IO-470Continental IO-470

Parts most often named Cylinder (18) · Piston (7) · Cylinder Head (5) · Lifter (2)

ENGINE RAN INTERMITTENTLY ROUGH . NR 1 CYLINDER SHOWED VERY LOW EGT AND CHT. PERFORMED COMPRESSION TEST ON NR 1 CYLINDER. COMPRESSION WAS LOW AND AIR WAS ESCAPING PAST EXHAUST VALVE INTO EXHAUST STACK. R & R CYLINDER WITH REPAIRED AND INSPECTED UNIT. REPORT SHOWED REMOVED CYLINDER TO HAVE WAVY WALLS WHICH COULD NOT BE RETURNED TO STANDARD LIMITS AND WOULD REQUIRE HONING TO P.015 OVERSIZE. THE EXHAUST VALVE GUIDE WAS OUT OF LIMITS. THE EXHAUST VALVE WAS BURNED AND UNSERVICEABLE. PISTON CHECKED OK.

WHILE ON A 3 MILE FINAL, OIL STARTED APPEARING ON THE RIGHT ENGINE NACELLE AND THE PILOT REPORTED A VIBRATION. AFTER AN UN EVENTFUL LANDING, THE ACFT TAXIED BACK UNDER ITS OWN POWER. THE MECHANIC FOUND THAT THE RT ENGINE NR 2 CYLINDER HEAD WAS STARTING TO SEPARATE FROM THE CYLINDER BARREL BY ABOUT .5".

ENGINE CYLINDERS HAD LOW COMPRESSION. REMOVED CYLINDERS AND FUND LIFTERS HAD SPALLING AND CAM SHAFT WAS WORN. LIFTER PN 653888 AND PN 653877 INSTALLED. THESE PN ARE DESIGNATED AS NOT AFFECTED BY MSB 09-8 OR AD 2009-24-52.

Parts most often named Piston (8) · Crankcase (5) · Crankshaft (5) · Bolt (4)

PILOT FELT A SHUDDER OF THE LEFT ENGINE AND IT SHUT DOWN ON ITS OWN. THE AIRCRAFT LANDED WITHOUT INCIDENT. UPON INSPECTION WE FOUND THAT THE PROP DID NOT FEATHER, THE ENGINE SEIZED, THERE ARE THREE HOLES IN THE TOP ON THE LEFT ENGINE CASE HALF, OBSERVED THROUGH THE LARGER HOLE IN THE CASE HALF THAT THE NR 4 CYLINDER CONNECTING ROD WAS BROKEN AND THE CONNECTING ROD CAP WAS SITTING ON TOP OF THE ENGINE. IT HAD COME UP THROUGH THE LARGER HOLE. IT HAD ALSO PUT A SMALL DENT IN THE TOP COWL.

WHEN REMOVING RT ENGINE NR 4 CYLINDER DUE TO A CRACK, NR 4 PISTON SKIRT FOUND BROKE OFF AT THE 4TH RING LAND. ENGINE THEN REMOVED FROM ACFT FOR TEAR-DOWN INSPECTION. I HAVE FOUND BROKEN PISTON SKIRTS ON THIS PARTICULAR ACFT ON 3 DIFFERENT ENGINES.

CRANKSHAFT GEAR WAS FOUND WITH FOUR TEETH MISSING FROM THE GEAR. THE CAMSHAFT GEAR THAT IT IS MESHED WITH STILL ROTATED AROUND THE GEAR AND MESHED WITH THE REMAINING TEETH. SB 08-12 DATED 9/9/08 SUPERSEDES THIS GEAR PN WITH A NEW HEAVIER GEAR PN 657175 AT THE NEXT ENGINE DISASSEMBLY. THIS ENGINE HAD BEEN DISASSEMBLED FOR A PROPELLER STRIKE INSPECTION.

Parts most often named Magneto (6) · Spring (2) · Impulse Coupling (2) · Impulse Coupler (1)

ELECTRIC MAGNETO FAILED. TROUBLESHOOT FOUND MAGNETIC PIC-UP CIRCUIT OPEN. REPLACED WITH NEW AND RUN CHECK SATISFACTORY. REMOVED PART APPEARS TO HAVE DEBONDED FROM CYLINDER AND THERE IS EVEDENCE THAT IT CONTACTED THE CRANK TRIGGER. OAT TEMPERATURE WAS JUST BELOW FREEZING.

DURING A ROUTINE INSP, ALL MAGNETOS WERE REMOVED FOR POINTS AND CONDENSER REPLACEMENT. RUST WAS FOUND ON THE FLYWEIGHT/AXLE AREA OF THE IMPULSE COUPLING. A WEAR CHECK WAS MADE AND IT WAS DETERMINED THAT ALL COUPLINGS FAILED IAW MSB. NOTE: THE FLYWEIGHT/ AXLE PIN WEAR IS IN EXCESS OF .014 AND MAY BE DUE TO RUST. THIS AREA OF INSPECTION MAY BE OVERLOOKED DUE TO THE OMISSION OF MANY IMPULSE COUPLINGS INSTALLED ON ENGINE NOT INCLUDED IN AD. (K)

JUST AFTER DEPARTURE A BURNING ODOR WAS NOTICED FROM THE FRONT OF THE AIRCRAFT. A STANDARD FLIGHT PATTERN BACK TO RUNWAY WAS EXPEDITED. LATER FINDING THE IGN VIBRATOR HAD STARTED A FIRE IN THE FRONT PILOTS LOWER FIREWALL PANEL. A GEAR UP LANDING BECAME THE RESULT OF THE ELECTRICAL BURN UP. THE FINAL PART OF THE FLIGHT WAS CONDUCTED AS AN EMERGENCY. (WP11200403343)

Parts most often named Low Pitch Stop (3) · Support (3) · Bulkhead (2) · Backplate (1)

(CAN) DURING MFG PROGRESSIVE CARE INSPECTION THE SPINNER DOME WAS FOUND TO BE LOOSE. UPON FURTHER INSPECTION THE SPINNER BULKHEAD WAS FOUND TO BE CRACKED ALL THE WAY AROUND CRANKSHAFT FLANGE. SPINNER AND PROPELLER RE & RE AND NEW BULKHEAD INSTALLED, PN D-7522.

(AUS) RT PROPELLER SPINNER BACKING PLATE FAILED. BACKING PLATE HAD CRACKED AROUND THE CIRCUMFERENCE BEND FOR APPROXIMATELY 100 DEGREES.

(CAN) DURING INSPECTION, THE PROPELLER SPINNER WAS FOUND LOOSE. INVESTIGATION FOUND THE THREADS ON THE LOW PITCH STOP WERE STRIPPED. THE FORWARD END OF THE SPINNER IS SECURED TO THE LOW PITCH STOP. THIS LOW PITCH STOP WAS INSTALLED 24 HOURS PREVIOUSLY FOR THE SAME PROBLEM. THE THEN LOW PITCH STOP WAS ALSO FOUND STRIPPED AFTER 30 HOURS TIME SINCE NEW. THE LOW PTICH STOP WAS AGAIN REPLACED AND THE AIRCRAFT RETURNED TO [S/N removed].

Parts most often named Cable (3) · Throttle Cable (2) · Rod End (1) · Actuator Cable (1)

DURING ANNUAL INSPECTION HEIM JOINT USED TO CONNECT THROTTLE CABLE TO THROTTLE BODY WAS FOUND TO BE PARTIALLY UNSCREWED FROM THROTTLE CABLE. THE WITNESS HOLE ALLOWED A WIRE TO PASS THROUGH, INDICATING INSUFFICIENT ATTACHMENT.

LT THROTTLE CONTROL LEVER FAILED TO CHANGE POWER DURING CHANGE FROM TAKE-OFF TO CRUISE POWER SETTING. IT WAS DISCOVERED THT THE CRIMPING HAS FAILED ON THE CLIP THROTTLE CONTROL PN RA1039C WHICH IS PART OF THE THROTTLE CABLE ASSY PN 50-389012-15. THIS CLIP IS LOCATED ON THE ENGINE SIDE OF THE CONTROL CABLE AND IS ATTACHED TO BRAKE THROTTLE CONTROL PN 96-940021.

DURING APPROACH FOR LANDING, RIGHT ENGINE THROTTLE CONTROL MOVEMENT HAD NO RESPONSE IN ENGINE POWER. CONTROL FELT NORMAL. ENGINE FEATHERED AND AIRCRAFT MADE A NORMAL LANDING. INSPECTION REVEALED THROTTLE CABLE BROKE ABOUT 12 INCHES AFT OF THROTTLE ASSEMBLY. BREAK OCCURED INSIDE CONTROL HOUSING.

Parts most often named Engine (2) · Oil Valve (1) · Lifter (1) · Gasket (1)

ENGINE DEVELOPED OIL LEAK, FOUND THIS ADAPTER LEAKING AT THREADS, LOCKING NUT SAFETY WAS INTACT, TORQUE DOPE WAS INTACT. ALL REQUIREMENTS OF AD 96-12-22 WERE MET AS PREVIOUSLY INSPECTED 18 HOURS BEFORE FAILURE.

DISASSEMBLING ENG FOR OVERHAUL FOUND THE OIL SUCTION TUBE WAS BROKEN IN 2 PLACES. TUBE WAS BROKE OFF FROM SCREEN AND ONE OF THE ATTACHING ANGLES WAS BROKEN BY BOLT HOLE. TT ENG 4306.44. SMOH 1448.84.

Parts most often named Engine (5) · Case (1) · Snap Ring (1) · Solenoid Valve (1)

ENGINE FAILURE DURING FLIGHT. ACFT CRASHED INTO THE OCEAN NEAR AIRPORT. NTSB INVESTIGATION ONGOING TO DETERMINE CAUSE OF ENGINE FAILURE. ENGINE SENT TO MFG FOR EVALUATION.

(CAN) DURING CLIMBOUT THE #2 ENGINE OIL PRESSURE BEGAN TO DROP AND THE RPM BEGAN TO DECAY. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT LANDED WITHOUT INCIDENT. INVESTIGATION FOUND THE ENGINE WAS PRODUCING EXCESSIVE AMOUNTS OF NON-FERROUS METAL OBSTRUCTING THE PROP GOVERNOR OIL INLET PORT. THE SOURCE OF THE METAL IS UNKNOWN PENDING TEARDOWN.

Parts most often named Pump (4) · Relief Valve (1) · Gear (1) · Drive Coupling (1)

(CAN) LEFT ENGINE LOST POWER IN FLIGHT, APPROXIMATELY 25 MINUTES AFTER DEPARTING, WHILE IN CRUISE AT 8000`, THE LT ENGINE QUIT. FUEL PUMP REMOVED AND FOUND THE COUPLING SHAFT PN: 631683 ROUNDED INTERNALLY AND DRIVE GEAR, PN: 631684 WORN. DRIVE GEAR AND COUPLING REPLACED.

(CAN) LEFT ENGINE LOST POWER IN FLIGHT. APPROXIMATELY 25 MINUTES AFTER DEPARTING, WHILE IN CRUISE AT 8000 FT, THE LT ENGINE QUIT. FUEL PUMP REMOVED AND FOUND THE COUPLING SHAFT, PN: 631683 ROUNDED INTERNALLY AND DRIVE GEAR, PN: 631684 WORN. DRIVE GEAR AND COUPLING REPLACED.

AIRCRAFT IN CRUISE, ENGINE SPUTTERED AND DIED. BOOST PUMP ACTIVATED AND ENGINE RESTARTED. PART IS AN ON-CONDITION ITEM. THE SQUARE DRIVE ROUNDED OFF UNTIL IT WOULD NO LONGER ENGAGE THE DRIVE GEAR P/N 631684. THIS CAUSED THE FUEL PUMP TO STOP ROTATING RESULTING IN ENGINE STOPPAGE. THESE PUMPS ARE DELIVERED WITH OVERHAULED ENGINES. THIS PARTICULAR PUMP WAS REMOVED PRIOR TO OVERHAUL AND RE-INSTALLED ON ANOTHER ENGINE RESULTING IN THE 2600+ HOURS INSTEAD OF BEING OVERHAULED AT ENGINE TBO OF 1700 HOURS.

Parts most often named Cable (5) · Control Cable (2) · Nut (1)

DURING FLIGHT, THE RT ENGINE MIXTURE CONTROL FAILED AND THE ENGINE QUIT. AFTER LANDING, FOUND THE SWAGGED END OF THE MIXTURE CONTROL CABLE (PN 50-389010-21) HAD SEPARATED AT THE FUEL CONTROL UNIT.

(CAN) DURING CRUISE FLIGHT THE PILOT NOTICED THAT THE RT MIXTURE WAS NOT RESPONDING TO CONTROL MOVEMENT. THE AIRCRAFT RETURNED TO BASE UNEVENTFULLY AND UPON MAINTENANCE INSPECTION FOUND THE ENGINE SIDE OF THE CABLE HAD BROKEN AT THE ROD END WHERE THE CABLE SHEATH WAS SWAGED ONTO THE CABLE. THE CABLE IS BEING REPLACED. THE TOTAL TIME ON THIS CABLE ASSY WAS 4.6 TSN.

(AUS) LH ENGINE MIXTURE CUTOFF CONTROL CABLE WORN AND BROKEN AT A POINT 190MM (7.48IN) FROM THE ENGINE END ATTACHMENT BEARING.

Parts most often named Blade (3) · Retention Nut (1) · Seal (1) · Clamp (1)

PROPELLER RECENTLY OVERHAULED 10/29/2009 PROPELLER CAME IN FOR REPITCH WITH NO TIME ON SINCE OVERHAULED. 1 BLADE PAINT WAS REMOVED AND LOTS OF CORROSSION LEFT UNDER PAINT NOT REMOVED AS SHOULD BE WITH OVERHAUL. PROPELLER WILL HAVE TO BE REOVERHAULED TO DETERMINE THAT SPECIFICATIONS OF WIDTH AND THICKNESS WILL STILL BE AMPLE AFTER REPAIRS.

(CAN) FACTORY NEW PROPELLER STC SA00920CH. ONLY OBTAIN 2300 RPM STATIC, SHOULD BE 2600 RPM. FOUND BLADE LOW END STOPS INCORRECTLY SET.- PROP RETURNED TO OBTAIN NEEDED 2600 RPM. ERROR IN ENGINEERING APPROVAL AT MCCAULEY INCORRECT BLADE ANGLES.

(AUS) PROPELLER BLADE FERRULE CRACKED AROUND BEARING SHELF ORIGINATINGFROM A PREVIOUSLY DRILLED ACTUATING PIN HOLE. CRACK LENGTH 50.8MM (2IN).