182Skylane

Parts most often named Cylinder (49) · Exhaust Valve (24) · Pushrod (23) · Valve Guide (16)

CYLINDER NR 3 HEAD SEPARATED FROM BARREL. THE OPERATOR HAD PREVIOUSLY INSPECTED AN OIL LEAK ON OR AROUND CYLINDER NR 3. PRESENTATION OF OIL LEAK AND SEPARATION OF HEAD FROM BARREL IS THE SAME AS DESCRIBED IN AD 86-13-04 R3. THIS CYLINDER PN STAMPED ON THE FLANGE IS 658175B [S/N removed], NOT LISTED ON THE PREVIOUSLY MENTIONED AD.

CONTINENTAL (AIRBOSS) CYLINDER P/N 658598 [S/N removed] INSTALLED ON AUGUST 31, 2015 PER THE ENGINE LOG BOOK. COMPRESSION TEST IN JULY 2020 IDENTIFIED LOW COMPRESSION ON THIS CYLINDER, WITH A LEAK IN THE EXHAUST VALVE. THE EXHAUST VALVE WAS REMOVED AND THE VALVE SEAT FOUND TO BE MISALIGNED. MECHANIC BELIEVES THIS TO BE A MANUFACTURING DEFECT IN THE CYLINDER ASSEMBLY. PART WAS REPLACED WITH A NEW SUPERIOR MILLENNIUM CYLINDER ASSEMBLY.

DURING PERFORMANCE OF SB 388C, IT WAS FOUND THAT THE NR 3 CYLINDER EXHAUST VALVE TO GUIDE CLEARANCE MEASURED .031". THIS EXCEEDS THE MAXIMUM ALLOWABLE CLEARANCE OF .030". THIS ENGINE WAS OVERHAUL. THE TOTAL TIME SINCE NEW IS NOT BEING LISTED AS IT IS NOT KNOWN HOW LONG THIS CYLINDER OR EXHAUST VALVE HAVE BEEN ON THIS ENGINE. IT IS KNOWN THAT THE ENGINE WAS OVERHAULED 897.7 HOURS AGO AND THIS CYLINDER AND VALVE WERE INSTALLED AT THAT TIME. WHETHER THEY WERE NEW OR OVERHAULED AT THAT TIME IS NOT KNOWN.

Parts most often named Bulkhead (71) · Doubler (4) · Screw (1)

DURING ROUTINE MAINTENANCE, FOUND CRACKED 0712616-1 BULKHEAD FROM LH UPPER RADIUS. INSTALLED SK210-161A1 PER SEB99-12 REV 2.

CRACKS WERE FOUND IN THE AFT BULKHEAD AND ALL FIVE VERTICAL FIN ATTACHMENT BOLTS WERE FOUND LOOSE. THIS WAS CAUSED BY THE AFT BULKHEAD BEING UNDER DESIGNED.

CRACK DISCOVERED IN AFT BULKHEAD DURING INSPECTION. 0.25 INCH CRACK LOCATED IN UPPER LEFT CORNER BETWEEN RUDDER CABLE CUTOUT AND BULKHEAD FLANGE.

Parts most often named Magneto (22) · Impulse Coupling (15) · Points (7) · Contact (2)

MAGNETO TIMING REPORT AFTER EACH FLIGHT. (TWO CONSECUTIVE FLIGHTS WITH THE SAME REPORT) - DISTRIBUTOR BLOCK CRACKS FOUND AT MAGNETO INSPECTION.

SLICK BY CHAMPION SB2-19A MANDATORY INSPECTION OF IMPULSE COUPLING. THE SB HAS YOU INSPECT THE IMPULSE COUPLING PER THE MAINTENANCE MANUAL. IF ANY MOVEMENT IS FOUND IN THE RIVETS, THE IMPULSE COUPLING MUST BE REJECTED. INSPECTED MAGNETO MODEL NO. 6351 P/N: 66LC35SDNN [S/N removed] TSN: 305.0 INSTALLED IN THE RH POSITION AND FOUND 1 RIVET OF THE TWO WITH MOVEMENT. THIS IMPULSE COUPLING FAILED THE INSPECTION AND IS NO LONGER [S/N removed].

DURING RUN UP, MAGETO FAILED TEST. LESS THAN 1 HR OPERATION AFTER OVERHAULED MAGETOS INSTALLED. DURING INSPECTION FOUND THE CAPACITOR LOOSE IN HOUSING AND COIL WIRE LOOSE AND MAGETO SET IN E GAP. REMOVED OTHER MAG AS A PRECAUTION AND FOUND ITS COIL WIRE LOOSE AND ALSO SET IN E GAP. CORRECTED THE ISSUE AND REINSTALLED MAGS, OPS CHECKED OK.

Parts most often named Piston (9) · Camshaft (8) · Lifter (7) · Crankcase (6)

DURING ROUTINE MAINTENANCE SEVERE DISTRESS OF CAMSHAFT LOBE AND LIFTERS WAS IDENTIFIED. THE MAINTENANCE WAS CARRIED OUT DURING INTERNATIONAL TRAVEL, IN AUSTRALIA. PLEASE CONTACT ME FOR PHOTOGRAPHS/ENGINE INSPECTION REPORT.

CRANKSHAFT GEAR CHIPPED ONE TOOTH OFF. PROB DUE TO STARTER KICKBACK (ENERGIZER STARTER). AROUND 05/20/2018 AT TACK 3175 OWNER REPORTED TICKING NOSE ON GROUND. SOUND WENT AWAY WITH INCREASE RPM. ABOUT 1500. EVENTUALLY FOUND ONE TOOTH MISSING FROM CRANKSHAFT GEAR PN 657175. THIS DID NOT CAUSE AN ENGINE SHUT DOWN OR FAILURE. PULLED ENGINE AND SENT TO OVERHAULER. CO 970-249-0232 INV NUMBER WO54555 DATE 08/30/2018.

AFTER REMOVAL OF THE CYLINDER, FOUND THAT THE CRANKSHAFT MAIN BEARINGS FROM THE NR 6 CYLINDER WERE CRUSHED AND PARTS OF THEM MISSING, LATER FOUND THE REMAINING PIECES OF BEARING MATERIAL AND PIECES OF THE CONNECTING ROD END CAP, NUTS AND BOLTS IN THE OIL SUMP. THE CRANK LOB WAS FOUND DISCOLORED AND DAMAGED FROM POSSIBLE OIL STARVATION AND HEAT.

Parts most often named Gasket (9) · Dowel (5) · Piston Rod (3) · Piston Tube (3)

DURING INSPECTION, IT WAS NOTED THAT THE NR 3 BLADE ROTATED WITHIN THE HUB. DISCOVERED THAT THE BLADE ACTUATING LINK, WAS BROKEN WHICH ALLOWED THE BLADE TO ROTATE. IT WAS UNDETERMINED IF THE LINK WAS BROKEN DUE TO MISHANDLING OF THE PROPELLER OR HAPPENED DURING NORMAL OPERATION OF THE PROPELLER ASSY.

RED DYE OIL LEAKAGE AT THE CYLINDER TO HUB ATTACH POINT. OIL IS LEAKING PAST THE CYLINDER GASKET TO THE ATTACHING SCREWS AND FOLLOWING THE THREADS OUT. ADDITIONAL SEALANT NEEDS TO BE ADDED TO THE SCREWS DURING INSTALLATION AND PARTICULAR ATTENTION SHOULD BE GIVEN TO TORQUING THE SCREWS TO ASSURE PROPER SEATING OF THE GASKET. (K)

(AUS) CRANKSHAFT PROPELLER MOUNTING FLANGE PROPELLER LOCATING DOWELS INCORRECTLY FITTED. DOWELS HAVE A SLIGHT TAPER WHICH ALLOWS FOR A SLIP FIT INTO THE CRANKSHAFT AND AN INTERFERENCE FIT ONTO THE PROPELLER. THE DOWELS WERE INCORRECTLY FITTED WITH THE INTERFERENCE FIT ONTO THE CRANKSHAFT. THE INCORRECT FITMENT OFTHE DOWELS DAMAGED THE CRANKSHAFT. PERSONNEL/MAINTENANCE ERROR.

Parts most often named Hub (31) · Dowel Pin (2) · Snap Ring (1) · Piston (1)

PROPELLER WAS BROUGHT IN FOR REPAIR, DUE TO RED DYE LEAKAGE. DURING THE COURSE OF INSPECTION, A CRACK WAS FOUND. THE HUB IS CRACKED ON THE REAR SIDE OF BLADE SOCKET NR 1. ACFT ENG IS A O470-50 WITH A P PONK CONVERSION, STC SA02092SE, WHICH RAISES THE HORSEPOWER PRODUCED BY THE ENG, THE INCREASED HORSEPOWER COULD BE A PROBABLE CAUSE. DEFINITIVE CAUSE IS UNKNOWN. THE OWNER OF THE PROPELLER HAS BEEN NOTIFIED THAT THE HUB IS TO BE RETIRED AND REPLACED.

(CAN) PROP WAS TESTED DURING A ROUTINE INSPECTION FOR OPERATION. ROUGHNESS WAS NOTED IN CYCLING THE PROPELLER. INVESTIGATION DETERMINED THAT THE BEARINGS AND PRE-LOAD BEARINGS WERE ROUGH DUE TO PITTING. PROP REMOVED FOR O/H.

LIQUID PENETRANT INDICATION ON THE EXTERNAL SOCKET ON NR 2 BLADE AT 4 O`CLOCK. THIS IS NOT A RADIAL INDICATION. THIS CRACK INDICATION WAS DISCOVERED DURING O/H. THE PART IS UNAIRWORTHY. HUB WAS SENT TO MFG FOR DESTRUCTIVE TESTING.

Parts most often named Fuel Cap (9) · Cap (5) · Fuel Cell (4) · Cell (3)

NEW FFC BLADDER INSTALLED SEPT 2023 .. LEAKED .. UNABLE TO RESOLVE LEAKING, BLADDER RETURNED TO FFC FOR INSPECTION AND REPAIR FEB 2024 .. REPAIRED BLADDER INSTALLED MAR 2024 .. LEAKING CONTINUED .. AGAIN RETURNED TO FFC .. BLADDER REPLACED WITH ANOTHER NEW BLADDER UNDER WARRANTY .. LEAKING CONTINUED .. FFC BLADDER REPLACED WITH EAGLE FUEL CELLS BLADDER .. LEAK RESOLVED.

FUEL CAPS WERE INSTALLED ON AIRCRAFT IAW STC SA2376CE AND HAD BEEN IN [S/N removed] FOR ABOUT 40 HOURS IN A 4 MONTH PERIOD. THEY BEGAN VENTING FUEL FROM BOTH TANKS RESULTING IN A FORCED EMERGENCY LANDING DUE TO FUEL STARVATION.

FLOATS AND FUEL CELLS. RECEIVED NEW MFG LEFT WING FUEL CELL, MFG DATE 3/03. INSTALLED IN AIRCRAFT, FILLED WITH 1000LL AVGAS, DISCOVERED FUEL LEAK, RETURNED FUEL CELL TO MFG, FFC DISCOVERED MFG LT REAR BOTTOM CHANNEL LEAK DEFECT. FFC REPAIRED DEFECT AND RETURNED FUEL CELL.

Parts most often named Carburetor (8) · Float (5) · Support (2) · Valve Seat (2)

CARB HEAT SHAFT WAS FOUND TO BE SHEARED AT RIVET HOLE DURING ACCIDENT INVESTIGATION. SHEARING OF THE SHAFT DID NOT APPEAR TO BE RELATED TO THE ACCIDENT.

AT THE END OF THE FLIGHT, PILOT REPORTED THAT THE ENGINE WOULD NOT IDLE. DURING INSPECTION OF THE CARBURETOR, MECHANIC FOUND THE MIXTURE ADJUSTMENT NEEDLE VALVE MISSING. CARBURETOR WAS REMOVED AND SENT BACK FOR REPAIR.

PILOT REPORTED THAT AFTER A NORMAL START, HE WAS UNABLE TO ADVANCE THE THROTTLE CONTROL TO CRUISE OR TAKEOFF POWER. A PARTIAL DISASSEMBLY OF THE CARBURETOR REVEALED THAT THE AIR METERING PIN/AIR METERING JET WAS BLOCKING THE THROTTLE SHAFT TRAVEL. THE CARBURETOR WAS SENT FOR REPAIR. (K)

Parts most often named Line (11) · Connector (3) · Hose (3) · Fuel Line (2)

FUEL SYSTEM LEAKING AT FLARE ON LINE UNDER PILOT SEAT. LINE MFG WITH A SEAM IN THE TUBING. WHEN FLARED, THE SEAM CAN BE FELT WITH THUMBNAIL. EVIDENTLY CREATING LEAK PATH. B-NUT WAS TORQUED WHEN PROBLEM WAS FOUND. REPLACED LINE WITH NEW PART.

COPILOT’S RUDDER PEDDLE COVER IS CHAFING INTO THE FUEL LINE. THIS CHAFING IS CAUSED BY INSUFFICIENT CLEARANCE OF THE RUDDER PEDDLE COVER AND THE FUEL LINE. THE SAME CONDITION HAS BEEN FOUND ON 2 OTHER ACFT, [S/N removed] AND [S/N removed]. WE CORRECTED THE PROBLEM BY TRIMMING THE RUDDER PEDDLE COVER PN 0719085-4 FOR POSITIVE CLEARANCE BETWEEN THE FUEL LINE AND COVER ON ALL 3 ACFT. THE FUEL LINE ON 1821675 REQUIRED REPLACEMENT DUE TO CHAFE DAMAGE BEYOND LIMITS.

FUEL LEAKING FROM GAS COLATOR BOWL, TIGHTENED AT FACTORY DURING ACCEPTANCE FLIGHT (5.0 HOURS). FUEL LEAKING FROM GAS COLATOR INLET LINE (10 HOURS SINCE NEW) RESULTED IN OFF-AIRPORT LANDING DUE TO FUEL QUANTITY. (K)

Parts most often named Oil Filter (5) · Adapter (3) · Gasket (3) · T-Fitting (1)

ON SHUT DOWN NOTICED POOL OF OIL ON RAMP AND THICK ALONG ENTIRE BELLY. MEASURED 5 QTS OIL REMAINING. INSPECTION REVEALED FIBER GASKET SHOWED NICK AND DEFORMATION OF OIL FILTER ADAPTER GASKET SWIFT PN FM-07. ON REMOVAL IT WAS CONFIRMED THAT GASKET ON OIL FILTER ADAPTER [F&N, NOW SWIFT] WAS DEFORMED EXACTLY LIKE EXAMPLES IN NTSB ASR-20-05 SAFETY RECOMMENDATION.

ON SHUTDOWN, NOTICED A POOL OF OIL ON THE RAMP, AND THICK ALONG THE ENTIRE BELLY. MEASURED 5 QTS OF OIL REMAINING. INSPETION REVEALED THE FIBER GASKET SHOWED A NICK AND DEFROMATION OF THE OIL FILTER ADAPTER. ON REMOVAL, CONFIRMED THE GASKET ON THE OIL FILTER ADAPTER WAS DEFORMED.

THE AIRCRAFT HAD A OIL LEAK. WE FOUND THE THREADS IN THE OIL PUMP HOUSING WERE GAULDED AND THE OIL FILTER ADAPTER THREADS WERE DAMAGED. MOST LIKELY FROM OVER TORQUE. THE PUMP BODY P/N 632563 WAS REPLACED AND AIR WOLF REMOTE OIL FILTER KIT INSTALLED.