120/​140Cessna 120 · 140 · 140A

Parts most often named Guide (1) · Piston (1) · Piston Ring (1) · Exhaust Valve (1)

(CAN) BROKEN VALVE GUIDE DETECTED AS THE ANNUAL 1 100 HR INSPECTION. CYLINDER ASSY REMOVED, LOW COMPRESSION ON DIFFERENTIAL TEST 20/80 SENT TO AMO FOR REPAIR NOTE: CYLINDER ASSY WAS PURCHASED NEW OCT. 2004 - 245.0 HR.

(CAN) DURING THE ANNUAL AIRCRAFT INSPECTION THE #2 CYLINDER COMPRESSION CHECK WAS LOW AT 43/80. UPON REMOVAL OF THE CYLINDER, THE PISTON WAS FOUND CRACKED IN TWO PLACES ON THE WRIST PIN BOSSES. A NEW CYLINDER AND PISTON WILL BE INSTALLED.

Parts most often named Engine (2) · Crankshaft (1)

Parts most often named Fulcrum Pin (1) · Needle Valve (1) · Needle (1)

CARBURETOR FLOAT CHAMBER NEEDLE VALVE TIP SWELLED UP, PROBABLY DUE TO 100 LL OR AUTOGAS. ENGINE FALTERED AT HIGH POWER SETTINGS. TAKEOFF ABORTED.

Parts most often named Washer (1) · Distributor Blk (1) · Magneto (1)

BOTH MAGS REMOVED FOR SB, 500 HOUR INSPECTION. MFG DEFECT NOTED. ROTATING MAGNET AND BEARING ASSY NOT PRESSED (FAR ENOUGH) INTO FRONT MAG HOUSING . MAGS PURCHASED NEW 1/9/98. UNEVEN WAR NOTED THROUGHOUT WITH FINE BRONZE POWDER COATING INTERNAL PARTS. OD (GREEN) IN COLOR. MORE CAREFUL ASSEMBLY OF MAG COMPONENTS AT FACTORY. (NOTE) MAG SN 14 UNITS APART. (K)

UPON MAGNETO AD NOTE INSPECTION NOTED: SCREW RETAINING CAM LOOSE ON ROTATING MAGNET. WASHER UNDER SCREW HAD ALMOST WORN AWAY SCREW HEAD. INSTALLED NEW SCREW AND WASHER.

Parts most often named Control Cable (2)

(CAN) 2 CABLES FOUND CORRODED AND FRAYED AT FUSELAGE STA. 20.5. BOTTOM OF FORWARD LANDING GEAR BULKHEAD. DEFECT WAS FOUND ON CABLES BECAUSE THEY HAD TO BE REMOVED FOR MAJOR STRUCTURAL REPAIRS. THOSE CABLES RUN ON PULLIES ATTACHED TO THE BULKHEAD AT THE VERY BOTTOM OF THE FUSELAGE. VERY HARD TO DETECT UNLESS CABLES ARE REMOVED. FUSELAGE BOTTOM USUALLY VERY DIRTY IN THAT AREA WHERE WATER AND MUD ACCUMULATE.

BOTH RUDDER CABLES FOUND FRAYED 6-10 STRANDS AT FORWARD-MOST PULLEYS JUST AFT OF RUDDER PEDALS. TWO MONTHS PREVIOUSLY, SAME DEFECT FOUND IN EXACT LOCATION ON A CESSNA 120. SUBMITTER SUGGESTS 100 HR/ANNUAL INSPECTION BE REQUIRED.

Parts most often named Fitting (1) · Hinge (1)

THE PART WAS BEGINNING TO RUST THROUGH IN LOCATION RESPONSIBLE FOR ATTACHING THE LT FLAP TO THE FLAP CONTROL. THE DEFECT WAS FOUND DURING AN ANNUAL INSPECTION. PROBABLE CAUSE WAS RUSTING DUE TO AGE. A MORE THOROUGH INSPECTION OF THE AREA DURING PREFLIGHT SHOULD HELP DETECT THE PROBLEM SO THAT CORRECTIVE ACTION CAN BE TAKEN.

DURING ANNUAL INSPECTION, THE LEFT WING FLAP HINGES WERE FOUND CRACKED. LEFT AND RIGHT ONLY. THE AREA OF THE CRACKS WAS FOUND AT THE ATTACHING SCREW HOLES. THE CRACKS ORIGINATED IN THE HOLES AND RAN TO EACH CORNER OF THESE HINGES. PARTS TOTAL TIME UNKNOWN.

Parts most often named Axle (2)

LEFT AXLE BROKEN IN HALF ON LANDING CAUSING ACCIDENT AND SUBSTANTIAL DAMAGE TO ACFT. AXLE FOUND SEPARATED IN 2 INBD OF INNER BEARING RACE LOCATION. EVIDENCE NOTED OF POSSIBLE PRIOR DAMAGE IN AREA OF CRACK AND SEPARATION, POTENTIALLY FROM PRIOR ACCIDENT OR USE OF SKIS FOR EXTENDED PERIOD. NTSB LAB ANALYSIS IN PROCESS TO DETERMINE CAUSE OF FAILURE.

DURING TAKEOFF FROM PRIVATE TURF STRIP, RT AXLE BROKE AT JUNCTURE OF TUBE AND MOUNTING FLANGE. RT WHEEL TIRE BRAKE ASSY DEPARTED AIRCRAFT. AIRCRAFT GROUND LOOPED CAUSING SUBSTANTIAL DAMAGE TO AIRCRAFT. INSPECTION OF AXLE INDICATED A CRACK APPROXIMATELY 150 DEGREES OF CIRCUMFERENCE OF TUBE. CRACKED AREA DISCOLORED INDICATING IN EXISTENCE FOR SOME TIME AND WAS LOCATED ON BOTTOM IN THIS INSTALLATION.

Parts most often named Propeller (2)

Parts most often named Bulkhead (2)

DURING ROUTINE INSPECTION, FOUND ELEVATOR CONTROL CABLE TENSION LOW. ATTEMPT TO ADJUST, COULD NOT ATTAIN PROPER TEST. INSPECT CABLE ROUTING, NOT ABLE TO VERIFY PULLEY MOVEMENT. THERE ARE NO ACCESS PLATES OR PANELS TO VISUALLY INSPECT. ENTIRE TAIL GROUP WAS REMOVED TO FURTHER FACILITATE INSPECTION. FOUND AFT HORIZONTAL BULKHEAD CRACKED SEVERAL LOCATIONS. ELEVATOR CONTROL CABLES WERE DETERMINED TO BE STRETCHED.

Parts most often named Oil Filter (2)