TULSAIR BEECHCRAFT, INC.

Part: ENGINE — FAILED (RIGHT) · airframe 1,472 hrs · 969 cycles

CREW REPORTED OILY SMOKE ODOR IN CABIN. ISOLATED SOURCE TO RT ENGINE BLEED AIR. RT ENGINE "SHUDDERED" AND BEGAN INCREASING ITT. CREW SHUTDOWN NR 2 ENGINE AND DIVERTED.

Part: WHEEL HALF — FAILED (ZONE 700) · airframe 7,762 hrs · 5,637 cycles

PRIOR TO LIFTOFF, THE OUTER RIM OF THE RIGHT INBD MAIN WHEEL SEPARATED FROM THE WHEEL ASSEMBLY. THE FLIGHT CREW WAS NOTIFIED BY RADIO THAT A "TIRE BLEW" DURING TAKEOFF. THE ACFT RETURNED TO BASE AND MADE AN UNEVENTFUL LANDING. BOTH RT MAIN WHEEL ASSEMBLIES WERE REPLACED WITH NEW UNITS.

Part: WIRE — CHAFED (FIRE DETECTION)

APU FIRE DETECT CIRCUIT BREAKER POPPED ON RT COCKPIT CIRCUIT BREAKER PANEL DURING POWER UP OF AIRCRAFT. TROUBLESHOT SYSTEM FOUND WIRING CHAFED AT FUSELAGE STATION 614.210 AFT EQUIPMENT BAY UPPER AVIONICS SHELF SUPPORT ANGLE PN 4525708307. THE ANGLE DOES NOT HAVE ANY PROTECTION TO PREVENT CHAFING OF WIRING FROM THE FACTORY AND IT APPEARS THAT CLEARANCE IS NOT GREAT ENOUGH TO KEEP THE WIRING FROM CHAFING. HAVE NOTIFIED MFG TECH SUPPORT. (K)

Part: BULKHEAD — CRACKED (FUSELAGE)

DURING ANNUAL INSPECTION, CRACKS WERE FOUND IN BULKHEAD FS 257.6.

Part: DOOR — DEPARTED (NACELLE)

LT INBOARD NACELLE DOOR DEPARTED AIRCRAFT IN FLIGHT AND PUNCTURED THE FUSELAGE.

Part: SEAL — LEAKING (COCKPIT WINDOW)

THE AIRCRAFT WAS PARKED OUTSIDE IN A HEAVY ALLOWING WATER TO ENTER CONNECTORS AFT OF THE PILOTS CIRCUIT BREAKER PANEL. APPROX. FIFTEEN MINUTES AFTER TAKEOFF, THE LEFT AND RIGHT ESSENTIAL (A) CIRCUIT BREAKERS OPENED. THE RIGHT ESSENTIAL (A) BREAKER WAS RESET, ALLOWING THE CREW TO DECLARE AN EMERGENCY. RIGHT ESS. (A) BREAKER OPENED AGAIN ON FINAL APPROACH, AND ASSOCIATED WIRING WERE INSPECTED BY MFG MAINTENANCE, NO DEFECTS NOTED. ALL SYSTEM CHECKS SATISFACTORY. PILOTS SIDE WINDOW SEAL REPLACED.

Part: ACTUATOR — PINS BROKEN (NLG DOWNLOCK)

UPON SELECTING GEAR DOWN FOR LANDING, THE PILOT COULD NOT GET A NOSE DOWN AND LOCK INDICATION. AIRCRAFT WAS LANDED AND NOSE WHEEL COLLAPSED. INVESTIGATION REVEALED THE NOSE GEAR ACTUATOR DOWNLOCK PINS WERE BROKEN WHICH ALLOWED ONE OR BOTH PINS TO VIBRATE INBOARD WHICH PREVENTED ACTUATOR SHAFT FROM RETRACTING COMPLETELY, THEREFORE, NOT ALLOWING DOWNLOCK MECHANISM TO LATCH OVER PINS. IT APPEARS PINS HAD BEEN BROKEN FOR SOME TIME AND HAD FAILED AT THE MACHINED GROOVE WHICH WAS CUT FOR ROLL PIN PROTRUSION. CESSNA SEB 9520 DATED 12-29-95 COVERS THIS SUBJECT. SUBMITTER RECOMMENDS THE INITIAL INSPECTION SHOULD BE REVISED TO 'BEFORE FURTHER FLIGHT'.