188AgWagon · AgTruck · AgHusky

Parts most often named Hub (36) · Blade Socket (1)

HUB, [S/N removed], CRACKED ALL THE WAY THROUGH HUB AT 2ND AND 3RD THREAD IN BLADE SOCKET APPROXIMATELY 3.50 INCHES LONG. RED DYE LEAKING FROM PROPELLER. CAUSE OF CRACK UNKNOWN. PROPELLER USED IN AG OPERATION. REPLACED HUB WITH [S/N removed]. (X)

PROPELLER CAME IN LEAKING RED DYE. ALL THREE BLADE RETENTION NUTS CRACKED AND HUB CRACKED IN NR 2 BLADE SOCKET. BLADE, [S/N removed], HAD EXCESSIVE CORROSION IN BLADE THREADS (SCRAP). PROPELLER USED IN AG OPERATIONS. TWO GOOD BLADES RETURNED TO CUSTOMER. EXACT CAUSE OF CRACK UNKNOWN. (X)

(CAN) PROPELLER WAS SENT FOR CORROSION INSPECTION AND AFTER TEARDOWN, THE PROPELLER HUB AND TWO NUTS WERE FOUND CRACKED. PROPELLER ASSEMBLY WAS OVERHAULED.

Parts most often named Blade (14) · Nut (1)

PROPELLER LEAKING RED DYE. TEAR-DOWN INSPECTION REVEALED BLADE CRACKED ALL THE WAY THROUGH INTO THE WEIGHT HOLE. DYE COMING FROM BLADE PATCH. CAUSE UNKNOWN. PROPELLER USED IN AG OPERATION. (X)

CRACK APPROXIMATELY THREE INCHES LONG INSIDE BOTTOM OF HUB (ABOVE STUDS). DETECTED BY EDDY CURRENT DURING OVERHAUL. CAUSE KNOWN.

PROPELLER HAD BLADE FAILURE AT THE 30 INCH STATION. DURING DISASSEMBLY, ALSO NOTICED THAT AT LAST ASSY, THE A4140 LOCKING PLUGS FOR THE BLADE RETENTION NUTS HAD NOT BEEN INSTALLED. AFTER FURTHER DISASSEMBLY, THE BLADE THAT HAD FAILED ALSO HAD A CRACKED BLADE RETENTION FERRULE.

Parts most often named Crankshaft (3) · Camshaft (2) · Bolt (2) · Thru Bolt (1)

(CAN) ENGINE WAS FOUND TO HAVE SIGNIFIGANT LIFTER SPALLING AND CAMSHAFT LOBE WEAR AFTER ONLY 197.7 HRS. TTSO AND THE SAME AMOUNT OF TIME ON THE FAILED PARTS BUT THEIR TIME IS TTSN. METAL WAS FOUND IN THE SCREEN ON ROUTINE INSPECTION. ENGINE OTHERWISE GAVE NO INDICATION OF ANY PROBLEMS.

ENGINE LOCKED UP IN-FLIGHT. FOUND REAR PULLEY NOT MOVING WHEN MOVING PROPELLER. SUSPECT CRANKSHAFT BROKEN AT NR 1/NR 2 JOURNAL. AD 87-23-08 PREVIOUSLY C/W 909 HOURS AGO.

(CAN) DURING INSPECTION AND UPON DISMANTLING, #3 & #4 INTAKE LOBES, #5 EXHAUST LOBE, AND #5 & #6 INTAKE LOBES ON CAMSHAFT WERE SPALLED. TWO LOBES WERE SPALLED OVER ENTIRE FACE AND TWO WERE SPALLED ONLY IN THE CENTRE. TWO LIFTERS WERE CORRODED BADLY. ALL MAIN BEARING INSERTS AND ALL CONNECTING ROD BEARING INSERTS WERE METAL CONTAMINATED.

Parts most often named Cylinder (5) · Intake Valve (1) · Valve Spring (1) · Cylinder Head (1)

CYLINDER HEADS FOUND TO BE CRACKED. ALL OF THE CYLINDERS WERE INSTALLED NEW FEB 15,2012. ACFT HAS BEEN FLOWN 404.3HRS. PILOT HAD LOSE OF POWER AND RETURNED TO AIRPORT. 2 CYLINDERS FOUND CRACKED AND LEAKING DURING COMPRESSION CHECK. REMAING CYLINDERS COMPRESSION CHECKED OK. VISUAL INSP OF CYLINDERS REVIELED THAT 5 OF THE 6 WERE CRACKED. SN OF CRACKED CYLINDERS ARE AS FOLLOWS; 52119-16, 52119-19, 52119-22, 52119-24, 52119-25

AT 470 HOURS ON REBUILT ENGINE, ALL CYLINDERS WERE REMOVE FOR INTAKE VALVE LEAKAGE. ALL VALVE SEATS WERE EASILY RECONDITIONED, BUT VALVES SHOWED MAJOR IDENTATION AT THE SEAT CONTACT AREA, WITH APPARENT MOVEMENT OF VALVE MATERIAL OUTWARD.

DURING ANNUAL INSPECTION, PERFORMED A COMPRESSION CHECK ON ALL ENGINE CYLINDERS. TWO CYLINDERS FAILED THE CHECK LEAKING BY THE VALVES. REMOVED CYLINDERS, DISASSEMBLED. CHECKED VALVE SPRINGS INNER AND OUTER TENSION PER CONT OVERHAUL MANUAL USING A VALVE SPRING TESTER AND FOUND THAT THE INNER AND OUTER VALVE SPRINGS FAILED. TOTAL TIME ON THESE SPRINGS 910 SINCE NEW. REPLACED INNER AND OUTER VALVE SPRINGS WITH NEW SPRINGS AFTER CHECKING SPRING TENSIONS.

Parts most often named Spring (2) · Bracket (1) · Leg Assy (1)

(CAN) AT ABOUT 20 MILE AN HR ON THE TAKE OFF ROLL THE LT MAIN GEAR SPRING [S/N removed] OFF ABOUT 6 " UP FROM THE AXLE, CAUSING THE ACFT TO SPIN TO THE LT AND TILT UP RESULTING IN THE PROPELLER IMPACTING THE GROUND AND A SUDDEN STOPPAGE OF THE ENGINE. ACFT CAME TO REST ON ITS LT WING. THERE WERE NO INJURIES SUSTAINED BY THE PILOT. ACFT ONLY HAD ABOUT 120 GALLONS OF SPRAY CHEMICAL ON BOARD AT TIME OF INCIDENT.

LANDING GEAR BRACKET ASSY FAILED ON TAKEOFF DUE TO METAL FATIGUE, CAUSING ABORTED TAKEOFF, SUBSTANTIAL DAMAGE TO THE ACFT. DATA DERIVED FROM FAA FORM 8020-23 DATED 05/31/09 WITH NTSB ID: WPR09LA281.

AIRCRAFT ACCIDENT. LT MLG (SPRING) FAILED DURING TAKEOFF ATTEMPT, APPROXIMATELY 6 INCHES ABOVE AXLE. NO EVIDENCE OF PREVIOUS FRACTURE (CRACK) COULD BE DETECTED. LT WING BUCKLED AND AIRCRAFT NOSED OVER. SUBSTANTIAL DAMAGE, NO INJURIES.

Parts most often named Kit Assy (1) · Piston Tube (1) · Nut (1) · Ferrule (1)

Parts most often named Arm (2) · Bellcrank (1)

RUDDER BELLCRANK PN 0712309-16AGW HAD EXTREME WEAR SEVERAL PLACES, BOTH SIDES. WHERE THEY ARE LOCATED THEY ARE DIFFICULT TO INSPECT AND LUBERCATE. MADE INSPECTION PANEL TO BE ABLE TO GAIN ACCESS TO THIS VITAL AREA. FAILURE OF THIS PART WOULD POTENTIALLY CAUSE GROUND LOOP.

Parts most often named Hinge (2)

(AUS) TAILPLANE AFT BOTTOM HINGE BOLTS LOOSE CAUSING HINGES PN 0732101-10 AND PN 0732101-11 TO WEAR BEYOND LIMITS. PART TC: 2,150.

Parts most often named Muffler (2)

SHROUD MISSING FROM EXHAUST SYSTEM MUFFLER WHICH CAUSED MUFFLER TO HEAT UP ENOUGH TO BURN A HOLE IN IT. BURNED UP INTAKE AIR FILTER WHICH WAS INDUCED INTO ENGINE CAUSING ENGINE FAILURE.

Parts most often named Harness (1) · Seat (1)

PILOT SEAT SLID BACK ON LANDING CAUSING THE PILOT TO LOSE DIRECTIONAL CONTROL. THE FRONT LEFT ROLLER HOUSING WAS FOUND SPREAD OPEN TO .4687 INCH. THE SEAT RAIL MEASURED .5000 INCH. AD 87-20-03 HAD BEEN SIGNED OFF AS ACOMPLISHED APPROX 4 MONTHS EARLIER. THE FRONT RIGHT HOUSING WAS ALSO SPREAD OPEN. BOTH HOUSINGS WERE BELIEVED TO BE SPREAD OPEN PRIOR TO THE ACCIDENT.

PILOT'S SHOULDER HARNESS WEBBING BROKE. WAS NOTED DURING ACCIDENT INVESTIGATION. SUBMITTER STATED COULD BE A RESULT OF FORCES DURING IMPACT. WEBBING MAY HAVE BEEN 'SUN' DETERIORATED.