INCHES LONG HAD BROKEN OFF AND WAS BECOMING WEDGED BETWEEN THE BRAKE HOUSING AND THE WHEEL ASSEMBLY. THE BROKEN PIECE HAD DAMAGED THE INNER WHEEL HALF ENOUGH TO CAUSE REJECTION OF THE WHEEL FORM FURTHER SERVICE. VISUAL INSPECTION OF THE BROKEN PIECE INDICATES IT HAD BECOME HOT AT SOME POINT IN TIME. IF THE BRAKE HAD NOT BEEN INSPECTED AT THIS TIME THE WHEEL MAY HAVE SEPARATED AT THE INNER WHEEL BEAD AREA
DURING COMPLIANCE OF SB 32-3134 AND AD 2002-01-10, RIGHT LANDING GEAR UPPER TORQUE KNEE WAS FOUND TO BE CRACKED AT PROTRUSION OF CENTER LUG. THIS UNIT HAD BEEN INSPECTED MULTI TIMES PRIOR TO THIS INSPECTION AND PASSED THOSE INSPECTIONS. UNITS EXACT TOTAL TIME AND TOTAL LANDINGS IS UNKNOWN, BUT IS IN EXCESS OF 6000 HOURS AND 6000 LANDINGS. UNIT HAD BEEN INSPECTED 748.4 HOURS AND 953 LANDINGS AND 18 MONTHS PRIOR TO THIS INSPECTION. NOTE: AD 2002-01-10 AND SB 31-3134 HAVE DIFFERENT COMPLIANCE INTERVALS. INDICATES TORQUE KNEES ARE TO BE INSPECTED IAW SB 32-3134, WHICH COULD RESULT IN CONFUSION. EITHER SB OR THE AD SHOULD BE AMENDED TO MAKE THE COMPLIANCE INTERVALS SAME, EITHER BY HOURS OR BY LANDINGS.
DURING THE COMPLIANCE OF RAYTHEON RECURRING SERVICE BULLETIN 32-3134, INSPECTION OF THE MAIN LANDING GEAR TORQUE KNEE'S, CRACKS WERE FOUND IN THE RADIUS AREA OF THE UPPER TORQUE KNEE, ON EACH SIDE OF THE SINGLE LUG. THE CRACK IN THIS WAS IN THE AREA NOTED TO BE INSPECTED ON THE SERVICE BULLETIN. THE TOTAL TIME AND TOTAL LANDINGS ON THE SPECIFIC UNIT ARE UNKNOWN. THIS UNIT WAS INSPECTED AT 980 LANDINGS PRIOR TO THIS AND UNIT WAS FOUND TO BE OK AT THAT TIME.
THE RIGHT INBOARD LANDING GEAR ACTUATOR SUPPORT BRACKET IS CRACKED AT THE BOTTOM AREA OF THE BRACKET WHERE IT ATTACHES TO THE WING SPAR STRUCTURE. THE WING SPAR STRUCTURE IS NOT EFFECTED BY THIS CRACK. THE CRACK IS APPROXIMATELY .5 INCH LONG AND IS THE RADIUS OF THE FLANGE OF THE BRACKET. THE PART NUMBER OF THE SUPPORT BRACKET IS 50-120077-17.
DURING TAKEOFF ROLL, PILOT HEARD A LOUD BANG. WHEN AIRCRAFT CAME TO A STOP, THE OUTBOARD WHEEL HALF HAD SPLIT IN HALF STARTING AT INBOARD WHEEL HALF MATING FLANGE AND CRACK WORKING ITS WAY TOWARD WHEEL BEAD AREA.