N399CZ

Beech 99 None injury — FREIGHT RUNNERS EXPRESS, INC.

ATA 7200

PILOT REPORTS "RH ENGINE SN PC-51404 FAILURE ON TAKEOFF ROLL. ALL ANNUNCIATORS WERE EXTINGUISHED AND ENGINE INSTRUMENTS IN THE GREEN. AS I BEGAN MY ROLLOUT AND BEFORE I COULD REACH THE DESIRED POWER SETTING, THERE WAS A POP FROM THE RH SIDE AND THE AIRPLANCE PULLED TO THE RIGHT. I IMMEDIATELY RETARTED THE THROTTLE AND CAME TO A STOP, WHERE I SAW THE RH WINDOW COVERED IN CLEARISH FLUID. ADVISED ATC OF ABORTED T/O AND THEY REQUESTED ME OFF THE ACTIVE RUNWAY AS AN AIRLINER WAS ON 3 MILE FINAL." MAINTENANCE, UPON INVESTIGATION OF AIRCRAFT IT WAS DETERMED THERE WAS A MISSING POWER TURBINE BLADE FROM FIR TREE, A FEW BROKEN BLADES (APPROX 1/2 MISSING) AND BENT BLADES ON THE PT DISK. IT IS SUSPECTED EITHER PT BLADE FAILURE OR GEAR REDUCTION FAILURE CAUSED THIS EVENT.

ATA 3410

PILOT'S SIDE EFIS PRIMARY FLIGHT DISPLAY (PFD) LOST ALL AIRSPEED, ATTITUDE AND HEADING DATA WHILE IN IMC AND PILOT'S AIRSPEED INDICATOR FAILED AT THE SAME TIME. OAT AT CRUISE ALTITUDE OF 17,000 FT WAS APPROXIMATELY -10 DEGREES C. THE PILOT COMMUNICATED WITH THE COMPANY AND THE COMPANY DETERMINED THE MOST LIKELY REASON OF THE FAILURE TO BE A LOSS OF AIRSPEED WHICH CAUSED THE PFD TO FAIL. LOGIC OF THE PFD IS THAT IF AIRSPEED IS LOST AND GPS GROUND SPEED IS OVER 50 KNOTS THE PFD WILL REMOVE ALL FLIGHT ATTITUDE AND HEADING DATA. THE WEATHER AT THE DESTINATION WAS VFR WHICH WAS NOT THE CASE AT THE DEPARTURE AIRPORT OR AN AIRPORT WITHIN CLOSE PROXIMITY OF THE ACFT AT THE TIME, THEREFORE THE FLIGHT CONTINUED TO THE DESTINATION AND LANDED WITHOUT INCIDENT. THE PITOT TUBE LINE DRAINS HAVE BEEN OPENED TO REMOVE ANY POSSIBLE MOISTURE FROM THE SYS WHICH COULD FREEZE AND CAUSE A FAILURE OF THE EFIS AND AIRSPEED INDICATIONS.

ATA 2897

NR 2 ENGINE FUEL FLOW FLUCTUATED, FUEL PRESSURE LIGHT ILLUMINATED, FLAMED OUT AND PROPELLER FEATHERED. FUEL QUANTITY INDICATOR INDICATED 600 POUNDS AND WAS APPROPRIATE WITH THE STARTING INDICATING FUEL FOR THE DAY AND THE ESTIMATED BURN WHEN NR 2 ENGINE FLAMED OUT. ENGINE SURGED AGAIN AFTER THE INITIAL FLAME OUT AND THE PILOT ELECTED TO SHUTDOWN THE ENGINE AS OUTLINED IN THE COCKPIT REFERENCE HANDBOOK EMERGENCY PROCEDURES. AT THE TIME OF THE ENGINE FLAME OUT THE AIRCRAFT WAS ON A 2 MILE APPROACH IN VMC CONDITIONS. PILOT DECLARED AN EMERGENCY AND ACFT LANDED WITHOUT INCIDENT. UPON EXAMINATION OF THE FUEL TANKS IT WAS DISCOVERED THAT THE RIGHT FUEL SYSTEM WAS EMPTY AND FUEL QUANTITY SYSTEM INDICATING 600 POUNDS. FUEL DRAINS WERE OPENED, APPROXIMATELY .5 GALLON OF FUEL WAS RECOVERED. ACFT WAS FUELED ON FEBRUARY 10 TO A TOTAL OF 1000 POUNDS PER SIDE INDICATED WHICH WAS VERIFIED BY THE CREW PRIOR TO THE SERIES OF FLIGHTS ON FEBRUARY 12. THE TOTAL FLIGHT TIME ON FEBRUARY 12 PRIOR TO THE FLAME OUT WAS 1.2 HOURS, AN ESTIMATED BURN OF 400 POUNDS PER SIDE, THE INDICATION OF 600 POUNDS REMAINING IS CONSISTENT WITH FUEL BURN. AFTER INVESTIGATION IT WAS DISCOVERED THAT THE CONNECTION FROM THE HI Z HARNESS ASSY, FUEL QUANTITY RT PN 99-361000-662 TO THE HI Z JUNCTION BOX, RT PN 1289-305 WAS CAUSING ERRONEOUS INDICATIONS UNLESS THE CONNECTION WAS "PUSHED" IN. BOTH SIDES OF THE CONNECTOR WERE CLEANED AND FUNCTIONALLY CHECK OK.

ATA 2913

UNABLE TO RETRACT GEAR DUE TO PUMP WEAKENING CAUSED BY LEAKING/WORN SEALS AND BLEED DOWN OF SYSTEM.