N8216T
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 A ROUTINE ELT INSPECTION IAW 14 CFR 91.207, THE ELT G SWITCH WAS FOUND TO BE INTERMITTENT. THIS IS A RECURRING PROBLEM WITH THESE UNITS.
DURING A ROUTINE 100 HOUR INSPECTION, THE NR 2 CYLINDER WAS FOUND TO HAVE COMPRESSION OF 30/80 WITH LEAKAGE OUT THE INTAKE VLV. THIS IS THE THIRD OCCURRENCE OF THE SAME PROBLEM ON THIS FACTORY OVERHAULED ENG IN LESS THAN 500 HOURS SINCE OVERHAUL. THE FIRST TWO WERE THE NR 3 CYLINDER AT 294 HOURS SINCE OVERHAUL, FOLLOWED BY NR 5 AT 384 HOURS SINCE OVERHAUL. FOR COMPARISON, PRIOR TO THIS IN OVER 10,000 HOURS OF ENG OPERATION WITH IO540K SERIES WE HAD NOT HAD TO PULL A CYLINDER DUE TO LOW COMPRESSION.
CRACK WAS DISCOVERED IN THE FORWARD LEFT CASE HALF PROPAGATING OUT FROM NR 2 CYLINDER BASE. DAMAGE FOUND DURING ROUTINE 100 HOUR INSPECTION. ENGINE GROUND RUN CONFIRMED CRACK WAS LEAKING OIL.
NOTICED EXCESS PLAY BETWEEN RT AND LT PEDALS DUE TO ELONGATED THRU BOLTS IN ASSY. UPON DISASSEMBLY, FOUND TUBE TO HAVE EXTREME CRACK RADIATING FROM THRU BOLT HOLE AND RADIATING AROUND TO BACK SIDE OF TUBE AND GOING OUT TO EACH SIDE IN A SPIRAL FRACTURE. PART WAS VERY NEAR TOTAL FAILURE. THIS PART IS IMPOSSIBLE TO INSPECT WITHOUT TOTALLY REMOVING AND DISASSEMBLING RUDDER BAR ASSY. BELIEVE THIS IS CAUSED BY PRESSING HARD ON PEDALS TO TURN NOSE WHEEL BEFORE AIRCRAFT IS IN MOTION, CAUSING A STRONG RADIAL FORCE BEING APPLIED TO RUDDER BAR. (AL05200502805) (K)
UPON ROUTINE INSPECTION OF IMPULSE COUPLING, FOUND ONE OF THE PAWL ANCHOR PINS LOOSE IN THE BODY OF THE IMPULSE. PART WAS IN SERVICE 202 HOURS. SUBMITTER HAS FOUND 4 OR 5 CASES OF EXCESSIVE WEAR OF LOW TIME IMPULSE COUPLERS (UNDER 300 HOURS).
UPON ROUTINE INSPECTION OF IMPULSE COUPLING, FOUND THAT ONE OF THE PAWL ANCHOR PINS WAS LOOSE IN THE BODY OF THE IMPULSE. PART WAS IN SERVICE 202 HOURS.
DURING 100-HOUR INPSECTION OF MAGNETO, IMPULSE WAS FOUND TO BE NEAR TOTAL FAILURE. BOTH PAWL PINS WERE LOOSE IN BODY OF IMPULSE WITH ONE NEARLY READY TO PULL FREE. THIS ASSY HAD BEEN INSPECTED 98 HOURS PRIOR AND FOUND TO HAVE NORMAL WEAR.
ROUTINE CHECK OF IMPULSE COUPLING REVEALED BOTH PAWLS EXCEED NORMAL GAP BETWEEN PAWLS AND PLATE BY AN EXTREME AMOUNT. ALSO, ONE PAWL PIN WAS OBVIOUSLY BENT SO THE HEAD TIPPED OUTBOARD FROM CENTER. THIS PART HAD BEEN INSPECTED 100 HOURS PRIOR AND FOUND TO BE NORMAL IN ALL RESPECTS. THESE COUPLERS SEEM TO BE TOTALLY UNPREDICTABLE FOR SERVICE LIFE. SUBMITTER STATED HAVE FOUND FAILURES AS LOW AS 50 HOURS IN SERVICE.
UPON REPORT OF DEAD RIGHT MAGNETO, FOUND CONTACT POINT LOOSE IN POINT SET BODY. OTHERWISE, POINT SET IN EXCELLENT CONDITION.
MAG IMPULSE COUPLING FAILED. REMOVED FROM ENGINE AT 469.8 HOURS SINCE NEW.
RUN-UP, ROUGH ENGINE, FUEL SMELL. FOUND INJECTOR LINE CRACKED. AIRCRAFT JUST OUT OF 100-HOUR INSPECTION, NO INDICATION OF CRACKS, ETC. HAVE SEEN ALERT ON THIS IN THE PAST, HAVE NEVER FOUND ONE CRACKED BEFORE.