BIDZY TA HOT AANA CORP

Operated by BIDZY TA HOT AANA CORP (per NTSB report)

LEFT SIDE EXHAUST STACK ASSY FAILED AT MUFFLER ATTACH FLANGE. MUFFLER COMPLETELY SEPARATED FROM STACK ASSY.

LEFT MAIN LANDING GEAR SUPPORT BRACKET FAILED.

BRAKE RESERVOIR (PN 6846400) HAD A CRACKED HOSE ATTACH FITTING LEAKING HYDRAULIC FLUID ON TO DEFROSTER HOSE, CAUSING SMOKE IN COCKPIT. REPLACED BRAKE RESERVOIR WITH A SERVICEABLE PART.

DURING 500 HOUR INSPECTION MECHANIC FOUND MISSING TOOTH ON LEFT HAND DRIVE GEAR. THIS IS 2ND MAG INSTALLED ON AIRCRAFT DUE TO DRIVE GEAR FAILURE UNKNOWN.

MAGNETO RAN ROUGH ON RIGHT SIDE. DURING RUN, MAGNETO FOR INSPECTION OF PROBLEM FOUND HALF OF RIGHT SIDE GEAR DRIVE TEETH BROKEN OUT.

AIRPLANE LANDED, LEFT GEAR UNLOCKED AFTER ELECTRICAL POWER FAILURE ON APPROACH TO LAND. INSPECTION OF ELECTRICAL SYSTEM, FOUND BATTERY POST CORRODED ON POSITIVE TERMINAL.

DISCOVERED DURING 100 HOUR INSPECTION NOTED MOVEMENT OF WING AT FORWARD WING ATTACH FITTING WHEN WING WAS PUSHED FROM BOTTOM OR TOP.

MAGNETO DEAD ON LEFT SIDE DURING RUNUP MAG CHECK. FOUND SEVERAL TEETH BROKEN ON BOTH DISTRIBUTOR GEARS.

MAGNETO DEAD ON LEFT SIDE DURING RUNUP MAG-CHECK. FOUND SEVERAL TEETH BROKEN ON BOTH DISTRIBUTOR GEARS.

DURING ENGINE INSTALLATION AFTER OVERHAUL, FOUND ALL 4 GOVERNOR HOLD DOWN STUDS NOT SCREWED FAR ENOUGH INTO CASE. STUDS HAD TO BE TURNED IN .2500 FURTHER TO ALLOW GOVERNOR TO MATE WITH ENGINE.

DURING VALVE CLEARANCE INSPECTION, FOUND NR 6 INTAKE ROCKER ARM FACE WHERE IT CONTACTS ROTATER CAP, WORN SEVERELY .1250 AND BADLY PITTED. ENGINE HAS BEEN ON OIL ANALYSIS SINCE OVERHAUL WITH NO PROBLEMS NOTED. ALL OTHER ROCKER ARMS FOUND NORMAL. PROBABLE CAUSE IS THAT A WORN UNAIRWORTHY PART WAS PUT IN ENGINE DURING OVERHAUL.

DURING FLIGHT, ENGINE STARTED RUNNING VERY ROUGH, HAD POWER LOSS. AFTER LANDING, INSPECTION FOUND NR 1 CYLINDER EXHAUST VALVE ROCKER ARM SHAFT RETAINING PLATE HAD COME OFF ALLOWING THE ROCKER SHAFT TO SLIDE OUT. THE ROCKER THEN WAS PUSHED OUT BY THE PUSH ROD. DAMAGE TO THE VALVE COVER AND CLYLINDER HEAD ENSUED. NO OTHER ENGINE DAMAGE OCCURRED. SUBMITTER SUGGESTED A POSSIBLE CAUSE COULD BE STAR WASHERS UNDER SECURING NUTS FOR PLATE DID NOT RETAIN TORQUE ON NUTS. RECOMMEND SPECIFIC ATTENTION BE GIVEN DURING INSPECTION TO RETAINING HARDWARE.

DURING TAKEOFF ROLL, PILOT EXPERIENCED POWER LOSS AND STRONG SMOKE SMELL. TAKEOFF WAS SAFELY ABORTED. UPON INSPECTION, THE INNER HALF OF THE ALTERNATE AIR BOX DOOR WAS FOUND BROKEN. THE BROKEN PIECE WAS INJESTED INTO THE INDUCTION SYSTEM CREATING MOMENTARY POWER LOSS. THE DOOR IS MADE OF PLASTIC COMPOSITE MATERIAL AND WAS BURNED UP. THIS CREATED THE SMOKE SMELL. THE SERVO AND ALL INDUCTION TUBES WERE REMOVED TO VERIFY NO REMAINING PORTION WAS IN ENGINE. SPARKPLUGS REMOVED AND CYLINDERS BORESCOPE INSPECTED FOR ANY RESIDUE. NONE FOUND. ENGINE RAN NORMALLY AFTER NEW VALVE INSTALLED. RECOMMEND REGULAR CLOSE INSPECTION OF THIS AREA AS IT IS DIFFICULT TO SEE WITHOUT SOME DISASSEMBLY. (X)

RIGHT NOSE GEAR DOOR HINGE WAS FOUND BROKEN AT AFT ATTACH POINT. THE HINGE (PIANO HINGE) ATTACHES TO THE ENGINE MOUNT WITH 2 NR 3 BOLTS AND .50 INCH APART. THIS BREAK ALLOWED THE RT DOOR TO HANG DOWN WITH THE POTENTIAL FOR JAMMING UP THE RETRACTION OF THE NOSE GEAR. SUBMITTER STATES THIS SAME BREAK HAS BEEN SEEN ON OTHER OCCASIONS BY THE OPERATOR. SPECULATE THAT VIBRATION CAUSED THE STRESSING WHICH ALLOWED THE BREAK. THIS APPEARS TO BE THE WEAK SPOT IN THE NOSE GEAR DOOR SYSTEM. (X)

PILOT REPORTED DIFFICULTY STARTING AIRCRAFT. UPON INSPECTION OF THE FUEL SERVO, THE MIXTURE CONTROL STOP SCREW WAS FOUND MISSING. THE SAME STOP SCREW ON THIS SERVO SERVES FOR BOTH FULL RICH AND IDLE CUT-OFF. THE SCREW AND BUSHING WERE COMPLETELY GONE ALLOWING UNCONTROLLED MIXTURE TRAVEL. THIS SCREW IS NORMALLY SAFETIED. RECOMMENDATION IS CLOSE INSPECTION BE GIVEN TO ALL SAFETIED ITEMS DURING SCHEDULED MAINTENANCE. (X)

LOST APPROXIMATELY 6.5 INCHES OF PROPELLER TIP JUST PRIOR TO LANDING AFTER A 30-MINUTE FLIGHT. NO OTHER DAMAGE FOUND TO AIRCRAFT AFTER COMPLETE INSPECTION.

DURING INSPECTION FIREWALL WAS FOUND CRACKED BETWEEN LOWER RIGHT ENGINE MOUNT ATTACH POINT AND COWLING FLANGE. CRACK WAS 2.50 INCHES LONG AND RAN HORIZONTALLY. SUBMITTER SPECULATES CAUSE WAS AGE OF PART. RECOMMEND CLOSE AND DETAILED INSPECTION OF THIS AREA OF THE FIREWALL ON REGULAR BASIS. (X)

DURING ANNUAL INSPECTION, FOUND CRANKCASE CRACKED FROM EDGE OF NR 2 CYLINDER FLANGE TO FORWARD CORNER AT CYLINDER BASE STUD. EDDY CURRENT INSPECTION VERIFIED CRACK TO BE SUBSURFACE. VISUAL INSPECTION SHOWED NO CRACKING ON INSIDE OF CASE. THE CRACK WAS APPROXIMATELY 1.50 INCHES LONG. ENGINE REPLACED. (X)

DURING FLIGHT, ENGINE BEGAN RUNNING VERY ROUGH. THE PILOT LANDED AT NEAREST AIRPORT. UPON INSPECTION, FOUND LINE GOING FROM THE SPIDER TO THE NR 3 CYLINDER FUEL NOZZLE HAD BROKEN. THIS BREAK OCCURRED UNDER THE B-NUT NEXT TO THE BALL AT THE END OF THE LINE WHERE IT CONNECTS TO THE FUEL NOZZLE. THE NUT WAS TIGHT AND CONNECTED PROPERLY. FUEL LINE REPLACED WITH NEW.